TEST BORRADO, QUIZÁS LE INTERESE:
BANCO DE PREGUNTAS EQUIPO Y-12E SATENA
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Título del Test:
BANCO DE PREGUNTAS EQUIPO Y-12E SATENA Descripción: TEST BOOK AVIC Autor: MAURICIO ALEJANDRO JARAMILLO OSPINA OTROS TESTS DEL AUTOR Fecha de Creación: 18/12/2013 Categoría: Test de conducir Número Preguntas: 80 |
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If you want to check the voltage of the GPU in the cockpit, the control switch of the voltmeter shall be set at ____ position battery left engine right engine. When the voltage of the battery is lower than ____, caption "BAT. DISCH" will be illuminated 24V 25.5V 28V. The illuminated green GPU indicator lights shows that____ GPU is supplying electricity to the network of the aircraft the polarity of the GPU plug is correctly plugged in the GPU receptacle the polarity of the GPU plug is connected in reverse. When de "BAT.T" warning light is illuminated ____ shall be switched OFF first generator switch battery/GPU control switch bus-tie switch. When the voltage of the generator is ____ volts higher than that of the bus bar, and the generator switch is set at "ON" position, the generator can be put in the network for electrical power supply o 0.3~0.5 5. Output voltage can be regulated by ___ generator generator control box low voltage detector. One of the following statements is true, for Y12 Aircraft DC power supply system ___ When one of the generators is out, the other generator will supply power together with battery to the aircraft electrical power supply network When the aircraft is supplied by the GPU, the voltage of the generator must be zero The main contactor operation is cotrolled by corresponding control box of the generating system. There are ____ temperature sensors for the battery 1 2 3. The generating system control box (25P / 26P ) in installed____ between frame No7. and 8 of the aiframe inside the LH & RH engine compartments on the overhead power distribution control box. The operation power supply for edge-plate lighting is ____ 26V/400Hz 115V/400Hz 28V DC. The roof light switch for the front luggage hold is installed ____ on the web of from No.3 on RH contro panel in the overhead power distribution control box 4α. The passanger call indicator lights is of ___ color red amber blue. To check the reading lights in the passanger cabin, the reading lights control switch must be put at ____ position, then al reading lights will be illuminated ON TEST both A or B. Landing lights is installed on ____ leading edge of LH/RH stub-wing leading edge of LH/RH wing ventral fuselaje. There are ____ gate circuits inside the master alarm control box 5 17 24. Master alarm system consist of ____ master warning lights and one master alarm control box. 1 2 3. When a red caption on the warning panel illuminated, the two master alarms are ___ not flashing flashing on the failure side only all flashing. Press the "TEST" button on the warning panel, then ____ All indicator blocks on the warning panel will be illuminated All indicators windows blocks on the warning panel and signal panel will be iluminated All windows blocks on the signal panel will be illuminated. When the ____ door is not well closed , the door indicator lights illuminates pilot door luggage door any one of the doors. On signal panel, the caption "FLAP DN" in amber illuminated indicates ____ during the flaps down operation mechanical overloading over-limit of the flaps travel over-speed of flap down. The primary control system includes: ______ aileron control system, rudder control system and elevator control system aileron control system, rudder control system and flap control system aileron control system, elevator control system an flap control system. The limit screw of the aileron control system is fitted on ____ central quadrant roller arm bracket. The aileron trim tab cotrol system is used to be controlled by ___ Hydraulic device mechanic device motoreducer. A limiting device of the elevator control system is fitted on the rear quadrant to limit the maximum up and down deflections of the elevator, wich are 25° + 20 up and ______ down respectly 10° +1-0.5 20° +1-0.5 25° + 20. The rudder trim tab control system is used to be controlled by ____ Hydraulic device mechanic device motoreducter. the are