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CPL Test Series
Question Bank
Questions for INDIGO SYSTEMS( 515-806)
Answer the following questions
Test Mode
Training Mode
1.
Generally, on modern jet transport aircraft, how can the landing gear be extended if there is a complete hydraulic system failure
Mechanically
By hydraulic accumulators
Pneumatically.
Electrically.
2.
In order that DC generators will achieve equal load sharing when operating in parallel, it is necessary to ensure that
the synchronising bus-bar is disconnected from the busbar system
their voltages are almost equal
equal loads are connected to each generator busbar before paralleling.
adequate voltage differences exists
3.
Hydraulic fluids of synthetic origin are
purple.
pink.
blue.
red.
4.
The pack cooling fan provides
cooling air to the primary and secondary heat exchanger during slow flight and ground operation
cooling air to the pre-cooler
air to the eyeball outlets at the Passenger Service Unit (PSU).
cooling air to the primary and secondary heat exchanger during cruise
5.
The resistors R1 and R2 are connected in parallel. The value of the equivalent resistance (Req) so obtained is given by the following formula
1/Req = 1/(R1 + R2)
1/Req = 1/R1 + 1/R2
Req = R1 x R2
Req = R1 + R2
6.
The function of a constant speed drive (CSD) in an AC generating system is to
vary generator rpm in order to compensate for various AC loads
directly maintain a constant proportion between the rpm of an engine and a generator
drive the generator at a constant speed
vary the engine rpm (within limits) to compensate for various AC loads.
7.
The true statement among the following in relation to the application of Ohm's law is
power in the circuit is inversely proportional to the square of the current
Current in a circuit is directly proportional to the applied electromotive force
current in a circuit is inversely proportional to the electromotive force.
The current in a circuit is directly proportional to the resistance of the circuit.
8.
The low pressure switch of a hydraulic circuit sets off an alarm if
there is a leak in the reservoir return line.
the pump output pressure is insufficient
the pump power accumulator is deflated
the reservoir level is at the normal operation limit
9.
Assume a constant speed DC generator providing a constant output voltage. If the electrical load increases, the voltage regulator will
decrease the intensity of the excitation current
change the direction of the excitation current
maintain the intensity of the excitation current constant
increase the intensity of the excitation current
10.
On a transport type aircraft the fuel tank system is vented through
The return lines of the fuel pumps
Ram air scoops on the underside of the wing.
A pressure regulator in the wing tip.
Bleed air from the engines
11.
Hydraulic fluids used in systems of large modern airliners are
Mineral base fluids.
Vegetable base fluids.
Phosphate ester base fluids
Water base fluids
12.
Assuming a CSD fault is indicated, the CSD should be disconnected
at flight idle engine rpm
in accordance with the regulated voltage level of the AC generator
during engine operation only
on the ground only.
13.
On-board electrical systems are protected against faults of the following type:1. AC generator over-voltage2. AC generator under-voltage3. over-current4. overspeed5. under-frequency6. undue vibration of AC generatorsThe combination of correct statements is
1,3,5,6
1,2,4,5
1,2,4,6
2,3,4,5,6
14.
The function of a fusible plug is to
function as a special circuit breaker in the electric system
protect against excessive pressure in the pneumatic system.
protect the tyre against explosion due to excessive temperature.
protect the brake against brake disk fusion due to excessive temperature
15.
The frequency of an AC generator is dependent on the
number of individual poles and the field strength
number of individual poles only
number of pairs of poles and the speed of the moving part
field strength and the speed of the moving part.
16.
The vapor lock is
The effect of the water vapor bubbles in the induction manifold caused by the condensation
The exhaust gases obstructions caused by an engine overheating
The abnormal mixture enrichment caused by a greater gasoline vaporisation in the carburettor
A stoppage in a fuel feeding line caused by a fuel vapor bubble
17.
Cabin pressure is controlled by
delivering a substantially constant flow of air into the cabin and controlling the outflow.
controlling the flow of air into the cabin with a constant outflow
the cabin air mass flow control inlet valve(s).
the cabin air re-circulation system
18.
The purpose of the baffles in an aircraft's integral fuel tank is to
Prevent the fuel from flowing in the vent lines
Prevent mixture of the fuel and hydraulic fluid
Restrict the fuel from flowing to the wing tips during abnormal manoeuvre (side slipping...).
Prevent overpressure in the tank.
19.
On modern transport aircraft, cockpit windows are protected against icing by
Rain repellent system
Electric heating
Anti-icing fluid
Vinyl coating
20.
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
these aeroplanes often consume too much fuel on short haul flights
the lifetime of the fatigue sensitive parts has been based on a determined load spectrum
in that case some fuel tanks remain empty during the whole flight, which stresses the aeroplane's structure in an unacceptable way
the procedures and checklists for this kind of aeroplanes will take too much time
21.
The purpose of a voltage regulator is to control the output voltage of the
generators at varying speeds and the batteries at varying loads
generator at varying loads and speeds
batteries at varying loads
output of the TRU.
22.
In large modern aircraft, in the air conditioning system, reduction of air temperature and pressure is achieved by
a compressor
a condenser
an expansion turbine
an evaporator.
23.
In flight, the most commonly used anti-icing method for the wings of modern commercial aircraft fitted with turbo-jet units is
Mechanical (pneumatic source which acts by deforming the profiles of the leading edge).
Thermal (use of hot air).
Physical/chemical (glycol-based liquid).
Electrical (electrical resistances).
24.
