Quiz
B737
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Questions in this quiz (104)
1
1. Which statement is correct regarding EMER EXIT LIGHT switch positions?- AA. The ARMED position illuminates all emergency lights if AC transfer bus 1 fails.
- BB. The OFF position prevents emergency light system operation if the
airplane electrical power fails or is turned off. - CC. The ON position illuminates only the flight deck emergency lights.
- DD. The ON position illuminates only the emergency lights in the galleys.
22. When squeezed and pulled, the oxygen mask inflation levers :
- AA. activate the oxygen flow yellow cross momentarily as the harness inflates.
- BB. lock the masks in their stowage boxes.
- CC. activate the oxygen and microphone
- DD. deflate the mask harness when the deflation lever is squeezed
33. Servicing of the water system:
- AA. requires DC power from the airplane transfer busses.
- BB. is through an exterior panel located on the bottom right side of the aft fuselage.
- CC. is through an exterior panel located on the top left side of the fuselage.
- DD. is accomplished by gravity filling of the two storage tanks.
44. On the flight deck, where is the flight crew oxygen pressure displayed?
- AA. Behind the Captain's seat on the P-18 panel.
- BB. Behind the First Officer's seat on the P-6 panel.
- CC. At the flight crew oxygen shutoff valve.
- DD. On the flight crew oxygen pressure indicator on the aft overhead panel.
55. At what cabin altitude is the passenger oxygen system automatically activated?
- AA. 12,500 feet.
- BB. 10,000 feet.
- CC. 17,000 feet.
- DD. 14,000 feet.
66. The amber PASS OXY ON light illuminates. What does this indicate?
- AA. The OVERHEAD annunciator light is extinguished on the Master Caution system.
- BB. The passenger oxygen system pressure is low.
- CC. The passenger oxygen quantity is low.
- DD. The passenger oxygen system is activated and masks have dropped.
77. Interior emergency exit lights are located:
- AA. over the entry/service and overwing emergency hatches to indicate the door and hatch exits.
- BB. on the floor to locate carry-on luggage and other valuable items.
- CC. only within the cockpit and galley areas.
- DD. in the lower inboard comer of the stowage bins to illuminate the ceiling.
88. What happens to the signs with the NO SMOKING switch in AUTO?
- AA. The NO SMOKING signs illuminate when the landing gear is retracted
- BB. The NO SMOKING signs illuminate when the landing gear is extended
- CC. The NO SMOKING signs illuminate when the flaps are extended.
- DD. The NO SMOKING signs extinguish when the flaps are retracted.
99. Placing the EMER EXIT LIGHTS switch in the ARMED position:
- AA. iIIuminates the emergency lights at all times.
- BB. activates the emergency light system with APU generator power only.
- CC. illuminates all interior emergency lights if there is a loss of electrical power on AC transfer bus 2.
- DD. illuminates all interior and exterior emergency lights if there is a loss of electrical power on DC bus 1, or if AC power has been turned off.
1010. LOWER CARGO COMPARTMENTS are:
- AA. sealed and unpressurized to allow fresh air circulation.
- BB. designed and constructed to satisfy FAA category class A compartment requirements.
- CC. designed to completely confine a fire without endangering the safety of the airplane or its occupants.
- DD. on the lower left side of the fuselage.
1111. During pilot adjustment, a sight reference indicating proper adjustment includes:
- AA. sight over the control column (in the neutral position) until the top edge of
the outboard display unit is visible. - BB. sight along the upper surface of the glareshield with a small amount of the airplane nose structure visible.
- CC. adjust the fore/aft displacement of the seat until abeam the aft end of window 3.
- DD. the "T" below the outboard display unit is visible.
- AA. sight over the control column (in the neutral position) until the top edge of
1212. With the FASTEN BELTS switch in the AUTO position the FASTEN SEAT BELTS and RETURN TO SEA T signs will:
- AA. be illuminated when the flaps and gear are retracted
- BB. be illuminated when the flaps or gear are extended.
