INDIGO SYSTEMS(515-806) - Dgca question bank for pilots

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#1. DURALUMIN alloys :1 have an aluminium-copper base.2 have an aluminiummagnesium base.3 are easy to weld.4 are difficult to weld.5 have a good thermal conductivity.6 have a poor air corrosion resistanceThe combination regrouping all the correct statements is :

2,3,6

1,3,6

1,4,5

2,4,5

#2. Among the different types of aircraft structures, the shell structures efficiently transmit the:1. normal bending stresses2. tangent bending stresses3. torsional moment4. shear stressesThe combination regrouping all the correct statements is :

1, 3, 4

1, 2, 3

2, 3, 4

1, 2, 4

#3. ‘Fail safe construction’ is :

A construction which is suitable for aerobatic flight

A simple and cheap type of construction

A type of construction for small aircraft only.

A type of construction in which the load is carried by other components if a part of the structure fails.

#4. The fuselage of an aircraft consists, among others, of stringers whose purpose is to:

assist the skin in absorbing the longitudinal traction-compression stresses

provide sound and thermal isolation

integrate the strains due to pressurization to which the skin is subjected and convert them into a tensile stress.

withstand the shear stresses

#5. 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

these aeroplanes often consume too much fuel on short haul flights

in that case some fuel tanks remain empty during the whole flight, which stresses the aeroplane's structure in an unacceptable way

the lifetime of the fatigue sensitive parts has been based on a determined load spectrum

#6. 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.

tension, then in compression

compression, then in tension.

compression.

#7. In flight the wing of an aircraft containing fuel is subjected to vertical loads that produce a bending moment which is:

equal to the zero -fuel weight multiplied by the span

highest at the wing root

equal to half the weight of the aircraft multiplied by the semi span

lowest at the wing root

#8. The Maximum Zero Fuel Mass:1 Is a limitation set by regulation.2 Is designed for a maximum load factor.3 Is due to the maximum bending moment at wing root.4 Requires to empty external tanks first.5 Requires to empty internal tanks first.The correct combination of true statements is :

1,2,3

1,3,5

2,4

2,5

#9. On a non-stressed skin type wing, the wing structure elements which take up the vertical bending moments Mx are:

the skin.

the spars

the ribs

the webs

#10. The advantage of mounting the tailplane on top of the vertical stabilizer is :

to a have greater effectiveness at high speed

to decrease fuel consumption by creating a tail heavy situation

that it does not require a de-icing system

to withdraw it from the influence of wing turbulence

#11. A torsion link assembly is installed on the landing gear to :

absorb the spring tension

avoid rotation of the piston rod relative to the gear oleo strut.

control the wheels

lock the landing gear

#12. In a commercial transport aircraft the landing gear operating system is usually:

Mechanically driven

Pneumatically driven

Hydraulically driven

Electrically driven.

#13. Generally, on modern jet transport aircraft, how can the landing gear be extended if there is a complete hydraulic system failure

Mechanically

Pneumatically.

By hydraulic accumulators

Electrically.

#14. If the profile grooves or the tread of a new aircraft tyre are worn, the tyre can be:

repaired once

Repaired several times

Used on the nose wheel only.

Never repaired.

#15. The operating principle of an anti skid system is as follows : the brake pressure will be :

Decreased on the faster turning wheels

Decreased on the slower turning wheels

Increased on the faster turning wheels

Increased on the slower turning wheels

#16. The type of brake unit found on most transport aeroplanes is a:

Belt brake

Single disk brake

Multiple disk brake.

Drum type brake.

#17. The reason for fitting thermal plugs to aircraft wheels is that they :

release air from the tyre in case of overheating

prevent the brakes from overheating.

prevent heat transfer from the brake disks to the tyres.

release air from the tyre in case of overpressure

#18. Thermal plugs are installed in:

cargo compartments

fire warning systems

wheel rims

cabin windows

#19. When a landing gear wheel is hydroplaning, its friction factor is equal to:

0.1

0.5

#20. 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:

1, 3.

1, 4.

2, 3.

2, 4.

#21. The illumination of the green landing gear light indicates that the landing gear is :

in the required position

not in the required position

locked-down and its door is locked

locked-down

#22. 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.

2, 4.

2, 3.

