NEW
Font size
WorksheetsVnhk7
Total questions: 71
Worksheet time: 36mins
The reason for fitting thermal plugs to aeroplane wheels is that they:
prevent the brakes from overheating.
prevent tyre burst after excessive brake application.
prevent heat transfer from the brake disks to the tyres.
release air from the tyre in the event of overpressure due to over-inflation.
An aeroplane equipped with reversible flight controls:
does not require an artificial feel system.
need not be equipped with a separate gust lock system.
does not have mechanical back-up.
is equipped with simple spring type feel units.
If the control stick of an aircraft with properly rigged flight controls is moved rearward and to the left, the right aileron will move:
down and the elevator will move down.
up and the elevator will move down.
up and the elevator will move up.
down and the elevator will move up.
Which of the following statements is UNTRUE?
Bleed air may be supplied by an APU.
Use of engine bleed air reduces engine thrust.
Engine bleed air is considered to be high pressure.
Bleed air may be taken from the HP compressor of a gas turbine engine.
Which of the following statements is UNTRUE?
Power assisted flight control systems require a Q-feel system.
Powered flight control systems require an artificial feel system.
In a powered flight control system there is no physical link between the pilot and the control surfaces.
In a power assisted flight control system there is a physical link between the pilot and the control surfaces.
Pneumatic mechanical devices that provide ice protection:
are usually used as de-icing devices.
can only be used as anti-icing devices.
require large quantities of bleed air.
are usually used on aeroplanes equipped with turbo-fan engines.
The automatic fuelling shut off valve:
stops fuelling as soon as a certain fuel level is reached inside the tank.
cuts off the fuel in case of engine fire.
stops fuelling as soon as the fuel spills into the ventline.
stops fuelling as soon as a certain pressure is reached.
Fuel tank air pressure is maintained at ambient by:
the fuel vent system.
the fuel tank drains.
the fuel top off unit.
the fuel dump system.
The capacitance type fuel gauging system indicates the fuel quantity by measuring the:
resistivity variation of the fuel.
density variation of the fuel.
dielectric change between fuel and air.
electrical resistance change.
The purpose of baffles in an aeroplane's wing fuel tank is to:
prevent the fuel from flowing in the vent lines.
prevent overpressure in the tank.
restrict fuel movement in the tank.
prevent mixture of the fuel and hydraulic fluid.
The blades in an axial flow compressor decrease in size from the:
The blades in an axial flow compressor decrease in size from the:
high pressure to the low pressure stages in order to allow for expansion at increased velocity.
root to the tip in order to maintain a constant angle of attack.
low pressure to the high pressure stages in an attempt to sustain axial velocity.
Regarding a jet engine:
The maximum thrust increases slightly as the pressure altitude increases.
The specific fuel consumption decreases slightly as the pressure altitude increases at constant TAS.
1) is incorrect, 2) is correct.
1) is incorrect, 2) is incorrect.
1) is correct, 2) is correct.
1) is correct, 2) is incorrect.
The purpose of la chip detector in the oil system of an engine/gearbox is to indicate that:
the piston rings are worn.
there are metal particles in the oil.
the seals are worn.
the oil temperature is too high.
If the main oil filter of a gas turbine engine becomes clogged, oil to the main bearings is still assured:
because fuel upstream of the bil filter will be mixed with oil to allow easier passage through the filter.
because the oil filter bypass valve opens.
if breather pressure in the main compartments is increased to ensure positive lubrication of the bearings.
if a higher engine RPM is selected to increase oil pressure.
What can be the cause of a significant increase in battery temperature?
Thermal runaway
Excessive battery load
A failure of the voltage regulator
A falure of the alternator
Which of the following statements is correct regarding baberies (P.56)
Secondary cell battenes cannot be recharged
Primary cell batteries can be recharged
Batteries perform better in cold temperature
Batteries perform better in varm teMperature
The engine pressure ratio (EPR) is the ratio of:
total compressor outlet pressure to the total turbine outlet pressure.
the total turbine inlet pressure to the total compressor inlet pressure.
total compressor inlet pressure to the total turbine outlet pressure.
the total turbine outlet pressure to the total compressor inlet pressure.