- CC. only be illuminated in flight.
- DD. be extinguished when the flaps and gear are extended
1313. The retractable landing lightsare installed:
- AA. in each wing leading edge.
- BB. in each wing root.
- CC. on each wingtip.
- DD. in the lower airplane fuselage.
1414. An illuminated amber exit annunciation on the overhead panel indicates:
- AA. the related overwing emergency exit is not fully closed and locked or the related flight lock is not engaged, either during takeoff roll or in flight.
- BB. the overwing escape slide is not armed.
- CC. the related overwing emergency exit is closed and locked.
- DD. the related flight lock engaged when commanded locked.
1515. The over-wing emergency exits lock when:
- AA. the airplane air/ground logic indicates that the airplane is on the ground and both thrust levers are at idle, either engine is running, and two of the tour Entry/Service doors are closed.
- BB. the airplane air/ground logic indicates that the airplane is in the air or both thrust levers are advanced, both engines are running, and tour of the tour Entry/Service doors are closed.
- CC. the airplane air/ground logic indicates that the airplane is in the air or both thrust levers are advanced, either engine is running, and three of the tour Entry/Service doors are closed.
- DD. the airplane air/ground logic indicates that the airplane is in the air or at least one thrust levers is advanced, both engines are running, and three of the tour Entry/Service doors are closed.
1616. The lower cargo compartments are fire containment compartments designed and constructed to satisfy Federal Aviation Administration category compartment requirements.
- AA. Class D.
- BB. Class A.
- CC. Class C.
- DD. Class B.
1717. A flight attendant reports that there is a paper fire in the cabin. What extinguisher should be used on the fire?
- AA. Nitrous oxide (N20).
- BB. Water (H20).
- CC. BCF (Halon 1211).
- DD. Carbon dioxide (CO2).
1818. When rotated to the EMERGENCY position, the flight crew oxygen mask emergency/test selector:
- AA. supplies 100% oxygen only at high altitudes.
- BB. supplies 100% oxygen under positive pressure at all cabin altitudes.
- CC. tests the positive pressure supply to the regulator.
- DD. provides a mixture of ambient air with oxygen on demand.
1919. Emergency access to the flight deck from outside the airplane is accomplished:
- AA. through the Captain's or First Officer's number two windows.
- BB. through the First Officer's number two window only.
- CC. through a special emergency hatch.
- DD. through the Captain's number two window only.
2020. The overboard exhaust valve:
- AA. is normally open in flight and exhaust air is diffused to the lining of the forward cargo compartment.
- BB. remains Closed if both pack switches are in high.
- CC. allows for increased ventilation in the smoke removal configuration.
- DD. remains Closed on the ground and in flight with low differential pressure.
2121. What is the position of the isolation valve when the ISOLA TION VALVE switch is in AUTO?
- AA. The isolation valve automatically modulates between open and Closed, depending on pneumatic load.
- BB. It depends on the position of the APU bleed switch
- CC. The isolation valve is always closed.
- DD. Open, if either engine BLEED air or air conditioning PACK switch is positioned OFF.
2222. When making a no engine bleed takeoff and an engine failure occurs, when should the engine bleed air switch be positioned to ON?
- AA. After passing through 2000 feet.
- BB. There is no altitude restriction.
- CC. At not less than 400 feet and prior to 2000 feet.
- DD. When reaching 1500 feet or until obstacle clearance height has been attained.
2323. The maximum cabin differential pressure allowed by the two pressure relief valves is:
- AA. 7.8 psi.
- BB. 9.1 psi.
- CC. 7.1 psi.
- DD. 8.3 psi.
2424. The cabin pressurization panel MANUAL light is illuminated green; what does this light indicate?
- AA. The aircraft is in an off-scheduled descent.
- BB. The pressurization system is operating in the manual mode.
