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TEST BORRADO, QUIZÁS LE INTERESEC750

COMENTARIOS ESTADÍSTICAS RÉCORDS
REALIZAR TEST
Título del test:
C750

Descripción:
banco de preguntas

Autor:
AVATAR

Fecha de Creación:
17/10/2017

Categoría:
Personal

Número preguntas: 100
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Temario:
1. The microswitch that signals the NOSE DOOR OPEN L–R CAS message is located: A. At the cam key lock B. At the mechanical latches C. At the safety latch D. On the locking pin .
2. The emergency over-wing exit: A. Is not monitored by a CAS message B. Can be removed from inside or outside of the aircraft C. Can be removed from inside the aircraft only D. Is the only exit available for emergency evacuation .
3. Which publication must be immediately available to the flight crew: A. The FAA-approved AFM B. The CE-750 Operating Manual C. The FlightSafety International Pilot Train
ing Manual D. The FAA-approved CE-750 Weight & Balance Manual .
4. During initial power up on the ground with both batteries connected, if just the left battery switch is placed on, how many buses are powered? (Conditions assume that the avionics button is OFF, the BUS TIE is open, and L ELEC relay is in its normal closed position and indicating NORM for ground operations). A. Left buses(left hot battery bus. Left emergency bus, left main bus) and right hot battery bus. B. Both hot-battery buses, left and right emergency/DC power buses, and left and right main generator buses but none of the avionics buses. C. Only the hot battery buses are powered. D. Both hot battery buses and both emergency/ DC-power buses but no main DC buses. .
5. In flight during cruise at FL430, what are the consequences of losing the left generator ( DC GEN OFF L CAS message)? A. Loss of the left main DC system will occur until the pilot selects BUS TIE to CLOSED. B. The right generator automatically powers all buses and keeps both batteries charged. C. The right generator automatically powers all main DC buses and keeps the right battery charged. The left battery is not being charged and is powering the left emergency bus. D. The right generator is powering the right main DC bus and is keeping the right battery charged. The left battery is not being charged and is powering the left emergency bus and the left main DC bus. .
6. During the APU start sequence, power into the APU starter motor is coming from the: A. Left emergency bus. B. Right emergency bus. C. Left main DC bus. D. Right main DC bus. .
7. If a 28-volt external power unit is connected and supplying power to the DC bus system, what would be the voltage on the right emergency bus if the R ELEC button is indicating EMER? A. 0Volts. B. 22Volts. C. 24Volts. D. 28Volts. .
8. Concerning External power electrical logic, which statement below is NOT correct? A. External power does not share electrical load with any generator. B. External power can share electrical load with the left engine generator. C. External power can share electrical load with right engine generator. D. External power can share electrical load with the APU generator only. .
9. What does it mean if the standby power pack is in the ON position and the amber indicator light next to the STBY PWR switch in the cockpit is illuminated assuming left emergency bus is not powered from TRU or any other source? A. The power pack is receiving a charge from the left main DC bus system. B. The power pack is receiving a charge from the right main DC bus system. C. The power pack is receiving a charge from the left emergency bus system. D. The power pack is being discharged as it powers the standby instrument bus.
10. After a dual generator failure in flight, how much of an amperage load can be put on the TRUs? A. 100 amps B. 200 amps C. 300 amps D. 400 amps .
11. What does the AVAIL indication on the EXT PWR button indicate? A. An external power unit is connected to the airplane and voltage is present. B. An external power unit is connected to the airplane and putting out proper voltage (25.5± 0.5 to 31.5 ± 0.5 VDC). C. The external power unit is connected to the airplane and capable of providing a minimum of 1,000 amps. D. The external power relay is closed and routing 28-volt power to the DC bus system.
12. The correct statement concerning interior lighting is: A. When emergency cabin lighting is ON the amber light beside the EMER LTS switch illuminate B. With the batteries installed and connected the cabin entry lights illuminate if selected on C. The cabin emergency lighting consists of the exit signs, over-wing walkway lights, downwash lights, and aft partition lighting D. Emergency cockpit lighting consists of one cockpit panel flood lights and auxiliary lights .
13. The cabin entry lights button: A. Is powered by the main DC electrical 
system B. Is powered by right battery bus and has a timer C. Is powered by the left EMER bus D. Does not discharges the aircraft batteries if left on .
