TECHGEN-BNC-MODULE1

TECHGEN-BNC-MODULE1

1. The purpose of baffle check valves fitted in aircraft fuel tanks is to:

a) prevent positive pressure build up inside the tank.
b) prevent fuel movement to the wing tip.
c) close the vent lines in case of turbulence.
d) damp out movement of the fuel in the tank.

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

a) may exceed the maximum permitted differential unless immediate preventative action is taken.
b) remains constant
c) increases
d) decreases

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

a) Phosphate ester base fluids.
b) Water base fluids.
c) Mineral base fluids.
d) Vegetable base fluids.

4. Hydraulic fluids:

a) Are irritating to eyes and skin and cause high fire risk.
b) Do not require special care.
c) Are irritating to eyes and skin.
d) Cause high fire risk.

5. The purpose of the baffles in an aircraft's integral fuel tank is to:

a) Restrict the fuel from flowing to the wing tips during abnormal manoeuvre (side slipping...).
b) Prevent the fuel from flowing in the vent lines.
c) Prevent overpressure in the tank.
d) Prevent mixture of the fuel and hydraulic fluid.

6. (For this question use annex 021-786A) In a pressurized aircraft whose cabin altitude is 8000 ft, a crack in a cabin window makes it necessary to reduce the differential pressure to 5 psi. The flight level to be maintained in order to keep the same cabin altitude is:

a) FL 180
b) FL 280
c) FL 340
d) FL 230

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

a) prevent heat transfer from the brake disks to the tyres.
b) release air from the tyre in the event of overpressure.
c) prevent the brakes from overheating.
d) release air from the tyre in the event of overheating.

8. Thermal plugs are installed in:

a) cabin windows.
b) cargo compartments.
c) fire warning systems.
d) wheel rims.

9. The wavelength of a radio transmitted on frequency 121.95 MHz is:

a) 2.46 m
b) 24.60 m
c) 24.60 cm
d) 2.46 cm

10. In addition to energy storage, the accumulator of the hydraulic system is used:

a) as a pressure relief valve.
b) for fluid storage.
c) for pressure storage.
d) for damping pressure surges in the system.

11. Hydraulic power is a function of:

a) System pressure and tank capacity.
b) Pump RPM only.
c) System pressure and volume flow.
d) Pump size and volume flow.

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

a) trim the aeroplane at low airspeed.
b) trim the aeroplane during normal flight.
c) lower manoeuvring control forces.
d) reduce or to cancel control forces.

13. Main cabin temperature is:

a) controlled by individual passenger.
b) not controllable at the maximum cabin differential pressure.
c) controlled automatically, or by flight crew selection.
d) Only controllable at maximum cabin differential pressure.

14. 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 rate-of-change, 3. limitation of differential pressure 4. balancing aircraft altitude with cabin altitude 5. cabin ventilation 6. keeping a constant differential pressure throughout all the flight phases. The combination regrouping all the correct statements is:

a) 5, 6, 1
b) 2, 6, 4
c) 1, 2, 3
d) 4, 5, 3

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

a) 6000 ft
b) 4000 ft
c) 10000 ft
d) 8000 ft

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

a) 4000 psi
b) 2000 psi
c) 3000 psi
d) 1000 psi

17. The trim tab:

a) reduces hinge moment and increases control surface efficiency.
b) increases hinge moment and control surface efficiency.
c) increases hinge moment and reduces control surface efficiency.
d) reduces hinge moment and control surface efficiency.

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

a) prevent pump cavitation
b) keep the hydraulic fluid at optimum temperature
c) seal the system
d) reduce fluid combustibility

19. Where in a hydraulic system might overheat detectors be installed?

a) At the pumps.
b) At the coolers.
c) At the actuators.
d) In the reservoirs.

20. Cabin differential pressure means the pressure difference between:

a) cabin pressure and ambient air pressure.
b) cabin pressure and ambient air pressure at MSL.
c) actual cabin pressure and selected pressure.
d) cockpit and passenger cabin.

21. Shuttle valves will automatically:

a) guard systems against overpressure.
b) reduce pump loads.
c) shut down systems which are overloaded.
d) switch hydraulically operated units to the most appropriate pressure supply.

22. The air-conditioning pack of a present-day aircraft consists of several components: these include two heat exchangers; the primary exchanger (P) and the secondary exchanger (S). The functions of these heat exchangers are as follows:

a) P: warms up engine bleed air S: increases the temperature of air originating from the compressor of the pack.
b) P: pre-cools the engine bleed air S: increases the temperature of the air used for air-conditioning of cargo compartment (animals).
c) P: precools the engine bleed air S: reduces the temperature of the air from the primary exchanger or from the pack's compressor.
d) P: warms up engine bleed air S: recirculates the cabin air, reducing its temperature.

23. The pressurization of tanks is maintained by the fuel:

a) dump system.
b) tank drains.
c) vent system.
d) top off unit.

24. Hydraulic fluids must have the following characteristics: 1. thermal stability 2. low emulsifying characteristics 3. corrosion resistant 4. good resistance to combustion 5. high compressibility 6. high volatility 7. high viscosity The combination regrouping all the correct statements is:

a) 1, 2, 3, 4
b) 1, 3, 4, 6
c) 2, 3, 4, 5
d) 1, 2, 5, 7

25. Cabin pressurisation is controlled by the:

a) The engine's bleed valves.
b) The engine's RPM.
c) The cabin inlet airflow.
d) The cabin outflow valve.

