Test atr42-2

TEST BORRADO, QUIZÁS LE INTERESE: ATR42-2

COMENTARIOS	ESTADÍSTICAS	RÉCORDS

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Título del Test:
ATR42-2

Descripción:
ATR42-2

Autor:
ATR42
OTROS TESTS DEL AUTOR

Fecha de Creación:
23/01/2014

Categoría: Test de conducir

Número Preguntas: 50

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Temario:

51. ON THE LANDING GEAR PANEL, “UNLK” LIGHT ILLUMINATES TO INDICATE : A. Uplock device has failed B. Downlock device has failed C. Respective gear not seen locked in lever selected position, or on ground, uplock box not in the right position.
52. WHEN “ F” LIGHT ILLUMINATES ON ANTISKID PANEL : A. Antiskid is lost on associated wheel B. Antiskid system is not supplied C. Antiskid electrical supply is in stand-by.
53. TO CONSIDER THE GEAR DOWN, 3 GREEN LIGHT MUST BE ILLUMINATED ON : A. Both. Overhead and Center Instrument Panel B. Either, Overhead or Center Instrument Panel C. One panel only. The Center Instrument Panel.
54. ROLL CONTROL OPERATION IS ACHIEVED : A. Mechanically from the ailerons, hydraulically from the spoilers B. Mechanically from the spoilers, hydraulically from the ailerons C. Mechanically from the ailerons and spoilers.
55. ROLL TRIM CONTROL IS PERFORMED USING : A. Only right aileron TAB B. Only left aileron TAB C. Both. Left and right aileron TAB.
56. IF ONE CONTROL COLUMN IS JAMMED : A. Pitch uncoupling allows the other channel to be operated B. Pitch uncoupling allows the other channel to be operated before flaps retraction C. Pitch uncoupling allows the other channel to be operated after flaps retraction.
57. THE TWO AHRS (ATTITUDE AND HEADING REFERENCE SYSTEM) PROVIDE THE FOLLOWING DATA : A. Pitch, roll, heading and groundspeed B. Pitch, roll and heading C. Pitch, roll, heading, groundspeed and time to go.
58. THE TWO AHRS START THEIR ALIGNMENT PERIOD (3 MINUTES): A. Automatically provided a DC External Power is connected or aircraft batteries selected “ON” C. After first engine start and AHRS 1 and 2 selected “ON”.
59. WHEN THE “ERECTED/FAIL” WARNING ILLUMINATES “ON” ONE AHRS : A. The crew must switch “off” this equipment, and perform a switching to the remaining system B. The crew must switch “OFF” this equipment for 5 minutes period, then start a new alignment process C. The crew must press this switch during 15 seconds, while maintaining the aircraft on non-accelerated flight( straight&level) for gyro erection.
60. HOW THE GPWS “GLIDE SLOPE” WARNING CAN BE INHIBITED? A. Anytime by selecting the GPWS Switch to “Flap Override” B. Below 1000 feet/AGL by pressing one of the GPWS/GS P/B C. By selecting 30° flaps and the gear down.
61. THE WEATHER RADAR DETECTION IS DISPLAYED ON : A. The EHSI selected to full (rose) mode only B. The EHSI selected to arc mode only C. The EHSI either to full or arc mode.
62. AUTOMATIC DISCONNECTION OF AP IS OBTAINED IF: 62. AUTOMATIC DISCONNECTION OF AP IS OBTAINED IF: B. A 30 da N effort is applied on the pedals C. A+B.
63. ‘AIL LOCK’ AMBAR LOCAL LIGHT AND ASSOCIATED MASTER CAUTION WILL BE ON WHEN: A. Both ailerons lock actuators are engaged B. Gust lock not engaged C. Both ailerons lock actuators are not engaged D. In case of discrepancy between any actuator and any control switch.
64. TO PERFORM PEC-EEC TRIMING IS REQUIRE ENGINES RUNNING AT : A. MAX RPM B. 80% RTO C. MAX POWER B. MAX RPM B. 80% RTO C. MAX POWER D. Not required engines running.
65. DC EMER BUS SECT 1 IS DIRECTLY SUPPLIED BY A. DC emer and DC battery bus. B. DC emer bus only. C. DC stanby bus only.
66. ENGINES POWER RTO IS: a- 2400 SHP b- 2100 SHP c- 2750 SHP d- None one of above mentioned.
67. De-icing sys controls the operation of wing and stabilizers leading edges by: a- Pressure Regulator valves b- Dual distributor valves c- None of above mentioned d- A and b are true.
68 -Fault light comes on the Bleed pushbutton Switch when? In case of pneumatic leak in the system. There is disagreement between P/B and the Valve In case of electrical failure in the valve. All mentioned above are true.