three selections positions for flaps, i.e. _____ the flap posicion are indicater by the indicator on central instrument panel 0°, 10° and 20° 0°, 15° and 20° 0°, 10° and 25°. The axis of the strut of nose landing gear tilts ____ forward 15 10 7.5. Charging pressure of the shock absorber strut of nose landing gear is ____ Mpa 0.34 0.47 0.88. When the inner cylinder is compressed over ____mm, the upper and lower teeth parts get disengaged completely 20 30 40. The size of tyre of the nose landing gear is 480x200. The normal operating pressure is ____Mpa 0.34 +/- 0.02 0.47 +/- 0.02 0.88 +/- 0.02. Chargin pressure of shock absorber of the main landing gear is: ____ Mpa 0.47 0.88 3.8. ____ can compensate automatically the wear brake block in the manner of step by step to keep the brake block in an optimum condition The pistons The automatic compensating mechanism The movement disk. When the pressure in either of the accumulator is below ____ Mpa, the relative pressure switch YYF-4C is closed, the electric hydraulic pump operates 7.0+/-0.5 9.5+/-0.5 12+/-0.5. When the presure rises to ___ Mpa, the relative safety valve Y11T-5560-50B is opened to make the pressure drop 9.5 +0.5 0 12 +0.5 0 15 +0.5 0. If the control circuit is in failure and the pressure in normal accumulator drops to ___Mpa the low pressure warning lights is lit; when the pressure increases to be not more than 10Mpa, the warning light goes out 7 0+1 -0.5 9.5 0+1 -0.5 12 0+1 -0.5. The color of the low pressure warning is ____ red yellow amber. The normal brake is fulfilled by ____ YS-127 YS-117B YS-106. The normal braking pressure is provided by ____ A normal accumulator Emergency accumulator Both. The fineness of hydraulic filter is: ____ 10 um 20 um 50 um. The reservoir of the hydraulic system is a no pressure type reservoir with ____ of volume. 2.9 L 4.0 L 4.5 L. Y-12IV Aircraft fuel tank is of ____ type Bladder Integral fuel cell External fuel cell. Y-12IV Aircraft fuel system: the two fuel tanks are located respectively on LH wing and RH wing between rib number 6 – 17 6 – 16 7 – 17. Y-12IV Aircraft fuel system: the total capacity of LH & RH fuel tank is ____ liters 1620 1630 1640. The volumetric capacity of the feeder of the fuel tank is ____ liters 180 190 200. On the lower skin structure of the feeder tank, between the front spar and rear spar, along with the stringer, there riveted a bulkhead of ____ mm height, to separate the bottom of the feeder tank into two small cells 56 65 66. The fuel filter is of ____ micro 30 40 50. Y12IV Aircraft fuel booster pumps are installed ____ on the fuel feeding pipe lines inside the fuel tanks in the luggage bay. The vacuum valve for the fuel tank is located on the ____ point of the sealed rib web plate to the outer extremity of the fuel tank. Lowest Middle Highest. Cross feed of the fuel will be needed only when one engine is inoperative or the fuel quantity difference between LH and RH fuel tank is of ____ 150 Kg 100 Kg 50 Kg. The “L” & “R” pointers of the cross-pointer meter indicate respectively the fuel quantity of the LH and RH fuel tanks. The outer scale indicates the ____ , and the inner scale indicates the ____ total quantity in the fuel tank, fuel quantity in the fedder tank fuel quantity in the feeder tank, total quantity in the fuel tank total quantity in the fuel tank, consumable fuel quantity. Each engine compartment has ____ fire detectors 4 5 6. The fire extinguisher is charged with pressurized nitrogen, and the charging pressure shall be _____ MPa at 15°C 4.0 4.2 4.4. The sphere extinguisher pressure drops to ____ or more of the rated value, the extinguisher must be removed and charged with nitrogen. 6% 8% 10%. When the generator (LH or RH) temperature rises to ____ °C and both related over temperature detectors are cut off, the red caption “L GEN T” or “R GEN T” will be illuminated, and the master alarm will flashing at the same time. 200+20 200+30 200+40. The “FAIL/FIRE” test switch on the instrument panel is set at “FIRE” position, the ____ color fire warning indicator light on the instrument panel shall be illuminated red amber green. Cockpit heating system is used to keep the normal temperature inside the cockpit in winter time, and is also used for heating and demisting of ____ windshield instrument panel console. Cockpit heating system