1, 4.

#23. In a hydraulic braking system, the accumulator is:

an accumulator designed to restore brake energy in the event of a hydraulic failure.

a buffer accumulator whose function is to assist the hydraulic system during high intensity braking.

designed to take up the hydraulic energy filtered by the anti-skid system in order to prevent wheel blocking.

a damping type accumulator designed to take up the pressure fluctuations of the automatic braking system

#24. Which is (are) the damping element(s) in a landing gear shock absorber used on larger aircraft ?

Springs.

Nitrogen.

Oxygen.

Nitrogen and a viscous liquid

#25. In some aircraft, there is a protection device to avoid the landing gear being inadvertently retracted on the ground. It consists of :

A warning light which is activated by the WOW (Weight On Wheels) sensor system.

An aural warning horn

A latch located in the landing gear lever.

A bolt.

#26. A tubeless tyre is a tyre:1. which requires solid or branched wheels2. whose valve can be sheared in sudden accelerations3. whose mounting rim must be flawless4. which requires no rim protection between rim flange and tire removing device5. which does not burst in the event of a tire puncture6. which eliminates internal friction between the tube and the tireThe combination regrouping all the correct statements is :

3, 4, 5.

2, 3, 6.

1, 2, 5.

1, 5, 6.

#27. Landing gear torque links are used to:

take up the lateral stresses to which the gear is subjected

prevent the extension of the landing gear oleo strut rod

maintain the compass heading throughout taxiing and take-off.

prevent rotation of the landing gear piston in the oleo strut

#28. A main landing gear is said to be “”locked down”” when:

it is in the down position

the corresponding indicator lamp is amber

the strut is locked by an overcentre mechanism

the actuating cylinder is at the end of it's travel

#29. The modern anti-skid processes are based on the use of a computer whose input data is:1. idle wheel speed (measured)2. braked wheel speed (measured)3. brake temperature (measured)4. desired idle wheel train slipping rate5. tire pressureThe combination regrouping all the correct statements is :

1, 3.

1, 2, 3, 4, 5

2, 4.

1, 2, 4.

#30. On large aeroplanes equipped with power brakes, the main source of power is derived from :

the master cylinders

the brake actuators

pressure to the rudder pedals

the aeroplane's hydraulic system.

#31. “”Nose wheel shimmy”” may be described as :

the amount of free movement of the nose wheel before steering takes effect.

the oscillatory movement of the nose wheel when extended prior to landing

aircraft vibration caused by the nose wheel upon extension of the gear.

a possibly damaging vibration of the nose wheel when moving on the ground.

#32. The part of the flight that will cause the highest loads on the torsion link in a bogie gear is

Braking with an inoperative anti skid system

Touch down with crosswind

Gear down selection

Taxiing with a small turning radius.

#33. Tyre “”creep”” may be described as the :

the increase in inflation pressure due to drease in ambient temperature

circumferential movement of the tyre in relation to the wheel flange.

gradual circumferential increase of tyre wear.

the decrease in inflation pressure due to increase in ambient temperature

#34. The ABS (Auto Brake System) is being diconnected after landing ..

by pilot action

the system is always armed

at a certain low speed

automatically

#35. The purposes of the oil and the nitrogen in an oleo-pneumatic strut are :

the oil supplies the damping function and the nitrogen supplies the spring function

the oil supplies the spring function and the nitrogen supplies the damping function

the oil supplies the damping and lubrication function, the nitrogen supplies the heatdissipation function.

the oil supplies the sealing and lubrication function, the nitrogen supplies the damping function.

#36. The function of a fusible plug is to

protect the tyre against explosion due to excessive temperature.

protect against excessive pressure in the pneumatic system.

protect the brake against brake disk fusion due to excessive temperature

function as a special circuit breaker in the electric system

#37. (For this question use appendix )Associate the correct legend to each of the numbered diagrams :

1- cantilever 2- dual wheels 3- half fork 4- fork

1- half fork 2- fork 3- cantilever 4- tandem

1- cantilever 2- fork 3- half fork 4- dual wheels

1- half-fork 2- single trace 3- cantilever 4- dual wheels

#38. A scissor is a component found on landing gears. Its function is to :

create the wheel pitch on bogie gears

make the body gears pivot when the nosewheel is turned through more than 20°.

transform the translational movement of the rudder pedals into the rotational movement of the nosewheel

prevent any rotation of the oleo strut in the undercarriage shock absorber.