- CC. The manual outflow valve is fixed in the full closed position.
- DD. The pressurization mode selector is in the ALTN position
2525. The bleed air duct pressure indicator:
- AA. is DC operated.
- BB. cannot indicate external air pressure.
- CC. is AC operated.
- DD. indicates both temperature and pressure in the bleed air duct.
2626. The blue RAM DOOR FULL OPEN light illuminates:
- AA. when the ram door is in the full open position.
- BB. when the airplane is not in flight with the packs in AUTO.
- CC. when the airplane is in flight with the packs in HIGH.
- DD. only on the ground.
2727. The amber OFF SCHED DESCENT light illuminates; what does this light indicate?
- AA. The cabin pressure differential exceeds system limitations during aircraft descent.
- BB. The pressurization controller is unable to maintain cabin pressure.
- CC. The pressurization controller has failed and will automatically shift to the alternate mode.
- DD. The airplane has descended before reaching the planned cruise altitude set in the FL T ALT indicator.
2828. What is the normal source of conditioned air for the flight deck ?
- AA. Air from the left pack.
- BB. Both air conditioning packs.
- CC. The mix manifold.
- DD. The right air conditioning pack.
2929. The amber DUAL BLEED light indicates:
- AA. a possible APU back pressure condition and thrust must be limited to idle.
- BB. the APU BLEED switch is OFF.
- CC. the isolation valve has failed in the closed position.
- DD. an overpressure of the left and right bleed air systems.
3030. What systems rely on the bleed air system for operation?
- AA. Engine starting, air conditioning/pressurization, wing and engine thermal anti-ice, hydraulic reservoirs pressurization, and water tank pressurizatio
- BB. APU, engine starting, and air conditioning/pressurization
- CC. Wing anti-ice, APU, and engine starting.
- DD. Air conditioning/pressurization, wing anti-ice, and fuel tanks.
3131. What happens when the wing-body OVHT TEST switch is pushed?
- AA. The precise location of any bleed air duct leak is identified.
- BB. Both of the amber WING BODY OVERHEAT lights illuminate.
- CC. 80th of the amber PACK lights illuminate.
- DD. Both of the amber BLEED TRIP OFF lights illuminate.
3232. With the engine bleed air switch ON, how are the engine bleed air valves
?- AA. They are pressure activated and AC operated.
- BB. They are DC activated and pressure operated.
- CC. They are pressure activated and DC operated.
- DD. They are AC activated and pressure operated.
3333. What causes the amber PACK light to illuminate?
- AA. Excessive air pressure in the pack
- BB. Failure of either primary or standby pack control.
- CC. Failure of both the primary and secondary pack controls.
- DD. The temperature upstream of the pack has exceeded limits.
3434. What causes the amber PACK TRIP OFF light to illuminate?
- AA. Selecting MANUAL with the related temperature selector.
- BB. The temperature in the respective pack air cycle machine has exceeded limits.
- CC. Placing the air temperature source selector to SUPPL y DUCT.
- DD. The temperature upstream of the related pack valve has exceeded limits.
3535. What fault indications can be reset with the TRIP RESET switch ?
- AA. BLEED TRIP OFF, PACK TRIP OFF, DUAL BLEED.
- BB. BLEED TRIP OFF, PACK TRIP OFF AND DUCT OVERHEAT.
- CC. PACK TRIP OFF, DUAL BLEED, WING-BODY OVERHEAT.
- DD. BLEED TRIP OFF, RAM DOOR FULL OPEN, DUAL BLEED
3636. In the PACK TRIP OFF non-normal procedure, the crew selects a warmer temperature in order to:
- AA. reduce the workload on the other pack.
- BB. reduce cabin air outflow.
- CC. reduce the airflow through the air mix valves.
- DD. reduce the workload on the affected air conditioning pack
3737. The recirculation fan:
- AA. provides overheat detection downstream of the packs.
