MI Helicopter Airframe & Engine Questions (09.07.2019) PDF

MI HELICOPTER AIRFRAME AND ENGINE QUESTION BANK ATA – 025.00.00 FURNISHING EQUIPMENT 1. The pilot and co-pilot seats can be adjusted: (A, B1) a) In vertical direction b) Tilt angle c) In vertical direction and tilt angle Ref: Mi-172 MMA 025.10.00 page 1, para. 2.1 2. The emergency axe should be used: (A, B1) a) In flight accidents and damages when it is necessary to chop the cutout in the fuselage skin for emergency escape of people b) In the case of fire, when it is necessary to chop off some pipelines or electrical cable bundles c) In the case of forced landing when it is necessary to clean out the site off trees and bushes for the subsequent takeoff d) All above are correct Ref: Mi-172 MMA 025.10.00 page 5/6, para. 2.14 ATA – 026.00.00 FIRE PROTECTION EQUIPMENT 3. The fire extinguishing facilities consist of: (A, B1) a) The stationary fire extinguishing system b) The portable fire extinguishers c) The stationary fire extinguishing system and the portable fire extinguishers Ref: Mi-172 MMA 026.20.00 page 1, para. 1 4. The stationary system is used for extinguishing fire in: (A, B1) a) The compartment of main engines and auxiliary power unit b) The compartment of main engines, auxiliary power unit and main gear box c) The compartment of main engines and main gear box Page 1 d) The compartment of main engines, auxiliary power unit, main gear box and fuel service tank Ref: Mi-172 MMA 026.20.00 page 1, para. 1 5. The portable manually controlled fire extinguishers may be used for: (A, B1) a) Crew cabin and cargo cabin b) Cargo cabin only c) Other helicopter zones not protective by the stationary fire extinguishing system d) Crew cabin, cargo cabin and other helicopter zones not protective by the stationary fire extinguishing system Ref: Mi-172 MMA 026.20.00 page 1, para. 1 6. The stationary fire extinguishing system can be activated by: (A, B1) a) Automatic and manual control b) Automatic control c) Manual control Ref: Mi-172 MMA 026.20.00 page 1, para. 1 7. The main discharge bottle is provided with: (A, B1) a) Automatic discharge control b) Manual discharge control c) Automatic discharge control and manual discharge control Ref: Mi-172 MMA 026.20.00 page 5, para. 3 8. The alternate discharge bottle is actuated by: (A, B1) a) Automatic discharge control b) Manual discharge control c) Automatic discharge control and manual discharge control Ref: Mi-172 MMA 026.20.00 page 5, para. 3 Page 2 9. The clearances between fire extinguishing system pipelines and structural elements of helicopter should be: (A, B1) a) Less than 5mm b) Not less than 5mm c) More than 3mm Ref: Mi-172 MMA 026.20.00 page 101/102, para. 1 10. If scratches on fire extinguishing pipes more than 0.3mm in depth: (A, B1) a) Repair the pipeline b) Replace the pipeline c) Continue use the pipeline Ref: Mi-172 MMA 026.20.00 page 101/102, para. 11 ATA – 028.00.00 FUEL SYSTEM 11. The pump is installed in service tank is: (A, B1) a) 02 fuel pumps 463B. b) 01 fuel pump 463B. c) 01 fuel pump EHCN-91S Ref: Mi-172 MMA 028.10.00 page 1, para. 2.1 12. Type of the fuel service tank: (A, B1) a) Flexible b) Rigid. c) All of above are incorrect Ref: Mi-172 MMA 028.10.00 page 1, para. 2.1 13. The pump is installed in external fuel tanks: (A, B1) a) 01 fuel pump EHCN-91S in each tank. b) 02 fuel pumps EHCN-91S in each tank c) 01 fuel pump 463B in each tank Page 3 Ref: Mi-172 MMA 028.10.00 page 1, para. 2.2 14. The pump EHCN-91S can be removed: (A, B1) a) Without removing of external fuel tank from the fuselage b) If remove the external fuel tank from the fuselage c) From the LH external fuel tank only Ref: Mi-172 MMA 028.10.00 page 1, para. 2.2 15. Before install the fuel service tank packaged into the box on the helicopter: (A, B1) a) Hold the tank during 4 – 5 hours in a room with the temperature of 15 – 200C in the unpackaged condition b) In the cases of transportation of the tank at low outside air temperature before unpacking the tank hold the box with the packaged tank a minimum of 15 hours in the room with the temperature not lower than 100C c) All above are correct Ref: Mi-172 MMA 028.10.00f, Para. 2 16. The fuel draining from the tanks is performed through: (A, B1) a) The drain valve of the service fuel tank b) The drain valve of the additional fuel tank c) The drain valve of the external fuel tank Ref: Mi-172 MMA 028.20.00 page 1, Para. 1 17. The fuel pump 463B supplies fuel from the service fuel tank to: (A, B1) a) 02 engines and APU b) 02 engines c) APU Ref: Mi-172 MMA 028.20.00 page 1, Para. 2.1 18. The fuel pump 463B is installed: (A, B1) a) Inside the service fuel tank Page 4 b) Outside and at the lower part of the service fuel tank c) Inside the external fuel tanks Ref: Mi-172 MMA 028.20.00 page 1, Para. 2.1 19. In case of failure of the fuel pump 463B: (A, B1) a) The standby fuel pump will supply fuel to engines b) The operation of the engines will be degraded c) The operation of the engines remain undisturbed, the fuel from the service fuel tank runs to the engines by gravity Ref: Mi-172 MMA 028.20.00 page 1, Para. 2.1 20. Function of the fuel pumps EHCN-91S: (A, B1) a) Supply fuel for the main engines and APU b) Transfer fuel from external fuel tanks to service fuel tank c) Transfer fuel from additional fuel tank to external fuel tanks Ref: Mi-172 MMA 028.20.00 page 1, Para. 2.2 21. Type of fuel pump 463B: (A, B1) a) Gear pump b) Centrifugal pump c) Vane pump Ref: Mi-172 MMA 028.20.00 page 1, Para. 2.1 22. Type of fuel pump EHCN-91S: (A, B1) a) Centrifugal pump b) Vane pump c) Gear pump Ref: Mi-172 MMA 028.20.00 page 1, Para. 2.2 23. Function of the float valve: (A, B1) Page 5 a) To prevent the additional fuel tank overfilling during fuel transferred from the external fuel tanks. b) To prevent the external fuel tanks overfilling during fuel transferred from the additional fuel tank. c) To prevent the service fuel tank overfilling during fuel transferred from the external fuel tanks. Ref: Mi-172 MMA 028.20.00 page 2, Para. 2.4 24. Function of shutoff valves in the fuel system: (A, B1) a) Prevent the service fuel tank overfilling b) Prevent the additional fuel tank overfilling c) Shutting and opening the fuel pipelines Ref: Mi-172 MMA 028.20.00 page 2, Para. 2.5 25. Type of shutoff valves in fuel system: (A, B1) a) Electrically actuated remote controlled valves b) Manually controlled valves c) All above are correct Ref: Mi-172 MMA 028.20.00 page 2, Para. 2.5 26. When the float valve is failed in its closed position: (A, B1) a) The fuel from external fuel tanks bypass to service fuel tank through one shutoff valve b) The fuel from additional fuel tank bypass to external fuel tanks through one shutoff valve c) The service fuel tank is no longer fuel supplied Ref: Mi-172 MMA 028.20.00 page 2, Para. 2.5 27. Function of the manually controlled fuel shutoff valve: (A, B1) a) Cutoff fuel flow through the forward cross-feed pipeline of the additional fuel tank b) Cutoff fuel flow through the forward cross-feed pipeline of the service fuel tank c) Cutoff fuel flow through the forward cross-feed pipeline of the external fuel tanks Ref: Mi-172 MMA 028.20.00 page 2, Para. 2.6 Page 6 28. The manually controlled fuel shutoff valve should be closed in case of: (A, B1) a) Demounting of the of the right hand external fuel tank b) Draining of fuel from the additional fuel tank c) Demounting of the of the right hand external fuel tank and draining of fuel from the additional fuel tank Ref: Mi-172 MMA 028.20.00 page 2, Para. 2.6 29. In normal operation, the manually controlled fuel shutoff valve should be: (A, B1) a) In the closed position b) In the opened position c) In the neutral position Ref: Mi-172 MMA 028.20.00 page 2, Para. 2.6 30. Function of the electromagnetic valve 610200A: (A, B1) a) Control of the fuel delivery into the main engines b) Control of the fuel delivery into the APU c) Control of the fuel delivery into the APU and the main engine Ref: Mi-172 MMA 028.20.00 page 2, Para. 2.7 31. The electromagnetic valve 610200A opens automatically: (A, B1) a) When depressing the APU starting push-button b) When start the main engines c) When shutdown the main engines Ref: Mi-172 MMA 028.20.00 page 2, Para. 2.7 32. Function of bypass valve 637600: (A, B1) a) To transfer the fuel between external fuel tanks. b) To transfer the fuel from the additional fuel tank to the external fuel tanks c) To transfer the fuel from the external fuel tanks to the service fuel tank Ref: Mi-172 MMA 028.20.00 page 2, Para. 2.8 Page 7 33. Type of bypass valve 637600: (A, B1) a) Electrically controlled valve b) Manually controlled valve c) Electrically and manually controlled valve Ref: Mi-172 MMA 028.20.00 page 2, Para. 2.8 34. To drain fuel from additional fuel tank: (A, B1) a) Use the electromagnetic valve 610200A b) Use the bypass valve 637600 c) Use shutoff valve 768600MA Ref: Mi-172 MMA 028.20.00 page 2, Para. 2.8 35. Function of fuel filter 11TF30ST: (A, B1) a) Cleaning fuel from foreign particles in the pipeline feeding of main engines b) Cleaning fuel from foreign particles in the pipeline feeding of APU c) Cleaning fuel from foreign particles in the pipeline feeding of APU and main engines Ref: Mi-172 MMA 028.20.00 page 3, Para. 2.9 36. The engines preservation valves are used for: (A, B1) a) Preserving main engines b) Preserving APU c) Preserving main engines and APU Ref: Mi-172 MMA 028.20.00 page 3, Para. 2.10 37. Function of fuel check valves: (A, B1) a) Allow fuel flow only in one direction from external fuel tanks to service fuel tank b) Allow fuel flow only in one direction from service fuel tank to external fuel tanks c) Allow fuel flow only in one direction from external fuel tanks to additional fuel tank Ref: Mi-172 MMA 028.20.00 page 3, Para. 2.11 Page 8 38. The clearances between fuel system pipelines and structural elements of helicopter should be: (A, B1) a) Less than 5mm b) Not less than 5mm c) More than 3mm Ref: Mi-172 MMA 028.20.00 page 101, para. 1 39. If nicks, chafes and streaks more than 0.1mm in depth on fuel pipeline: (A, B1) a) Repair the pipeline b) Replace the pipeline c) Continue use the pipeline Ref: Mi-172 MMA 028.20.00 page 101, para. 2 40. If corrosion more than 0.1mm in depth on fuel pipeline: (A, B1) a) Dress the corroded areas with sandpaper No. 6-8 and recondition paint coating b) Replace the pipeline c) Continue use the pipeline Ref: Mi-172 MMA 028.20.00 page 102, para. 6 41. When remove the fuel pump EHCN-91S: (A, B1) a) Need to drain the fuel from the external fuel tank b) No need to drain the fuel from the external fuel tank c) Need to remove the external fuel tank from the fuselage Ref: Mi-172 MMA 028.20.00f, para. 1 