Quiz
737NG MQF Practice Test
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Fragen in diesem Quiz (150)
1The designation of the engine on the 737NG is CFM International CFM56-7B26
- ARichtig
- BFalsch
2What system is used to open the forward cargo (baggage) door?
- ABattery
- BStandby DC
- CExternal AC
- DManual (mechanical)
3With the emergency light switch in the "armed" position under normal power, what condition will cause the lights to illuminate automatically?
- ALoss of transfer buses
- BLoss of #1 DC bus or AC power is turned off
- CLoss of a main generator bus
- DLoss of the #1 TR
4In flight, when the gear horn sounds, under what conditions can it be silenced?
- AFlaps >15, both thrust levers any position
- BFlaps 15, both thrust levers at idle
- CFlaps 1-10, thrust levers at any position
- DFlaps 30, thrust levers full forward
5What warning inhibits are available in the GPWS system?
- AGlide slope
- BExcessive descent
- CFlaps config, gear config, and terrain
- DSink on go around
6How are the bleed valves operated?
- APneumatically controlled and operated
- BElectrically control and pneumatically operated
7A reactive windshear alert inhibits all others.
- ARichtig
- BFalsch
8Can the engines be started with the engine BLEED valve switches in the “OFF” position?
- AYes
- BNo
9With loss of System A hydraulic pressure, nose wheel steering:
- AAutomatically operates from System B by a shuttle valve
- BIs not available
- CIs manually selectable to System B hydraulics
- DNone of these
10What causes a bleed trip?
- AExcessive bleed pressure
- BExcessive bleed temperature
- CBoth
11How many fuel measuring sticks are used to check the center tank quantity?
- A1 only
- B2
- C1 each side
- D4
12What does a duct overheat light indicate?
- AAny time the DUCT OVERHEAT light illuminates
- BAny time the air mix valves go full cold
- CBleed air temperature in related duct exceeds limit
- DWhen the bleed valve closes
13What is the function of the EEC?
- AN1 is used by the EEC to set thrust in three control modes: normal and two alternates
- BEEC uses thrust lever inputs to automatically control forward and reverse thrust
- CBoth
14Where is the engine oil pressure measured?
- AOn the outlet side of the engine driven oil pump, prior to the fuel filter
- BPrior to the fuel/oil heat exchanger
- COn the outlet side of the engine driven oil pump, prior to engine lubrication
- DIn the oil tank
15What is the purpose of the isolation valve?
- AAllows separation of the bleed valves from the packs when required
- BAllows separation or connection of the left and right pneumatic systems when required
- CIsolates the hydraulic system from the pneumatic system during servicing
- DIsolates air conditioning system from the anti-ice system
16What are the in-flight operating limits of the APU?
- AUp to 10,000 - pneumatic and electrical load
- BUp to 17,000 - pneumatic load only
- CUp to FL410 - Electrical load only
- DAll of the above
17When should the starter automatically cutout?
- A20% N2
- B25% N2
- C35% N2
- D56% N2
18What are the power sources of igniters?
- ALeft, respective AC TRANSFER bus and Right, STBY bus
- BLeft GEN BUS and Right MAIN BUS
- CLeft AC TRANSFER bus and BATTERY BUS
- DHOT BATT BUS and Right AC TRANSFER BUS
19Will the APU fire detection system automatically discharge the fire bottle?
- AYes, but only if AC power is on the aircraft
- BNo, it only shuts the APU down
- CNo, you will only get the fire warning
- DNothing will happen
20What requirements must be met before Reverse is available?
- AFire switch down
- BEither Radio Altimeter sensing less than 10 feet, or the Air/Ground sensor in Ground mode
- CHydraulic pressure and battery power available
- DAll answers and reverse selected
21What is the purpose of the landing gear transfer unit?
- AAllow landing gear retraction in the event of a #1 engine failure
- BAllows the lowering of the gear in the event of at #1 engine failure
- CAllows for steering in the event of System A hydraulic failure
22What are the electrical sources for the 737?
- AEngine driven generators
- BAPU
- CGround power
- DAll answers
23How are the primary flight controls normally powered?
- AA hydraulic system only
- BB hydraulic system only
- CBy hydraulic systems A & B
- DElectro/mechanical only
24How could the STBY RUDDER be activated manually?