In the statonof a turbine, the gas velocity "V" and static pressure "p" vary as follows:
V decreases; p increases.
V increases; p increases.
V decreases; p decreases.
V increases; p decreases.
In a free turbine engine:
its power output shaft may be connected to either a compressor or another turbine.
there is no mechanical connection between the compressor and the power output shaft.
the air enters the compressor via the turbine inlet.
the compressor and power output shaft are mechanically connected.
Using compressor bleed air to power systems:
increases aircraft performance.
has no influence on aircraft performance.
decreases aircraft performance.
is limited to the phases of take-off and landing.
A "hung start" is the failure of an engine to accelerate to its normal idle speed. It may be caused by:
compressor surging.
an attempt to ignite the fuel before the engine has been accelerated sufficiently by the starter.
the starter cutting out early in the starting sequence before the engine has accelerated to the required RPM for ignition.
failure of the fuel to ignite in the starting sequence after the engine has been accelerated to the required RPM by the starter.
A turbofan engine with an inlet air mass flow of 300 kg/s and a bypass mass flow of 250 kg/s has a bypass ratio of:
1.2
2.2
5
6
The primary reason for a limitation being imposed on the temperature of gas flow in a gas turbine is to:
ensure that the maximum acceptable temperature within the combustion chamber is not exceeded.
prevent damage to the jet pipe from overheating.
prevent overheating and subsequent creep of the nozzle guide vanes.
ensure that the maximum acceptable temperature at the turbine blades is not exceeded.
Turbine blade stages may be classed as either IMPULSE or REACTION. In an impulse turbine stage:
the pressure remains constant across the stator blades and drops across the rotor blades.
the pressure drops across the stator blades and remains constant across the rotor blades.
the pressure rises across the stator blades and remains constant across the rotor blades.
the pressure remains constant across the stator blades and rises constant across the rotor blades.
The fuel temperature, at which, under standard conditions, the vapour ignites in contact with a flame and extinguishes immediately, is the:
flash point.
fire point.
combustion point.
self ignition point.
Assuming cabin differential pressure has reached the required value in normal flight conditions, if flight altitude and air conditioning system setting are maintained:
the mass air flow through the cabin is constant.
the outflow valves will move to the fully open position.
the pressurization system ceases to function until leakage reduces the pressure.
the outflow valves will move to the fully closed position.
If the cabin altitude rises (aircraft in level flight), the differential pressure:
may exceed the maximum permitted differential unless immediate preventative action is taken.
increases.
remains constant.
Decrease
The wing ice protection system currently used on most large jet transport aeroplanes is:
a liquid de-icing system.
an electrical de-icing system.
a hot air system.
a pneumatic system with expandable boots.
The use of a hot air wing anti-icing system:
does not affect aerodynamic performance of the wing and causes a reduction in maximum thrust.
does not affect aerodynamic performance of the wing and causes no reduction in maximum thrust.
reduces aerodynamic performance of the wing and causes no reduction in maximum thrust.
reduces aerodynamic performance of the wing and causes a reduction in maximum thrust.
Generally, for large aeroplanes, electrical heating for ice protection is used on:
slat leading edges.
fin leading edges.
pitot tubes.
elevator leading edges.
Where is EGT typically measured?
In the jet pipe.
HP turbine outlet.
HP compressor outlet.
Combustion chamber.
For a subsonic airflow, in a divergent duct the:
static pressure decreases, speed increases and static temperature increases.
static pressure increases, speed decreases and static temperature increases.
static pressure increases, speed decreases and static temperature decreases.
static pressure decreases, speed increases and static temperature decreases.
The compressor blades in a rotating gas turbine engine are held in position by:
a centrifugal latch.
the mountings and the resultant of aerodynamic and centrifugal forces.
abradable seals and aerodynamic forces.
the mountings and thermal expansion only.