42. The outside dial of fuel quantity gauge indicator: (A, B1) a) Measure total reserve of the fuel b) Measure the fuel reserve in an individual tank c) Measure total reserve of the fuel in 2 external fuel tanks Ref: Mi-172 MMA 028.40.00 page 1, para. 2.1 Page 9 43. The inside dial of fuel quantity gauge indicator: (A, B1) a) Measure total reserve of the fuel b) Measure the fuel reserve in an individual tank c) Measure total reserve of the fuel in 2 external fuel tanks Ref: Mi-172 MMA 028.40.00 page 1, para. 2.1 44. The fuel quantity gauge СКЭС-2027В measures: (A, B1) a) Fuel quantity of service tank b) Fuel quantity of 02 external fuel tanks c) the fuel reserve in an individual tank or the total reserve of the fuel in all the helicopter tanks (excluding the quantity of fuel in the RH additional tank) Ref: Mi-172 MMA 028.40.00 page 2, para. 3.1 45. The pump 463Б is used for feeding: (A, B1) a) The LH engine b) The RH engine c) The APU (AИ-9B) d) All above are correct. Ref: Mi-172 MMA 028.20.00 page 1, Para. 2.1 46. How many 768600MA valves are installed in the tank crossfeed pipelines interconnecting external tanks? (A, B1) a) 1 valve b) 2 valves c) 3 valves d) 4 valves Ref: Mi-172 MMA 028.20.00 page 2, Para. 2.6 ATA – 036.00.00 PNEUMATIC POWER SYSTEM 47. Function of the helicopter pneumatic power system: (A, B1) Page 10 a) Brake the wheels of the main landing gear b) Inflate the wheel tires from the airborne air bottles under off-field conditions with the aid of a special charging rig c) All of above are correct Ref: Mi-172 MMA 036.00.00 page 1/2 48. Pressure of compressed air in helicopter pneumatic power system should be within: (A, B1) a) (30 to 40) ± 4 kgf/cm2 b) (35 to 45) ± 4 kgf/cm2 c) (40 to 50) ± 4 kgf/cm2 Ref: Mi-172 MMA 036.00.00 page 1/2 49. When the helicopter is in flight, the pneumatic power system is replenished by: (A, B1) a) The air compressor mounted on the main gear box b) The air compressors mounted on the engines c) Auxiliary power unit Ref: Mi-172 MMA 036.00.00 page 1/2 50. Function of air compressor AK-50T1: (A, B1) a) Recharge the helicopter pneumatic power system with compressed air on ground b) Recharge the helicopter pneumatic power system with compressed air in flight c) Recharge the helicopter pneumatic power system and floatation gear cylinders in flight Ref: Mi-172 MMA 036.10.00 page 1, para 1.1 51. Type of air compressor AK-50T1: (A, B1) a) One-stage, single-cylinder, piston-type b) Two-stage, double-cylinder, piston-type c) Two-stage, single-cylinder, piston-type Ref: Mi-172 MMA 036.10.00 page 1, para 1.1 Page 11 52. The AK-50T1 air compressor is driven from: (A, B1) a) Engine b) Main gearbox c) Auxiliary power unit Ref: Mi-172 MMA 036.10.00 page 1, para 1.1 53. Function of gravity filter of pneumatic power system: (A, B1) a) Clean air from the oil and moisture fed from the air compressor to the pneumatic power system b) Clean air from foreign particles c) All of above are incorrect Ref: Mi-172 MMA 036.10.00 page 1, para 1.2 54. Function of check valve 636100M: (A, B1) a) Pass air in one desired direction and shut off the lines for an air return flow b) Pass air in two desired directions and shut off the lines for an air return flow c) Pass air to the environment when overpressure occurs in system Ref: Mi-172 MMA 036.10.00 page 1, para 1.3 55. Function of air filter 723900-4AT of pneumatic power system: (A, B1) a) Clean air from the oil and moisture fed from the air compressor to the pneumatic power system b) Clean air from foreign particles c) All of above are incorrect Ref: Mi-172 MMA 036.10.00 page 1, para 1.4 56. Function of air filter 723900-6AT of pneumatic power system: (A, B1) a) Clean air from the oil and moisture fed from the air compressor to the pneumatic power system b) Clean air from foreign particles c) All of above are incorrect Page 12 Ref: Mi-172 MMA 036.10.00 page 1, para 1.4 57. Function of AD-50 pressure control unit: (A, B1) a) Change over the AK-50T1 air compressor from its normal rate of operation to no-load operation and vice versa b) Take over the function of AK-50T1 air compressor when the air compressor failed c) Change over the air compressor from normal to no-load operation at air pressure below 40 kgf/cm2 Ref: Mi-172 MMA 036.10.00 page 1, para 1.5 58. Which sentence below is correct? (A, B1) a) The air compressor is changed over from the normal to no-load operation at air pressure of 50 ± 4 kgf/cm2 in the air bottles b) The air compressor is changed over from the no-load to its normal rate of operation at an air pressure below 40 kgf/cm2 c) Both a) and b) are correct d) Both a) and b) are incorrect Ref: Mi-172 MMA 036.10.00 page 1, para 1.5 ATA – 065.00.00 HELICOPTER MAIN AND TAIL ROTORS 59. Function of main rotor and blades: (A, B1) a) Create the lift and drag b) Create the lift and thrust c) Create the drag and thrust Ref: Mi-172 MMA 065.00.00 page 1/2 60. Function of the swashplate assembly: (A, B1) a) Control the helicopter in longitudinal and yaw axes b) Control the helicopter in longitudinal and lateral axes c) Control the helicopter in lateral and yaw axes Ref: Mi-172 MMA 065.00.00 page 1/2 Page 13 61. Function of tail rotor and blades: (A, B1) a) Counteract the torque reaction produced by the main rotor and control the helicopter in longitudinal axis b) Counteract the torque reaction produced by the main rotor and control the helicopter in yaw axis c) Counteract the torque reaction produced by the main rotor and control the helicopter in lateral axis Ref: Mi-172 MMA 065.00.00 page 1/2 62. Helicopter longitudinal and lateral control is accomplished by: (A, B1) a) Control stick b) Collective pitch control lever c) Foot control pedals Ref: Mi-172 MMA 065.00.00 page 1/2 63. Helicopter directional control is accomplished by: (A, B1) a) Control stick b) Collective pitch control lever c) Foot control pedals Ref: Mi-172 MMA 065.00.00 page 1/2 64. The main rotor blades are prevented from impact against the tail boom during landing and when taxiing by: (A, B1) a) A hydraulic pitch stop installed in the longitudinal control system b) A hydraulic pitch stop installed in the lateral control system c) A hydraulic pitch stop installed in the directional control system Ref: Mi-172 MMA 065.00.00 page 1/2 65. Tail rotor maximum pitch limit system is installed on: (A, B1) a) Foot pedal control b) Control stick Page 14 c) Collective pitch control lever Ref: Mi-172 MMA 065.00.00 page 1/2 66. The main rotor blades are attached to the main rotor hub through: (A, B1) a) Laminated spherical thrust bearing b) Flapping, drag and feathering hinges c) Universal joint (cardan) Ref: Mi-172 MMA 065.10.00 page 1, para. 1 67. The main rotor blades can be changed the blade setting angle thanks to: (A, B1) a) Flapping hinge b) Drag hinge c) Feathering hinge Ref: Mi-172 MMA 065.10.00 page 1, para. 1 68. The main rotor blades angular oscillations are damped by hydraulic dampers about: (A, B1) a) Flapping hinge b) Drag hinge c) Feathering hinge Ref: Mi-172 MMA 065.10.00 page 1, para. 1 69. Function of centrifugal droop stops: (A, B1) a) Reduce blade droop and create required clearances between the main rotor blades and the tail boom when the main rotor does not rotate or rotates at a low speed b) Reduce blade droop and create required clearances between the main rotor blades and the tail boom when the main rotor does not rotate or rotates at a high speed c) Increase blade droop and create required clearances between the main rotor blades and the tail boom when the main rotor does not rotate or rotates at a low speed Ref: Mi-172 MMA 065.10.00 page 1, para. 1 Page 15 70. Type of blade angular oscillation damper on main rotor hub: (A, B1) a) Spring b) Elastic c) Hydraulic d) Pneumatic Ref: Mi-172 MMA 065.10.00 page 1, para. 1 71. Rotation direction of the main rotor: (A, B1) a) Counterclockwise when viewed from below b) Counterclockwise when viewed from upper c) Clockwise when viewed from below Ref: Mi-172 MMA 065.10.00 page 1, para. 1 72. The main rotor blade shape: (A, B1) a) Rectangular, with geometric twist unchanged b) Rectangular, with geometric twist increases from the blade root to tip c) Rectangular, with geometric twist, 5° in blade sections No.1-4 and then blade twist is changed by linear law up to 0° in blade section No.22 Ref: Mi-172 MMA 065.10.00 page 13, para. 2.2.1 73. The main rotor blade trim tabs are used to: (A, B1) a) Adjust the main rotor blade tracking b) Adjust the main rotor blade weight c) Secure the blade when transport Ref: Mi-172 MMA 065.10.00 page 15, para. 2.2.2 74. Function of vibration damper: (A, B1) a) Damp main rotor hub oscillations in the plane of its rotation b) Damp main rotor blades angular oscillations about drag hinge c) Damp main rotor blades angular oscillations about flapping hinge Page 16 Ref: Mi-172 MMA 065.12.00 page 1/2 75. Which of the following descriptions about the pendulum-type vibration damper is correct? (A, B1) a) The damper pendulums start swinging and moving in isophasal with hub vibrations b) The damper pendulums start swinging and moving in counter-phase with hub vibrations c) The damper pendulums are set to their neutral position Ref: Mi-172 MMA 065.12.00 page 1/2 76. The tail rotor is driven from the main gearbox through: a) Tail gearbox b) Intermediate and tail gearboxes c) Transmission shafts, intermediate and tail gearboxes Ref: Mi-172 MMA 065.20.00 page 1/2 77. Tail rotor pitch is changed by: (A, B1) a) Operating the control stick b) Operating the collective pitch control lever c) Operating the foot control pedals Ref: Mi-172 MMA 065.20.00 page 1/2 78. Rotation direction of the tail rotor: (A, B1) a) Counterclockwise when viewed from LH side b) Clockwise when viewed from RH side c) Clockwise when viewed from LH side Ref: Mi-172 MMA 065.20.00 page 1/2 79. The tail rotor blades flapping motion about the plane of rotation through: (A, B1) a) Flapping hinge b) Feathering hinge c) Cardan joint Page 17 Ref: Mi-172 MMA 065.20.00 page 1/2 80. Function of tail rotor hub feathering hinges: (A, B1) a) Ensure a required blade angle as rotor pitch is changed b) Ensure blade flapping motion about the plane of rotation c) All above are incorrect Ref: Mi-172 MMA 065.20.00 page 1/2 81. The tail rotor hub tilt angle is limited in range: (A, B1) a) -10o to 10o b) -11o to 11o c) -12o to 12o Ref: Mi-172 MMA 065.20.00 page 8 82. The tail rotor blade shape: (A, B1) a) Rectangular, flat, free from twist b) Rectangular, with geometric twist increases from the blade root to tip c) Rectangular, with geometric twist decreases from the blade root to tip Ref: Mi-172 MMA 065.20.00 page 9 83. The helicopter is controlled in flight about its three axes by: (A, B1) a) Changing the