1 The International Standard Atmosphere specifies :
O Standardized atmospheric values of temperature, pressure and density at all altitudes
O Sea level conditions of atmospheric temperature, pressure and density
O values of actual conditions of temperature, pressure and density that exist at all levels of the atmosphere.
2 The variable physical properties of the atmosphere that affect aircraft performance are:
O temperature, pressure, density and humidity.
O pressure, humidity and oxygen content
O temperature, pressure and humidity.
3 The International Standard atmosphere assumes that the ambient temperature:
O decreases with increase in height above the Earth.
O will decrease with height only if an inversion layer is present.
O increases with increase in height above the Earth.
4 The percentage oxygen content of the atmosphere at higher altitudes compared to that at lower altitudes :
O remains constant, but the lower pressure makes it more difficult for the body to absorb oxygen
O decreases due to the decreased air pressure.
O falls, but since the quantity is adequate, the fall has little effect on the pilot at any altitude.
5 When compared with perfectly dry air at the same temperature and pressure, air which contains a maximum amount of water vapour will have a :
O lower density
O similar density
O greater density
O the pressure falls.
O of the fall in water vapour content.
O the temperature falls.
7 The definition of relative humidity is:
O - the amount of water vapour present in the air compared to the maximum amount of water vapour the air could hold at the same temperature. This is expressed as a percentage.
O - the percentage of water in a measured volume of air irrespective of temperature.
O - the relative amount of water vapour in the air at any time.
8 A stall is characterised by :
O a nose pitch down and aircraft sink.
O a nose pitch up and aircraft sink
O airspeed decay and wing drop
9 If air is maintained at a constant temperature and volume while its pressure is decreased, its density will:
O decrease.
O increase.
O remain constant because the volume is constant.
10 The pressure of air flowing under the forward section of a wing in straight and level flight when compared with the free airflow will be:
O higher.
O lower.
O the same
11 An aircraft in straight and level fight is in equilibrium when:
O the weight equals lift and the drag equals the thrust.
O the lift equals the drag and the thrust equals the weight.
O the weight equals the drag and the lift equals the thrust.
12 A coefficient of lift reaches Its maximum value:
O at or just prior to the stall.
O between 4° and 6° angle of attack in straight and level flight.
O at the minimum drag speed in the clean configuration.
13 The reason for 'washout' being designed into an aeroplane wing is to:
O cause the inboard section of the wing to stall first.
O cause the outboard section, of the wing to stall first.
O decrease the effectiveness, of the ailerons.
14 The speed scale of an airspeed indicator is colour coded. The green band is:
O the normal operating range (Vno)
O the flap extension range (Vfe)
O the caution range (Vne)
15 Deviation from the maintenance schedule specified in the Certificate of Airworthiness (C of A):
O renders the C of A invalid until the specified maintenance is carried out.
O will require the issue of a new C of A if the specified maintenance is not completed within 50 flying hours.
O will not affect the C of A but invalidates any subsequent Certificate of Release to Service.
16 Ferrous objects in close proximity to a magnetic compass will:
O induce significant errors in the magnetic heading indication.
O not affect the magnetic compass as its housing is screened from magnetic field distortion.
O not affect flight operations provided the heading indicator is synchronised with the magnetic compass before the ferrous items are brought on board.
17 Complete the following statement.
O X :greatest Y: heavy Z : slow
-greatest Y - light Z- high
O X : least Y : heavy Z : slow
18 An aircraft that has been overstressed:
O must be inspected by a qualified engineer before the next flight.
O must be inspected by the pilot in command and if no defect is found, s/he will not be required to make an appropriate entry in the aircraft technical log.
O must be inspected by at least two pilots licensed on the type, one of whom must be the pilot in command.
19 An increase in aircraft weight amongst other things will:
O cause an increase in the stalling speed.
O not effect the stalling speed.
O cause a decrease in the stalling speed.
20 If an aircraft is maintaining a constant angle of attack but increases its airspeed, this will cause: -
O an increase of both lift and drag.
O no change in lift generated by the wing, but an increase in airframe drag.
O a decrease in lift but an increase in drag.
21 The valve which allows oil to either flow through or by-pass a serviceable engine oil cooler is:
O temperature activated
O pressure activated
O manually activated.
22 The speed at which a particular aircraft stalls whilst in straight and level flight is 60kt. The approximate stalling speed of the same aircraft in a 60° bank turn would be:
O 84kt.
O 75kt.
O 90kt.
23 An aeroplane wing will stall at a given:
O angle of attack
O angle of incidence
O angle of lift
24 A stalling angle of attack is increased by 'slots' because:
O they delay the break up of the smooth airflow over the wing.
O they dump positive pressure airflow from under the wing.
O they increase the effective wing area at the leading edge.
25 The consequence of an aircraft with its centre of gravity positioned at or very close to its designed aft limit could be
O Greatly reduced applied elevator force during flare.
O an increased applied elevator force during rotation.
O an increased stalling speed.
26 As an aeroplane's True Air Speed (TAS) increases:
O Induced drag decreases and parasite drag increases.
O Parasite drag decreases and induced drag increases.
