Email
info@vayudootaviation.com
Phone No
+91 7276526726
become a pilot
Home
About us
courses
CPL
ATPL
RTR(A)
Airline Cadet Program
IGRUA Entrance Prep
B.Sc. Aviation
Pilot Training
INDIA
USA
CANADA
SOUTH AFRICA
NEW ZEALAND
EUROPE
Aircraft Type-Rating
Airbus A320
Boeing 737
Blogs
contact
CPL Test Series
Question Bank
Questions for INDIGO SYSTEMS( 515-806)
Answer the following questions
Test Mode
Training Mode
1.
On starting, in a brushless AC generator with no commutator rings, the generator is activated by
the stabilizer winding jointly with the voltage regulator.
the main field winding.
the auxiliary winding.
a set of permanent magnets.
2.
When AC generators are operated in paralllel, they must be of the same
voltage and frequency
frequency and amperage
amperage and kVAR
voltage and amperage.
3.
A thermal circuit breaker
is a protection system with a quick break capacity of about one hundredth of a second.
can be reset without any danger even if the fault remains
protects the system in the event of overheating, even without exceeding the maximum permissible current
forbids any overcurrent
4.
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
1000 psi
4000 psi.
2000 psi
3000 psi.
5.
The operating principle of an anti skid system is as follows : the brake pressure will be
Increased on the faster turning wheels
Decreased on the faster turning wheels
Decreased on the slower turning wheels
Increased on the slower turning wheels
6.
Fire precautions to be observed before refuelling are
Ground Power Units (GPU) are not to be operated
Passengers may be boarded (traversing the refuelling zone) providing suitable fire extinguishers are readily available
Aircraft must be more than 10 metres from radar or HF radio equipment under test
All bonding and earthing connections between ground equipment and the aircraft should be made before filler caps are removed
7.
Discounting the possibility of leak, the level in a hydraulic reservoir will
fluctuate with jack displacement and accumulator pressure
initially increase with system pressurisation
increase as ambient temperature decreases
always remain the same
8.
Large transport aeroplane hydraulic systems usually operate with a system pressure of approximately
1000 psi
2000 psi
4000 psi
3000 psi
9.
Static dischargers :1. are used to set all the parts of the airframe to the same electrical potential2. are placed on wing and tail tips to facilitate electrical discharge3. are used to reset the electrostatic potential of the aircraft to a value approximating 0 volts4. are located on wing and tail tips to reduce intererence with the on-board radiocommunication systems to a minimum5. limit the risks of transfer of electrical charges between the aircraft and the electrified cloudsThe combination regrouping all the correct statements is
3,4,5.
2,4,5.
1,3,4.
1,2,5.
10.
A current limiter fuse in a DC generation system is used to
limit the current in the field circuit
instantaneously rupture to limit the current in the load
allow a short term overload before rupturing
limit the current in the armature
11.
The advantages of fly-by-wire control are:1. reduction of the electric and hydraulic power required to operate the control surfaces2. lesser sensitivity to lightning strike3. direct and indirect weight saving through simplification of systems4. immunity to different interfering signals5. improvement of piloting quality throughout the flight envelopeThe combination regrouping all the correct statements is
1 and 2
2 and 3
3 and 5
1 and 5
12.
The purpose of a trim tab (device) is to
reduce or to cancel control forces
trim the aeroplane at low airspeed.
trim the aeroplane during normal flight
lower manoeuvring control forces
13.
In hydraulic systems of large modern transport category aircraft the fluids used are
Water and glycol
Vegetable oil.
Synthetic oil.
Mineral oil.
14.
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
increase by 10 %.
increase by 5 %.
remain the same
decrease by 5 %.
15.
When carrying out battery condition check using the aircraft's voltmeter
a load should be applied to the battery in order to give a better indication of condition
no load should be applied to the battery because it would depress the voltage.
the battery should be isolated
the load condition is unimportant
16.
The purposes of the oil and the nitrogen in an oleo-pneumatic strut are
the oil supplies the damping and lubrication function, the nitrogen supplies the heatdissipation function.
the oil supplies the spring function and the nitrogen supplies the damping function
the oil supplies the sealing and lubrication function, the nitrogen supplies the damping function.
the oil supplies the damping function and the nitrogen supplies the spring function
17.
Main cabin temperature is
controlled by individual passenger
not controllable at the maximum cabin differential pressure
controlled automatically, or by flight crew selection
Only controllable at maximum cabin differential pressure
18.
The cabin air for modern airplanes is usually supplied by
single radial compressors
main engine compressors
piston compressors
roots type compressors
19.
The heating facility for the windshield of an aircraft is
Used on a continual basis as it reduces the thermal gradients which adversely affect the useful life of the components.
Used only at low altitudes where there is a risk of ice formation.
Harmful to the integrity of the windows in the event of a bird strike
Only used when hot-air demisting is insufficient
20.
The frequency of an AC generator is dependent on the
number of individual poles and the field strength
field strength and the speed of the moving part.
number of pairs of poles and the speed of the moving part
number of individual poles only
21.
The purpose of the cabin pressure controller, in the automatic mode, is to perform the following functions:1. control of cabin altitude,2. control of cabin altitude rateof- change,3. limitation of differential pressure4. balancing aircraft altitude with cabin altitude5. cabin ventilation6. keeping a constant differential pressure throughout all the flight phases.The combination regrouping all the correct statements is
4, 5, 3
2, 6, 4
1, 2, 3
5, 6, 1
22.
Hydraulic fluids used in systems of large modern airliners are
Mineral base fluids.
Water base fluids
Vegetable base fluids.
Phosphate ester base fluids
23.
