This page requires a JavaScript-enabled browser
Instructions on how to enable your browser are contained in the help file.
TECHGEN-SB-AIRFRAME-MODULE2-TEST&LEARN
1.
The component that converts hydraulic pressure into linear motion is called:
a) An actuator or jack
b) A hydraulic pump.
c) An accumulator.
d) A pressure regulator.
2.
Torsion in a wing can be caused by
a) Wing tip vortex
b) Dihedral
c) Positive swee
d) Propwash
3.
'Fail safe construction' is:
a) A type of construction for small aircraft only.
b) A construction which is suitable for aerobatic flight.
c) A simple and cheap type of construction.
d) A type of construction in which the load is carried by other components if a part of the structure fails
4.
Assuming cabin differential pressure has attained the required value in normal flight conditions, if flight altitude is maintained:
a) a constant mass air flow is permitted through the cabin
b) the pressurisation system must be controlled manually.
c) the pressurisation system ceases to function until leakage reduces the pressure.
d) the outflow valves will move to the fully open position.
5.
The level in a hydraulic reservoir will:
a) initially increase with system pressurisation.
b) always remain the same.
c) increase as ambient temperature decreases.
d) fluctuate with accumulator pressure
6.
In hydraulic system, a shuttle valve:
a) allows two units to be operated by one pressure source.
b) regulates pump delivery pressure.
c) is a non-return valve.
d) enables an alternate system to operate the same actuators in case of normal system failure
7.
VLE is the maximum:
a) speed with flaps extended in a given position
b) speed at which the landing gear can be operated with full safety
c) flight speed with landing gear dow
d) speed authorized in flight
8.
Flutter results from two deformation modes which are:
a) torsion and bendin
b) torsion and shearing
c) shearing and elongation
d) bending an elongation
9.
The damping element in a landing gear shock absorber used on large aircrafts is:
a) Oil
b) Nitrogen.
c) Oxygen.
d) Springs.
10.
In some aircraft, there is a protection device to avoid the landing gear being inadvertently retracted on the ground. It consists of:
a) An aural warning horn.
b) A bolt.
c) A warning light which is activated by the WOW (Weight On Wheels) sensor system.
d) A latch located in the landing gear lever
11.
The function of the selector valve is to:
a) automatically activate the hydraulic system.
b) discharge some hydraulic fluid if the system pressure is too high.
c) communicate system pressure to either side of an actuator
d) select the system to which the hydraulic pump should supply pressure.
12.
The aircraft hydraulic system is designed to produce:
a) high pressure and small flow.
b) small pressure and small flow.
c) high pressure and large flow
d) small pressure and large flow.
13.
The hydraulic device similar to an electronic diode is a:
a) shutoff valve.
b) flow control valve.
c) distribution valve.
d) check valve
14.
The cross-feed fuel system is used to:
a) allow the unusable fuel elimination.
b) allow the fuel to be quickly thrown away in case of emergency
c) automatically fill every tank up to the desired level.
d) feed every engine from any fuel tank
15.
One of the purpose of the fuel system booster pumps to be submerged in the fuel is:
a) To shorten the fuel lines, so minimising the pressure losses.
b) To facilitate the priming of the pumps
c) To improve their efficiency.
d) To cool the pumps.
16.
The capacitance type fuel gauging system indicates the fuel quantity by measuring the:
a) electrical resistance change.
b) density variation of the fuel.
c) resistivity variation of the fuel.
d) dielectric change between fuel and air
17.
The vapour lock is:
a) The exhaust gases obstructions caused by an engine overheating.
b) A stoppage in a fuel feeding line caused by a fuel vapour bubble
c) The effect of the water vapour bubbles in the induction manifold caused by the condensation.
d) The abnormal mixture enrichment caused by a greater gasoline vaporisation in the carburettor.
18.
The fuel system boost pumps are used to:
a) feed the lines with fuel for directing it to the engine at a positive pressure.
b) feed the fuel control units, which inject the pressurized fuel into the engine.
c) avoid the bubbles accumulation.
d) avoid the bubbles accumulation and feed the lines with fuel for directing it to the engine at a positive pressure
19.