value of main rotor thrust and by changing the value of tail rotor thrust b) Changing the direction of main rotor thrust and by changing the value of tail rotor thrust c) Changing the value and direction of main rotor thrust and by changing the value of tail rotor thrust Ref: Mi-172 MMA 065.40.00 page 1/2 84. Function of separate throttle control for each engine: (A, B1) a) Allows the pilot to test each engine without changing the main rotor collective pitch b) Allows the pilot to test each engine combines with changing the main rotor collective pitch c) All above are incorrect Page 18 Ref: Mi-172 MMA 065.40.00 page 1/2 85. The stabilizer angle: (A, B1) a) Can be changed in flight b) Can be changed on ground c) Cannot be changed in flight and on ground Ref: Mi-172 MMA 065.40.00 page 1/2 86. The control linkage is designed to transmit movements of the helicopter controls operated by the pilots to: (A, B1) a) The combination control hydraulic actuators mounted on the main gearbox b) The control levers of the fuel flow control units located on the engines c) The main rotor brake d) All above are correct Ref: Mi-172 MMA 065.40.00 page 14, para 2.1 87. What type of hydraulic control actuator used on MI-172 helicopter? (A, B1) a) KAY-30Б b) РА-60Б c) KAY-115(A) Ref: Mi-172 MMA 065.40.00 page 19/20 88. What type of hydraulic control actuator used on MI-17-1V helicopter? (A, B1) a) KAU-30B and RА-60B b) KAU-30B or RА-60B c) KAU-115(A) Ref: AMS MI-17-1V, components inspection 89. In normal operation, the KAY-115(A) hydraulic actuators are operated from: (A, B1) d) Main hydraulic system e) Auxiliary hydraulic system Page 19 f) Both main and auxiliary hydraulic systems Ref: Mi-172 MMA 065.40.00 page 17, para 2.1.2 90. In the event of main hydraulic system failure: (A, B1) a) KAY-115(A) is changed over automatically for operation from the auxiliary hydraulic system b) KAY-115(A) is converted automatically to operate as the push-pull control rods in the control linkage of the helicopter c) All above are correct Ref: Mi-172 MMA 065.40.00 page 17, para 2.1.2 91. In the event of both hydraulic systems failure: (A, B1) a) KAY-115(A) can't be controlled b) KAY-115(A) is converted automatically to operate as the push-pull control rods in the control linkage of the helicopter c) All above are correct Ref: Mi-172 MMA 065.40.00 page 17, para 2.1.2 92. The hydraulic stop serves to limit tilt of the swashplate backwards in the longitudinal control up to: (A, B1) a) 2° ± 12' b) 3° ± 12' c) 4° ± 12' Ref: Mi-172 MMA 065.40.00 page 23, para 2.2.2 93. Function of СПУУ-52: (A, B1) a) Limit automatically the main rotor blade maximum angle depending upon the ambient temperature and pressure which characterize air density b) Limit automatically the tail rotor blade maximum angle depending upon the ambient temperature and pressure which characterize air density c) All of above are correct Page 20 Ref: Mi-172 MMA 065.40.00 page 31, para 2.2.3.2 94. The tail rotor blade angle is automatically reduced with: (A, B1) a) Decreasing air density b) Increasing air density c) Increasing air temperature Ref: Mi-172 MMA 065.40.00 page 31, para 2.2.3.2 95. Function of ЭМТ-2М solenoid brake: (A, B1) a) Increase pressure forces from the helicopter controls under unsteady-state flying conditions b) Increase pressure forces from the helicopter controls under steady-state flying conditions c) Remove pressure forces from the helicopter controls under steady-state flying conditions Ref: Mi-172 MMA 065.40.00 page 35, para 2.4.2 96. Function of main rotor and engines collective pitch control: (A, B1) a) Change main rotor thrust followed by a simultaneous change in engine power in order to maintain main rotor speed without substantial changes b) Change tail rotor thrust followed by a simultaneous change in engine power in order to maintain tail rotor speed without substantial changes c) All of above are correct Ref: Mi-172 MMA 065.40.00 page 35, para 2.5 97. Function of main rotor and engine collective pitch control system: (A, B1) a) Transmit the movements performed by the pilots from the collective pitch control levers to the combination control hydraulic actuator b) Transmit the movements performed by the pilots from the collective pitch control levers to the fuel supply levers of the fuel flow control unit installed in the helicopter engines c) All above are correct Ref: Mi-172 MMA 065.40.00 page 43, para 2.5.3 98. The engines can be started only when: (A, B1) Page 21 a) Main rotor brake is in fully released position b) Main rotor brake is in brake position c) Main rotor brake is in upper position Ref: Mi-172 MMA 065.40.00 page 53, para 2.9 99. The main rotor brake control handle is installed in: (A, B1) a) Flight compartment floor, pilot’s seat right hand side b) Flight compartment ceiling right hand side c) Flight compartment ceiling left hand side Ref: Mi-172 MMA 065.40.00 page 53, para 2.9 100. When washing of filtering elements in hydraulic actuators, blow the filter from the inside with compressed air at a pressure not exceeding: (A, B1) a) 1.5 to 2 kgf/cm2 b) 2.5 to 3 kgf/cm2 c) 3.5 to 4 kgf/cm2 Ref: Mi-172 MMA 065.40.00g1 para 5 101. Prior to insall the hydraulic actuators: (A, B1) a) Check the hydraulic actuator for free from corrosion traces and physical damage, presence of locking devices and seals b) Check for shipping plugs are intact on the actuator connections and the hydraulic actuator is filled with operating fluid, check the hydraulic actuator by its Certificate that it is fit for service c) Check for lockpins are installed in the helicopter controls, the control sticks, control levers and foot pedals should be set to their intermediate (neutral) positions d) All above are correct Ref: Mi-172 MMA 065.40.00l1 para 2 102. Lateral play in the hydraulic actuator ball bearing supports should be within: (A, B1) a) 0.1 to 0.5 mm b) 0.3 to 0.7 mm Page 22 c) 0.5 to 0.9 mm Ref: Mi-172 MMA 065.40.00l1 para 3 103. Total play between the hydraulic actuator end fitting and the bellcrank should be within: (A, B1) a) 0.1 to 0.5 mm b) 0.5 to 1 mm c) 1 to 1.5 mm Ref: Mi-172 MMA 065.40.00l1 para 4 104. When install the hydraulic actuator, maintain the axial plays in the hinged joints: (A, B1) a) At least 0.1 mm b) At least 0.2 mm c) At least 0.3 mm Ref: Mi-172 MMA 065.40.00l1 para 4 105. Maximum travel of the collective pitch sleeve: (A, B1) a) 33 mm b) 43 mm c) 53 mm Ref: Mi-172 MMA 065.50.00 para 1, page 1 106. The swashplate tilt can be adjust in the longitudinal and lateral control plane with and accuracy up to: (A, B1) a) 6 minutes b) 10 minutes c) 12 minutes Ref: Mi-172 MMA 065.50.00 para 2, page 3/4 107. When install the swashplate, the hoist crane characteristics required: (A, B1) Page 23 a) Load capacity of at least 200 kg and a hoisting height of 5m minimum b) Load capacity of at least 200 kg and a hoisting height of 2m minimum c) Load capacity of at least 100 kg and a hoisting height of 5m minimum Ref: Mi-172 MMA 065.50.00e para 4 108. What is the procedure required after install the swashplate? (A, B1) a) Check engine to main gearbox alignment b) Adjust the swashplate assembly in tilt c) All of above are incorrect Ref: Mi-172 MMA 065.50.00e para 16 109. When inspect the clamp getaway stop plates, if detect sheared attachment screws of one of the plates and appearance of orange-coloured surface of the half ring: (A, B1) a) Replace the swashplate assembly b) Replace the main rotor hub c) Replace the swashplate assembly and main rotor hub Ref: Mi-172 MMA 065.50.00f para 2 110. Clearance between the plate lower edge and the upper end face of the swashplate link clamp: (A, B1) a) Clearance should be within 0.2 to 0.6 mm b) Clearance should be within 0.5 to 1 mm c) Clearance should be within 0.2 to 1.6 mm Ref: Mi-172 MMA 065.50.00f para 3 111. To measure total plays in swashplate assembly, need to: (A, B1) a) Apply brake to the main rotor b) Set all blades to the front stops by turning them in the drag hinge c) Remove all main rotor blades, lock the control stick in its neutral position with lock pin d) All of above are correct Ref: Mi-172 MMA 065.50.00g para 1, 2, 3, 4 Page 24 112. Total plays to be set for the swashplate assembly in the longitudinal and lateral control: (A, B1) a) 0.5 mm b) 1.5 mm c) 2.5 mm Ref: Mi-172 MMA 065.50.00g para 18 113. Total plays to be set for the swashplate assembly in the swashplate link joints: (A, B1) a) 0.0 mm b) 0.5 mm c) 1.5 mm Ref: Mi-172 MMA 065.50.00g para 18 114. Total plays to be set for the swashplate assembly in a vertical plane: (A, B1) a) 0.0 mm b) 0.7 mm c) 1.2 mm Ref: Mi-172 MMA 065.50.00g para 18 115. Total plays to be set for the swashplate assembly in the plane of rotation: (A, B1) a) 0.0 mm b) 0.7 mm c) 1.2 mm Ref: Mi-172 MMA 065.50.00g para 18 116. How many blades of the main rotor are there on MI helicopter? (A, B1) a) 3 b) 4 c) 5 d) 6 Page 25 Ref: Mi-172 MMA 065.00.00, page 1/2 117. What is the main rotor used for? (A, B1) a) to create the lift required for helicopter flight b) to create the thrust required for helicopter flight c) A and B are correct Ref: Mi-172 MMA 065.00.00 page 1/2 118. How many blades of the tail rotor are there on MI helicopter? (A, B1) a) 2 b) 3 c) 4 d) 5 Ref: Mi-172 MMA 065.00.00, page 1/2 119. What is the tail rotor used for? (A, B1) a) to counteract the torque reaction produced by the main rotor b) to ensure directional stability c) to ensure directional control d) All of above are correct Ref: Mi-172 MMA 065.00.00, page 1/2 120. To protect the main rotor blades against icing, the main rotor blades are equipped with? (A, B1) a) rotor blade spar damage pneumatic warning system b) rotor blade spar damage hydraulic warning system c) rotor blade spar damage liquid warning system Ref: Mi-172 MMA 065.00.00, page 1/2 121. Directional control is carried out by the foot control pedals by: (A, B1) a) Changing the direction of tail rotor thrust; Page 26 b) Changing the RPM of tail rotor; c) Changing the tail rotor pitch. Ref: Mi-172 MMA 065.00.00, page 1/2 122. How is the main rotor thrust changed? (A, B1) a) by changing the main rotor collective pitch b) by changing engine operating conditions c) A and B are correct Ref: Mi-172 MMA 065.00.00, page 1/2 123. To test each engine without changing the main rotor collective pitch, what does the pilot do? (A, B1) a) use the engine separate throttle control; b) select a desired mode of operation when flying with one operating engine; c) A and B are correct Ref: Mi-172 MMA 065.00.00, page 1/2 124. The main rotor hub is designed to: (A, B1) a) transmit rotation to the blades from the main gear box b) take up the aerodynamic forces arising in the main rotor to the fuselage c) transmit