14. Selecting the PAX SAFETY (with the NO SMOKING option) button illuminates the: A. Seat belt and nosmoking icons and external emergency egress lights B. No smoking icons, pathway lighting, cabin and external emergency lights C. Seat belt icon, cabin/exterior emergency lights, and raises the window shades D. No smoking icons, all exit signs, and selected internal and external lights .
15. Which of the following is true regarding the cabin emergency lighting system? A. The left and right battery buses power the cabin emergency lights. B. With the EMER LTS switch ARMED, the cabin emergency lighting illuminates automatically upon the loss of main DC power, a 5G impact, or with the PAX SAFETY button selected ON. C. The cabin emergency lights include all seat/table lights, wash lights, and emergency exit signs. D. The cabin emergency lights are powered from the lead-acid battery in the nose compartment. .
16. With batteries installed and connected, but no power turned on in the cockpit, the following items are powered: A. Cabin entry lighting, cockpit panel flood lights, and APU service panel lights B. Tailcone service lighting, cabin entry lights, and baggage compartment lights C. Cockpit flood lighting, baggage compartment lighting, and tailcone service lights D. APU service panel, cabin entry lights, and the hydraulic volume gauge in the hydraulic access panel .
17. System test can be accessed through: A. The Aircraft Systems > System Test Control page B. The Aircraft Systems > Propulsion page C. The Utilities > Setup page D. EIS display on the MFD .
18. CAS messages are displayed on: A. The MFD B. The GTCs C. The left PFD only D. The left and right PFDs .
19. CAS messages can be scrolled: A. Using the CCD B. Only if amber or white C. Using the up/down arrows on the GTC 
PFD home page D. Off of the display and cannot be retrieved .
20. Autotest results can be viewed: A. On the CAS message window B. When the results are automatically dis- played on the PFD C. By selecting the Aircraft systems > Synoptics summary D. When the results are automatically displayed on the MFD .
21. Red CAS messages: A. Flash inverse video red for 5 seconds, and then automatically cancel B. Flash inverse video red until acknowledged (reset) with a MASTER WARN- ING buttons C. Flash inverse video red until acknowledged (reset) with a MASTER CAUTION button D. Activates a single chime when illuminated.
22. Amber CAS messages: A. Flash standard video amber until acknowledged (reset) with a MASTER CAUTION button B. Flash inverse video amber and illuminate the steady amber MASTER CAUTION lights C. Flash inverse video amber until acknowledged (reset) with a MASTER WARN- ING button D. Are fixed and cannot be scrolled off the CAS message area.
23. Which of the following is true regarding engine shutdown inhibit (ESDI)? A. ESDI is activated when the respective engine has been shut down by pilot action B. A white ENGINE SHUTDOWN message activates the ESDI. C. During engine start, ESDI is deactivated when the engine reaches idle D. All of the above are correct. .
24. What is true concerning White CAS messages: A. When a white CAS message displays, it appears in a steady ON state. B. When a white CAS message displays, it appears with flashing inverse video for 5 seconds then reverts to a steady ON state. C. White message require immediate pilot action D. New white messages appear at the bottom of the message stack on the PFD.
25. During which operations should the fuel gravity cross-flow valve be closed? A. Ground operations B. Crossfeed operations C. Fuel balancing operations D. If a wing tank is over-full (fuel in the surge 
tank.
26. In order to fill the center tank when SPPR is not available: A. There must be fuel in the right wing tank B. Center gravity fill valve must be opened manually C. Both A and B D. Center gravity fill valve must be opened electrically .
27. The FUEL DOOR OPEN CAS message indicates: A. SPPR access door is open B. SPPR access door is not locked C. Over wing fill caps are open D. All the above .
28. LH TANK position is selected using the crossfeed knob. What effect on tank quantities would occur under the following conditions: left wing 3,400 pounds; right wing 3,100 pounds; center tank 2,000 pounds? A. The left tank quantity increases and the center tank remains at 2,000. B. The right tank quantity increases and the center tank remains at 2,000. C. The center tank quantity decreases. D. The left tank and the center tank quantities decrease. .
29. Maximum takeoff fuel imbalance is: A. 200lb B. 400 lb C. 500 lb D. 800 lb .
30. The engines pull fuel from which tank? A. Forward center tank B. Respective wing hopper tank via the respective wing tank C. Vent surge tank D. Aft center tank .
31. Fuel for APU operations is taken from: A. Left wing tank only B. Right wing tank only C. Both wing-tanks simultaneously D. Left tank but can also be taken from the 
right tank, if crossfeed is selected .