#39. Compared to a tyre fitted with an inner tube, a tubeless tyre presents the following characteristics :1 – high heating2 – valve fragility3 – lower risk of bursting4 – better adjustment to wheelsThe combination containing all the correct statements is:

04-Fev

03-Fev

04-Mar

1 - 2 - 3 - 4

#40. 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:

the ""Emergency Burst"" function of the anti-skid system which adapts braking to the tyre temperature

a hollow bolt screwed into the wheel which melts at a given temperature (thermal fuse) and deflates the tyre.

water injection triggered at a fixed temperature in order to lower tyre temperature.

a pressure relief valve situated in the filler valve

#41. On an aircraft landing gear, an under-inflated tyre:

it's tread will deteriorate faster

will have an increased critical hydroplanning speed

will wear at the shoulders

will be more subject to viscosity aquaplaning on dry runway

#42. The trim tab :

increases hinge moment and reduces control surface efficiency

reduces hinge moment and control surface efficiency

increases hinge moment and control surface efficiency.

reduces hinge moment and increases control surface efficiency

#43. The purpose of a trim tab (device) is to:

lower manoeuvring control forces

reduce or to cancel control forces

trim the aeroplane during normal flight

trim the aeroplane at low airspeed.

#44. An artificial feel unit is necessary in the pitch channel when:

there is a trimmable stabilizer.

the elevators are actuated by reversible servo-control units.

the elevators are actuated by irreversible servo-control units.

the elevators are fitted with servo-tabs or trim tabs.

#45. An artificial feel unit system:

is mounted in parallel on a spring tab.

must be mounted in parallel on an irreversible servo-control unit

is necessary on a reversible servodyne unit.

must be mounted in series on an irreversible servo-control unit.

#46. A Yaw Damper is :

An elevator augmentor to avoid the nose-down effect at speeds greater than M=0.8.

An elevator augmentor

A rudder damper designed to avoid the ""Dutch roll"".

A roll trim tab.

#47. In a steep turn to the left, when using spoilers …

The right aileron will ascend, the left one will descend, 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 descend, the left one will ascend, the right spoiler will extend and the left one will retract.

#48. 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 5

2 and 3

3 and 5

1 and 2

#49. Which of these signals are inputs, at least, in the stall warning computers?

Angle of attack and flaps and slats deflection.

Angle of attack, flaps deflection and EPR

Angle of attack, flaps deflection, EPR and N1.

Angle of attack and flaps and spoilers deflection

#50. On an aircraft, the Krueger flap is a:

leading edge flap close to the wing tip

leading edge flap

leading edge flap close to the wing root

trailing edge flap

#51. 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

Because there are two trim motors

To be able to use two different trim speeds, slow trim rate at high speed and high trim rate at low speed

To reduce the probability of a trim-runaway

#52. On an aeroplane, spoilers are :

lower wing surface devices, their deflection is always asymmetrical

upper wing surface devices, their deflection is always asymmetrical

lower wing surface devices, their deflection is symmetrical or asymmetrical

upper wing surface devices, their deflection is symmetrical or asymmetrical.

#53. On an airplane, the Krueger flaps are:

leading edge flaps close to the wing root

leading edge flaps close to the wing tip

trailing edge flaps close to the wing tip

trailing edge flaps close to the wing root

#54. Hydraulic fluids must have the following characteristics:1. thermal stability2. low emulsifying characteristics3. corrosion resistance4. good resistance to combustion5. high compressibility6. high volatility7. high viscosityThe combination regrouping all the correct statements is :

1, 2, 3, 4

1, 3, 4, 6

1, 2, 5, 7

2, 3, 4, 5

#55. In a hydraulic braking system, an accumulator is precharged to 1200 psi.An electrically driven hydraulic pump is started and provides a system pressure of 3000 psi. The hydraulic pressure gauge which is connected to the gas section of the accumulator, reads:

1800 psi

3000 psi

1200 psi

4200 psi

#56. Hydraulic fluids :

Are irritating to eyes and skin.

Cause high fire risk.

Are irritating to eyes and skin and cause high fire risk.