the aerodynamic forces arising in the main rotor to the fuselage d) All of above are correct Ref: Mi-172 MMA 065.10.00, page 1, para. 1 125. The flapping hinges allow the blades: (A, B1) a) to perform flapping motion under the action of the aerodynamic forces variable in azimuth b) to make angular oscillations in the plane of rotation c) to change blade setting angles Ref: Mi-172 MMA 065.10.00, page 1, para. 1 126. The drag hinges allow the blades: (A, B1) Page 27 a) to perform flapping motion under the action of the aerodynamic forces variable in azimuth b) to make angular oscillations in the plane of rotation c) to change blade setting angles Ref: Mi-172 MMA 065.10.00, page 1, para. 1 127. The feathering hinges are designed: (A, B1) a) to perform flapping motion under the action of the aerodynamic forces variable in azimuth b) to make angular oscillations in the plane of rotation c) to change blade setting angles Ref: Mi-172 MMA 065.10.00, page 1, para. 1 128. Blade angular oscillations (hunting) about the drag hinges are damped by: (A, B1) a) Pneumatic dampers b) Hydraulic dampers; c) Liquid dampers. Ref: Mi-172 MMA 065.10.00, page 1, para. 1 129. Where is the tail rotor mounted? (A, B1) a) on the flange of a intermediate gearbox output shaft and located on the left side of the tail boom pylon b) on the flange of a intermediate gearbox output shaft and located on the right side of the tail boom pylon c) on the flange of a tail gearbox output shaft and located on the left side of the tail boom pylon Ref: Mi-172 MMA 065.20.00, page 1/2, para. 1 130. The major components of the foot pedal control are as follows: (A, B1) a) two pairs of pedals for the pilot and co-pilot b) control linkage, KAY-115 hydraulic actuator c) CПYY-52 tail rotor maximum pitch limit system d) All of above are correct Page 28 Ref: Mi-172 MMA 065.40.00, page 25, para. 2.2.3 131. Engine speed readjustment control is used in the helicopter: (A, B1) a) to allow the pilot to act upon operation of the main rotor speed automatic control in flight b) to allow the pilot to act upon operation of the LH engine rotor speed automatic control in flight c) to allow the pilot to act upon operation of the RH engine rotor speed automatic control in flight Ref: Mi-172 MMA 065.40.00, page 51, para. 2.7 132. The engine speed readjustment control of the main rotor speed includes: (A, B1) a) The HIGH - LOW SPEED selector switch mounted on the pilot's collective pitch control lever b) The HIGH - LOW SPEED selector switch mounted on the co-pilot's collective pitch control lever c) The MП-100M electric actuator d) All of above are correct Ref: Mi-172 MMA 065.40.00, page 51, para. 2.7 133. The combination control hydraulic actuators of Mi-172 helicopter hydraulic systems include: (A, B1) a) 04 KAY-115 b) 03 KAY-115 & 01 PA- 60 c) 03 KAY-30 & 01 PA- 60 Ref: Mi-172 MMA 065.40.00 page 5/6, fig 1. 134. The combination control hydraulic actuators in Mi-17-1B helicopter hydraulic systems include: (A, B1) a) 04 KAY-115 b) 03 KAY-115 & 01 PA- 60 c) 03 KAY-30 & 01 PA- 60 Ref: Mi-17-1B MMA 065.40.00 page 4, 5. Page 29 135. Operating modes of the combination control hydraulic actuators: (A, B1) a) Only manual control b) Only combination control c) Combination control – manual control Ref: Mi-172 MMA 065.40.00 page 17. 136. The main rotor thrust is changed by changing the main rotor collective pitch and engines power condition by using: (A, B1) a) Foot pedal control b) Control stick c) Collective pitch control lever Ref: Mi-172 MMA 065.00.00 page 1/2 137. Purpose of engine separate throttle control: (A, B1) a) To test each engine without changing the main rotor collective pitch b) Select a desired mode of operation when flying with one operating engine c) To control main rotor thrust when the collective pitch control failed d) Both a) and b) are correct Ref: Mi-172 MMA 065.00.00 page 1/2 138. Purpose of CПYY-52 in the helicopter foot pedal control? (A, B1) a) To control tail rotor pitch angle automatically. b) To control tail rotor speed for changing direction c) To limit automatically the maximum setting angle of tail rotor blades d) To limit automatically the tail rotor speed Ref: Mi-172 MMA 065.00.00 page 1/2 139. CПYY-52 limit automatically the maximum setting angle of tail rotor blades depending on: (A, B1) a) The temperature of ambient air b) The pressure of ambient air. c) The ambient temperature and pressure which characterize air density Ref: Mi-172 MMA 065.00.00 page 1/2 140. Purpose of the flapping hinges of main rotor hub: (A, B1) Page 30 a) Allow the blades to perform flapping motion (angular oscillation or hunting in the vertical plane) b) Allow the blades to make angular oscillations in the plane of rotation c) Change blade setting angles Ref: Mi-172 MMA 065.10.00 page 1, para. 1 141. Purpose of the drag hinges of main rotor hub: (A, B1) a) Allow the blades to perform flapping motion (angular oscillation or hunting in the vertical plane) b) Allow the blades to make angular oscillations in the plane of rotation c) Change blade setting angles Ref: Mi-172 MMA 065.10.00 page 1, para. 1 142. The drag hinges of main rotor hub are lubricated by: (A, B1) a) MC-20 oil. b) Б3B oil c) TCГИП Ref: Mi-172 MMA 012.20.00 page 12, para. 4.1 143. Carry out main rotor blades tracking at wind velocity not excess: (A, B1) a) 5 m/s b) 8 m/s c) 10 m/s Ref: Mi-172 MMA 065.10.00o, para. 5 144. Carry out tracking of blades is performed at main rotor speed: (A, B1) a) 55% to 70% b) 93% to 97% c) All of above are correct Ref: Mi-172 MMA 065.10.00o, para. 17 145. Adjustment of blades tracking at main rotor speeds of 55% to 70% is carried-out by: (A, B1) a) Changing the length of blade turn control rods b) Change angles of trim tabs c) Add weight at main rotor blade tips Ref: Mi-172 MMA 065.10.00o, para. 18 Page 31 146. Adjustment of blades tracking at main rotor speeds of 93 % to 97 % is carried-out by: (A, B1) a) Changing the length of blade turn control rods b) Change angles of trim tabs c) Add weight at main rotor blade tips Ref: Mi-172 MMA 065.10.00o, para. 18 147. The purpose of the hydraulic stop in longitudinal control: (A, B1) a) Limit tilt of the swashplate backwards in the longitudinal control up to 2°±12' as the helicopter is taxied on the ground to prevent the main rotor blades from touching the tail bstrrfi. b) Limits in longitudinal control the swash plate tilt backwards up at helicopter flight in ground effect so as to avoid touchup of main rotor blades against the tail boom. c) All of above are correct Ref: Mi-172 MMA 065.40.00 page 23, para 2.2.2 ATA – 073.00.00 ENGINE SUPPLY SYSTEM 148. Function of engine supply system: (A, B1) a) Adjust the compressor turbine inlet gases temperature b) Restrict the rotational speed (rpm) of the engine turbo-compressor rotor to the specified limit c) All above are correct Ref: Mi-172 MMA 073.00.00 page 1/2 149. The engine supply system includes: (A, B1) a) Temperature regulator PT-12-6 b) Electronic engine governor ЭВД-ЗВМ c) All above are correct Ref: Mi-172 MMA 073.00.00 page 1/2 150. The annunciators with yellow light filter FUEL FLTR CLOG L ENG and FUEL FLTR CLOG R ENG are located on: (A, B1) a) Left instrument board Page 32 b) Right instrument board c) All above are incorrect Ref: Mi-172 MMA 073.00.00 page 1/2 151. Function of the PT-12-6 temperature regulator: (A, B1) a) Automatically restrict the engine compressor turbine inlet gases temperature to the specified limit b) Adjust the compressor turbine inlet gases temperature c) All above are correct Ref: Mi-172 MMA 073.10.00 page 1, para. 1.1 152. To restrict the engine compressor turbine inlet gases temperature to the specified limit: (A, B1) a) The PT-12-6 temperature regulator increases the flow of fuel supplied to the nozzles b) The PT-12-6 temperature regulator reduces the flow of fuel supplied to the nozzles c) All above are incorrect Ref: Mi-172 MMA 073.10.00 page 1, para. 1.1 153. How many PT-12-6 temperature regulators are there in engine supply system? (A, B1) a) 1 b) 2 c) 3 Ref: Mi-172 MMA 073.10.00 page 1, para. 1.1 154. The PT-12-6 temperature regulators are installed: (A, B1) a) Inside the tail boom b) On the engines c) On the ceiling of the cargo compartment at frames No. 3 and 4 Ref: Mi-172 MMA 073.10.00 page 1, para. 1.1 Page 33 155. Function of the ЗРД-ЗВМ electronic engine governor: (A, B1) a) Restrict the turbo-compressor rotational speed to the specified limit b) Transition of the turbo-compressor rotational speed limiting circuit to the operation at the contingency power c) Sending of the command to the respective light annunciator and to stop the engine d) All above are correct Ref: Mi-172 MMA 073.10.00 page 1, para. 1.2 156. The ЭРД-ЗВМ electronic engine governors are installed: (A, B1) a) Inside the tail boom b) On the engines c) On the ceiling of the cargo compartment between frames No. 3 and 4 Ref: Mi-172 MMA 073.10.00 page 1, para. 1.2 157. How many ЭРД-ЗВМ electronic engine governors are there in engine supply system? (A, B1) a) 1 b) 2 c) 3 Ref: Mi-172 MMA 073.10.00 page 1, para. 1.2 158. The ЭРД-ЗВМ governor consists of two functionally independent control circuits: (A, B1) a) Turbocompressor speed (rpm) limiting circuit (TC circuit) and compressor turbine automatic protecting circuit b) Turbocompressor speed (rpm) limiting circuit (TC circuit) c) Turbocompressor speed (rpm) limiting circuit (TC circuit) and free turbine automatic protecting circuit (FT circuit) Ref: Mi-172 MMA 073.10.00 page 2, para. 2.2 GENERAL - ENGINE Page 34 159. The gas turbine engine comprises: a) Air intake, compressor, turbine b) Compressor, combustion chamber, turbine, exhaust nozzle c) Air intake, compressor, combustion chamber, turbine d) Air intake, compressor, combustion chamber, turbine, exhaust nozzle 160. Function of the air intake of the gas turbine engine: a) To compress air b) Supply air in sufficient quantity and guide the air flow to the compressor c) All above are correct 161. Function of the compressor of the gas turbine engine: a) To compress air b) Supply the high pressure air flow into the combustion chamber c) All above are correct 162. Function of the combustion chamber of the gas turbine engine: a) Where combustion takes place b) Supply thermal energy for air flow of engine c) All above are correct 163. Function of the turbine of the gas turbine engine: a) Transform the thermal energy of gas flow to work b) Drive the compressor, fan c) Drive others components of engine and aircraft d) All above are correct 164. Function of the exhaust nozzle of the gas turbine engine: a) Where the gas expansion b) Direct the flow of hot gases rearward c) All above are correct 165. Type of air intake, classify