TECHGEN-BNC-MODULE13

TECHGEN-BNC-MODULE13

1. During a flight under normal conditions, a main rotor blade is seen to be flying higher than the other blades in the disc during cruise. This can usually be adjusted by:

a) Shortening the pitch change rod on the subject blade.
b) Adjusting the weights on the blade tip.
c) Adjusting the trim tabs on the subject blade.
d) Lengthening the pitch change rod on the subject blade.

2. The purpose of the rotor brake can be defined by: 1. To bring the rotor to rest as quickly as possible post engine shut down. 2. To stop the rotor from Flight RPM. 3. To aid high wind rotor engagement. 4. To enable an abrupt stop of the rotor during low RPM blade sailing. The combination of all the correct statements is:

a) 3, 4.
b) 2, 4.
c) 1, 3 , 4.
d) 1, 3.

3. According to JAR 29, a tail rotor drive shaft running between two engines should be:

a) Mounted to allow for expansion.
b) Protected by the engine fire extinguishing system.
c) Either protected by a firewall or fire proofed.
d) Mounted on its own bearing hangers, the first being directly behind the main rotor gearbox.

4. Dynamic balancing of main rotor systems:

a) Is usually achieved by adding weights to certain nominated rotor blades only.
b) Is usually achieved by adding or subtracting weights to either the main rotor blade attachment pins or to the main rotor head itself.
c) Is not necessary as the hub and blades are statically balanced at manufacture.
d) Is usually achieved by adding or subtracting weights to the main rotor blade tips.

5. The tail rotor gearbox changes direction of drive:

a) through 90Â°, reduces rotational speed and provides facilities for tail rotor control.
b) through minus 90Â° and increases rotational speed.
c) and provides facilities for tail rotor control maintaining a constant speed.
d) and increases rotational speed.

6. Rotor brakes are usually located:

a) Around the main rotor output shaft.
b) Within the main rotor gearbox.
c) On the tail rotor drive shaft.
d) On the drive shaft between the engine and the main rotor gearbox.

7. Fuel system indications available to the pilot are normally restricted to:

a) Fuel contents; Fuel low level; Fuel pressure; Fuel flow; Fuel transfer status; Fuel filter condition.
b) Fuel contents and low level only.
c) Fuel low level; Fuel flow; Fuel temperature; Fuel filter monitor; Tank transfer status.
d) Fuel flow; Tank transfer status; Fuel contents; Fuel temperature; Fuel cooler status.

8. Tail rotors differ from most main rotors in that:

a) The pitch changes from a negative angle setting to a positive angle setting.
b) The lead/lag hinge is incorporated with the flapping hinge.
c) The tail rotor rotates at a lower speed.
d) They always have few blades.

9. A pressure regulator is used in a hydraulic system:

a) In conjunction with a constant delivery type pump.
b) To ensure that an equal pressure flow is delivered to critical components such as servo actuators.
c) As an interface between the system and the cockpit indicators.
d) In conjunction with a variable delivery type pump.

10. Fuel low level warnings usually provide the pilot with information regarding:

a) The level of fuel in the supply tanks.
b) The level of fuel in all tanks.
c) Fuel pressure at the outlet of the high pressure pump.
d) Fuel pressure at the outlet of the booster pump.

11. Rotor brake discs are manufactured from:

a) Steel or carbon fibre.
b) Boron aluminide or titanium.
c) Aluminium or steel.
d) Steel or titanium.

12. A tandem rotor system is the term given to a system using:

a) Two main rotors mounted one above the other.
b) Two main rotors mounted one in front of the other.
c) One main rotor and an anti-torque tail rotor.
d) Two main rotors mounted at either side of the fuselage.

13. A type of freewheel unit incorporating rollers and ramps is known as a:

a) Episoidal Cam Freewheel Unit.
b) Sprag Freewheel Unit.
c) Differential Freewheel Unit.
d) Ramp and Roller Freewheel Unit.

14. When using a strobe type tracking and balancing system on a fully articulated rotor head, one blade is not equidistant from the other blades in the lateral plane. The cause of this defect is that:

a) The blade damper on the subject blade is not functioning correctly.
b) The pitch change rod is not correctly adjusted.
c) The blade trim tabs are not correctly adjusted.
d) The blade rigging is out of adjustment.

15. Tail rotors rotate:

a) At the same speed as the shafts and gear boxes.
b) At a lower speed than the main rotor.
c) At a greater speed than the main rotor and the tail rotor drive shafts.
d) At a greater speed than the main rotor and at a different speed than the drive shaft and intermediate gearbox.