26. During a normal pressurised climb after take-off:

a) the cabin differential pressure is maintained constant
b) the pressurisation system is inoperative until an altitude of 10 000 feet is reached
c) absolute cabin pressure increases to compensate for the fall in pressure outside the aircraft
d) cabin pressure decreases more slowly than atmospheric pressure

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

a) control the wheels.
b) absorb the spring tension.
c) avoid rotation of the piston rod relative to the gear oleo strut.
d) lock the landing gear.

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

a) Partially open.
b) Fully closed until the cabin descends to a selected altitude.
c) At the pre-set position for take-off.
d) fully closed until the cabin climbs to a selected altitude.

29. Assuming cabin differential pressure has reached the required value in normal flight conditions, if flight altitude and air conditioning system setting are maintained:

a) the mass air flow through the cabin is constant.
b) the pressurisation system ceases to function until leakage reduces the pressure.
c) the outflow valves will move to the fully open position.
d) the outflow valves will move to the fully closed position.

30. Cabin pressure is controlled by:

a) delivering a substantially constant flow of air into the cabin and controlling the outflow.
b) the cabin air mass flow control inlet valve(s).
c) the cabin air re-circulation system.
d) controlling the flow of air into the cabin with a constant outflow.

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

a) synthetic oil
b) vegetable oil
c) mixture of mineral oil and alcohol
d) mineral oil

32. The purpose of a ditching control is to:

a) achieve rapid depressurisation.
b) open the outflow valve(s).
c) direct pressurisation air to the flotation bags.
d) close the outflow valve(s).

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

a) By hydraulic accumulators.
b) Pneumatically.
c) Mechanically
d) Electrically.

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

a) the elevators are actuated by irreversible servo-control units.
b) there is a trimmable stabilizer.
c) the elevators are fitted with servo-tabs or trim tabs.
d) the elevators are actuated by reversible servo-control units.

35. In a modern hydraulic system, "hydraulic fuses" can be found. Their function is:

a) To switch to the secondary system in case of a leak in the primary brake system.
b) To prevent total system loss in case of a leaking hydraulic line.
c) To allow by-passing of a hydraulic pump in case it is subject to excessive pressure, without further damage to the system.
d) To isolate a part of the system and protect it against accidental pollution.

36. The types of fuel tanks used on most modern transport aircraft are:

a) Integral tanks.
b) Cell tanks.
c) Combined fuel tanks.
d) Fixed built-in tanks.

37. The cabin pressure is regulated by the:

a) Air conditioning pack.
b) Cabin inlet airflow valve.
c) Air cycle machine.
d) Outflow valve.

38. The advantages of fly-by-wire control are: 1. reduction of the electric and hydraulic power required to operate the control surfaces 2. lesser sensitivity to lightning strike 3. direct and indirect weight saving through simplification of systems 4. immunity to different interfering signals 5. improvement of piloting quality throughout the flight envelope The combination regrouping all the correct statements is:

a) 3 and 5
b) 3, 4 and 5
c) 1 and 2
d) 1 and 5

39. In a hydraulic braking system, an accumulator is pre-charged 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:

a) 4200 psi
b) 1800 psi
c) 1200 psi
d) 3000 psi

40. On a transport type aircraft the fuel tank system is vented through:

a) Ram air scoops on the underside of the wing.
b) A pressure regulator in the wing tip.
c) The return lines of the fuel pumps.
d) Bleed air from the engines.

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

a) Pneumatically driven.
b) Hydraulically driven.
c) Mechanically driven.
d) Electrically driven.

42. Environmental system: in the air refrigeration unit, the water separation unit is placed:

a) just after the heat exchangers.
b) after the cooling turbine.
c) before the cooling turbine.
d) before the heat exchangers.

43. An artificial feel system:

a) is mounted in parallel on a spring tab.
b) functions in parallel to an irreversible servo-control unit.
c) is necessary in a reversible flight control actuator unit.
d) functions in series to an irreversible servo-control unit.

44. In a bootstrap system, the purpose of the heat exchangers is to:

a) cool bleed air and compressor air from the turbo refrigerator.
b) allow a steady compressor outlet temperature.
c) cool bleed air.
d) allow a homogeneous temperature by mixing air flows from various air conditioning groups in operation.

45. In aviation, the reflection on ionosphere layers phenomenon is used in the following frequencies:

a) UHF
b) HF
c) VLF
d) VHF

46. In flight, a cantilever wing of an airplane containing fuel undergoes vertical loads which produce a bending moment:

a) equal to the zero -fuel weight multiplied by the span
b) highest at the wing root
c) equal to half the weight of the aircraft multiplied by the semi span
d) lowest at the wing root

47. On most transport aircraft, the low pressure pumps of the fuel system are:

a) Piston pumps.
b) Diaphragm pumps.
c) Gear type pumps.
d) Centrifugal pumps.

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

a) Maintain a constant and sufficient mass air flow to ventilate the cabin and minimise cabin pressure surges.
b) discharge cabin air to atmosphere if cabin pressure rises above the selected altitude.
c) regulate cabin pressure at the maximum cabin pressure differential.
d) regulate cabin pressure to the selected altitude.

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

a) Belt brake.
b) Drum type brake.
c) Multiple disk brake.
d) Single disk brake.

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

a) Water and glycol.
b) Vegetable oil.
c) Synthetic oil.
d) Mineral oil.

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