69. Fuel shut off valves are supplied by. Hot emergency battery bus. DC essential bus. AC 1 main bus d- None of above mentioned.
70. The feeder tank low level is performed by MFC ( bite loaded ) a-False b-True. c-None is true.
71. The purpose of the Propeller 568F is: a-Reduce the noise. b-High power applications. c-B AND C are true. e- None is true.
72. The propeller is six blades Hamilton Sundstrand 568F is a-All compose design. b-Blade retention design for ease removal/installation. c-High simplified pitch change designs mechanism. d-All are true.
73- The propeller brake functions are monitored by MFC a- True b- False.
74-The Propeller automatic speed control and synchrony phasing system are carried out by: a- PVM b- PCU c- PVM and PCU d- None of above is true.
75- The accessory gear box on engine PW series is driven by? A. LP spool. B. PT Pack spool. C. HP spool by angle driven gear. D. None above is true.
76- Where is located the HP vane ring on PW engine series? a- Between combustion chamber and HP turbine blades airfoils b- Between combustion chamber and HP compressor. c- A and B are true d-None is true.
77- What kind of impeding bypass indicators are installed on oil system on PW127E? a-Electrical b-Electrical-Mechanical c-Mechanical d-None one is true.
78-The fuel system and propeller pitch fault codes are monitored by MFC system. a-False b-True.
79- HP and bleed air shutoff valves control and system monitoring provided by. a- Left system MFC 1A and 1B b- Right system MFC 2A and 2B c- Both are correct. d- None is true.
80-The cross feed on pneumatic system is controlled by? A- MFC 1A b-MFC 2B C- MFC1B D- MFC 2A.
81 – The Blue auxiliary pump is controlled by a-MFC 2B b-MFC 2A c-MFC 1A d. all are true.
82- The landing gear system is controlled by. a-PSEU Computer b- MFC Computers c-Bothe A and B are true d-None one true.
83- The elevator pitch uncoupling system is. a - Mechanical re-clutch system. b - Electrical re-clutch system c - Both are true. d - None is true.
84-Local alerts total independent of CCAS module a.True B. False.
85. FDAU main functions is acquire mandatory parameters, formatting them and send to SSFDR to be stored. True False.
86. How many AFCS computers are used in ATR 42-500 a. one b. two c. none.
87. Autopilot functions are: A. AP, YD and FD B. AP and Auto Thrust C. TCS, GA and Auto Thrust.
88. YD and Roll coordination is a function of MFC A. True B. False.
89. RCAU functions are a. Interphone and radio communications b. PA c. All are correct.
90. Cockpit announcements are give priority over cabin attendant and tape reproducer music via CPS A. True B. False.
91. How many radio altimeters are installed in ATR 42-500 A. one B. two.
92. Which ADC normally supplies data for TAT/SAT/TAS indicator? A. ADC 1 B. ADC 2 C. Either ADC.
93. Lavatory dust bin fire extinguishing is electrical opered. A. True B. False.
94. Where is located the refuel/defuel panel? A. RH main gear fairing B. LH main gear fairing C. Cockpit.
95. The EPC (PEC) Controls A. Propeller Speed Function B. Synchropahsing C .Beta Scheduling D. All of the above.
96. Aircraft ice protection provided by: A. Pneumatic system only B. Electrical system only C. Electrical heating and pneumatic system.
97. MLG Doors are attached by means of: A. Hinges and adjustable rods B. Hydraulic actuators C. Cable linkage.
98. Oil contained in the hub (Barrel) Is: a. For Lubrication b. To Pitch change mechanism c. To drive the propeller into reverse mode.
99. Pushing the EFIS control panel’s the ADI DIM/HD test knob will cause? A. Display cautions and flags on EADI B. Display cautions and flags on EHSI C. Radio Altimeter Shows 100ft D. All are correct.
100. THE T.O INHI ACTION IS CANCELLED? A. Automatically as one gear leg is not locked down and manually by pressing RCL p/b B. Automatically when gear is locked up and by pressing RCL p/b C. Automatically when gear and flaps are up.

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