- APlacing either or both system A & B flight control switches to STBY RUDDER
- BPlacing the STBY hydraulic switch to ON
- CPlacing the rudder switch to STBY
25Under what conditions would a IDG disconnect (either manually or automatically) be necessary when low oil is sensed by a DRIVE caution light?
- AHigh oil temperature
- BIDG failure
- CBoth
26Can the STBY hydraulic pump be activated by any additional method?
- AYes, placing the STBY hydraulic switch to on
- BYes, placing the elevator switch to STBY
- CYes, placing the aileron switch to STBY
- DYes, by selecting the ALTERNATE FLAP MASTER switch to ON
27Which buses supply the “essential” loads?
- AThe STANDBY buses
- BThe TRANSFER buses
- CThe ESSENTIAL buses
- DThe MAIN buses
28What are the temperature limits of the APU?
- AStart: 760 C, no max continuous
- BStart: 760 C, Max continuous 710 C
- CStart: 710 C, Max 660 C
- DMax limits are not displayed but are set by the ECU
29What is the minimum fuel to operate the electric hydraulic pumps on the ground?
- A1675 lbs. in each wing tank
- B1675 lbs. in the right tank only
- C1676 lbs. in the left tank only when the system B pumps are on
30Why is there a minimum fuel requirement to operate the electric hydraulic pumps?
- ATo have enough fuel for thrust during flight control maneuvering
- BTo keep the hydraulic pumps submerged for cooling
- CTo prevent sloshing during ground taxi
- DThe A & B system heat exchangers are located in the main tanks
31What are the primary and the backup sources of power for the XFER BUSes?
- APrimary: respective IDG, Backup opposite XFER BUS
- BPrimary: respective IDG, backup MAIN BUS
- CPrimary: respective MAIN BUS. Backup: STBY GEN
- DPrimary: respective MAIN BUS, Backup: STBY BUS
32At what degree of control wheel displacement does flight spoiler deployment begin to assist the ailerons in roll control?
- A8
- B12
- C15
- D10
33Does aileron trim physically effect control wheel position?
- AYes. The control wheel position directly indicates the amount of aileron applied.
- BNo. The control wheel will remain in the same position.
34What is the function of a TR?
- AConvert 28 volt DC power to 115 volt AC power
- BConvert 115 volt AC power to 28 volt DC power
- CProvides power to the battery
- DAllows APU to power the buses
35What is the voltage output of the TRs?
- A28 volts
- B115 +/- volts
- C22-28 volts
- D400 +/- 10 volts
36If the trailing edge flaps are extended by the alternate method, what flap protections are available?
- ANone
- BAsymmetry but not skew
- CSkew but not asymmetry
- DBoth skew and asymmetry
37What powers the trailing edge flaps down with the Alternate Flaps system selected?
- ASystem A hydraulic pressure
- BStandby hydraulic system pressure
- CAn electric motor
- DThe PTU (power transfer unit)
38When is the automatic Standby Power feature available?
- AWhen the STBY power switch is in the BAT position
- BIt's never automatic
- CAlways. It functions the same on the ground as in the air
- DAny time there is power on the aircraft
39Which of the following is not on the Hot Battery Bus?
- AAPU and engine fire bottle discharge
- BFuel shutoff valves
- CExternal power control
- DStandby rudder shutoff valve
40If the system “B” electric pump or lines develop a leak, what would the indications be?
- ASystem B quantity would decrease to approximately 1.84 gal.
- BSystem B quantity would decrease to approximately 1/2 full
- CThe quantity indication would go to zero. But sufficient fluid would be available to operate the power transfer unit
- DSystem B quantity would remain full due to the blocking valve in the pump
41If you lost all Standby system hydraulic fluid, would there be a cockpit indication?
- AYes, but only if the standby pump was operating at the time
- BYes. The standby LOW QUANTITY light would be illuminated and system B reservoir would read between 1/2 and RFL
- CNo. However, you may notice lower quantity in the other reservoirs
42What activates the Standby hydraulic pump?
- APlacing either flight control switch to STBY RUDDER
- BPlacing the alternate flap switch to ARM
- CThe automatic activation occurs with loss of either system A or B, when the flaps are extended, while airborne or with wheel speed greater than 60 knots
- DAll of the above and activation of the FFM
43What is the power source for APU start?