- BB. is driven by a DC motor
- CC. increases airflow at greater cabin differential pressures.
- DD. reduces air conditioning system pack load and engine bleed air demand.
3838. An overheat condition that illuminates the amber DUCT OVERHEAT light causes
- AA. the air mix valves to drive to full hot.
- BB. the air mix valves to drive to full cold.
- CC. a BLEED TRIP OFF condition.
- DD. an automatic shutdown of the pack.
3939. Illumination of the amber AUTO FAIL light only on the cabin pressurization panel indicates:
- AA. the pressurization mode selector is in the MAN mode.
- BB. loss of both AC and DC power.
- CC. the backup controller is operating.
- DD. loss of DC power.
4040. The amber BLEED TRIP OFF light indicates excessive engine bleed air temperature or pressure.
- ATrue
- BFalse
4141. The amber DUAL BLEED light indicates a possible APU back pressure condition and thrust must be limited to idle.
- ATrue
- BFalse
4242. What fault indications can be reset with the TRIP RESET switch?
- AA. PACK, DUAL BLEED, WING-BODY OVERHEAT.
- BB. BLEED TRIP OFF, RAM DOOR FULL OPEN, DUAL BLEED
- CC. BLEED TRIP OFF, PACK, DUAL BLEED.
- DD. ZONE TEMP, PACK, BLEED TRIP OFF.
4343. In the PACK non-normal procedure, the crew selects a warmer temperature in order to:
- AA. reduce the airflow through the air mix valves.
- BB. reduce cabin air outflow.
- CC. reduce the workload on the other pack.
- DD. reduce the workload on the affected air conditioning pack.
4444. On the Master Caution recall, an amber ZONE TEMP light indicates:
- AA. failure of the flight deck primary or standby temperature control.
- BB. the trim air modulating valve has failed.
- CC. failure of both the flight deck primary and secondary standby temperature control.
- DD. automatic shutdown of the pack.
4545. Illumination of the amber BLEED TRIP OFF light indicates which valve has automatically Closed?
- AA. Related pack valve.
- BB. Related engine bleed air valve.
- CC. Modulating and shutoff valve.
- DD. Isolation valve.
4646. The rain removal system for the forward windows consists of:
- AA. a bottled solution located behind the Captain's seat
- BB. windshield wipers and a permanent rain repellent coating on the windows.
- CC. surface evaporative heating elements.
- DD. rain repellent switch is located on the forward overhead panel.
4747. What does a TAI indication shown at the top left side of each engine N1 display indicate?
- AA. If it is amber, the cowl anti-ice valve position agrees with the related engine anti-ice switch position.
- BB. If it is amber, an overheat condition exists in the duct downstream of the engine cowl anti-ice valve.
- CC. If it is green, the cowl anti-ice valve is Closed and the related ENG ANTI- ICE switch is OFF.
- DD. If it is green, the related cowl anti-ice valve is open.
4848. Selection of the window heat test switch to PWR TEST:
- AA. tests the L 1 and R1 windows only.
- BB. must be tested before each flight.
- CC. can be accomplished if all green window heat ON lights are illuminated (or amber OFF lights are extinguished).
- DD. verifies operation of the window heat system.
4949. When are theENG ANTI ICE switches turned ON if icing conditions exist on the ground ?
- AA. During the After Start procedure.
- BB. When cleared anta the runway.
- CC. During taxi out.
- DD. After takeoff.
5050. Which window(s) are heated with the L FWD WINDOW HEAT switch ON?
- AA. L 1 only.
- BB. L1,L2,L3, L4, L5.
- CC. L 1, L2, L3.
- DD. L2, L3, L4, L5.
5151. When do you normally use wing anti-ice?
- AA. On the ground when icing conditions exist or are anticipated unless the airplane is protected by the application of Type 11 or Type IV fluid in compliance with an approved ground de-icing program.
- BB. To replace ground de-icing/anti-icing.