The purpose of an accumulator in a hydraulic system is:
a) to enable the starting of hydraulic devices.
b) to bypass the pumps in the hydraulic system.
c) to damp the fluid pressure variations
d) to eliminate the fluid flow variations.
20.
Maximum power output and low mass of aeroplane hydraulic systems can be achieved with
a) medium system pressure and low volume flow.
b) medium system pressure and high volume flow.
c) high system pressure and low volume flow
d) low system pressure and high volume flow.
21.
The accumulator in a hydraulic system works as
a) a fluid storage.
b) a pressure storage.
c) a volume storage.
d) an energy storage
22.
The type of hydraulic fluid which has the greatest resistance to cavitation is:
a) Synthetic fluid
b) Water and glycol based fluid.
c) Vegetable oil based fluid (caster oil).
d) Mineral oil based fluid.
23.
Parameters to monitor a hydraulic system in the cockpit can be:
a) Pressure and RPM of the hydraulic pump.
b) Pressure and hydraulic pump output.
c) Pressure, fluid temperature and quantity
d) Pressure and fluid viscosity.
24.
The working principle of the anti-skid system is:
a) Reduction of the brake pressure at the slower turning wheels
b) Increase of the brake pressure at the slower turning wheels.
c) Increase of the brake pressure at the faster turning wheels.
d) Reduction of the brake pressure at the faster turning wheels.
25.
The ice protection system currently used for the most modern jet aeroplanes is the
a) Liquid de-icing system.
b) Electrical de-icing system.
c) Hot air system
d) Pneumatic system with expandable boots.
26.
During flight, the wing anti-ice system has to protect
a) the whole leading edge and the whole upper wing surface.
b) a part of the whole leading edge
c) slats and the leading edge flaps only.
d) the whole upper wing surface and the flaps.
27.
In jet aeroplanes the 'thermal anti-ice system' is primarily supplied by
a) ram air, heated via a heat exchanger.
b) bleed air from the engines
c) turbo compressors.
d) the APU.
28.
The de-icing system which is mostly used for the wings of modern turboprop aeroplanes is:
a) Fluid de-icing.
b) Electrical heating.
c) Pneumatic boots
d) Thermal anti-icing.
29.
The ice protection for propellers of modern turboprop aeroplanes works
a) electrically
b) with hot air.
c) with anti-icing fluid.
d) pneumatically.
30.
On an aircraft, the Krueger flap is a:
a) leading edge flap close to the wing root
b) leading edge flap close to the wing tip
c) trailing edge flap
d) leading edge fla
31.
"Conditioned" air is air that has:
a) been controlled in respect of temperature and pressure
b) had the oxygen content increased.
c) had the oxygen content reduced.
d) had any moisture removed from it.
32.
A cabin pressure controller maintains a pre-set cabin altitude by regulating the:
a) position of the outflow valve(s)
b) position of the duct relief valve(s).
c) mass air flow into the cabin.
d) position of the inward relief valve.
33.
Assuming an accumulator is pre-charged with air to 1000 psi and the hydraulic system is pressurised to 1500 psi, the accumulator gauge will read:
a) 1500 psi
b) 500 psi.
c) 1000 psi.
d) 2500 psi.
34.
Internal leakage in a hydraulic system will cause:
a) fluid loss.
b) an increased fluid temperature
c) a decreased fluid temperature.
d) an increased fluid pressure.
35.
On large aeroplanes equipped with power brakes, the main source of power is derived from:
a) pressure to the rudder pedals.
b) the master cylinders.
c) the aeroplane's hydraulic system
d) the brake actuators.
36.
Fire precautions to be observed before refuelling are:
a) Ground Power Units (GPU) are not to be operated.
b) Aircraft must be more than 10 metres from radar or HF radio equipment under test.
c) All bonding and connections to the earth terminal between ground equipment and the aircraft should be made before filler caps are removed
d) Passengers may be boarded (traversing the refuelling zone) providing suitable fire extinguishers are readily available.
37.
"Nose wheel shimmy" may be described as:
a) the amount of free movement of the nose wheel before steering takes effect.
b) the oscillatory movement of the nose wheel when extended prior to landing.
c) a possibly damaging vibration of the nose wheel when moving on the ground
d) aircraft vibration caused by the nose wheel upon extension of the gear.