On the ground, the Auxiliary Power Unit (APU) can provide:
electricity.
air for main engine starting.
hydraulic pressure.
air for air conditioning.
The combination that regroups all of the correct statements is:
1
1.2.3.4
1.2.4
1.3.4
The color of a fresh synthetic hydraulic fluid is:
purple
Pink
Blue
yellow / straw
To allow for a failure of the normal method of system pressure limiting control, a hydraulic system often incorporates:
high pressure relief valve.
a stand-by hydraulic pump.
an accumulator.
auxilary hydraulic motors.
A torsion link assembly is installed on the landing gear to:
lock the landing gear.
absorb the spring tension.
control the wheels.
avoid rotation of the piston rod relative to the gear oleo strut.
"Nose-wheel shimmy" may be described as:
aircraft vibration caused by the hose-wheel upon extension of the gear.
the oscillatory movement of the hose-wheel when extended prior to landing.
the amount of free movement of the nose-wheel before steering takes effect.
a possibly damaging vibration of the hose-wheel when moving on the ground.
"Nose-wheel shimmy" mav be described as:
aircraft vibration caused by the nose-wheel upon extension of the gear.
the oscillatory lateral movement of the hose-wheel about the longitudinal axis of the aircraft when the hose-wheel is in contact with the runway during the take-off or landing run.
the amount of free movement of the nose-wheel before steering takes effect.
a possibly damaging vibration of the hose-wheel when extended prior landing.
The type of brake unit most frequently found on transport category aeroplanes is a:
drum type brake
multiple disk brake.
single disk brake.
belt brake
The autobrake system is disconnected after landing:
by pilot action by using the brake pedals.
automatically.
at a certain low speed.
the system is always armed.
One of the advantages of a turbocharger is:
the power available is less affected by altitude.
an increased propulsive efficiency.
that there is no torsion at the crankshaft.
that there is no danger of detonation.
Maximum exhaust gas temperature (EGT) of a piston engine is theoretically associated with a:
air to fuel ratio of 15:1.
cruising mixture setting.
full rich mixture setting.
mixture ratio very close to idle cut-out.
Pre-ignition refers to the condition that may arise when:
the mixture is ignited before the piston has reached top dead centre.
The mixture is ignited by abnormal conditions within the cylinder before the spark occurs at the plug.
a rich mixture is ignited by the sparking plugs.
the sparking plug ignites the mixture too early.
The reading on the oil pressure gauge is the:
pressure of the bil on the outlet side of the pressure pump.
difference between the pressure pump pressure and the scavenge pump pressure.
pressure in the oil tank reservoir.
pressure of the bil on the inlet side of the pressure pump.
Regarding detection systems, ion detectors are used to detect:
smoke.
fire.
overtemperature.
overtemperature and fire.
Smoke detectors fitted on transport aircraft are of the following type:
optical or ionization
chemical
electrical
magnetic
Halon is used as a fire extinguishing agent because it:
acts as a very effective flame inhibitor.
uses the cooling effect created by the venturi during discharge.
is highly volatile.
iS an electrical conductor
In the event of an gas turbine engine fire:
an automatic shut-off valve is moved to the closed position controlled by the fire sensing system.
the fuel supply is disconnected by a quick release coupling
the fuel supply is isolated from the engine by pilot action.
the fuel installation is protected by an automatic fire extinguishing system.
Regarding the oxygen system of EASA CS-25 certified aeroplane:
with the setting on "NORMAL", the cockpit crew breathes a mixture of bxygen and cabin air.
the same source of supply is used by the crew and passengers.
the seals must be carefully greased to avoid sparks.
the passenger source of supply never uses chemically generated oxygen.
Modern pressurized transport airplanes are equipped with:
only portable oxygen bottles.
only one oxygen system supplying the whole aircraft
two oxygen systems both supplying the cockpit and the cabin.
two independent oxygen systems, one supplying the cockpit, the other the cabin.
The automatic ground spoiler extension system is normally activated during landing by:
ground spoiler handle.
brake pressure application.
idle thrust selection.
main wheel spin up.