- CC. As a de-ice and anti-ice on the ground or in flight.
- DD. Any time you use engine anti-ice.
5252. What is the maximum airspeed limit with an amber window OVERHEAT light illuminated?
- AA. 280 knots, at all altitudes.
- BB. 250 knots, at all altitudes.
- CC. 280 knots, below 10,000 feet.
- DD. 250 knots, below 10,000 feet.
5353. The amber R ELEV PITOT light is illuminated. What does this indicate?
- AA. The related probe is heated.
- BB. The right elevator pitot probe is blocked
- CC. A malfunction in the left pitot probe system.
- DD. The right elevator pitot probe is not heated.
5454. The windshield wipers maintain a clear area on the flight deck forward windows. Which of the following statements is correct?
- AA. The windshield wipers are hydraulically operated and electrically controlled.
- BB. Each wiper is operated by a separate control.
- CC. The windshield wipers are limited to an airspeed less than 210 knots.
- DD. The windshield wipers may be operated on a dry windshield.
5555. How are the alpha vanes heated?
- AA. By placing the A and B PROBE HEAT switches to ON.
- BB. By actuating the L or R FWD WINDOW HEAT switches.
- CC. Automatically, whenever wing anti-ice is being used.
- DD. Automatically, whenever the alternate static ports are heated.
5656. Which probes and sensors are not heated?
- AA. The First Officer's pitot probe.
- BB. The Captain's pitot probe.
- CC. The static ports.
- DD. The elevator pitot probes.
5757. Each cowl anti-ice valve is:
- AA. electrically controlled and pressure actuated.
- BB. automatically actuated by the thermal anti-ice detection system.
- CC. AC motor operated.
- DD. automatically closed when the thrust levers are placed in the takeoff position.
5858. The wing anti-ice system provides bleed air lo:
- AA. All leading edge slats.
- BB. All leading edge slats and flaps.
- CC. the three outboard leading edge slats.
- DD. the three inboard leading edge slats.
5959. Illumination of an amber COWL ANTI-ICE light indicates:
- AA. the cowl anti-ice valve position disagrees with the respective engine anti-ice switch position.
- BB. an overpressure condition.
- CC. an overtemperature or overpressure condition.
- DD. the related cowl anti-ice valve is open.
6060. After lift-off, the autothrottle remains in THR HLD until:
- AA. 800 feet radio altitude and 18 seconds after lift-off.
- BB. 400 feet radio altitude and 18 seconds after lift-off.
- CC. 800 feet radio altitude.
- DD. 400 feet radio altitude.
6161. When control wheel pressure is released during CWS R operation, the airplane will roll wings level when the bank angle is:
- AA. 15 degrees or less.
- BB. 8 degrees or less.
- CC. 6 degrees or less.
- DD. 10 degrees or less.
6262. The automatic flight system consists of:
- AA. the autopilot flight director system and the autothrottle.
- BB. a single flight control computer.
- CC. triple-redundant control display units and the flight management computer.
- DD. dual, independent mode control panels.
6363. In normal operation, what provides the autothrottle system with N1 limit values?
- AA. The air data inertial reference units.
- BB. The autothrottle computer.
- CC. The automatic flight director system.
- DD. The flight management computer.
6464. Which statement is true concerning the autothrottle system?
- AA. The autothrottle system will not operate properly with the electronic engine control in ALTN.
- BB. The autothrottle will reduce thrust toward idle at 50 feet radio altitude.
- CC. Following manual positioning, the autothrottle may reposition the thrust levers to comply with computed thrust requirements except while in THR HLD and ARM modes.
- DD. The autothrottle moves the thrust levers with a common servo motor for both thrust levers.
6565. During a dual autopilot ILS approach, at which radio altitude should the FLARE mode engage?
- AA. 50 feet.
- BB. 300 feet.
- CC. 200 feet.
- DD. 150 feet.