38.
The term "Bootstrap", when used to identify a cabin air conditioning and pressurisation system, refers to the:
a) charge air across the inter-cooler heat exchanger.
b) cold air unit (air cycle machine) arrangement
c) means by which pressurisation is controlled.
d) source of the charge air.
39.
In a bootstrap cooling system the supply air is first:
a) used to increase the cabin air supply pressure when the charge pressure is too low.
b) compressed, passed through a secondary heat exchanger, and then across an expansion turbine
c) passed across an expansion turbine, then compressed and passed through a secondary heat exchanger.
d) passed across an expansion turbine, then directly to the heat exchanger.
40.
The term "pressure cabin" applies when an aeroplane:
a) has the ability to maintain a constant cabin differential pressure at all flight altitudes.
b) is only pressurised in the area of the control cabin.
c) has the ability to maintain a constant cabin altitude at all flight altitudes.
d) has the means to maintain cabin pressure higher than ambient pressure
41.
Under normal flight conditions, cabin pressure is controlled by:
a) regulating the discharge of air through the outflow valve(s)
b) pressurisation duct relief valve(s).
c) engine rpm.
d) inward relief valve(s).
42.
Assuming cabin pressure decreases, the cabin rate of climb indicator should indicate:
a) zero.
b) a rate of descent of approximately 300 feet per minutes.
c) a rate of descent dependent upon the cabin differential pressure.
d) a rate of climb
43.
An accumulator in a hydraulic system will:
a) reduce fluid temperature only.
b) increase pressure surges within the system.
c) reduce fluid temperature and pressure.
d) store fluid under pressure
44.
Assuming a hydraulic accumulator is pre-charged with air to 1000 psi. If the hydraulic system is then pressurised to its operating pressure of 3000 psi, the indicated pressure on the air side of the accumulator should be:
a) 4000 psi.
b) 1000 psi.
c) 2000 psi.
d) 3000 psi
45.
To allow for failure of the normal method of system pressure limiting control, a hydraulic system often incorporates
a) auxiliary hydraulic motors.
b) a high pressure relief valve
c) an accumulator.
d) a stand-by hydraulic pump.
46.
The Ram Air Turbine (RAT) provides emergency hydraulic power for:
a) flap extension only.
b) undercarriage selection and automatic brake system.
c) nose wheel steering after the aeroplane has landed.
d) flight controls in the event of loss of engine driven hydraulic power
47.
In a compensated capacitance type quantity indicating system, the contents gauge of a half-full fuel tank indicates a fuel mass of 8000 kg. If a temperature rise increased the volume of fuel by 5%, the indicated fuel mass would:
a) remain the same
b) increase by 5%.
c) decrease by 5%.
d) increase by 10%.
48.
Tyre "creep" may be described as the:
a) gradual circumferential increase of tyre wear.
b) the increase in inflation pressure due to decrease in ambient temperature.
c) the decrease in inflation pressure due to increase in ambient temperature.
d) circumferential movement of the tyre in relation to the wheel flange
49.
The reason for the fact that an aeroplane designed for long distances cannot simply be used for short haul flights at higher frequencies is that
a) the procedures and checklists for this kind of aeroplanes will take too much time
b) in that case some fuel tanks remain empty during the whole flight, which stresses the aeroplanes structure in an unacceptable way
c) these aeroplanes often consume too much fuel on short haul flights.
d) the lifetime of the fatigue sensitive parts has been based on a determined load spectru
50.
The ABS (Auto Brake System) is being disconnected after landing ..
a) by pilot actio
b) the system is always armed
c) at a certain low speed
d) automatically
51.
The purposes of the oil and the nitrogen in an oleo-pneumatic strut are:
a) the oil supplies the damping and lubrication function, the nitrogen supplies the heat dissipation function.
b) the oil supplies the spring function and the nitrogen supplies the damping function.
c) the oil supplies the sealing and lubrication function, the nitrogen supplies the damping function.
d) the oil supplies the damping function and the nitrogen supplies the spring functio
52.