16. Freewheel units between engine and main rotor gearbox are, in most cases, lubricated from:

a) An independent lubrication system driven by the main rotor gearbox.
b) An independent system driven by either the engine or an electrically driven pump.
c) The main rotor gearbox lubrication system.
d) The engine lubrication system.

17. A red 'landing gear up' warning light is fitted to some helicopters. This is to inform the pilot that:

a) The helicopter is on the ground with weight on wheels.
b) A combination of altitude and/or airspeed is below safe operating limits with the landing gear retracted.
c) The normal landing gear extension system has failed.
d) Hydraulic pressure has fallen below the locked up value.

18. Metal tail rotor drive shafts are normally manufactured from:

a) Aluminium tubing only.
b) Titanium and steel tubing.
c) Steel bar.
d) Aluminium or steel tubing.

19. The systems used for emergency extension of landing systems may comprise: 1. Compressed C0Â². 2. Compressed nitrogen. 3. Compressed oxygen. 4. Auxiliary hydraulic system. 5. Freefall.

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

20. On activation of a fuel dump system:

a) All fuel load with the exception of the supply tanks may be discharged overboard.
b) The pilot must particularly be careful of the handling of the engines to prevent overheating the turbine.
c) The pilot will be informed of free power turbine overspeed by either a power failure warning light or an overspeed light.
d) The total fuel load will be jettisoned, the engines shut down and the helicopter enters autorotation.

21. Modern tail rotor blades are usually manufactured from:

a) Carbon fibre.
b) Wood.
c) Composite materials.
d) Metal.

22. What indication will be available to the pilot of wear in either tail rotor gimbal or pitch change link bearings?

a) Vibration through the tail rotor/yaw pedals.
b) Loud noise from the tail rotor.
c) Instability in pitch control.
d) Stiffness in the tail rotor controls.

23. The type of hydraulic fluid most commonly used in helicopters is a:

a) Vegetable based fluid with a medium viscosity.
b) Phosphate ester based fluid with particularly good fire resistant properties.
c) Mineral based fluid with low viscosity.
d) Mineral based fluid with high viscosity.

24. Helicopter standby hydraulic pumps are:

a) Usually driven by electric motors or the main rotor gearbox.
b) Driven by the helicopters slipstream.
c) Usually fitted to the engine reduction gearbox.
d) For use on the ground only.

25. Fuel dump systems:

a) Are systems fitted to helicopters flying in hot and high conditions to supply large amounts of fuel to the combustion chamber, bypassing the fuel control unit, to meet power requirements.
b) Allow a rapid reduction in helicopter weight by discharging fuel to atmosphere.
c) Are not fitted to helicopters.
d) Provide for rapid deceleration of the gas generator in the event of free power turbine overspeed.

26. Fuel flow information:

a) Is used by the centre of gravity control system.
b) May be displayed on a cockpit gauge and passed to the auto-pilot and navigational systems.
c) Is not used on helicopters.
d) Is measured at the outlet of the booster pump.

27. The viscosity of a hydraulic fluid should be:

a) The highest to provide excellent lubrication properties.
b) The highest to minimize power consumption and resistance to flow.
c) The lowest to minimize power consumption and resistance to flow.
d) The lowest to provide excellent lubrication properties.

28. A snatch engagement of a freewheel unit:

a) Will cause the freewheel to ratchet until the pilot recovers the situation.
b) May result in the shearing of the engine drive shaft.
c) Is normal engagement.
d) Is absorbed by flexible couplings on the engine drive shaft.

29. Tail rotors differ from main rotors in that:

a) They do not provide for blade pitch cyclic variation.
b) Pitch remains constant throughout all flight regimes.
c) They always have fewer blades.
d) They rotate at a lower speed.

30. The most common material used in the construction of gearbox casings is:

a) Titanium alloy.
b) Aluminium alloy.
c) Steel alloy.
d) Magnesium alloy.

31. Loss of hydraulic system pressure from one system in a dual system equipped helicopter will normally be indicated in the cockpit by:

a) A master caution and a red light accompanied by an audio warning.
b) Either a red or amber light, with a loss of system pressure on the gauge accompanied b y a severe increase in stick forces.
c) A red light only.
d) A master caution, an amber light and the loss of pressure indication on the hydraulic system pressure gauge.

32. A rotor blade flying out of track produces:

a) A lateral vibration three and five times per revolution in a four bladed rotor system.
b) A vertical vibration four times per revolution in a four bladed rotor system.
c) A vertical vibration once per revolution.
d) A lateral vibration once per revolution.

33. A single action actuator:

a) Is a one shot actuator used for emergency systems only.
b) Travels one direction under one application of hydraulic power and in the opposite direction under a second application of hydraulic power.
c) Cannot be used for variable position operations as it is designed to lock in the extremities of travel.
d) Is powered in one direction only by hydraulic power, the return movement being under spring force.