- AAC power if available
- BMain battery only if AC not available
- CBoth
44Will the AUTOBRAKE DISARM light normally illuminate after takeoff with RTO selected?
- AYes
- BNo
45When selected, at what speed is RTO available?
- AAbove 60 knots
- BAbove 80 knots
- CAbove 90 knots
- DAbove 100 knots
46What is the maximum airspeed for retracting the landing gear?
- A250 knots
- B200 knots
- C225 knots
- D235 knots
47When is the fuel heated?
- AThe fuel is constantly heated by a fuel/oil heat exchanger
- BWhen you turn on the fuel heater switch
- CAutomatically when the fuel temperature is below 0 degrees
- DThere is no requirement for fuel heat on this aircraft
48When retracting the high lift devices using the alternate method, will the LED’s return to the retracted position?
- AYes
- BNo
49What are the two sources of power for the Ground Service Bus?
- ATRANSFER BUS #1
- BMAIN BUS #2
- CGround power via the ground services switch on the F/A panel
50When are the Ground Service Buses powered?
- AWhen external power is available and the ground service switch in ON, or both TRANSFER BUSES are powered
- BWhen the battery switch in ON and the STBY power switch is in NORMAL
- CWhen the battery switch is ON or GEN BUS #1 is powered
- DAutomatically when the ground power is plugged into the aircraft
51When is the latest you should wait for oil pressure to be indicated?
- ABy the time the START VALVE OPEN light illuminates
- BBy the time the OIL PRESS LOW light extinguishes
- CBy idle RPM
- D25% N2
52The APU has an overheat warning system.
- ARichtig
- BFalsch
53Must the Battery switch be on to operate the APU?
- AYes, to provide fire protection when unattended
- BNo, it's not required
- CYes, on the ground and in-flight
- DNo, battery is only required for starting
54Can the APU be started without the battery?
- AYes, using the external DC receptacle
- BBattery is required for start on the ground but not in-flight
- CNo, the battery is required
- DYes using external power
55What actuates the thrust reversers?
- AHydraulic pressure
- BElectrical signal
- CPneumatic pressure
56What do the Start Levers control?
- AFuel
- BHydraulics
- CIgnition
57How long should you operate the APU before using it as a bleed air source?
- AOne minute
- BTwo minutes
- CNo time requirement
- DNone of these
58The EGPWS gets position information from:
- AThe GPS position
- BBoth FMCs
- CXM Satellite
- DThe multi-mode receivers through DME/DME triangulation
59When are the Aux and Main batteries tied together?
- AWhen selected in parallel
- BNever
- CAt all times
- DWhen the batteries are the only source of power (except during APU start)
60What is the primary source for DC power?
- ABattery
- BAPU
- CThree transformer recifiers (TRs) and a ground service TR
- DXFER BUS
61What is the maximum EGT allowed during engine start?
- ANot given, but the APU start will automatically terminate in an exceedance
- B710C
- C760C
- D860C
62What would indicate an APU hung start?
- AThe start is automatically terminated
- BNo rise in EGT within 20 seconds of starter engagement
- CRunaway fuel flow
63How high may the APU be started?
- AUp to the service ceiling of the aircraft
- BUp to FL350
- C17,000'
- DNo limit
64What is a good test indication of the TCAS?
- AFour traffic symbols on the NDs
- BAn aural message that the test is OK
- CNone. It is continuously monitored by the BITE system
65Where do the air conditioning packs get their air?
- AEngines
- BAPU
- CGround pneumatics
66How is the APU compartment and exhaust system cooled?
- AFan bypass air
- BCooling fan on the accessory drive
- CAir enters the cooling inlet above the exhaust opening
- DRam air through the intake
67If the APU EGT rises above acceptable limits during engine start:
- AIt will reduce bleed air output to maintain electrical voltage
- BIt will reduce electrical output to maintain bleed air pressure
- CThe ECU will reduce fuel to the APU to limit EGT
- DIt will make strange noises
68What is the primary source of cockpit air?
- AThe left pack, upstream of the mix manifold
- BAir from the mix manifold
- CRecirculation fan
- DThe right pack, upstream of the mix manifold
69What would be your indication be with a TR3 failure?