The function of a feed box in the fuel tank is to
a) distribute the fuel to the various tanks during refuelling
b) increase the fuel level at the boost pump locatio
c) trap fuel sediments or sludge in the lower part of the tank
d) ventilate the tank during refuelling under high pressure
53.
The part of the flight that will cause the highest loads on the torsion link in a bogie gear is
a) Taxiing with a small turning radius
b) Touch down with crosswind
c) Gear down selection
d) Braking with an inoperative anti skid system.
54.
The reason for the trim switch on a control column to consist of two separate switches is
a) To be able to use two different trim speeds, slow trim rate at high speed and high trim rate at low speed
b) To prevent that both pilots perform opposite trim inputs.
c) Because there are two trim motors.
d) To reduce the probability of a trim-runawa
55.
Assume that during cruise flight with air-conditioning packs ON, the outflow valve(s) would close. The result would be that:
a) the pressure differential would go to the maximum valu
b) the cabin pressure would become equal to the ambient outside air pressure
c) the air supply would automatically be stopped
d) the skin of the cabin would be overstressed
56.
The function of an air cycle machine is to:
a) decrease the pressure of the bleed air.
b) pump the conditioned air into the cabin.
c) cool the bleed air
d) remove the water from the bleed air.
57.
Hydraulic fluid, entering the hydraulic pump, is slightly pressurised to:
a) ensure sufficient pump output.
b) prevent overheating of the pump.
c) prevent vapour locking.
d) prevent cavitation in the pump
58.
The function of a fusible plug is to
a) function as a special circuit breaker in the electric system
b) protect the brake against brake disk fusion due to excessive temperature.
c) protect against excessive pressure in the pneumatic system.
d) protect the tyre against explosion due to excessive temperature
59.
The reservoirs of a hydraulic system can be pressurized:
a) by an auxiliary system.
b) by bleed air from the engine
c) in flight only.
d) by the air conditioning system.
60.
The cross-feed fuel system enables:
a) the supply of the outboard jet engines from any outboard fuel tank.
b) the supply of any jet engine from any fuel tank
c) the supply of the jet engines mounted on a wing from any fuel tank within that wing.
d) only the transfer of fuel from the centre tank to the wing tanks.
61.
Fuel pumps submerged in the fuel tanks of a multi-engine aircraft are:
a) low pressure variable swash plate pumps.
b) centrifugal low pressure type pumps
c) centrifugal high pressure pumps.
d) high pressure variable swash plate pumps.
62.
If the pressure in the cabin tends to become lower than the outside ambient air pressure the:
a) negative pressure relief valve will close
b) outflow valve open completely.
c) air cycle machine will stop.
d) negative pressure relief valve will open
63.
Regarding a thermal wing anti-icing system, the correct statement is:
a) Aerodynamic performances of the wings are not maintained and there is a reduction of maximum engine thrust.
b) Aerodynamic performances of the wings are maintained and there is no reduction of maximum engine thrust.
c) Aerodynamic performances of the wings are not maintained and there is no reduction of maximum engine thrust.
d) Aerodynamic performances of the wings are maintained and there is a reduction of maximum engine thrust
64.
The correct statement about rain protection for cockpit windshields is that:
a) wipers are sufficient under heavy rain conditions to provide adequate view through the cockpit windows.
b) rain repellent should never be sprayed onto the windshield unless the rainfall is very heavy
c) the alcohol de-icing system for cockpit windows is also suitable for rain protection.
d) the electric de-icing system for cockpit windows is also suitable for rain protection.
65.
For a JAR25 aeroplane, spoilers are:
a) lower wing surface devices, their deflection is always asymmetrical.
b) lower wing surface devices, their deflection can be symmetrical or asymmetrical.
c) upper wing surface devices, their deflection can be symmetrical or asymmetrical
d) upper wing surface devices, their deflection is always asymmetrical.
66.
On an airplane, the Krueger flaps are:
a) trailing edge flaps close to the wing tip
b) trailing edge flaps close to the wing root
c) leading edge flaps close to the wing roo
d) leading edge flaps close to the wing tip
67.
