TEST BORRADO, QUIZÁS LE INTERESE:
ATR72-2
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Título del Test:
ATR72-2 Descripción: ATR72-2 ULTIMAS 50 Preguntas Autor: ATR42 OTROS TESTS DEL AUTOR Fecha de Creación: 23/01/2014 Categoría: Test de conducir Número Preguntas: 50 |
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51- Turbo fan shut off valve is controlled by: a) Pack sw b) Pack valve c) MFC. a) Pack sw b) Pack valve c) MFC. 52- In automatic mode each pack delivery temperature is controlled by: a) Zone temperature demand selector directly b) An electronic temperature controller c) Non are correct. 53- In manually mode each pack delivery temperature is controlled by: a) Zone temperature demand selector directly b) An electronic temperature controller c) Non are correct. 54- ATR 72 uses on aileron: a) Spring tab b) aileron tab c) a) and b) are correct. 55- is used for aileron trim: a) left aileron tab b) right aileron tab c) both aileron tabs. 56- provides flexible compensation with automatically increases with aerodynamics loads applied on the ailerons thus ensuring a reduction of the pilots efforts: a) spring tabs b) ailerons tabs c) non are correct. 57- limit pedals travel in order to prevent any damage to rudder structure when flying at high speed: a) ADC b) TLU c) MFC. 58- TLU automatic control is performed when reaching: a) 108kts during acceleration and deceleration b) 190kts during acceleration and deceleration c) 180kts during acceleration and deceleration. 59- Which ADC has priority over the TLU operation: a) ADC1 b) ADC2 c) Both ADCs. 60- The stall warning system includes: a) 2 stick pusher, 1 stick shaker b) 2 stick pusher, , 2 stick shaker c) 1 stick pusher, 2 stick shaker. 61- In the pitch uncoupling mechanism, in the event of pitch uncoupling : a) System recoupling has to be performed on ground b) System recoupling is not possible we have to change the mechanism c) It’s possible recoupling in flight. 62- The position of the right and left inboard flaps are monitored by: a) Feedback position unit b) MFC c) Flaps control unit. 63- Flaps block valve receive hydraulic pressure from: a) Blue hydraulic system b) Green hydraulic system c) Both hydraulic system. 64- An elevator mechanical locking device and an aileron electromechanical locking device is known as: a) Unlocking mechanism b) Locking mechanism c) Gust lock. 65- The hydraulic system has : a) 2 hyd pump b) 1 hyd pump c) 3 hyd pump. 66- Nose wheel steering, flaps, spoilers, propeller brake (rh engine), emergency and parking brake are supply by: a) Blue syst b) Green syst c) Both syst. 67- Landing gear, normal braking are powered by: a) Blue syst b) Green syst c) Both syst. 68- In ON position the cross feed push button is pressed and the cross feed valve is: a) close both hydraulic system are connected b) Open both hydraulic system are connected c) Open both hydraulic system are not connected. 69- This light illuminates blue when the airframe de-icing system is selected ON: a) ICING AOA b) DE-ICING c) FAULT ICING. 70- Ensure acquisition and management of fault signals and generate associated audio and visual warning in relation with the anti-ice alerting system : a) MFC b) Icing sensor c) Non are correct. 71- The airframe de-icing system comprises: a) 4 dual distributor valve b) 3 dual distributor valve c) 5 dual distributor valve. 72- The engine and airframe pneumatic de-icing is controlled and monitored by: a) Anti-ice controller b) MFC c) MPC. 73- The de-icing system has 2 cycles: a) Fast cycle (60 sec),slow cycle (180 sec) b) Fast cycle (60 sec),slow cycle (108 sec) c) Fast cycle (60 min),slow cycle (180 sec). 74- ATR landing gear is a retractable tricycle , fuselage mounted type and is: a) it is electrically controlled and hydraulically operated b) it is electrically actuated and hydraulically operated c) it is electrically controlled and hydraulically actuated. 