34. A red or an amber light on an undercarriage position indicator signifies:

a) The landing has been selected down using the emergency extension system.
b) All wheels are up and locked.
c) At least one wheel is in the travelling or unlocked condition.
d) All wheels are down and locked.

35. Overcentre mechanisms in landing gear systems are used to:

a) Ensure that the nose-wheel does not exceed the maximum steering arc.
b) Lock the landing gear in the up and/or down positions.
c) Lock the landing gear in the up position only.
d) Ensure the nose-wheel is positioned fore and aft prior to retraction.

36. Fuel flow information is:

a) Measured in the line between the booster pump and the engine.
b) Measured in the line between the fuel control unit and the engine burners.
c) Measured at the outlet of the high pressure fuel pump.
d) Not used on helicopters.

37. Filtration in a hydraulic system is usually ensured by:

a) A filter in the pressure line only.
b) Filters in both the pressure and return lines.
c) The use of sealed containers only during replenishment.
d) A filter on the return line only.

38. The pilot may be prevented from retracting the landing gear whilst the aircraft is on the ground by:

a) A guard on the selector switch which cannot be moved until the aircraft is airborne.
b) A pneumatic interlock which disables the hydraulic up selector.
c) The electrical control system being routed through the weight on wheels switch.
d) Any attempt to select the landing gear up will result in a flashing warning light and a loud horn.

39. Fuel pressure is measured:

a) In the line between the booster pump and the engine or at the outlet of the high pressure filter.
b) In the line between the high pressure filter and the high pressure pump.
c) Always at the outlet of the high pressure pump only.
d) At the outlet from the fuel control unit.

40. Fuel contents is measured by:

a) The level of fuel in the tank.
b) Calculation of the centre of gravity of the helicopter.
c) The volume of fuel in the tank.
d) The weight of fuel in the tank.

41. To prevent excessive wear on landing gear skids when landing on hard surfaces:

a) Steel shoes can be fitted to the aluminium skids.
b) Sacrificial copper shoes are fitted to the titanium skids.
c) The underside of the steel skids are case hardened.
d) Aluminium shoes are fitted to steel or titanium skids.

42. Multi-segment tail rotor drive shafts are joined together by flexible couplings. These couplings allow for:

a) Bending and flexing of the tail cone during flight, and slight changes in length of shafts due to thermal expansion and contraction.
b) The rapid change of shafts and hangers without the need for alignment checks.
c) Imperfection in build standard.
d) The absorption of the tail rotor torque during start up, shut down and rapid power changes.

43. High frequency vibration usually emanates from:

a) Transmission shafting.
b) The main rotor blades.
c) The main rotor gearbox.
d) The engine or tail rotor.

44. Fuel management systems in helicopters:

a) Are usually automatic with the option of cross-feed in the event of engine failure.
b) Are totally automatic for all contingencies without the need of intervention from the pilot.
c) Allow the pilot during public transport operations, to control the centre of gravity of the aircraft.
d) Usually allow the selection of fuel feed from any tank in the group to the appropriate engine.

45. Should a hydraulic pump seize during operation:

a) The freewheel unit will disengage the pump from the gearbox.
b) A red light will illuminate in the cockpit to warn the pilot of the failure.
c) The inner barrel of the pump will rotate thus offloading and protecting the gearbox.
d) The quill drive will shear to offload and protect the gearbox.

46. Landing gear skids are normally manufactured from:

a) Stainless steel.
b) Aluminium alloy.
c) Titanium.
d) Steel.

47. A type of freewheel unit incorporating tumblers and springs is known as a:

a) Differential Freewheel.
b) Sprag freewheel.
c) Roller and Cam Freewheel.
d) Episoidal Cam Freewheel.

48. Filters in hydraulic systems often incorporate pop out indicators to:

a) Indicate that the filter is clogged and unfiltered oil is passing around the system.
b) Indicate that the filter is due maintenance.
c) Warn of a hydraulic system overheat.
d) Warn of an impending by-pass situation.

49. Intermediate or angle gearboxes are used to:

a) Change the speed only of the tail rotor drive.
b) Allow the incorporation of autopilot inputs into the tail rotor.
c) Change the direction only of the tail rotor drive.
d) Change the direction and speed of the tail rotor drive.

50. The input and output speeds of an intermediate gearbox:

a) Differ to establish the speed for the tail rotor.
b) Differ to counter the effects of vibration.
c) Are variable to provide varying thrust from the tail rotor to counteract torque loads from the main rotor system.
d) Are the same.

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