Compared to a tyre fitted with an inner tube, a tubeless tyre presents the following characteristics:
1 - high heating
2 - valve fragility
3 - lower risk of bursting
4 - better adjustment to wheels
The combination containing all the correct statements is:
a) 2, 4.
b) 2, 3.
c) 1, 2, 3, 4.
d) 3, 4
68.
On a modern aeroplane, to avoid the risk of tyre burst from overheating, due for example to prolonged braking during an aborted take-off, there is:
a) a hollow bolt screwed into the wheel which melts at a given temperature (thermal fuse) and deflates the tyre
b) a pressure relief valve situated in the filler valve.
c) water injection triggered at a fixed temperature in order to lower tyre temperature.
d) the "Emergency Burst" function of the anti-skid system which adapts braking to the tyre temperature.
69.
The low pressure switch of a hydraulic circuit sets off an alarm if:
a) the reservoir level is at the normal operation limit.
b) there is a leak in the reservoir return line.
c) the pump power accumulator is deflated.
d) the pump output pressure is insufficient
70.
Concerning the sequential pneumatic impulses used in certain leading edge de-icing devices, one can affirm that:
1 - They prevent ice formation.
2 - They are triggered from the flight deck after icing has become visible.
3 - A cycle lasts more than ten seconds.
4 - There are more than ten cycles per second.
The combination which regroups all the correct statements is:
a) 1 - 4
b) 2 –
c) 2 - 4
d) 1 – 3
71.
On an aircraft landing gear, an under-inflated tyre:
a) will have an increased critical hydroplaning speed
b) will be more subject to viscosity aquaplaning on dry runway
c) it's tread will deteriorate faster
d) will wear at the shoulder
72.
A scissor is a component found on landing gears. Its function is to:
a) create the wheel pitch on bogie gears.
b) make the body gears pivot when the nose wheel is turned through more than 20°.
c) transform the translational movement of the rudder pedals into the rotational movement of the nose wheel.
d) prevent any rotation of the oleo strut in the undercarriage shock absorber
73.
For an aeroplane hydraulic supply circuit, the correct statement is:
a) the regulation system deals only with emergency operation and is not applied to all hydraulic services but only those considered as essential.
b) the reservoir constitutes a reserve of hydraulic fluid maintained under pressure by a pneumatic back pressure (air or nitrogen) and destined to serve as a fluid or pressure reserve.
c) the security components comprise the filters, the pressure relief valves, the by-passes, and the fire shut-off valve
d) the pumps are always electric due to the high pressures which they must deliver (140 to 210 kg/cm²).
74.
For this question use annex 021-11494A) Associate the correct legend to each of the numbered diagrams:
a) 1- cantilever 2- dual wheels 3- half fork 4- fork
b) 1- cantilever 2- fork 3- half fork 4- dual wheel
c) 1- half-fork 2- single trace 3- cantilever 4- dual wheels
d) 1- half fork 2- fork 3- cantilever 4- tandem
75.
(For this question use annex 021-4960A) Automatic temperature control of the system as shown, would be accomplished by:
a) the temperature selector in conjunction with cabin sensors and the temperature regulator, modulating the mix valve
b) the temperature selector only modulating the mix valve.
c) the cabin sensors only modulating the mix valve.
d) automatic control of the ram air.
76.
(For this question use annex 021-6716A)
In the hydraulic press schematically shown, what balancing Force would be acting on the right hand side ? (The diagram is not to scale)
a) 20 N.
b) 100 N
c) 1 N.
d) 1000 N.
77.
(For this question use annex 021-5248A) The hydraulic systems which works correctly is shown in the figure:
a) Figure c)
b) a
c) d
78.
(For this question use annex 021-6736A) The schematic diagram annexed illustrates an actuator and a selector valve in a typical hydraulic system. Assuming hydraulic pressure throughout and no internal leakage:
a) the piston moves to the left due to pressure acting on differential areas.
b) since pressures are equal, the piston is free to move in response to external forces.
c) the piston moves to the right due to equal pressure acting on differential areas.
d) a condition of hydraulic lock exists and no movement of the piston will take place
This is more feedback!
This is the feedback!
Data Base Login Information: Please make
sure that you enter your name before
submitting your results.
My Name
*Enter your name here
Back to Top