In a commercial transport aircraft the landing gear operating system is usually
Pneumatically driven
Mechanically driven
Electrically driven.
Hydraulically driven
24.
A static inverter is a
static discharger
filter against radio interference
transistorized unit used to convert DC into AC.
device for reversing the polarity of the static charge
25.
The cabin heating supply in a heavy jet transport aircraft is obtained from
a fuel heater system
hot air coming from the engine's compressors
hot air coming from the engine's turbines
an electrical heater system
26.
Internal leakage in a hydraulic system will cause
a decreased fluid temperature.
an increased fluid temperature
an increased fluid pressure
fluid loss
27.
In large modern aircraft, in the air conditioning system, reduction of air temperature and pressure is achieved by
an expansion turbine
a condenser
a compressor
an evaporator.
28.
The fuel crossfeed system
is only used in flight for fuel transfer from one tank to another.
is only used to feed an engine from the tank of the opposite wing.
is only used on the ground for fuel transfer from one tank to another.
allows feeding of any engine from any fuel tank.
29.
Under normal flight conditions, cabin pressure is controlled by
inward relief valve(s).
regulating the discharge of air through the outflow valve(s).
pressurisation duct relief valve(s).
engine rpm
30.
When a conductor cuts the flux of a magnetic field
an electromotive force (EMF) is induced in the conductor
current will flow in accordance with Flemings left hand rule
there will be no effect on the conductor
the field will collapse
31.
A Yaw Damper is
An elevator augmentor to avoid the nose-down effect at speeds greater than M=0.8.
A roll trim tab.
A rudder damper designed to avoid the ""Dutch roll"".
An elevator augmentor
32.
The pressurization of the cabin is controlled by
The cabin inlet airflow
The cabin outflow valve.
The engine's RPM.
The engine's bleed valves
33.
The wing of an aircraft in flight, powered by engines located under the wing, is subjected to a bending moment which causes its leading edge, from the wing root to the wing tip, to operate in
tension, then in compression
compression.
tension.
compression, then in tension.
34.
The essential difference between aircraft AC alternators and DC generators (dynamos) is that the
induced windings of the alternators are rotating (rotor), and the dynamos have a rotary inductor coil
induced (output) windings of the alternators are fixed (stator), and the dynamos have a fixed inductor (field) coil
The alternators generate much less power than DC generators
alternators supply all of the output current through the commutators and brush assemblies
35.
Environmental system: in the air refrigeration unit, the water separation unit is placed
before the cooling turbine
just after the heat exchangers
before the heat exchangers.
after the cooling turbine
36.
Engine bleed air used for air conditioning and pressurization in turbo-jet aeroplanes is usually taken from the
fan section
turbine section.
by-pass ducting
compressor section.
37.
In a cabin air conditioning system, equipped with a bootstrap, the mass air flow is routed via the
secondary heat exchanger outlet to the turbine inlet of the cold air unit
turbine outlet of the cold air unit to the primary heat exchanger inlet
compressor outlet of the cold air unit to the primary heat exchanger inlet
secondary heat exchanger outlet to the compressor inlet of the cold air unit.
38.
When an underspeed fault is detected on an AC generator connected to the aircraft AC busbar, the protection device opens the
exciter breaker
generator breaker
exciter breaker, generator breaker and tie breaker
exciter breaker and generator breaker.
39.
Real load sharing in a parallel AC system is achieved by
carefully selecting the number of loads on the bus-bars at any one time
controlling the generator field current
automatic adjustment of the torque on each generator rotor via the CSD unit
monitoring the kVAR of each generator/alternator
40.
The tanks of a hydraulic system are pressurized
in flight only
by an auxiliary system
by bleed air coming from the turbine-engine.
by the air conditioning system.
41.
The anti-ice or de-icing system which is mostly used for the wings of modern turboprop aeroplanes is
Thermal anti-icing
Pneumatic boots
Electrical heating
Fluid de-icing
42.
The cabin pressure is regulated by the
Air cycle machine
Outflow valve
Air conditioning pack.
Cabin inlet airflow valve
43.
If the frequency of the supply in a series capacitive circuit is increased, the current flowing in the circuit will
increase.
remain the same
be zero
decrease
44.
The water separator of an air-conditioning unit is located at the cooling unit
outlet and uses an evaporation process
outlet and uses a centrifugal process.
inlet and uses an evaporation process
inlet and uses a centrifugal process
45.
The type of brake unit found on most transport aeroplanes is a
Single disk brake
Multiple disk brake.
Drum type brake.
Belt brake
46.
In an aircraft equipped with a DC main power system, AC for instrument operation may be obtained from
a TRU.
a contactor
an inverter
a rectifier
47.
The primary purpose of bonding the metallic parts of an aircraft is to
prevent electrolytic corrosion between mating surfaces of similar metals
isolate all components electrically and thus make the static potential constant.
provide a single earth for electrical devices
provide safe distribution of electrical charges and currents
48.
A warning device alerts the crew in case of an excessive cabin altitude. This warning must be triggered on reaching the following altitude
8000 ft (approx. 2400 m)
12000 ft (approx. 3600 m)
10000 ft (approx. 3000 m)
14000 ft (approx. 4200 m)
49.
Fuel dump systems are required
on all transport category aircraft.
on all transport category aircraft with more than 150 seats.
on aircraft with a Maximum Take-Off Weight (MTOW) higher than 5.7 tons.
on all transport category aircraft where the Maximum Take-Off Weight (MTOW) is significant higher than the Maximum Landing Weight (MLW).
50.
The hydraulic device similar to an electronic diode is a
flow control valve
check valve
distribution valve.
shutoff valve
Submit
Make New Set