uses ____ air introduced from engine compressor via ejector, and it will be mixed with air under the cabin floor for the cockpit heating. P1 P2 P3. The given value on the scale of the WTH-3 air conditions in the cockpit is ____ 10-20°C 16-26°C 15-25°C. During engine start, take off and landing, ____ to use heating system It is not allowed It is allowed It is allowed for a short time. When surrounding ambient temperature is higher than the temperature inside cabin or during the flight in rain, the use of cabin ventilation system is ____ allowed inadvisable of nothing important. The most proper thickness of ice layer for the operation of wing/empennage de-icing system is ____ mm. 10 13 18. When the wing/empennage de-icing system is in operation, Ng shall be greater than ____ 70% 75% 80%. The maximum thikness of ice layer for the operation of wing/empennage de-icing system is ____ mm. 20 25 30. The thermal resistance in the anti-icing boot on the air intake lips operates together with temperature control box to ensure the anti-icing boot a heating temperature of ____ 60 +- 15 65 +- 15 65 +- 10. Air pressure detector probe anti-icing check: after switching on the heating, touch with hand the probe and feel warm to switch off the heating. The heating time shall be not greater tan ____ minutes. 1 2 3. When the alcohol tank is topped to 11.5 L, this quantity can be used for windshield anti-icing protection for ____ min. 40 45 50. During the flight under icing condition, pilot switch "ON" the propeller de-icing system, the resistance wire will be energized in turn like right-outer, right-inner, left-outer and left-inner; the heating duration is ____ seconds each time, an will cycle once every 1.1 min. 24 34 44. PT6A-27 engine on Y-12 aircraft is limited to ____ SHP 580 660 620. One of the following sentences is true: ____ Once the engine is started, the FCU operates to control the fuel flow The FCU starts to control the fuel flow only when the Ng is greater or equal to 12% The fuel flow is controlled by both the pressure difference before and after the constant pressure valve and the position of the valve pin (The opening of the metering valve). One of the following sentences is true: ____ In flight, power rating is controlled via propeller lever In flight, power is automatically regulated by the fuel governor In flight, power is controlled with fuel condition lever. One of the following sentences is true: ____ Propeller reverse is realized by pulling rearward the propeller lever Propeller reverse is realized by pulling rearward the power lever Propeller reverse is realized by pulling rearward the condition lever. One of the following sentences is true: ____ PT6A-27 is of rear exhaust PT6A-27 is of front exhaust PT6A-27 is of center exhaust. One of the following sentences is true: ____ PT6A-27 is of single rear exhaust duct PT6A-27 is of double rear exhaust ducts PT6A-27 is of annular rear exhaust ducts. The function of the oil/air separator is ____ to separate air from oil to expel air in the oil to improve the cooling of the engine to expel the air in the oil to keep a constant oil temperature in the oil reservoir. One of the following sentences is true: ____ Over speed governing is realized by regulating the aerodynamic component Px of the FCU Over speed governing is realized by regulating the pitch angle of the propeller Over speed governing is realized by regulating the position of the propeller lever. One of the following sentences is true: ____ Propeller speed is of linear relation with free turbine speed Propeller speed is of linear relation with the speed of gas generator The propeller speed is constant, so there is no relation with the free turbine or gas generator speed. The principal power supply for Y-12 is from ____ Two DC starter-generator Battery GPU. GPU (Ground Power unit) is not allowed for the electrical power supply of ____ Ground starting Battery charging Ground checks. Switch off the master switch (49P) of the electrical power system of the Y12 Aircraft, bus bar ____ is still energized for electrical power supply PP5 PP7 PP1 and PP2. The amperemeter in DC power system can measure the load current of ____ Generator only Left generator, Right generator and battery Generators, battery and GPU. |
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