32. Bleed Air from the APU is used for: A. Engine Start B. Air Conditioning/Pressurization C. Service Air D. All of the above .
33. APU bleed air can be used for anti-ice on the ground only. 
 A. True B. False .
34. Maximum operating altitude of the APU is: A. 30,000feet B. 35,000 feet C. 41,000 feet D. 31,000 feet .
35. The ECU will automatically shutdown the APU and the APU Control PCB fires the bottle if a fire is detected. 
 A. True B. False .
36. Fuel for the APU normally comes form which source? A. Rightwing B. Left hopper via the left wing tank C. Vent surge tank D. Center fairing tank .
37. Minimum battery voltage for APU start is? A. 23VDC B. 24 VDC C. 28 VDC D. 21 VDC .
38. Fuel for the APU can come from the right hopper tank by use of the crossfeed selector knob. 
A. True B. False .
39. The APU provides:
 A. DC electrical power, hydraulic power, and conditioned bleed air B. Conditioned bleed air for ground operations and AC electrical power C. DC electrical power and bleed air D. Both DC and AC electrical power and service bleed air.
40. What is the difference between the and the ENGINEFAILED L CAS messages?
 A.ENG SHUTDOWN is a ground-only message B.ENGINE FAILED is an inflight-only message C.ENG SHUTDOWN indicates a FADEC initiated shutdown; ENG FAILED indicates other causes D. Throttle lever angle (TLA) position deter- mines the message .
41. What does it indicate when a blue target thrust bug turns amber? A. The two FADECs for that engine differ in terms of their N1 calculations for the TLA. B. The FADEC is using reversionary N1 logic for thrust calculations. C. The same FADEC, which is in control of the fuel metering, is also setting the max thrust target bug. D. The max thrust target bug has failed (unreliable indication).
42. What sources of electrical power can provide ignition excitation? A. Aircraft DC generator power B. Battery power and emergency bus C. PMA D. Standby battery pack .
43. What sources of electrical power can power the FADECs? A. Aircraft DC generator power B. Battery power and emergency bus C. PMA D. All the above .
44. During a cold weather start, the oil pressure has risen to 106 psi (above the red line). What is the recommended procedure? A. Shut down the engine B. Limit N1 to 40% until pressure is 105 psi or less C. Limit TLA to idle until pressure is back in the green D. There are no current recommended procedures for cold weather engine starts .
45. The CHIP DETECT CAS message indicates that: A. Metal particles are clogging up the oil filter B. Metal particles have entered the oil supply tank C. Metal particles have been trapped in one of the pump pressure output lines D. Metal particles are clogging up the fuel filter.
46. FADEC electrically shutsoff fuel to the engine by: A. Closing the MMV B. Closing the LSOV, shutting off fuel C. Closing the engine firewall shutoff valve D. Terminating fuel to the CVG actuator .
47. The ENG TR SW FAULT L CAS message indicates that: A. FADEC has commanded idle fuel schedule for the left engine due to an in-flight thrust reverser deployment B. Left thrust reverser has deployed but the FADEC did not command idle fuel schedule for the left engine C. FADEC will not be able to command idle fuel schedule for the left engine if there is an in-flight TR deployment D. Left thrust reverser is inoperative .
48. What condition or conditions will cause the FADEC to automatically shut off fuel to an engine? A. ExceedingN2of101% B. Exceeding ITT of 888°C C. N2 RPM at 54% or less D. N2 RPM at 63% or less .
49. What condition or conditions cause the FADEC to meter fuel back without shutting down the engine? A. ITTexceeding745°Cormore B. ITT exceeding 600° or more during start C. N1 exceeding 93.2% or N2 exceeding 
102.6% D. All the above .
50. What is the difference between the ENG VIBRATION L and the ENG VIBRATION L CAS messages?
 A. The amber indicates N2 vibration while the red indicates N1 vibration. B. The amber indicates either N1 or N2 vibra
tion is excessive; the red indicates that both are excessive. C. The amber indicates impending excessive vibration; the red indicates actual excessive vibration. D. The amber indicates excessive vibration for N1 and/or N2; the red indicates that the vibration level has gotten worse. .
51. On the ground, the APU FIRE DETECT FAIL CAS message is displayed. Under this condition, which of the following is true? A. The APU fire loop is failed B. The APU fire button will not illuminate during the APU fire test C. The APU should not be started D. All the above .