Do not require special care.

#57. Hydraulic fluids used in systems of large modern airliners are:

Phosphate ester base fluids

Water base fluids

Vegetable base fluids.

Mineral base fluids.

#58. Hydraulic power is a function of :

Pump RPM only.

Pump size and volume flow

System pressure and volume flow.

System pressure and tank capacity

#59. Large transport aeroplane hydraulic systems usually operate with a system pressure of approximately:

1000 psi

2000 psi

3000 psi

4000 psi

#60. In hydraulic systems of large modern transport category aircraft the fluids used are:

Synthetic oil.

Mineral oil.

Vegetable oil.

Water and glycol

#61. The type of hydraulic oil used in modern hydraulic systems is:

vegetable oil

mineral oil

mixture of mineral oil and alcohol

synthetic oil

#62. The type of hydraulic fluid which has the highest resistance against cavitation is :

Vegetable oil based fluid (caster oil).

Mineral oil based fluid

Synthetic fluid.

Water and glycol based fluid

#63. The component that transforms the hydraulic pressure into a linear motion is called …

An accumulator

A Pressure regulator.

An actuator or jack

A hydraulic pump

#64. The aircraft hydraulic system is designed to produce:

high pressure and small flow.

high pressure and large flow

small pressure and small flow

small pressure and large flow.

#65. Hydraulic fluids of synthetic origin are:

blue.

pink.

red.

purple.

#66. Internal leakage in a hydraulic system will cause :

fluid loss

a decreased fluid temperature.

an increased fluid pressure

an increased fluid temperature

#67. Discounting the possibility of leak, the level in a hydraulic reservoir will :

always remain the same

initially increase with system pressurisation

fluctuate with jack displacement and accumulator pressure

increase as ambient temperature decreases

#68. 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.

1000 psi

2000 psi

4000 psi.

#69. For an aeroplane hydraulic supply circuit, the correct statement is :

the security components comprise the filters, the pressure relief valves, the bypasses, and the fire shut-off valve.

the pumps are always electric due to the high pressures which they must deliver (140 to 210 kg/cm²).

the regulation system deals only with emergency operation and is not applied to all hydraulic services but only those considered as essential.

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.

#70. Where in a hydraulic system might overheat indicators be installed?

In the reservoirs.

At the pumps.

At the coolers.

At actuators.

#71. In a modern hydraulic system, “”hydraulic fuses”” can be found. Their function is :

To isolate a part of the system and protect it against accidental pollution.

To switch to the secondary system in case of a leak in the primary brake system.

To prevent total system loss in case of a leaking hydraulic line.

To allow by-passing of a hydraulic pump in case it is subject to excessive pressure, without further damage to the system.

#72. In a hydraulic system, the reservoir is pressurized in order to:

keep the hydraulic fluid at optimum temperature

prevent pump cavitation

reduce fluid combustibility

seal the system

#73. The purpose of a shuttle valve is to:

Prevent overloading of the hydraulic pump

Relieve excess pressure in hydraulic systems

Protect a hydraulic system from overpressure

Supply an operating unit with the most appropriate system pressure.

#74. Shuttle valves will automatically:

Shut down systems which are overloaded

Switch hydraulically operated units to the most appropriate pressure supply

Guard systems against overpressure

Reduce pump loads

#75. In addition to energy storage the accumulator of the hydraulic system is used :

for fluid storage.

for damping pressure surges in the system

as a pressure relief valve.

for pressure storage.

#76. The hydraulic device similar to an electronic diode is a :

flow control valve

distribution valve.

check valve

shutoff valve

#77. The function of the selector valve is to:

automatically activate the hydraulic system

communicate system pressure to either side of an actuator

select the system to which the hydraulic pump should supply pressure

discharge some hydraulic fluid if the system pressure is too high.

#78. 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 :

1500 psi

1000 psi.

2500 psi.

500 psi.

#79. An accumulator in a hydraulic system will :

increase pressure surges within the system

reduce fluid temperature and pressure

store fluid under pressure

reduce fluid temperature only.

#80. In hydraulic system, a shuttle valve :

is a self-lapping non-return valve.

allows two units to be operated by one pressure source

regulates pump delivery pressure

allows two possible sources of pressure to operate one unit.