Cabin air for modern transport airplanes is usually taken from:
the low pressure stage of the HP compressor and from the high pressure stage of the HP compressor if necessary.
the high pressure stage of the LP compressor and from the low pressure stage of the LP compressor if necessary.
the low pressure stage of the LP compressor.
the high pressure stage of the LP compressor.
In flight, the cabin air for large jet transport aeroplanes is usually supplied by:
piston compressors.
engine compressors.
ram air intakes.
single radial compressors.
In a fly-by-wire aircraft, rudder is controlled by (P. 192-
Flight Augmentation Computers
Elevator Alleron Computers
Spoller Elevator Computers
Flight control computer
Cabin differential pressure means the pressure difference between:
cabin pressure and ambient air pressure at MSL.
actual cabin pressure and selected pressure.
cabin pressure and ambient air pressure.
flight deck and passenger cabin.
Define the term "FATIGUE":
a one off loading that breaks the material.
a loading on the material but it returns fully to its former state when the load is removed.
if a material is continually loaded and unloaded it will eventually break even though the load remains the same.
the material suffers progressively more permanent damage each time that it is loaded and unloaded.
Strain is defined as the:
ultimate load.
yield point.
deformation due to stress.
expansion due to temperature rise
Refer to figure 021-33
In the attached diagram, which image represents TENSION?
1
2
3
4
A SANDWICH structural part:
is a so-called integral construction.
consists of two thin sheets separated by a core of a light material.
is unsuitable for fuel tanks.
always uses honeycomb as core material.
A SANDWICH structural part is:
composed of two thin sheets and a light core material.
a so-called integral construction.
composed of resin and fibres.
well suited for absorbing point concentrated loads
What are the most frequently used materials in a monocoque or semi-monocoque structure?
Aluminium or magnesium alloy.
Steel.
Wood.
Composite fibers.
When the wing skin is not able to carry loads, the structural elements of the wing, which carry the bending moment, are:
the ribs.
the rivets.
the spars.
the webs.
In straight and level flight the most important loads on a cantilever wing are:
compression in the upper skin, tension in the lower skin.
compression in both the upper and the lower skin.
tension in both the upper and the lower skin.
tension in the upper skin, compression in the lower skin.
The hydraulic system of a transport aircraft is typically designed to produce:
high pressure and small flow.
high pressure And large flow.
small pressure and large flow.
small pressure and small flow.
Which of the following statements is correct regarding bus bars (P.130)?
if one generator fails, it is automatically isolated from its respective bus bar and all bus
bar loads are taken over by the operating generator
In a twin-engine aircraft, if both generator tails, batteries wil
automalicaly supply powel
to non-essental services and keep them operating for 30 minutes
Non-essental services are those required to ensure sals fight in an in
cont emergency
Situaton
hot Bus" is the bus that is always connecled to the emergency generalor
Which of the following statements is correct regarding anti-skid and autobrake systems?
The autobrake system does not function without anti-skid.
The anti-skid system does not function without autobrake.
The autobrake system can work properly without anti-skid if thrust reversers are working.
The autobrake system can work properly without anti-skid if the brake pedals are used additionally.
Compressor surge during gas turbine engine acceleration is prevented by:
controlling the fuel flow (by the FU - Fuel Control Unit).
outlet guide vanes.
bleed valves.
variable setting type nozzle guide vanes.
A propeller blade is twisted , so as to
to maintain a constant angle of attack from root to tip of the blade
to compensate for the Centrifugal Twisting Moment
to increase the thrust given by the tip
to maintain constant thrust from root to tip
What are the possible cockpit indications for an engine fire?
Bell, red alert message, red light in the engine fire switch.
Beeper, amber alert message, amber light in the engine fire switch.
Beeper, amber alert message, red light in the engine fire switch.
Bell, red alert message, amber light in the engine fire switch.
In order to get the optimum efficiency of a piston engine, the positions of the intake and exhaust valve just after the power stroke are
intake valve closed and exhaust valve open
both valves open
both valves closed
exhaust valve closed and intake valve open