52. Regarding an initial APU fire condition: A. A flashing, APU FIRE CAS message is 
displayed and “APU FIRE” aural warning B. Both MASTER WARNING buttons flash C. Steady red APU FIRE button illuminates 
on the APU control panel D. All the above .
53. Regarding a right engine fire condition: A. Red RH ENG FIRE PUSH button on the 
upper instrument panel illuminates B. Special, fire bell sounds C. Because the R ENG FIRE button on the 
upper instrument panel illuminates, the CAS messages and MASTER WARNING buttons are inhibited D. White BOTTLE 1 and 2 ARMED PUSH lights also illuminate when the R ENG FIRE light comes on .
54. On the ground, with neither engine running and DC power connected, pushing a non illuminated R ENG FIRE button, A. Does not close the right fuel or hydraulic firewall shutoff valves B. Does not arm either fire bottle C. Arms bottle 2 (white BOTTLE 2 ARMED PUSH button illuminates) but not bottle 1 D. Electrically closes the right hydraulic/ fuel firewall SOVs and arms both bottles .
55. If a baggage fire exists: A. BAGGAGE SMOKE CAS message 
illuminates B. Air and heat into the baggage compartment area is automatically closed off C. Fire-extinguishing agent can be discharged into the baggage compartment from the cockpit D. Pilots must isolate the baggage compartment by selecting the PAC BLEED SELECT switch to LP .
56. The fire extinguishing agent for an engine fire is discharged into the compressor section of the engine. A. TRUE B. FALSE.
57. A bleed air leak from an engine could cause all of the alerts associated with an engine fire. A. TRUE B. FALSE.
58. During the cockpit preparation, the batteries are turned on and the pilot observes both BOTTLE 1 and BOTTLE 2 ARMED PUSH white lights illuminated on the upper panel. A. Fire Bottles are going through an auto- mated self-test B. Pilot should push the white BOTTLE ARMED lights to extinguish the lights C. Pilot should push the red ENG FIRE PUSH button(s) to extinguish the BOT- TLE ARMED lights D. Illuminated BOTTLE ARMED lights indicate low extinguisher bottle pressure and the bottles should be serviced.
59. What happens when the pilot pushes an illuminated LH ENG FIRE PUSH button? A. Fuel is shutoff to the left engine B. Hydraulic fluid is allowed to the A hydraulic pump for normal A system pressure C. PAC ISOLATION VALVE automatically opens allowing the RH bleed air to feed both PACs
 D. Just the left engine fire bottle is armed to discharge into the left engine.
60. On the ground, with T/O thrust, LP Air is used for: A. Service Air B. PACs C. Anti-Ice D. All of the above .
61. Which of the following systems do not use APU Bleed Air: A. Engine Starting B. Air-Conditioning C. Pressurization D. Anti-Ice .
62. HP bleed air supply line from the engine is monitored for: A. Excessive volume B. Excessive moisture C. Low Pressure D. Overpressure and excessive temperature .
63. With the isolation valve closed, which of the following operations are still available? A. LH-RH cross engine starts B. RH-LH cross engine starts C. Sending RH engine bleed air to the cockpit 
PAC D. Sending LH bleed air to the cabin PAC .
64. What happens when an HP/LP Crossover valve opens? A. Associated PAC receives HP Air CAS message is displayed B. LP Regulator valve is controlling the pressure of the air to the PACs to approximately 45 psi C. All of the above .
65. With the Engine Bleed Air knob in LP, what occurs? A. The PAC HP VALVE OPEN CAS message is displayed B. Loss of the use of the cockpit PAC C. Closing the associated HP firewall shutoff valve D. Closing the associated HP/LP crossover valve .
66. Service Air is supplied by engine bleed air, APU bleed air, or when an external air cart is delivering air pressure. A. True B. False.
67. LP/HP Bleed sources are: A. 10th and 15th Stage B. 12 and 16th Stage C. 8th and 14th Stage D. 1st and 2nd Stage .
68. APU and Ground Air Cart pressure requirements for engine starts are: A. 25 and 35psi B. 20 and 40 psi C. 25 and 30 psi D. 20 and 30 psi .
69. The minimum holding speed when holding in icing conditions with the slats up is: A. 180knots B. 200 knots C. 210 knots D. 220 knots .