- ATR1 would pick up the load
- BTR1 and TR2 would share TR3's load
- CZero volts and amps. TR3 output is read at the TR
- DTR3 amps 0 and volts normal
70What is the power source for TR3?
- AXFER BUS #2
- BMAIN BUS #2
- CGround service bus
71How could you verify that TR1 had failed?
- ATR3 will pickup the load
- BPlace the BUS TRANSFER switch to OFF. DC volts and amps will read zero
- CTR1 amps 0 and volts normal
- DTR1 amps normal and volts 0
72If the DC meter switch is placed to the STBY PWR position, what would you be able to read?
- ADC volts and amps
- BVolts and freqs
- CDC STANDBY BUS voltage only
73Normally, what would you expect to happen if the DC BUS #1 or XFER BUS #1 failed?
- AThe BAT BUS would power the STBY BUS and the STBY AC BUS through the static inverter
- BSTBY BUSes fail
- CXFER BUS #2 picks up the STBY BUSes
- DMAIN BUS #1 picks up the STBY BUSes
74What are the normal and back up power sources for the STBY AC & DC BUSes?
- ANormal: STBY AC is powered by XFER BUS #1
- BSTBY DC is powered from DC BUS #1
- CBackup for STBY AC is the BAT BUS through the static inverter
- DBackup for STBY DC is the BAT BUS
75What malfunctions does the reset button affect?
- ABleed trip, wing-body overheat, pack trip
- BWing body overheat, bleed trip, duct overheat
- CPack trip, duct overheat, wing-body overheat
- DBleed trip, pack trip, and duct overheat
76What would be a reason to switch the Standby Power switch to BAT on the ground?
- AOn engine start
- BWith APU powering one power train in the air
- CNone as the Standby buses are powered with the battery switch in the ON position on the ground
- DWhen refueling a "cold" airplane or if use of the VHF COM #1 is required.
77What are the power sources for the BAT BUS?
- AWith normal AC power and the BAT switch ON - TR3
- BWith normal AC power - #1 main generator bus
- CWith loss of AC power in flight - the battery
78With the BAT switch OFF and ground power supplying ground services in the cabin, are the batteries being charged?
- AYes, because the ground service busses supply the battery chargers
- BNo, the BAT switch must be ON
79How long will the Battery provide standby power?
- AFor the remainder of the flight due to the air driven generator
- BAs long as the hydraulics are maintained to the generator
- CUntil engines are shut down
- D60 minutes with the two-battery option
80What is the function of the Rd. 60 minutes with the twoecirculation Fan?
- AReduces fuel consumption
- BReduces the amount of bleed air demanded from the packs
- CProduces the gasper (eyeball) air at each seat
81 When are the deflector doors extended?
- AIn heavy precipitation
- BWhen the pack controllers sense demand
- COn the ground
82What is the power source for the recirculation fan?
- AEngine bleed air
- BDriven by an AC motor
- CSTBY power
- DAC main bus
83When will the EQUIP COOLING OFF light illuminate?
- AWith a loss of #1 GEN BUS
- BWhen the EQUIP door light illuminates
- CWhen airflow is insufficient to cool the airflow sensor
84What is the maximum lateral fuel imbalance?
- A1000 lbs. for all phases of flight
- B1200 lbs. for takeoff, climb and cruise. 1500 lbs. for landing.
- C1500 lbs. for all phases of flight.
- D1000 lbs. for takeoff, climb and cruise. 1500 lbs. for landing.
85Describe the normal fuel loading sequence.
- AFill the auxiliary tank, then the center tank, then the main tanks
- BFill the main tanks to full, then the auxiliary tank, then the center tank full
- CFill the main tanks to full, then center tank
- DFill the center tank, then top off the main tanks, then the auxiliary tank
86With fuel in all tanks and all boost pumps on, how is fuel feed scheduled to the engines?
- AMain tanks to their respective engines until they are empty, then the center tank to both engines
- BCenter tank to both engines until the tank is empty, then main tank to respective engine
- CAll tanks feed to all engines at the same time
- DOne tank at a time to both engines
87When is the air conditioning Ram Air Deflector Door open?
- AWhen on the ground
- BWhen on the ground, when flaps are out of UP and when ambient air dictates
- CWhenever the pack is running
- DWhen the recirculation fan is off
88What is the power source for the pack valves?