by air inlet flow velocity Page 35 a) Supersonic air intake b) Subsonic air intake c) All above are correct 166. Air flow temperature when passes through the air intake: a) Increase b) Decrease c) Invariable 167. Type of the compressor of the gas turbine engine: a) Axial compressor b) Centrifugal compressor c) Mixed flow compressor d) All above are correct 168. The basic gas turbine engine is divided into two main sections: the cold section and the hot section, which sentence below is correct? a) The cold section includes the engine air tintake, compressor, and turbine sections b) The hot section includes the combustor, diffuser, and exhaust nozzle c) The hot section includes the combustor, turbine, and exhaust nozzle 169. In a free turbine: a) There is a clutch between compressor and power output shaft b) There is a direct drive with a free-wheel unit c) There is no mechanical connection with the compressor 170. Bernoulli's Theorem states that at any point in a flow of gas: a) The static pressure and dynamic pressure are equal b) The static pressure is less than the dynamic pressure c) The total energy remains constant 171. The working fluid of a gas turbine engine is: a) Gasoline Page 36 b) Kerosene c) Air 172. As subsonic air flows through a convergent nozzle the velocity: a) Decreases b) Increases c) Remains constant 173. What section provides proper mixing of the fuel and efficient burning of the gases? a) Diffuser section and combustion section b) Combustion section and compressor section c) Combustion section only 174. The pressure of subsonic air as it flows through a convergent nozzle: a) Increases b) Remains constant c) Decreases 175. Newton's First Law of Motion, generally termed the Law of Inertia, states: a) To every action there is an equal and opposite reaction b) Force is proportional to the product of mass and acceleration c) Every body persists in its state of rest, or of motion in a straight line, unless acted upon by some outside force 176. Using standard atmospheric conditions, the standard sea level temperature is: a) 15oC b) 15oF c) 29oC 177. The highest pressure in a gas turbine engine is: a) At the nozzle exit. b) At the burner exit. c) Just after the last compressor stage but before the burner Page 37 178. The velocity of subsonic air as it flows through a convergent nozzle: a) Remains constant b) Increases c) Decreases 179. A modular constructed gas turbine engine means that: a) All engines have a specific component layout b) The engine is constructed by the vertical assembly technique c) Its major components can be removed and replaced without disturbing the rest of the engine 180. Which law relates to the kinetic, pressure, and potential energy in a fluid flow? a) Bernoulli's theorem b) Newton's laws c) Charles's law 181. The density of gas may be expressed as: a) Volume/weight b) Weight/volume c) Pressure/volume 182. A divergent duct will cause subsonic flow to: a) Decrease velocity, increase pressure b) Decrease velocity, pressure remains constant c) Decrease pressure, increase velocity 183. The purpose of a diffuser is to: a) Increase the kinetic energy of the air b) Induce a swirl to the air prior to combustion c) Increase the static pressure of the air 184. In a gas turbine engine, gas pressures is greatest at: a) Compressor outlet Page 38 b) Turbine outlet c) Compressor inlet 185. Which of the following is the ultimate limiting factor of turbine engine operation? a) Compressor inlet air temperature. b) Burner can pressure. c) Turbine inlet temperature 186. The point of maximum velocity in the engine is in the. a) Exhaust nozzle exit b) Combustion chamber c) Nozzle guide vanes 187. Power is adjusted in a gas turbine engine by: a) Increasing fuel flow b) Increasing air and fuel flow c) Increasing airflow to the combustion chamber 188. The main factor considered when designing an engine is. a) Maximum fuel consumption b) Maximum turbine temperature c) Maximum tip speed 189. The hottest component in a gas turbine engine is: a) The nozzle guide vanes b) The turbines c) The combustion chamber 190. The efficiency of a gas turbine would be greatest at: a) Cold temperatures b) Low pressure c) Hot temperatures 191. In a gas turbine engine, at turbine section: Page 39 a) Temperature decreases along with pressure and velocity b) Velocity decreases and pressure increases c) Velocity increases and pressure decreases 192. Through turbine rotor blades: a) Pressure increases, temperature increases b) Pressure decreases, temperature decreases c) Pressure remains constant, temperature increases 193. Temperature of the mass airflow through a Gas Turbine Engine: a) Increases from the inlet, through the compressor and the diffuser into the burner, and decreases through the turbine into the exhaust b) Increases from the inlet, through the compressor andremains constant through the diffuser and increases at the burner, and decreases through the turbine into the exhaust c) Remains constant at the inlet, increases from the compressor and the diffuser into the burner, and decreases through the turbine into the exhaust 194. A bellmouth compressor inlet is used on: a) Helicopter b) Supersonic aircraft c) Aircraft with low ground clearance 195. Intake air turbulence: a) Decreases the efficiency of the compressor b) Increases the efficiency of the compressor c) Has little effect on the efficiency of the compressor 196. The purpose of a bellmouth compressor inlet is to: a) Provide an increased ram air effect at low airspeeds b) Maximize the aerodynamic efficiency of the inlet c) Provide an increased pressure drop in the inlet 197. The intake of a gas turbine engine is designed to: Page 40 a) Protect compressor from FOD b) Provide turbulent free air c) Provide streamlined fairing for aircraft 198. What is true for a bellmouth intake? a) Pressure increases and velocity decreases b) Velocity increases and pressure decreases c) Pressure and velocity decrease GENERAL 199. An electric current is: a) An ordered flow of electrons b) A surplus of free electron c) An excitement of electrons in a metal 200. The S.I unit of power is: a) Henry b) Coulomb c) Watt d) Watt-hour 201. To increase resistance of electric wire: a) Increase the wire cross section area b) Increase the wire length c) Decrease the resistivity 202. With rise in temperature, the resistance of pure metals: a) Increases b) Decreases c) Remains constant 203. With rise in temperature, the resistance of semi-conductors: a) Increases Page 41 b) Decreases c) Remains constant 204. Which is the best conductor of electricity? a) Iron b) Silver c) Copper d) Carbon 205. The S.I unit of electric current is: a) Ampere b) Volt c) Watt d) Ohm 206. The S.I unit of voltage is: a) Ampere b) Volt c) Watt d) Ohm 207. The S.I unit of resistance is: a) Ampere b) Volt c) Watt d) Ohm 208. The purpose of bonding is to: a) Ensure all components have been securely fitted b) Stop different potentials developing with subsequent fire risks c) Give generated static an easy return path to the generator 209. On helicopter, the thermocouple is used to measure: Page 42 a) Exhaust gas temperature b) Oil temperature c) Fuel temperature 210. An ammeter is connected into a circuit in: a) Series b) Parallel c) All above are incorrect 211. An ammeter is used to measure: a) Current b) Voltage c) Resistance 212. An voltmeter is used to measure: a) Current b) Voltage c) Resistance 213. An ohmmeter is used to measure: a) Current b) Voltage c) Resistance 214. To decrease resistance of electric wire: a) Increase the wire cross section area b) Increase the wire length c) Increase the resistivity TÀI LIỆU, SB, A/C LOGBOOK, ENGINE LOGBOOK 215. A company’s safety policy should be defined in: a) The Maintenance Schedule b) The Maintenance Organization Exposition Page 43 c) Both a and b Ref: The MOE (Maintenance Organization Exposition) 216. Which statement below about Aircraft Maintenance Manual (MMA) is correct? a) The aircraft maintenance manual (MMA) specifies the manual procedures necessary to make sure that the helicopter always good condition. b) The aircraft maintenance manual (MMA) specifies the maintenance procedures necessary to service the helicopter. c) The aircraft maintenance manual (MMA) specifies the maintenance procedures necessary to ensure the helicopter can flight. 217. Which statement below about The Illustrated Parts Catalog (IPC) is correct? a) The Illustrated Parts Catalog (IPC) contains all the spare parts necessary to ensure continued serviceability of the helicopter. b) The Illustrated Parts Catalog (IPC) contains some the spare parts necessary to ensure continued serviceability of the helicopter. c) The Illustrated Parts Catalog (IPC) contains all the spare parts on the helicopter help to order spare parts to ensure continued serviceability of the helicopter. 218. An inoperative item may be removed from the aircraft if allowed by: a) MMA b) Only qualified personnel c) MEL d) Chief of technical team 219. Which document describes the system on helicopter? a) MMA b) MME c) IPC 220. Where do you find the maintenance action records? a) Technical log book b) Flight manual Page 44 c) Aircraft Log book 221. The flight limitation and emergency procedures are described in: a) Illustrated part catalogue b) Flight manual c) Aircraft Maintenance Manual 222. Identification (P/N) of an aircraft part can be found in: a) MMA b) MTC c) IPC 223. Minimum equipment list necessary to flight with respect to particular operation conditions can be found in: a) MEL b) MMA c) IPC 224. A minimum equipment list (MEL) shall be provided by: a) Approved Maintenance Organization b) The Design of aircraft c) Air Operator 225. Which of the following documents must be carried on an aircraft? a) Certificate of Registration b) Copy of Air operators Certificate c) Engine Log Book d) Both a) and b) are correct 226. An aircraft maintenance schedule (AMS) shall be approved by: a) The state of Registry b) The state of the Operator c) The state of Design Page 45 227. An aircraft maintenance schedule (AMS) shall be provided for the use and guidance of maintenance and operational personnel concerned by: a) Air operator b) Approved Maintenance Organization c) The Design of aircraft 228. An airline's MEL contains an additional note (M). This indicates: a) Mandatory operational restrictions b) Maintenance requirements c) Modified component or system 229. Which section of TV3-117VM engine logbook is used for record of engine’s component installed? a) Section 4 b) Section 6 c) Section 8 d) Section 10 Ref: TV3-117VM engine logbook 230. Which section of TV3-117VM engine logbook is used for engine service life limit record? a) Section 4 b) Section 6 or section 