70. When the SLATS anti-ice buttons are turned on (with ENGINE/STAB buttons ON): A.Wing fixed leading edge is also heated B. Wing cuffs are also heated C. Crossover valve opens D. Both A and B .
71. The WINGXOVER valve: A. Allows either engine to provide bleed air 
to both engine inlet ducts B. Allows either engine to provide bleed air to both slats C. Opens automatically when the slat anti- icing system is turned on D. Connects the left and right PAC bleed air lines .
72. Either engine can provide air to the opposite horizontal stabilizer with the crossover valve closed. A. True B. False .
73. Ice detect stalk lights are turned on: A. Automatically, when the wing inspection 
lights are turned on B. Automatically, when the windshield anti- ice system is turned on C. When the L BATT or EXT PWR buttons are ON D. Both A and B .
74. The PAC receives bleed air from 8th stage or L/P air. 
 A. True B. False .
75. With the ISOLVALVE closed, the left engine supplies bleed air to the cockpit PAC as the right engine supplies bleed air to the cabin PAC. 
 A. True B. False .
76. When the PAC knob is in HI, what amount of air volume is allowed to pass into the PAC? A. 10lb/min B. 22 lb/min C. 13 lb/min D. 16 lb/min .
77. When is HP not approved for use? A. Takeoff and Landing B. When aircraft altitude is above 20,000 feet and only one source of engine bleed air is available C. PAC HI above FL430 D. All of the above .
78. No manual control backup is available with the Garmin G5000 system. 
 A. True B. False .
79. If the PAC O’TEMP CABIN CAS message is displayed: A. The cabin PAC bleed valve automatically closes. B. Once the PAC cools, air is automatically restored with no crew action required. C. PAC BLEED SEL knob should be placed to LP. D. Right ENG BLD AIR switch should be placed off. .
80. If the cabin PAC is being used but the cockpit PAC is off or inoperative: A. Conditioned, warm air is still available for the cockpit air distribution system B. PAC isolation valve must be open to restore air to the cockpit C. Cockpit air distribution system is without conditioned, warm air D. Right side of the aircraft is deprived of cold air .
81. What should occur if the cabin PAC water separator freezes during the flight? A. Flow of cold air to cabin is stopped B. Bypass line allows cold air to continue to flow to the cabin C. Amber CAS message is displayed D. Both A and C are correct .
82. Maximum takeoff weight is: A. 36.600 lb B. 27.000 lb C. 38.600 lb.
83. Maximum Landing weight is: A. 32.000 lb B. 35.200lb C. 27.000 lb.
84. Main fuel system total capacity: A. 7.000 lb B. 10.500 lb C. 13.000 lb.
85. Max Asymmetric Fuel: A. 500 lb B. 200 lb C. 400 lb.
86. Emer Asymmetric Fuel: A. 800 lb B. 600 lb C. 400 lb D. 2.000 lb.
87. Minimum wing fuel per tank for T/O: A. 600 lb B. 500 lb C. 800 lb D. 1000.
88. Max Baggage Compartment load: A. 2.000 lb B. 700 lb C. 1.000 lb.
89. Max Tail Wind Component: A.15 B. 10 C. 8.
90. Mmo: A. 0.915 B. 0.95 C. 0.935.
91. Maximum tire Ground Speed: A. 165kts B. 178kts C. 182kts.
92. Will antiskid be available in the unlikely event of a total electrical failure? A. Yes B. No .
93. Where does the landing gear control get its power supply from? A. Emergency Bus B. Main Bus C. L Main Bus D. APU Transfer Bus .
94. What is indicated by the amber hash marks on the gear indicator located on the EIS? A. Gear is in transit B. Gear is in transit too long C. That particular landing gear is stuck D. Landing gear handle is not down and 
locked .
95. Can the gear handle be moved to the UP position while the aircraft is on the ground? A. Yes B. No .
96. The PARK BRAKE LOW PRESS CAS message is displayed with pressure less than: A. 1,200psi B. 1,500 psi C. 2,000 psi D. 2,300 psi .
97. Rudder pedal inputs allow ____ of steering commands left or right. A. 4° B. 7°±1° C. 20° D. 70° .
98. Can the gear handle be raised with weight off wheels and the nose gear NOT centered? A. Yes B. No .
99. In the event of A system hydraulic failure, will nose wheel steering be available after landing? A. Yes B. No.
100 . If both engine driven hydraulic pumps have failed, is antiskid still available? A. Yes B. No.
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