An artificial feel unit system
is necessary on a reversible servodyne unit.
must be mounted in series on an irreversible servo-control unit.
is mounted in parallel on a spring tab.
must be mounted in parallel on an irreversible servo-control unit
25.
On an airplane, the Krueger flaps are
trailing edge flaps close to the wing tip
leading edge flaps close to the wing tip
leading edge flaps close to the wing root
trailing edge flaps close to the wing root
26.
In flight, if the constant speed drive (CSD) temperature indicator is in the red arc the
pilot can disconnect it to allow it to cool and use it again
pilot has to throttle back
pilot must disconnect it and manually control the alternator
pilot must disconnect it, and the generator is not available for the rest of flight
27.
A torsion link assembly is installed on the landing gear to
avoid rotation of the piston rod relative to the gear oleo strut.
lock the landing gear
control the wheels
absorb the spring tension
28.
The Auxiliary Power Unit (APU) has its own AC generator which
is driven at constant speed throught a Constant Speed Drive (CSD), in the same way as the main AC generator
supplies the aircraft with three-phase 115-200 V, 400 Hz AC.
must have the same characteristics as the main AC generator so that it can be easily coupled with the latter
is excited by its Generator Control Unit (GCU) as soon as the APU starts up
29.
Environmental system: in the air refrigeration unit, the water separation unit is placed
before the heat exchangers.
after the cooling turbine
before the cooling turbine
just after the heat exchangers
30.
A 3 phase AC generator has 3 separate stator windings spaced at
120°.
60°.
90°.
45°.
31.
""Conditioned"" air is air that has
been controlled in respect of temperature and pressure
had any moisture removed from it.
had the oxygen content reduced
had the oxygen content increased
32.
A thermal circuit breaker
can be reset without any danger even if the fault remains
is a protection system with a quick break capacity of about one hundredth of a second.
forbids any overcurrent
protects the system in the event of overheating, even without exceeding the maximum permissible current
33.
The type of brake unit found on most transport aeroplanes is a
Single disk brake
Drum type brake.
Belt brake
Multiple disk brake.
34.
If two constant frequency AC generators are operating independently, then the phase relationship of each generator
is unimportant
must be 120° out of phase
must be 240° out of phase
must be synchronised
35.
The function of an air cycle machine is to
decrease the pressure of the bleed air
cool the bleed air
pump the conditioned air into the cabin
remove the water from the bleed air.
36.
A Yaw Damper is
A rudder damper designed to avoid the ""Dutch roll"".
A roll trim tab.
An elevator augmentor
An elevator augmentor to avoid the nose-down effect at speeds greater than M=0.8.
37.
The cabin air for modern airplanes is usually supplied by
roots type compressors
piston compressors
main engine compressors
single radial compressors
38.
On most transport aircraft, the low pressure pumps of the fuel system are
mechanically driven by the engine's accessory gearbox
electro-mechanical wobble pumps, with self-regulated pressure
removable only after the associated tank has been emptied
centrifugal pumps, driven by an electric motor
39.
The reason for the trim switch on a control column to consist of two separate switches is
To prevent that both pilots perform opposite trim inputs
To be able to use two different trim speeds, slow trim rate at high speed and high trim rate at low speed
Because there are two trim motors
To reduce the probability of a trim-runaway
40.
On most transport jet aircraft, the low pressure pumps of the fuel system are supplied with electric power of the following type
28 V DC
28 V AC
115 V DC
115 V AC
41.
The pneumatic ice protection system is mainly used for
wings.
engine intakes
pitot tubes
propellers.
42.
The term ""Bootstrap"", when used to identify a cabin air conditioning and pressurisation system, refers to the
means by which pressurisation is controlled.
cold air unit (air cycle machine) arrangement
charge air across the inter-cooler heat exchanger
source of the charge air.
43.
A tubeless tyre has :1- a built-in-air tube.2- no built-in-air tube.3- a crossed side casing.4- a radial side casing.The combination of correct statements is
1,3.
1, 4.
2, 3.
2, 4.
44.
Cabin air for modern aircraft is usually taken from
the high pressure compressor
the second fan stage
the low pressure compressor and from the high pressure compressor if necessary
the low pressure compressor
45.
The services connected to a supply bus-bar are normally in
series, so that isolation of loads increases the bus-bar voltage
series, so that isolating one load increases the bus-bar current consumption
series, so that isolating one load increases the bus-bar current consumption
parallel, so that isolating individual loads decreases the bus-bar current consumption
46.
Hydraulic fluids
Are irritating to eyes and skin and cause high fire risk.
Do not require special care.
Are irritating to eyes and skin.
Cause high fire risk.
47.
The correct statement about rain protection for cockpit windshields is that
the electric de-icing system for cockpit windows is also suitable for rain protection
rain repellent should never be sprayed onto the windshield unless the rainfall is very heavy
the alcohol de-icing system for cockpit windows is also suitable for rain protection
wipers are sufficient under heavy rain conditions to provide adequate view through the cockpit windows
48.
Large transport aeroplane hydraulic systems usually operate with a system pressure of approximately
3000 psi
4000 psi
2000 psi
1000 psi
49.
The purpose of a shuttle valve is to
Relieve excess pressure in hydraulic systems
Prevent overloading of the hydraulic pump
Supply an operating unit with the most appropriate system pressure.
Protect a hydraulic system from overpressure
50.
On a jet aircraft fuel heaters are
Installed only in the center tank
Installed in each tank
not necessary at all.
Located on the engines
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