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CPL Test Series
Question Bank
Questions for INDIGO SYSTEMS( 515-806)
Answer the following questions
Test Mode
Training Mode
1.
In aeronautics, the most commonly used batteries are NiCd because
they are cheaper than lead-acid batteries
they weigh less than lead-acid batteries.
their output voltage is more constant than lead-acid batteries
their electrolyte is neither corrosive nor dangerous
2.
Concerning electrically powered ice protection devices, the only true statement is
on modern aeroplanes, electrically powered thermal devices are very efficient, therefore they only need little energy
on modern aeroplanes, electrical power supply being available in excess, this system is very often used for large surfaces de-icing
on modern aeroplanes, electrically powered thermal devices are used as de-icing devices for pitot-tubes, static ports, windshield...
on modern aeroplanes, electrically powered thermal devices are used to prevent icing on small surfaces (pitot-static, windshield...).
3.
In flight, if the constant speed drive (CSD) temperature indicator is in the red arc the
pilot must disconnect it, and the generator is not available for the rest of flight
pilot must disconnect it and manually control the alternator
pilot has to throttle back
pilot can disconnect it to allow it to cool and use it again
4.
The cabin rate of descent is
a cabin pressure decrease
always the same as the airplane's rate of descent.
is not possible at constant airplane altitudes.
a cabin pressure increase
5.
Shimmy occurs on the nosewheel landing gear during taxiing when:1. the wheels tend to describe a sinusoidal motion on the ground2. the wheels no longer respond to the pilot's actionsThis effect is overcome by means of:3. the torque link4. an accumulator associated with the steering cylinderThe combination of correct statements is
2, 3.
1, 3.
2, 4.
1, 4.
6.
The so-called ""hot buses"" or ""direct buses"" are
directly connected to the battery
providing an alternative current.
automatically connected to the battery if generators have failed
kept in operating conditions by an electrical resistance in the case of energy failure
7.
In a steep turn to the left, when using spoilers
The right aileron will descend, the left one will ascend, the right spoiler will extend and the left one will retract.
The right aileron will descend, the left one will ascend, the right spoiler will retract and the left one will extend.
The right aileron will ascend, the left one will descend, the right spoiler will retract and the left one will extend.
The right aileron will ascend, the left one will descend, the right spoiler will extend and the left one will retract
8.
A turbo-fan cold air unit will
decrease charge air pressure whilst causing hte temperature to rise in the heat exchanger
increase charge air pressure whilst causing hte temperature to drop in the heat exchanger
cause a pressure drop as well as an associated temperature drop in the charge air
not affect the charge air pressure
9.
The speed of an asynchronous four-pole motor fed at a frequency of 400 Hertz is
1600 revolutions per minute
6000 revolutions per minute
12000 revolutions per minute
800 revolutions per minute
10.
""Conditioned"" air is air that has
been controlled in respect of temperature and pressure
had the oxygen content reduced
had any moisture removed from it.
had the oxygen content increased
11.
The measured output power components of a constant frequency AC system are
amperes and kilowatts.
kVA and kVAR.
volts and amperes
volts and kilowatts
12.
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
the procedures and checklists for this kind of aeroplanes will take too much time
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
these aeroplanes often consume too much fuel on short haul flights
13.
The fuel supply system on a jet engine includes a fuel heating device, upstream of the main fuel filter so as to
prevent fuel from freezing in fuel pipes due to low temperatures at high altitude
ease low pressure pumps work by increasing fuel fluidity.
prevent, at low fuel temperature, the risk of ice formation from water contained in the fuel
maintain and improve fuel heating power
14.
A Yaw Damper is
An elevator augmentor
A roll trim tab.
A rudder damper designed to avoid the ""Dutch roll"".
An elevator augmentor to avoid the nose-down effect at speeds greater than M=0.8.
15.
The ice protection for propellers of modern turboprop aeroplanes works
pneumatically.
with hot air.
with anti-icing fluid.
electrically.
16.
In an aircraft equipped with a DC main power system, AC for instrument operation may be obtained from
a TRU.
an inverter
a rectifier
a contactor
17.
The cabin heating supply in a heavy jet transport aircraft is obtained from
an electrical heater system
hot air coming from the engine's compressors
a fuel heater system
hot air coming from the engine's turbines
18.
Landing gear torque links are used to
maintain the compass heading throughout taxiing and take-off.
prevent rotation of the landing gear piston in the oleo strut
prevent the extension of the landing gear oleo strut rod
take up the lateral stresses to which the gear is subjected
19.
In a compensated capacitance type quantity indicating system, the contents gauge of a half-full fuel tank indicates a fuel mass of 8000 lb. If a temperature rise increased the volume of fuel by 5 %, the indicated fuel weight would
remain the same
increase by 10 %.
decrease by 5 %.
increase by 5 %.
20.
Cabin pressure is controlled by
delivering a substantially constant flow of air into the cabin and controlling the outflow.
the cabin air mass flow control inlet valve(s).
the cabin air re-circulation system
controlling the flow of air into the cabin with a constant outflow
21.
Main cabin temperature is
Only controllable at maximum cabin differential pressure
controlled by individual passenger
not controllable at the maximum cabin differential pressure
controlled automatically, or by flight crew selection
22.