O Induced drag increases and parasite drag increases
27 Induced Drag :
O is reduced as airspeed increases
O is not a factor of airspeed.
O is increased as airspeed increases
28 The purpose of a control surface anti-balance tab is to:
O ensure that the pilot's physical control load increases with increase of control surface deflection.
O ensure the centre of pressure is maintained forward of the hinge line.
O assist the pilot in moving the control surface.
29 If a flying control surface is fitted with a simple trim tab, any movement of the flying control surface in flight will result in the:
O trim tab position remaining constant relative to the control surface.
O trim tab moving to a new position and will have to be re-set.
O trim tab position remaining constant relative to the airflow
30 The angle of attack of an aerofoil may be defined as:
O the angle subtended by the aerofoil chord line and the relative airflow.
O the angle subtended by the aerofoil chord line and the longitudinal axis.
O the angle subtended by the aerofoil mean chord line and the horizontal.
31 In straight and level flight, the air flow over the wing's upper surface compared with the air flow unaffected by the wing Will have:
O a greater velocity
O a reduced velocity.
O the same velocity.
32 When trailing edge flaps are extended, the stalling angle of attack, if measured between the relative airflow and the aerofoil cord line with flaps retracted, will be:
O less
O greater.
O the same.
33 The movement of an aeroplane about its normal (vertical) axis is known as:
O yawing.
O rolling.
O side slipping.
34 Which of the following gives an aeroplane directional stability?
O The fin
O The rudder
O The rudder and trim tab.
35 A flying control surface that is aerodynamically balanced:
O has an area of the control surface forward of the hinge line.
O has been modified with a trim tab.
O uses a balance weight forward of the hinge line.
36 Differential aileron where the Up going aileron moves further than the down-going aileron is a design feature that helps to counteract:
O adverse aileron drag.
O aircraft inertia.
O positive aircraft instability.
37 The centre of pressure by design is behind the aircraft centre of gravity which is balanced in straight and level flight by:
O the tail plane producing a downward force.
O the tail plane producing an upward force.
O neither an upward or down ward tail plane force as the aircraft will be in equilibrium.
38 A flying Control lock :
O locks controls on the ground! to prevent damage in windy conditions.
O locks the trim tabs once straight and level cruise is established.
O locks controls in flight to neutralise aerodynamic loads and ease the physical load on the pilot.
39 It is important to carry out regular checks for water in the fuel system, as the presence of water will cause:
O fuel system contamination resulting in the loss of engine power.
O the fuel to freeze.
O intake and carburettor venturi icing.
40 The crankshaft in a piston engined aircraft:
O converts reciprocating movement into rotary motion.
O controls the clearance of the valves.
O converts rotary motion into reciprocating movement.
41 After starting a cold engine, if the oil pressure gauge does not indicate within approximately 30 seconds:
O the engine must be stopped immediately.
O this may be ignored if the oil temperature is still low and the oil level was checked before start-up.
O the engine RPM should be increased and the oil pressure re-checked.
42 If the starter warning light remains on after the starter button (starter switch) has been released:
O the engine should be immediately stopped.
O the alternator output level should be checked.
O the engine RPM should be increased as it is too low.
43 Information regarding aircraft that may legally be fuelled with MOGAS may be found in:
O CAA Airworthiness Notices
O AICs
O Notams
44 When refuelling, to ensure that the correct type of fuel is used, both the fuel itself and tank labels are colour coded. The primary colour for all labels relating to 100ll is ….(i)… and the colour of the fuel itself should be …..(ii)…..
O i) red ii) blue
O - i) black ii) red
O i) blue ii) straw
45 The normal location of an electrically driven fuel boost pump is:
O the lowest part of a fuel tank.
O upstream of the engine driven pump.
O the tank to tank fuel transfer line.
46 When a fuel priming pump is used before starting an engine, the fuel is normally delivered directly to:
O the induction manifold or inlet valve port.
O the carburettor float chamber.
O the combustion chamber.
47 What is the function of an idle cut off valve in a piston engined aeroplane?
O It inhibits fuel flow from the discharge nozzle in the carburettor when selected.
O It controls engine slow-running via the carburettor idle jet.
O changes fuel flow to the main jet from the idle jet when power is increased.
48 When leaning the fuel/air mixture at altitude, to achieve the most efficient mixture, the control is first moved towards the LEAN position until the engine RPM:
O Decreases. The mixture control is then moved slightly to the RICH side of peak RPM.
O Increases. The mixture control is then left in that position.
O Increases by approximately 50 RPM. The mixture control is then moved slightly more towards the LEAN position.
49 A piston engine fuel/ air mixture ratio, ideally, should be in the region of:
O 1 :12 by weight.
O 1:9 by volume.
O 1 :7 by weight.
50 The restrictive throat of a carburettor venturi changes the characteristics of the air that passes through it. These are:
O a drop in ambient pressure and velocity increase.
O a dynamic pressure decrease and a velocity increase.
O a dynamic pressure increase and a velocity decrease.
51. Which of the following prevents excessive engine oil pressures?
O An oil pressure relief valve.
O A vernier therm
O A filter by-pass valve.