6666. Which autothrottle modes permit manual thrust changes without autothrottle interference?
- AA. N1 and ARM.
- BB. GA and ARM.
- CC. Only THR HLD.
- DD. THR HLD and ARM.
6767. Which mode must be armed before the second autopilot can be selected for a dual autopilot approach?
- AA. LNAV.
- BB. VNAV.
- CC. VORLOC.
- DD. APP.
6868. Which of the following occurs when a TO/GA switch is pressed below 2000 feet radio altitude during a single autopilot ILS approach?
- AA. The autothrottle (if armed) advances thrust levers to the reduced go-around N1.
- BB. The autothrottle (if armed) engages in THR HLD mode.
- CC. The flight director commands 10 degrees nose up until reaching the programmed rate of climb.
- DD. The autopilot (if engaged) remains engaged.
6969. What pitch mode FMA is annunciated after takeoff when the autopilot is first engaged in CMD?
- AA. V/S.
- BB. CWS P.
- CC. MCP SPD
- DD. VNAV
7070. What is the minimum altitude for selecting CMD on the second autopilot during a dual channel autopilot approach?
- AA. 1500 feet radio altitude.
- BB. 2000 feet radio altitude.
- CC. 500 feet radio altitude.
- DD. 800 feet radio altitude.
7171. V NAV is terminated by:
- AA. entering a new altitude in the mode control panel altitude display.
- BB. selecting a different roll mode.
- CC. capturing the localizer course.
- DD. reaching the end of an NAV route.
7272. A LVL CHG climb and descent while using the autoflight system is made at the airspeed displayed on:
- AA. the standby altimeter/airspeed indicator.
- BB. the autothrottle computer.
- CC. the MCP IAS/MACH display.
- DD. the CDU scratchpad.
7373. With VNAV engaged, the autopilot flight director system pitch and autothrottle modes are commanded by the:
- AA. ground proximity warning system.
- BB. mode control panel.
- CC. flight management computer.
- DD. flight control computer.
7474. If the pilot overrides the autopilot with control column force pitch input, which of the following occurs immediately?
.- AA. LNAV disengages
- BB. The autopilot engages in LNAV.
- CC. LVL CHG annunciates on the flight management annuciator.
- DD. The autopilot changes to CWS P.
7575. Manually positioning the thrust levers does not cause autothrottle disengagement unless _____degrees of thrust lever separation is exceeded during a dual channel approach after FLARE arm.
- AA. 84.
- BB. 15.
- CC. 10.
- DD. 60
7676. Minimum speed reversion is not available when:
- AA. the autothrottle is OFF and the autopilot flight director system is in ALT HLD.
- BB. the autopilot flight director system is in V/S mode.
- CC. in any segment of VNAV PTH.
- DD. the autothrottle is ON and after glideslope capture.
7777. The use of aileron trim with the autopilot engaged is:
- AA. encouraged.
- BB. prohibited.
- CC. limited to 400 feet radio altitude.
- DD. limited to a maximum 25 knot headwind.
7878. LNAV automatically disconnects:
- AA. upon glideslope capture.
- BB. when within capture Criteria.
- CC. upon reaching a route discontinuity.
- DD. when the VNAV mode is engaged.
7979. Which statement is true concerning the cockpit voice recorder?
- AA. Recordings older than 60 minutes are automatically erased.
- BB. Only one channel records flight deck area conversations using the area microphone.
- CC. Other channels are used for audio control panel output (headset) audio and transmissions for the observers only.
- DD. The cockpit voice recorder uses two independent channels to record flight deck audio for 120 minutes
8080. The audio control panel push-to-talk switch:
- AA. is inoperative unless the MASK - BOOM switch is in MASK.
- BB. has an I/C position. This position keys the oxygen mask or boom, microphones for transmission via the transmitter selector.
- CC. has an R/T position. This position keys the oxygen mask or boom microphone for transmission as selected by the transmitter selector.