In a hydraulic braking system, the accumulator is
designed to take up the hydraulic energy filtered by the anti-skid system in order to prevent wheel blocking.
an accumulator designed to restore brake energy in the event of a hydraulic failure.
a damping type accumulator designed to take up the pressure fluctuations of the automatic braking system
a buffer accumulator whose function is to assist the hydraulic system during high intensity braking.
23.
A 3 phase AC generator has 3 separate stator windings spaced at
90°.
45°.
120°.
60°.
24.
Thermal plugs are installed in
fire warning systems
cargo compartments
wheel rims
cabin windows
25.
Internal leakage in a hydraulic system will cause
a decreased fluid temperature.
an increased fluid pressure
fluid loss
an increased fluid temperature
26.
A ""trip-free"" type circuit breaker is a circuit protection device which
will not allow the contacts to be held closed while a current fault exists in the circuit
can be reset at any time
is free from the normal CB tripping characteristic.
will allow the contacts to be held closed in order to clear a fault in the circuit
27.
Connecting two 12 volt 40 ampere-hour capacity batteries in series will result in a total voltage and capacity respectively of
12 volts, 80 ampere-hours
24 volts, 40 ampere-hours
12 volts, 40 ampere-hours.
24 volts, 80 ampere-hours
28.
On an aircraft, the Krueger flap is a
leading edge flap close to the wing tip
trailing edge flap
leading edge flap close to the wing root
leading edge flap
29.
Cabin differential pressure means the pressure difference between
actual cabin pressure and selected pressure
cabin pressure and ambient air pressure
cockpit and passenger cabin
cabin pressure and ambient air pressure at MSL.
30.
An accumulator in a hydraulic system will
store fluid under pressure
reduce fluid temperature and pressure
reduce fluid temperature only.
increase pressure surges within the system
31.
During flight, the wing anti-ice system has to protect
the whole upper wing surface and the flaps
leading edges, slats and the leading edge flaps
leading edges only
slats and the leading edge flaps only
32.
When a landing gear wheel is hydroplaning, its friction factor is equal to
0.1
0.5
1
33.
The advantages of alternating current on board an aircraft are:1. simple connection2. high starting torque3. flexibility in use4. lighter weight of equipment5. easy to convert into direct current6. easy maintenance of machinesThe combination of correct statements is
1, 2, 3, 4, 5, 6
1, 4, 6
3, 4, 5, 6
1, 2, 3, 5, 6
34.
In addition to energy storage the accumulator of the hydraulic system is used
for fluid storage.
for pressure storage.
as a pressure relief valve.
for damping pressure surges in the system
35.
If the frequency of the supply in a series capacitive circuit is increased, the current flowing in the circuit will
decrease
remain the same
be zero
increase.
36.
The advantages of grounding the negative pole of the aircraft structure are:1. Weight saving2. Easy fault detection3. Increase of short-circuit risk4. Reduction of short-circuit risk5. Circuits are not single-wired linesThe combination regrouping all the correct statements is
1, 2, 3
1, 3, 5
2, 3, 5
1, 2, 4
37.
The purpose of baffle check valves fitted in aircraft fuel tanks is to
prevent positive pressure build up inside the tank.
damp out movement of the fuel in the tank
prevent fuel movement to the wing tip.
close the vent lines in case of turbulence.
38.
The type of windings commonly used in DC starter motors are
series wound
series shunt wound.
shunt wound
compound wound
39.
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
3000 psi.
2000 psi
1000 psi
4000 psi.
40.
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
Prevent overpressure in the tank.
Restrict the fuel from flowing to the wing tips during abnormal manoeuvre (side slipping...).
41.
The cross-feed fuel system enables
the supply of the outboard jet engines from any outboard fuel tank.
the supply of the jet engines mounted on a wing from any fuel tank within that wing.
only the transfer of fuel from the centre tank to the wing tanks.
the supply of any jet engine from any fuel tank.
42.
The cabin air for modern airplanes is usually supplied by
roots type compressors
piston compressors
single radial compressors
main engine compressors
43.
The illumination of the green landing gear light indicates that the landing gear is
locked-down
in the required position
locked-down and its door is locked
not in the required position
44.
The services connected to a supply bus-bar are normally in
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
series, so that isolation of loads increases the bus-bar voltage
45.
In flight the wing of an aircraft containing fuel is subjected to vertical loads that produce a bending moment which is
equal to half the weight of the aircraft multiplied by the semi span
highest at the wing root
equal to the zero -fuel weight multiplied by the span
lowest at the wing root
46.
Concerning the sequential pneumatic impulses used in certain leading edge deicing 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
04-Fev
c) 03-Jan
04-Jan
03-Fev
47.
The refueling in a transport jet aircraft is made
Through a unique point (an underwing refueling center).
By means of the aircraft suction pumps through a unique point (an underwing refueling center).
By means of the aircraft suction pumps
Through the refueling cap of every tank
48.
It may be determined that an aircraft is not properly bonded if
static noises can be heard on the radio
a circuit breaker pops out
there is heavy corrosion on the fuselage skin mountings
there is interference on the VOR receiver
49.
The ABS (Auto Brake System) is being diconnected after landing
the system is always armed
at a certain low speed
by pilot action
automatically
50.
Pulling the fire shutoff handle causes a number of devices to disconnect. In respect of the AC generator it can be said that the
exciter control relay opens
exciter control relay, the generator breaker and the tie breaker open
exciter control relay and the generator breaker open
generator breaker opens
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