15 c) Section 8 d) Section 10 Ref: TV3-117VM engine logbook 231. If TV3-117VM engine was carried out service life extension, engine extension information can be found in: a) Section 4 b) Section 6 c) Section 8 Page 46 d) Section 10 Ref: TV3-117VM engine logbook 232. Which section of TV3-117VM engine logbook is used for engine preservation and depreservation record? a) Section 4 b) Section 6 c) Section 8 d) Section 9 Ref: TV3-117VM engine logbook 233. Which section of TV3-117VM engine logbook is used for record of transfers? a) Section 6 b) Section 8 c) Section 9 d) Section 10 Ref: TV3-117VM engine logbook 234. Which section of TV3-117VM engine logbook is used for engine hour and engine cycle record? a) Section 4 b) Section 6 c) Section 8 d) Section 10 Ref: TV3-117VM engine logbook 235. In TV3-117VM engine logbook, engine performance record is described in: a) Section 4 b) Section 8 c) Section 10 d) Section 14 Page 47 Ref: TV3-117VM engine logbook 236. In TV3-117VM engine logbook, if the engine was overhauled, engine overhaul record is described in: a) Section 8 b) Section 10 c) Section 14 d) Section 15 Ref: TV3-117VM engine logbook 237. Passports of TV3-117VM engine’s components are stored in: a) TV3-117VM engine logbook b) Aircraft logbook c) Component passport book 238. Which section of VR-14 MGB logbook is used for MGB service life limit record? a) Section 4 b) Section 6 or section 15 c) Section 8 d) Section 10 Ref: VR-14 MGB logbook 239. If VR-14 MGB was carried out service life extension, MGB extension information can be found in: a) Section 4 b) Section 6 c) Section 8 d) Section 10 e) Ref: VR-14 MGB logbook 240. Which section of VR-14 MGB logbook is used for MGB preservation and depreservation record? Page 48 a) Section 4 b) Section 6 c) Section 8 d) Section 9 Ref: VR-14 MGB logbook 241. Which section of VR-14 MGB logbook is used for record of transfers? a) Section 6 b) Section 8 c) Section 9 d) Section 10 Ref: VR-14 MGB logbook 242. Which section of VR-14 MGB logbook is used for MGB hour record? a) Section 4 b) Section 6 c) Section 8 d) Section 10 Ref: VR-14 MGB logbook 243. In VR-14 MGB logbook, MGB performance record is described in: a) Section 4 b) Section 8 c) Section 10 d) Section 14 Ref: VR-14 MGB logbook 244. In VR-14 MGB logbook, if the MGB was overhauled, MGB overhaul record is described in: a) Section 8 b) Section 10 Page 49 c) Section 14 d) Section 15 Ref: VR-14 MGB logbook 245. Which section of AI-9V engine logbook is used for service life limit record? a) Section 4 b) Section 6 or section 15 c) Section 8 d) Section 10 Ref: VR-14 MGB logbook 246. If AI-9V engine was carried out service life extension, AI-9V engine extension information can be found in: a) Section 4 b) Section 6 c) Section 8 d) Section 10 Ref: AI-9V logbook 247. Which section of AI-9V engine logbook is used for preservation and depreservation record? a) Section 4 b) Section 6 c) Section 8 d) Section 9 Ref: AI-9V logbook 248. Which section of AI-9V engine logbook is used for record of transfers? a) Section 6 b) Section 8 c) Section 9 Page 50 d) Section 10 Ref: AI-9V logbook 249. Which section of AI-9V engine logbook is used for hour, air bleeds, starts record? a) Section 4 b) Section 6 c) Section 8 d) Section 10 Ref: AI-9V logbook 250. In AI-9V engine logbook, if the AI-9V engine was overhauled, AI-9V engine overhaul record is described in: a) Section 8 b) Section 10 c) Section 14 d) Section 15 Ref: AI-9V logbook 251. Passports of AI-9V engine’s components are stored in: a) TV3-117VM engine logbook b) Aircraft logbook c) Component passport book d) AI-9V engine logbook ATA - 029.00.00 HYDRAULIC SYSTEM 252. Type of hydraulic system(s) on Mi-172 helicopter: (A, B1) a) Single b) Dual, included: 01 main system and 01 auxiliary system c) Dual, included: 02 main systems and 01 auxiliary system Ref: Mi-172 MMA 029.00.00 page 1. 253. Operating pressure in main and auxiliary hydraulic systems: (A, B1) Page 51 a) 45 ± 3 to 65 +-82 kgf/cm2 b) 40 ± 3 to 60 +-82 kgf/cm2 c) 45 ± 3 to 85 +-82 kgf/cm2 Ref: Mi-172 MMA 029.00.00 page 2. 254. Operating hydraulic fluid allowable temperature is up to: (A, B1) a) 80oC b) 70 oC c) 90oC Ref: Mi-172 MMA 029.00.00 page 2. 255. Quanlity of hydraulic fluid in hydraulic systems: (A, B1) a) 22 litres b) 32 litres c) 42 litres Ref: Mi-172 MMA 029.00.00 page 2. 256. Hydraulic system pressure necessary to put the pump into operating duty (hydraulic system feeding): (A, B1) a) 45 ± 3 kgf/cm2 b) 30 ± 5 kgf/cm2 c) 30 ± 2 kgf/cm2 Ref: Mi-172 MMA 029.00.00 page 2. 257. Hydraulic system pressure necessary to change-over the pump for idling (pumping fluid into the tank) (A, B1) a) 45 ± 3 kgf/cm2 b) 65 +-82 kgf/cm2 c) 30 ± 2 kgf/cm2 Ref: Mi-172 MMA 029.00.00 page 2. 258. Hydraulic pressure in main system necessary to changeover feeding of hydraulic actuators to auxiliary system: (A, B1) a) 32 ± 5 kgf/cm2 Page 52 b) 35 ± 5 kgf/cm2 c) 30 ± 5 kgf/cm2 Ref: Mi-172 MMA 029.00.00 page 2. 259. Pressure in hydraulic accumulators, charged with technical nitrogen (without pressure in hydraulic system): (A, B1) a) 32 ± 2 kgf/cm2 b) 35 ± 2 kgf/cm2 c) 30 ± 2 kgf/cm2 Ref: Mi-172 MMA 029.00.00 page 2. 260. The gas charging for hydraulic accumulators: (A, B1) a) Oxygen b) Nitrogen c) Pneumatic Ref: Mi-172 MMA 029.00.00 page 1. 261. The function of ГА-77B pump automatic by – pass valve in hydraulic system: (A, B1) a) Maintain automatically pressure in the hydraulic system within the desired limits b) Turn ON/OFF supply of hydraulic actuators with operating fluid from a respective hydraulic system c) Auto changed over from idle running to operating mode Ref: Mi-172 MMA 029.10.00 page 1. 244. The function of ГА -74M/5 two – position valve in hydraulic system: (A, B1) a) Maintain automatically pressure in the hydraulic system within the desired limits b) Turn ON/OFF supply of hydraulic actuators with operating fluid from a respective hydraulic system c) Auto changed over from idle running to operating mode Ref: Mi-172 MMA 029.10.00 page 1. 245. The function of ГА-59/1 emergency supply valve in hydraulic system: (A, B1) a) Maintain automatically pressure in the hydraulic system within the desired limits b) Turn ON/OFF supply of hydraulic actuators with operating fluid from a respective hydraulic system Page 53 c) Automatic actuation of the auxiliary hydraulic system in the event of failure of the main hydraulic system Ref: Mi-172 MMA 029.20.00 page 1. 246. The function of ГА-192T solenoid – operated valve in hydraulic system: (A, B1) a) Maintain automatically pressure in the hydraulic system within the desired limits b) Supply operating fluid to the combination control hydraulic actuators, collective pitch control friction clutch and the hydraulic stop in longitudinal control c) Cut off the supply pipeline of the hydraulic power cylinder used for control of the collective pitch control lever friction clutch Ref: Mi-172 MMA 029.10.00 page 1. 247. How many ГА-192T solenoid-operated valves are there on Mi-172 hydraulic systems? (A, B1) a) 03 b) 04 c) 05 Ref: Mi-172 MMA 029.10.00 page 1. 248. The function of ГА-172-00-2T flow metering device on hydraulic system: (A, B1) a) Maintain automatically pressure in the hydraulic system within the desired limits b) Turn ON/OFF supply of hydraulic actuators with operating fluid from a respective hydraulic system c) Cut off the supply pipeline of the hydraulic power cylinder used for control of the collective pitch control lever friction clutch Ref: Mi-172 MMA 029.10.00 page 1. 249. How many ГА-172-00-2T flow metering device are there in hydraulic sytems? (A, B1) a) 01 b) 02 c) 05 Ref: Mi-172 MMA 029.10.00 page 1. 250. The НШ-39М gear pumps of hydraulic systems are received torque from: (A, B1) a) Main engines b) Main gear box c) Electric motor Page 54 Ref: Mi-172 MMA 029.00.00 page 3/4, fig.1. 251. How to perform function test of the hydraulic system when the helicopter is not operating: (A, B1) a) Start the main engines b) Start the auxiliary engine c) Use ground hydraulic test set Ref: Mi-172 MMA 029.10.00f 252. Pressure exceeds 75kgf/cm2 in main hydraulic system due to: (B1 - troubleshoot) a) Failure of ГА -77B b) Failure of ГА -74M/5 c) Failure of ГА -59/1 Ref: Mi-172 MMA 029.10.00 page 102. 253. Main hydraulic system fails to start operating due to: (B1 - troubleshoot) a) Failure of ГА -77B b) Failure of ГА -74M/5 c) Failure of ГА -59/1 Ref: Mi-172 MMA 029.10.00 page 103/104. 254. Main hydraulic system pressure drops down to 30 ±5 kgf/cm2 but auxiliary hydraulic system is not operating (hydraulic pumps is in normal operation), due to: (B1 - troubleshoot) a) Failure of ГА -77 B b) Failure of ГА -74M/5 c) Failure of ГА -59/1 Ref: Mi-172 MMA 029.20.00 page 1. 255. The autopilot system is turned on in flight but hydraulic actuators are not operating, due to: (B1 - troubleshoot) a) Failure of ГА-172-00-2T b) Failure of ГA-59/1 c) Failure of ГА-192T Ref: Mi-172 MMA 029.00.00 256. Hydraulic pressure fluctuates in flight, due to: (B1 - troubleshoot) a) Failure of accumulator Page 55 b) Failure of ГА -192T c) Failure of ГА -74M/5 Ref: Mi-172 MMA 029.10.00 page 1, para 1.3 ATA - 032.00.00 LANDING GEAR 257. Function of landing gears: (A, B1) a) Cushion the impacts arising in the helicopter in flight b) Cushion the impacts arising in the helicopter on taking off or landing c) Cushion the impacts arising in the helicopter on landing, landing run or takeoff run as well as to facilitate helicopter motion on the ground Ref: Mi-172 MMA 032.00.00 page 1/2. 258. Type of landing gears: (A, B1) a) Three landing gears, retractable b) Three landing gears, nonretractable c) Two main landing gears, retractable Ref: Mi-172 MMA 032.00.00 page 1/2. 259. The main landing gear shock absorbers are mounted: (A, B1) a) On fuselage frame No. 7 b) On fuselage frame No. 10 c) On fuselage frame No. 11 d) On fuselage frame No. 13 Ref: Mi-172 MMA 032.10.00 page 1. 260. The main landing gear radius rods are mounted: (A, B1) a) On fuselage frame No. 7 b) On fuselage frame No. 10 c) On fuselage frame No. 11 d) On fuselage frame No. 13 Ref: Mi-172 MMA 032.10.00 page 1. 261. The main landing gear side struts are mounted: (A, B1) a) On fuselage frame No. 7 b) On fuselage frame No. 10 c) On fuselage frame No. 11 Page 56 d) On fuselage frame No. 13 Ref: Mi-172 MMA 032.10.00 page 1. 262. Type of operating fluid in landing gear shock absorbers: (A, B1) a) АМГ-10 or equivalent fluids b) Б-3В or equivalent oil c) МС-20 or equivalent oil d) ТСгип or equivalent oil Ref: Mi-172 MMA 032.00.00 page 1/2. 263. Type of gas in landing gear shock absorbers: (A, B1) a) Pneumatic b) Nitrogen c) CO2 d) Helium Ref: Mi-172 MMA 032.00.00 page 1/2. 