#81. To allow for failure of the normal method of system pressure limiting control, a hydraulic system often incorporates

a high pressure relief valve

a stand-by hydraulic pump.

an accumulator

auxiliary hydraulic motors

#82. The hydraulic oil, entering the hydraulic pump, is slightly pressurised to :

prevent vapour locking.

ensure sufficient pump output

prevent overheating of the pump.

prevent cavitation in the pump

#83. The Ram Air Turbine (RAT) provides emergency hydraulic power for :

nose wheel steering after the aeroplane has landed

flight controls in the event of loss of engine driven hydraulic power

undercarriage selection and automatic brake system

flap extension only

#84. The tanks of a hydraulic system are pressurized:

in flight only

by the air conditioning system.

by bleed air coming from the turbine-engine.

by an auxiliary system

#85. The low pressure switch of a hydraulic circuit sets off an alarm if :

the pump power accumulator is deflated

there is a leak in the reservoir return line.

the pump output pressure is insufficient

the reservoir level is at the normal operation limit

#86. If the cabin altitude rises (aircraft in level flight), the differential pressure:

decreases

remains constant

increases

may exceed the maximum permitted differential unless immediate preventative action is taken.

#87. 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 :

5, 6, 1

1, 2, 3

4, 5, 3

2, 6, 4

#88. During a normal pressurised climb after take-off:

the cabin differential pressure is maintained constant

absolute cabin pressure increases to compensate for the fall in pressure outside the aircraft

the pressurisation system is inoperative until an altitude of 10 000 feet is reached

cabin pressure decreases more slowly than atmospheric pressure

#89. The purpose of cabin air flow control valves in a pressurization system is to :

discharge cabin air to atmosphere if cabin pressure rises above the selected altitude.

regulate cabin pressure to the selected altitude.

regulate cabin pressure at the maximum cabin pressure differential

Maintain a constant and sufficient mass air flow to ventilate the cabin and minimise cabin pressure surge

#90. Assuming cabin differential pressure has attained the required value in normal flight conditions, if flight altitude is maintained:

the pressurisation system ceases to function until leakage reduces the pressure.

a constant mass air flow is permitted through the cabin.

the outflow valves will move to the fully closed position

the outflow valves will move to the fully open position.

#91. Cabin pressure is controlled by :

the cabin air mass flow control inlet valve(s).

delivering a substantially constant flow of air into the cabin and controlling the outflow.

the cabin air re-circulation system

controlling the flow of air into the cabin with a constant outflow

#92. During level flight at a constant cabin pressure altitude (which could be decreased, even at this flight level), the cabin outflow valves are:

Fully closed until the cabin descends to a selected altitude

fully closed until the cabin climbs to a selected altitude.

At the pre-set position for take-off

Partially open

#93. The purpose of a ditching control is to:

achieve rapid depressurisation.

close the outflow valve(s).

direct pressurisation air to the flotation bags.

open the outflow valve(s).

#94. The cabin pressure is regulated by the:

Cabin inlet airflow valve

Air cycle machine

Air conditioning pack.

Outflow valve

#95. The pressurization of the cabin is controlled by :

The engine's bleed valves

The cabin outflow valve.

The engine's RPM.

The cabin inlet airflow

#96. Cabin differential pressure means the pressure difference between:

actual cabin pressure and selected pressure

cabin pressure and ambient air pressure

cabin pressure and ambient air pressure at MSL.

cockpit and passenger cabin

#97. Under normal conditions (JAR 25) the cabin pressure altitude is not allowed to exceed:

6000 ft

8000 ft

10000 ft

4000 ft

#98. Cabin altitude means the:

flight level the aircraft is flying at.

flight level altitude at maximum differential pressure

cabin pressure expressed as altitude

difference in height between the cabin floor and ceiling

#99. A warning device alerts the crew in case of an excessive cabin altitude. This warning must be triggered on reaching the following altitude:

10000 ft (approx. 3000 m)

14000 ft (approx. 4200 m)

8000 ft (approx. 2400 m)

12000 ft (approx. 3600 m)

#100. On a modern large pressurized transport aircraft, the maximum cabin differential pressure is approximately:

22 psi

13 - 15 psi

7 - 9 psi

3 - 5 psi