- DD. has an I/C position. This position keys the oxygen mask or boom microphone for direct transmission over the flight interphone utilizing the transmitter selector.
8181. In the degraded mode, the audio system cannot access the passenger address system through the audio control panel. What are combinations for transmission and reception at the degraded station?
- AA. Captain/VHF-1, First Officer/VHF-2, Observer/VHF-1.
- BB. Captain/VHF-1, First Officer/VHF-1, Observer/VHF-1.
- CC. Captain/VHF-2, First Officer/VHF-1, Observer/VHF-1.
- DD. Captain/VHF-1, First Officer/VHF-2, Observer/VHF-2
8282. The flight deck CALL light illuminates:
- AA. pink, simultaneously with a two-tone chime.
- BB. blue, indicating the location of the call originator is the nose wheel well or attendant station.
- CC. pink, indicating that the flight deck is being called by flight attendants or ground crew.
- DD. blue, simultaneously with a single low-tone chime.
8383. Altitude alert, ground proximity warning system, and windshear audio warnings:
- AA. are audible through an audio control panel in the degraded mode.
- BB. are integral components of the flight mode alerting system.
- CC. may be placed on speaker using an audio control panel in the degraded mode.
- DD. are not heard on an audio system operating in the degraded mode.
8484.If the BUS TRANSFER switch is in the AUTO position and the source powering the transfer bus is disconnected or fails, the source powering the opposite transfer bus automatically picks up the unpowered transferred bus through the bus tie breakers.
- ATrue
- BFalse
8585. The AC transfer busses:
- AA. allow for external power or APU to continue to supply power to the remaining transfer bus, if previously connected, whenever engine generator power is applied to its onside transfer bus.
- BB. supply power to the 110 volt AC main busses.
- CC. can be powered by both external power and APU power at the same time.
- DD. can be powered by any available source through the tie bus with the generator circuit breaker, should the AC source powering either transfer bus fail or be disconnected.
8686. In flight, one engine-driven generator drops offline and the BUS TRANSFER switch is in the AUTO position. What indications will the pilot see on the failed side?
- AA. SOURCE OFF and GEN OFF BUS are illuminated and the TRANSFER BUS OFF light illuminates.
- BB. Illumination of the fuel pump, probe heat, and hydraulic pump lights.
- CC. SOURCE OFF and GEN OFF BUS are illuminated and the TRANSFER BUS OFF light remains extinguished.
- DD. A TRANSFER BUS OFF light and a GEN OFF BUS light illuminate.
8787. Under which of the following conditions will the cross bus tie relay automatically open, isolating DC bus 1 from DC bus 2?
- AA. In flight, if an amber TR light illuminates.
- BB. An engine-driven generator drops offline.
- CC. The bus transfer switch is positioned to OFF.
- DD. At localizer capture, during a flight director or autopilot ILS approach.
8888. With the STANDBY POWER switch in the AUTO position, the loss of all normal AC electrical power causes the battery to power the standby loads:
- AA. only on the ground.
- BB. only in the air.
- CC. only if the STANDBY POWER switch is placed to BAT.
- DD. both in the air and on the ground.
8989.AC amperage can be observed on the AC ammeter for the source selected by the, AC meters selector.
- ATrue
- BFalse
9090. Illumination of the amber BAT DISCHARGE light indicates:
- AA. that the battery bus is not being powered.
- BB. battery discharge when the DC meters selector is in the BAT position with the BAT switch placed to ON.
- CC. excessive battery discharge is detected with the BAT switch placed to ON.
- DD. the battery is being overcharged.
9191. In flight, an amber TR UNIT light illuminates if:
- AA. TR1 and TR3 fails.
- BB. any TR unit fails.
- CC. the cross bus tie relay opens.
- DD. TR1 fails, or both TR2 and TR3 fail.
9292. On the ground, an amber ELEC light will illuminate if:
- AA. a fault exists in the AC power system only.