264. Type of main landing gears: (A, B1) a) One shock absorber chamber b) Two high pressure chambers shock absorber c) Two low pressure chambers shock absorber d) One low pressure and one high pressure chamber shock absorber Ref: Mi-172 MMA 032.10.00 page 1. 265. Nitrogen pressure in low pressure chamber of main landing gear shock absorber: (A, B1) a) 22 +1 kgf/cm2 b) 26 +1 kgf/cm2 c) 28 ±2 kgf/cm2 d) 32 ±2 kgf/cm2 Ref: Mi-172 MMA 032.10.00 page 2. 266. Nitrogen pressure in high pressure chamber of main landing gear shock absorber: (A, B1) a) 45 ±2 kgf/cm2 b) 50 ±2 kgf/cm2 c) 55 +1 kgf/cm2 Page 57 d) kgf/cm2 Ref: Mi-172 MMA 032.10.00 page 2. 267. Capacity of operating fluid to be filled into low pressure chamber of main landing gear: (A, B1) a) 1105 cm3 b) 1110 cm3 c) 1115 cm3 d) 1120 cm3 Ref: Mi-172 MMA 032.10.00 page 2. 268. Capacity of operating fluid to be filled into high pressure chamber of main landing gear: (A, B1) a) 2200 cm3 b) 2300 cm3 c) 2400 cm3 d) 2500 cm3 Ref: Mi-172 MMA 032.10.00 page 2. 269. The AM-800K microswitch on the main landing gear of Mi-172 helicopter supplies signal to: (A, B1) a) The hydraulic stop in helicopter longitudinal control system b) The П-503Б (П-507Б) recorder or БУР-1-2 (KQ – 172) c) A and B are corrected d) The helicopter take off light Ref: Mi-172 MMA 032.10.00 page 2. 270. The clearance between upper arm and microswitch rod of AM-800K microswitch on the main landing gear is: (A, B1) a) 0.5 ± 0.5 mm b) 1 ± 0.5 mm c) 2 ± 0.5 mm d) No clearance Ref: Mi-172 MMA 032.10.00 page 3/4. 271. Type of nose landing gear: (A, B1) a) One shock absorber chamber Page 58 b) Two high – pressure shock absorber chamber c) Two low – pressure shock absorber chamber d) Two shock absorber chambers: high and low pressure chambers Ref: Mi-172 MMA 032.20.00 page 1. 272. The upper attachment fitting of the nose landing gear is secured to: (A, B1) a) Frame No. 1 on the fuselage center section b) Frame No. 2 on the fuselage center section c) Frame No. 3 on the fuselage center section d) Frame No. 4 on the fuselage center section Ref: Mi-172 MMA 032.20.00 page 1. 273. The lower attachment fitting of the nose landing gear is secured through a forked welded strut to: (A, B1) a) Frame No. 1 on the fuselage center section b) Frame No. 2 on the fuselage center section c) Frame No. 3 on the fuselage center section d) Frame No. 4 on the fuselage center section Ref: Mi-172 MMA 032.20.00 page 1. 274. Compression of the nose landing gear shock strut operating rod by the indicator when the helicopter is empty: (A, B1) a) 35 ± 10 mm b) 65 ± 10 mm c) 130 ± 10 mm d) 150 ± 10 mm Ref: Mi-172 MMA 032.20.00b 275. Compression of the nose landing gear shock strut operating rod by the indicator when the helicopter at a takeoff mass of 12000 kg: (A, B1) a) 35 ± 10 mm b) 65 ± 10 mm c) 130 ± 10 mm d) 150 ± 10 mm Ref: Mi-172 MMA 032.20.00b 276. Nitrogen pressure in nose landing gear shock strut: (A, B1) Page 59 a) 22 + 1 kgf/cm2 b) 26 + 1 kgf/cm2 c) 28 ± 1 kgf/cm2 d) 32 ± 1 kgf/cm2 Ref: Mi-172 MMA 032.20.00e 277. Capacity of operating fluid to be filled into nose landing gear shock strut: (A, B1) a) 2.05 litres b) 2.06 litres c) 2.08 litres d) 2.10 litres Ref: Mi-172 MMA 032.20.00 page 1 278. Pneumatic pressure in main wheels: (A, B1) a) 4.5 ±0.5 kgf/cm2 b) 5.5 ±0.5 kgf/cm2 c) 6.5 ±0.5 kgf/cm2 Ref: Mi-172 MMA 032.40.00 page 1 279. Pneumatic pressure in nose wheels: (A, B1) a) 4.5 ±0.5 kgf/cm2 b) 5.5 ±0.5 kgf/cm2 c) 6.5 ±0.5 kgf/cm2 Ref: Mi-172 MMA 032.40.00 page 1. 280. Type of the main landing gear wheel brake: (A, B1) a) Shoe brake controlled by machine b) Shoe brake controlled by pneumatic c) Disk brake controlled by hydraulic pressure d) Disk brake controlled by pneumatic Ref: Mi-172 MMA 032.00.00 page 1/2 281. Clearance between the brake shoes and the brake drum jacket should be within: (A, B1) a) 0,0 ÷ 0,3 mm b) 0,3 ÷ 0,4 mm c) 0,3 ÷ 0,5 mm Page 60 d) 0,5 ÷ 1,0 mm Ref: Mi-172 MMA 032.40.00c 282. The tail bumper is designed to: (A, B1) a) Protect the tail rotor blades from impact against the ground and reduce tail boom load acceleration on landing at a great nose-down pitch angle b) Protect the tail rotor blades from impact against the ground and reduce tail boom load acceleration on landing at a great nose-up pitch angle c) All above are incorrect Ref: Mi-172 MMA 032.00.00 page1/2. 283. Nitrogen pressure in shock absorber of tail bumper: (A, B1) a) 25 + 1 kgf/cm2 b) 26 + 1 kgf/cm2 c) 27 ± 1 kgf/cm2 d) 28 ± 1 kgf/cm2 Ref: Mi-172 MMA 032.70.00 page 1. 284. Capacity of operating fluid to be filled into shock absorber of tail bumper: (A, B1) a) 320 cm3 b) 330 cm3 c) 340 cm3 d) 350 cm3 Ref: Mi-172 MMA 032.70.00 page 1 285. Grease leaks through wheel bearing cover felt rings: (B1 – troubleshoot) a) Worn steel ring b) Worn copper ring c) Worn felt ring d) Worn rubber ring Ref: Mi-172 MMA 032.40.00 page 101 286. Decrease in clearance between brake shoes and brake drum jacket: (B1 – troubleshoot) a) Brake shoes broken b) Springs broken or lost their elasticity c) Brake cable broken or lost its elasticity Page 61 Ref: Mi-172 MMA 032.40.00 page 102. ATA - 049.00.00 AUXILIARY POWER UNIT (APU) 287. The engine compressor of APU is: (A, B1) a) Single-stage unit of the centrifugal type b) Single-stage unit of the axial type c) Double-stages unit of the axial and centrifugale type Ref: AИ-9B MAINTENANCE MANUAL para. 1.3.1 288. The engine compressor of APU consists of the following major assembles and parts: (A, B1) a) Rotor casing, Outer shroud, Radial diffuser, Front casing with a damper, oil spray rings b) Rotor casing, Outer shroud, Rotor, Radial diffuser, Front casing with a damper c) Rotor casing, Outer shroud, Rotor, Radial diffuser, Front casing with a damper, oil spray rings Ref: AИ-9B MAINTENANCE MANUAL para. 1.3.1 289. The combustion chamber assembly comprises: (A, B1) a) Combustion chamber casing b) Combustion chamber proper c) Main fuel nozzles, torch igniter, fuel manifold d) All of above are correct Ref: AИ-9B MAINTENANCE MANUAL para. 1.3.3 290. The auxiliary power unit serves: (A, B1) a) To supply the TB3-117BM engine air starting system on the ground and in flight b) To supply the helicopter electrical system with DC power to check its equipment on the ground c) To supply the helicopter electrical system in flight in case of failure of its main generators ГT40ПЧ8В d) All of above are correct Ref: Mi-172 MMA 049.00.00 page 1/2. 291. The maximum permissible EGT at power condition: (A, B1) a) 990oC b) 880oC c) 750oC d) 720oC Page 62 Ref: AИ-9B MAINTENANCE MANUAL para. 2.2.1 292. The maximum permissible EGT at starting: (A, B1) a) 990oC b) 880oC c) 750oC d) 720oC Ref: AИ-9B MAINTENANCE MANUAL para. 2.2.1 293. The permissible EGT at idle speed does not exceed: (A, B1) a) 990oC b) 880oC c) 750oC d) 720oC Ref: AИ-9B MAINTENANCE MANUAL para. 4.1.6 294. How many consecutive times does the AИ-9B engine start? (A, B1) a) 5 times b) 4 times c) 3 times d) 2 times Ref: AИ-9B MAINTENANCE MANUAL para. 2.2.14 295. The minimum period between 2 consecutive starting times of AИ-9B engine is: (A, B1) a) 4 minutes b) 3,5 minutes c) 3 minutes d) 2,5 minutes Ref: AИ-9B MAINTENANCE MANUAL para. 2.2.14 296. The minimum period between 2 consecutive of providing air pressure is: (A, B1) a) 90 s b) 45 s c) 60 s d) 75 s Ref: AИ-9B MAINTENANCE MANUAL para. 2.2.15 Page 63 297. The operating time of engine at generator mode is: (A, B1) a) 60 minutes b) Less than 30 minutes c) 20 minutes d) Not limited Ref: AИ-9B MAINTENANCE MANUAL para. 2.1.2 298. Maximum permissible number of air bleeds of AИ-9B: (A, B1) a) 12 times b) 10 times c) 7 times d) 5 times Ref: AИ-9B MAINTENANCE MANUAL para. 2.2.15 299. The maximum time to complete the AИ-9B starting phase: (A, B1) a) 9s b) 15 s c) 20 s d) 30 s Ref: AИ-9B MAINTENANCE MANUAL para. 4.1.3 300. The exhaust gas temperature at idle mode is: (A, B1) a) 990o C b) 750oC c) 880o C d) 720o C Ref: AИ-9B MAINTENANCE MANUAL para. 2.4 301. Oil volume filled into oil tank of the AИ-9B engine: (A, B1) a) 4.5 ± 0,1 litres b) 3,5 ± 0,1 litres c) 2,5 ± 0,1 litres d) 1,5 ± 0,1 litres Ref: AИ-9B MAINTENANCE MANUAL para. 2.2.9 302. The fuel provide to the starting process of the AИ-9B engine from: (A, B1) a) Starting fuel pump of AИ-9B engine Page 64 b) Under fuel gravity from service tank c) Fuel pump 463Б of feeder tank d) HP-9B pump Ref: AИ-9B MAINTENANCE MANUAL para. 1.5.1 303. The shutter in air bleed valve of AИ-9B engine is opened to supply air for CB-78 due to: (A, B1) a) Electric motor b) Fuel pressure from HP-9 c) Spring structure d) Differential pressure before and after shutter Ref: AИ-9B MAINTENANCE MANUAL 1. Para. 1.3.6 304. The shutter in air bleed valve of AИ-9B engine is closed when CB-78 is out of working: (A, B1) a) By solenoid valve b) By fuel pressure from HP- 9 c) By spring d) By air pressure of AИ-9B engine Ref: AИ-9B MAINTENANCE MANUAL 1. Para. 1.3.6 305. When CB-78 was not supplied, the air in the AИ-9B engine bleed out due to: (A, B1) a) Solenoid valve b) Fuel pressure from HP- 9 c) The shutter closed, the drain boss opened by spring force and air pressure d) AИ-9B air pressure Ref: AИ-9B MAINTENANCE MANUAL 1. Page 11. 306. When the engine supplies pressure air to main engine, the air bleed valve assembly is closed due to: (A, B1) a) The pressure difference made the butterfly valve open to provide the pressure air to CB-78 b) The butterfly valve open, air pressure in upper body of piston pushes the spring c) The butterfly valve open, air pressure in upper chamber of piston is more than the pressure under drain boss d) The shutter open, air pressure pushes the spring to close air bleed outside Ref: AИ-9B MAINTENANCE MANUAL 1. Page 8. Page 65 307. The pressure air of AИ-9B engine supply to main engine is bleeded from: (A, B1) a) The outlet of centrifugal compressor b) The outlet of centrifugal compressor to accumulator throughout the holes c) The outlet of centrifugal compressor to cool the combustion case d) The outlet of combustion chamber Ref: AИ-9B MAINTENANCE MANUAL 1. Page 8. 308. The oil pressure sensor in the AИ-9B engine is located: (A, B1) a) Downstream oil pump and upstream filter b) Downstream oil high pressure filter c) After lubricating the bearings d) In the oil path of twin drive gears and reduction gear of starter-generator Ref: AИ-9B MAINTENANCE MANUAL 1. Page 12. 309. The fuel system of AИ-9B engine is divided into: (A, B1) a) Low and hight fuel pressure system b) Low, hight pressure and starting systems c) Is not divided seperatedly d) Only hight fuel pressure system Ref: AИ-9B MAINTENANCE MANUAL 1. Page 16. 310. The engine fuel control equipment includes: (A, B1) a) The fuel regulating pump b) The electric starting fuel pump c) All of above are correct Ref: AИ-9B MAINTENANCE MANUAL 1. Page 18. 