75- the landing gear position detection and indications consist of 2 independent system: a) main instrument panel ( managed by MFC module 1A), overhead panel (managed by the MFC module 2B) b) main instrument panel ( managed by MFC module 1A), overhead panel (managed by the MFC module 2A) c) main instrument panel ( managed by MFC module 1B), overhead panel (managed by the MFC module. 76- bleed air protection system are: a) overheat, overpressure, air leak b) overheat, low pressure, air leak c) low pressure, air leak. 77- the air leak detection system consists of : a) 2 single loops, one for each engine, a control unit, and an indicating system b) 2 single loops, one for each engine, a control unit, and an indicating system c) 4 single loops, one for each engine, a control unit, and an indicating system. 78- ATPCS arming condition are the following: a) ATPCS ARM pushbutton is press in, PWR MGT selector to TO position, power lever 1+2 >49%,torque indicators>46% b) ATPCS ARM pushbutton is press in, PWR MGT selector to CL position, power lever 1+2 >49%,torque indicators>46% c) ATPCS ARM pushbutton is press out, PWR MGT selector to TO position, power lever 1+2 >49%,torque indicators>46%. 79- This component compares the sensed propeller RPM to the governing RPM, calculates a pitch change direction rate to correct the RPM error: a) PEC b) AFU c) EEC. 80- Loss of propeller control by one PEC channel is indicated by illumination of a) SGL CH light b) FAULT light c) Non are correct. 81- Is an electronic box located in the electronic bay that provides the interface between the PEC and flight compartment a) AFU b) MFC c) PIU. 82. Which hydraulic system provides brake propeller at a pressure of 3000 psi: a. Blue system b. Green system c. Both system. 83. The fuel flow supplied by the feeder jet pump is sufficient to maintain the feeder tank full in all flight configurations. a. V b. F. 84. In the event of failure of the opposite engine feed system, the jet pump supplies both engines during all flight phases A. V . B. F. 85. The pump may be removed without emptying the fuel tank. a. V. b. F. 86. 28VAC electric pump installed in each feeder tank supplies fuel to the engine during starting. It also serves to supply the engine throughout the flight envelope, in the event of feed jet pump failure or a restart in emergency. a. V. b. F. 87. The refuel/defuel coupling for refueling under pressure is located on the left wing leading edge. a. V. b. F. 88. REFUELING panel located in the right landing gear fairing. a. V . b. F. 89. Gravity refueling facilities are provided by overwing refueling caps; one per half wing a. V b. F. 90.The left and right fuel feed systems are interconnected by a crossfeed line comprising a dual motor solenoid valve. a. V b. F. 91. The engine feed system can be isolated by means of a single motor fuel LP valve a. V b. F. 92. The fuel distribution system is divided into four sub-systems: A. Engine feed system, B. Crossfeed system, C. LP fuel fire shut off control, D. Refuel/defuel system. a. V b. F. 93. A high level detection system doubles the safety offered by the indicator in case of overfilling, by closing the a. V b. F. 94. The system also serves for defueling of the tanks by suction. a. V b. F. 95. A fuel shut off system which serves to isolate the engine from the feed line is installed between the tank outlet and the associated engine. a. V b. F. 96. The crew alerting computer is comprised of 2 independent units • A digital unit for processing of the AMBER cautions and for redundant processing of the RED warnings. • A hardwired logic unit for processing of the RED warnings. Each unit acquires and generates its own alerts. a. V b. F. 97. The clock has An internal battery provides endurance of 25 days max: a. V b. F. 98. Main function of FDAU of is acquiring mandatory parameters and formatting them into two ARINC (Aeronautical Radio Incorporation) messages, one for the SSFDR (Solid State Flight Data Recorder). a. V b. F. 99. The SSFDR stores the information’s sent to it by the FDAU (via the ARINC 573 bus) on digital flash memories. a. V b. F. 100. The DFDR records on magnetic tape data received from the FDAU. a. V b. F. |
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