- BB. a fault exists in the AC, DC or the standby power system.
- CC. a fault exists in the DC or standby power system.
- DD. a fault exists in the AC or standby power system.
9393. Illumination of the amber DRIVE light indicates low oil pressure caused by which of the following?
- AA. A low engine N1 RPM.
- BB. An independent drive generator failure.
- CC. An independent drive generator disconnected through generator drive STANDBY POWER switch.
- DD. An independent drive generator automatic disconnect due to high oil pressure
9494. Illumination of the blue GRD POWER AV AILABLE light indicates:
- AA. external ground power is connected; however, no airplane power quality is assured.
- BB. external ground power is connected and the AC ground service bus 1 is automatically powered.
- CC. external ground power is connected and meets airplane power quality standards.
- DD. external ground power is connected and both AC ground service busses are automatically powered.
9595. The amber SOURCE OFF light will illuminate:
- AA. when no source has been manually selected to power the related transfer bus.
- BB. when the GEN OFF BUS switch is momentarily depressed.
- CC. when a manually selected source has been connected.
- DD. when no AC power source is available
9696. Illumination of the blue GEN OFF BUS light indicates:
- AA. the related transfer bus is not powered.
- BB. the related main bus is not powered.
- CC. the APU is running and not powering a bus.
- DD. the independent drive generator is not supplying power to the related transfer bus.
9797. The APU generator can meet the following conditions: bleed load maximum altitude off ________feet, bleed and electrical load maximum altitude of feet, and electrical load maximum altitude of feet.
- AA. 15,000; 17,000; 41,000
- BB. 10,000; 14,000; 41,000
- CC. 17,000; 10,000; 41,000
- DD. 10,000; 17,000; 41,000
9898. Illumination of the amber STANDBY PWR OFF light indicates which of the following busses are unpowered?
- AA. The DC bus 1.
- BB. The battery bus.
- CC. Both DC bus 1 and DC bus 2.
- DD. The AC transfer bus 1.
9999. Both AC transfer busses can be powered simultaneously by:
- AA. a single independent drive generator on the ground or in flight.
- BB. battery power.
- CC. the APU generator while on the ground only.
- DD. the APU or external power on the ground or in flight.
100100. When takeoffs are made with the APU powering both transfer busses:
- AA. both transfer busses will automatically disconnect after lift-off.
- BB. the generators will not automatically come on line if the APU is either shutdown or fails.
- CC. if the APU is either shut down or fails, the engine generators are automatically connected to their related transfer busses.
- DD. one transfer bus will disconnect automatically after lift-off.
101101. On the ground, with the BAT switch placed to OFF and the STANDBY POWER switch in AUTO, the battery bus is:
- AA. powered by the battery.
- BB. not powered.
- CC. powered by TR3.
- DD. powered by the hot battery bus.
102102. Momentarily moving the GRD PWR switch to the ON position, with ground power available, will:
- AA. connect ground power to the AC transfer busses if power quality is correct.
- BB. disconnect ground power from the AC transfer busses.
- CC. connect ground power to the AC main busses if power quality is correct.
- DD. remove previously connected power from the DC transfer buses.
103103. One basic principle of operation for the 737 electrical system is:
- AA. an AC power source may be used in parallel with a DC power source.
- BB. all generator bus sources can be automatically connected by the standby power system.
- CC. there is no paralleling of the AC sources of power
- DD. there is no paralleling of any power source.
104104. With the BUS TRANSFER switch in AUTO, the cross bus tie relay automatically opens under which of the following conditions?
- AA. When AC voltmeter reaches 26 volts (plus or minus 4 volts).
- BB. When TR1 and TR2 fail.
- CC. At glide slope capture during a flight director or autopilot ILS approach.
- DD. At localizer capture
Information
- Description
- Test en B737, creado por Fernanda Ojeda en 22/04/2019.
- Author
- Fernanda Ojeda
- Language
- Español
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