311. The hight pressure fuel pump of AИ-9B engine is: (A, B1) a) Piston type b) Centrifugal type c) Gear type d) Piston pump with inclined plate type Ref: AИ-9B MAINTENANCE MANUAL 1. Page 18. 312. The HP-9B fuel regulating pump function of AИ-9B engine is: (A, B1) a) Control of fuel supply commencement of start till acceleration to operating speed b) Cut-off of fuel flow into engine Page 66 c) Closing of electrical circuit when the engine attains maximum continuous speed and maining this speed d) All of above are correct Ref: AИ-9B MAINTENANCE MANUAL 2. Page 4. 313. Which crews can technician adjust on the fuel regulating pump? (A, B1) a) Screw N°1 & N°2 b) Screw N°3 & N°4 c) Screw N°4 & N°5 Ref: AИ-9B MAINTENANCE MANUAL 6. Page 5. 314. The engine gets shut down for acceleration to the maximum limit rpm at starting time should replace: (A, B1) a) The regulating pump fuel jet by a jet of a smaller diameter b) The regulating pump fuel jet by a jet of a bigger diameter c) The regulating pump fuel filter by a filter of a smaller than d) The regulating pump fuel filter by a filter of a bigger than Ref: AИ-9B MAINTENANCE MANUAL 6. Page 6. 315. The starting fuel pump of AИ-9B engine is type: (A, B1) a) Piston type b) Centrifugal type c) Gear type d) Piston pump with inclined plate type Ref: AИ-9B MAINTENANCE MANUAL 1. Page 27. 316. The 726B starting fuel pump function of AИ-9B engine is type: (A, B1) a) Fuel supply to starting and main fuel nozzles at starting b) Fuel supply to starting and auxiliary fuel nozzles at starting. c) Fuel supply to starting and main fuel nozzles after starting d) Fuel supply to starting and auxiliary fuel nozzles after starting Ref: AИ-9B MAINTENANCE MANUAL 2. Page 4. 317. The oil pump of AИ-9B engine is type: (A, B1) a) Piston type b) Centrifugal type c) Gear type Page 67 d) Piston pump with inclined plate type Ref: AИ-9B MAINTENANCE MANUAL 2. Page 4. 318. The oil system of AИ-9B engine is type: (A, B1) a) Self-contained, circulation-type, pressure feed b) Self-contained, electric, automatic c) Self-contained, immerse oil sump Ref: AИ-9B MAINTENANCE MANUAL 2. Page 4. 319. One turn of oil pressure adjusting screw will change: (A, B1) a) 0,25 kgf/cm2 b) 0,35 kgf/cm2 c) 0,50 kgf/cm2 Ref: AИ-9B MAINTENANCE MANUAL 6. Page 4b. 320. The tarting system of AИ-9B engine is type: (A, B1) a) Self-contained, circulation-type, pressure feed b) Self-contained, electric, automatic c) Self-contained, immerse oil sump Ref: AИ-9B MAINTENANCE MANUAL 2. Page 4. 321. The ignion coil of AИ-9B engine is type: (A, B1) a) Spark coil b) Magnetic c) Vibratory d) Induction coil Ref: AИ-9B MAINTENANCE MANUAL 2. Page 5. 322. The oil consumption of AИ-9B engine is: (A, B1) a) 0.20 kg/h b) 0.18 kg/h c) 0.15 kg/h d) 0.10 kg/h Ref: AИ-9B MAINTENANCE MANUAL 2. Page 7. 323. The maximum oil temperature of AИ-9B engine is: (A, B1) a) 150 °C b) 155 °C Page 68 c) 165 °C d) 170 °C Ref: AИ-9B MAINTENANCE MANUAL 2. Page 7. 324. The minimum permissible voltage in engine starting circuit of AИ-9B engine is: (A, B1) a) 15 V b) 18 V c) 20 V d) 25 V Ref: AИ-9B MAINTENANCE MANUAL 2. Page 7. 325. In emergency case, the AИ-9B engine can supply air and electric power at the same time? (A, B1) a) Yes, it can b) No, it is not permitted c) Depend on a certain case Ref: AИ-9B MAINTENANCE MANUAL 2. Page 2. 326. The engine rotor failes to rotate at starting due to: (A, B1) a) Start preparatory steps not completed b) No power supply to starter-generator c) Starter-generator failure d) All of above are correct Ref: AИ-9B MAINTENANCE MANUAL 10. Page 1. 327. The engine failes to light up at start (no increase in EGT) due to: (A, B1) a) No spark formation on ignition plug b) No fuel supply to starting nozzle c) All of above are correct Ref: AИ-9B MAINTENANCE MANUAL 10. Page 1. 328. High EGT during start due to: (A, B1) a) Sluggish spin-up of engine rotor by starter-generator b) Puddling of fuel in combustion chamber before start c) Air bleed valve is open or leak in helicopter air system d) High fuel flow as againt engine starting characteristic e) All of above are correct Page 69 Ref: AИ-9B MAINTENANCE MANUAL 10. Page 4. 329. Engine gets shut down for acceleration to limit rpm due to: (A, B1) a) Air in fuel system b) Clogging of regulating pump control pressure line fuel filter c) High fuel flow at idling d) All of above are correct Ref: AИ-9B MAINTENANCE MANUAL 10. Page 5. 330. Annuciator OIL PRESS NORMAL fails to come on during engine operation after warm up due to: (A, B1) a) Bulb failed faulty wiring or oil pressure switch b) Low resistance of oil pump block by-pass valve spring c) All of above are correct Ref: AИ-9B MAINTENANCE MANUAL 10. Page 7/8. 331. Flickering of OIL PRESS NORMAL annunciator due to: (A, B1) a) Foreign particles under oil pump block by-pass valve b) Low resistance of oil pump block by-pass valve spring c) All of above are correct Ref: AИ-9B MAINTENANCE MANUAL 10. Page 7/8. ATA - 077.00.00 ENGINE MONITORING INSTRUMENT 332. The engine power monitoring instruments intalled on the helicopter are: (A, B1) a) Electric magnetic drag-type tachometer ИТЭ-2Т b) Engine pressure ratio gauge ИP-117 c) All above are correct Ref: Mi-172 MMA 077.10.00 page 1/2 333. The ИТЭ-2Т tachometer set consitsts of: (A, B1) a) Two tachometer generators Д-2M, two tachometer indicators ИТЭ-2Т b) One tachometer generator Д-2M, two tachometer indicators ИТЭ-2Т c) Two tachometer generators Д-2M, one tachometer indicator ИТЭ-2Т d) One tachometer generators Д-2M one tachometer indicators ИТЭ-2Т Ref: Mi-172 MMA 077.10.00 page 1/2 334. The ИP-117M engine pressure ratio gauge set consists: (A, B1) a) Engine pressure ratio indicator УР-117M b) Two pressure transmitters ПM-10MP Page 70 c) Altitude corrector ДВK d) Temperature pickup П-1 e) All are corrected Ref: Mi-172 MMA 077.10.00 page 1/2. 335. The temperature of the inlet entering the turbine of the engine compressors is measured by: (A, B1) a) The helicopter-borne single temperature gauge 2ИА-6 b) The helicopter-borne dual temperature gauge 2ИА-6 c) The helicopter-borne triple temperature gauge 2ИА-6 Ref: Mi-172 MMA 077.20.00 page 1/2. 336. The 2ИA-6 temperature gauge set consists: (A, B1) a) Dual temperature indicator 2УТ-6К b) Dual amplifier 2УЭ-6Б c) Two intermediate thermocouple compensating blocks ПК-6 d) All are corrected Ref: Mi-172 MMA 077.20.00 page 1/2. 337. Which kind of equipment is installed on the helicopter to monitor vibration conditions of the TB3-117BM engines? (A, B1) a) The ИВ-400Е b) The ИВ-500Е c) The ИВ-600Е Ref: Mi-172 MMA 077.30.00 page 1/2. 338. The set of the ИВ-500Е vibration indicator equipment consists: (A, B1) a) Electronic unit БЭ-9Е b) Two matching devices УcC-6 c) Two vibration pickups MB-03-1 d) All are corrected Ref: Mi-172 MMA 077.30.00 page 1/2. ATA - 078.00.00 ENGINE EXHAUST SYSTEM 339. The exhaust extention is provided on the TB3-117BM engine to: (A, B1) a) Discharge the exhaust gases b) Discharge the redundant fuel Page 71 c) Discharge the redundant oil d) All are corrected Ref: Mi-172 MMA 078.00.00 page 1. 340. The exhaust extention is secured to the engine exhaust pipe by mean of: (A, B1) a) Clamp with turnbuckle b) Cable with turnbuckle c) Argon-arc electric welding Ref: Mi-172 MMA 078.00.00 page 1. 341. The exhaust extention is sealed off by mean of: (A, B1) a) Sealing o’ring b) Sealing gasket c) Sealing copper washer d) Sealing cord Ref: Mi-172 MMA 078.00.00 page 1. ATA 079.00.00 – ENGINE OIL SYSTEM 342. The oil system serves to provide lubrication of: (A, B1) a) The friction surfaces of the drive box, working and free turbines, shafts and other components of the engine b) The friction surfaces of the drive box, compressor bearings, shafts and other components of the engine c) The friction surfaces of the drive box, compressor bearings, working and free turbines, shafts and other components of the engine Ref: Mi-172 MMA 079.00.00 page 1. 343. What kind of the engine oil system? (A, B1) a) Plash type b) Circulating type c) No-circulating type Ref: Mi-172 MMA 079.00.00 page 1. 344. What kind of oil used for the engine oil system? (A, B1) a) MC-20 b) GIBOIT c) MC-8П d) Б-3В or equivalent oil Page 72 Ref: Mi-172 MMA 079.00.00 page 1. 345. The pressure and temperature of the oil are measured by means of: (A, B1) a) One set of electric engine guage units ЭМИ-3РИ b) Two sets of electric engine guage units ЭМИ-3РИ c) Three sets of electric engine guage units ЭМИ-3РИ d) Four sets of electric engine guage units ЭМИ-3РИ Ref: Mi-172 MMA 079.00.00 page 1. 346. Where is the chip detector CC-78 installed in the engine oil system? (A, B1) a) At the inlet into the oil cooler b) At the outlet of the oil cooler c) At the inlet into the oil filter d) At the outlet of the oil filter Ref: Mi-172 MMA 079.00.00 page 1. 347. Where is the oil temperature pickup П-1 installed in the engine oil system? (A, B1) a) On the pipeline supplying the oil to the oil cooler b) On the pipeline scavenging the oil from the oil cooler c) On the hose for returning oil to oil cooler d) On the hose for returning oil from oil cooler Ref: Mi-172 MMA 079.00.00 page 2. 348. What is the oil level shown on the oil tank? (A, B1) a) FULL-11 LIT and MIN-7 LIT b) FULL-12 LIT and MIN-8 LIT c) FULL-10 LIT and MIN-9 LIT d) FULL-11 LIT and MIN-8 LIT Ref: Mi-172 MMA 079.10.00 page 1. 349. The labyrinth cones at top of the oil tank use for: (A, B1) a) Separating the oil from the air b) Separating the air from the oil c) Separating the oil from the fuel d) Separating the fuel from the oil Ref: Mi-172 MMA 079.10.00 page 1. 350. Draining of the oil from the oil tank is made through: (A, B1) a) Drain valve 600300M b) Drain valve 600400M c) Drain valve 600500M Page 73 Ref: Mi-172 MMA 079.10.00 page 1. 351. Draining of the oil from the lubrication system is effected through: (A, B1) a) Drain valve 636700A b) Drain valve 636700B c) Drain valve 636700C d) Drain valve 636700D Ref: Mi-172 MMA 079.20.00 page 1. 352. Replacing the oil cooler when the obtained value of the back pressure is: (A, B1) a) More than 1,15 kgf/cm2 b) More than 1,25 kgf/cm2 c) More than 1,35 kgf/cm2 Ref: Mi-172 MMA 079.20.00 page 212. 353. The parameter sector in green colour mark on the indicator УИЗ-3К is: (A, B1) a) Normal sector b) Caution sector c) Warning (dangerous) sector Ref: Mi-172 MMA 079.30.00 page 211. 354. The parameter sector in yellow colour mark on the indicator УИЗ-3К is: (A, B1) a) Normal sector b) Caution sector c) Warning (dangerous) sector Ref: Mi-172 MMA 079.30.00 page 211. 355. The parameter sector in red colour mark on the indicator УИЗ-3К

MI Helicopter Airframe & Engine Questions (09.07.2019) PDF

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