- ASTBY AC bus
- BThe battery bus
- CRespective main bus
- DRespective transfer bus
89A pack valve can automatically regulate to high flow:
- AExcept on the ground, or in the air with flaps extended
- BIf the other pack is not operating
- CNone of these
90The forward outflow valve will open automatically:
- AWhen a pack trips
- BTo maintain warming airflow around the forward cargo compartment
- CIt's a trick! There's no forward outflow valve
91The overboard exhaust valve closes:
- AAt high cabin differential pressures
- B> 2.5 psid
- CWhen either pack is in HIGH and the recirculation fan is OFF
- D> .125 psid
92When is the overboard exhaust valve open?
- AWhen the main outflow valve is open more than 3 degrees open
- BWhen the flow control valve opens
- CWhen the recirculation fan is off
- DOn the ground
93When does the aircraft start pressurizing?
- AIt starts pressurizing the cabin to the altitude in the FLT ALT window at liftoff
- BIt starts pressurizing the cabin at higher power settings on the ground
- CTemporarily switches to the STBY mode of pressure until takeoff
- DIt temporarily closes the MAIN OUTFLOW valve until takeoff roll
94What causes illumination of the equipment cooling OFF light?
- AA loss of airflow
- BWhen the detector senses a loss of all generators, the light automatically illuminates
- CWith a loss of a bleed source the light will illuminate
95What action is required when the equipment cooling OFF light illuminates?
- AOpen the isolation valve to allow the opposite side to provide cooling
- BOpen the ram air doors for more airflow
- CPlace the switch to alternate
- DPlace the STBY switch to BAT
96What is the source of equipment cooling air?
- AAir from the cabin recirculates through the E&E bay
- BConditioned air from the cockpit is drawn across the circuit breaker panels, then routed through the E&E compartment racks
- CFan bypass air
- DGasper fans
97Where does the fuel temperature indicator get its reading?
- ABottom of #2 main tank
- BAt the fuel controller
- CAt the fuel filter
- D#1 main tank
98With all fuel pump switches on and the forward pump in the #1 tank not working, when will the MASTER CAUTION and FUEL CAP lights illuminate?
- AImmediately after the pump stops
- BWhen the CAP panel is pressed for "recall"
- CWhen the second pump in that tank quits
99With total loss of normal AC power, can the engines still be provided with fuel?
- AYes, through suction feed from the main tanks only
- BYes, with the pumps on the STBY BUS
- CNo, all pumps are AC powered
100At what cabin altitude will the cabin oxygen masks automatically deploy?
- AThe masks will not automatically deploy automatically
- BAt approximately 10,000 cabin altitude
- CAt approximately 12,000 cabin altitude
- DAt approximately 14,000 cabin altitude
101The fuel pumps for the main and center tanks are powered by which electrical system?
- AAC
- BDC
102What is another purpose of the defueling valve?
- AGround transfer of fuel
- BTank to tank transfer of fuel
- CFuel dumping
103A center tank fuel pump LOW PRESSURE light will illuminate when the pump switch is off.
- ARichtig
- BFalsch
104Each tank supplies pressurized fuel by using ___ boost pumps.
- A1
- B2
- C3
- D4
105With the crossfeed valve closed, the left center tank boost pump will feed the left engine and the right center tank boost pump will feed the right engine, until the center tank is dry.
- ARichtig
- BFalsch
106With a complete loss of electrical power, only fuel from which tanks will be available?
- ACenter tank
- BMain tanks
- CAll tanks
107The fuel quantity indicators are found on the upper MFD panel and require standby AC power to operate.
- ARichtig
- BFalsch
108Inflight, when the crossfeed valve is open, fuel may be fed from any tank to:
- AAny tank
- BOnly from tank #1 to #2
- CIts respective engine only
- DEither engine
109The engine fuel shutoff valves may be closed by:
- APulling the engine fire warning switch
- BPlacing the engine start lever to CUTOFF
- CPlacing both fuel pumps in the respective tank to OFF
110Which valve interconnects the engine feed system to the fueling station?
- AThe fueling valve
- BThe #2 start lever
- CManual defueling valve
- DThe crossfeed valve
111The Power Transfer Unit provides an alternate source of hydraulic power for automatic extension of the auto slats if the system B engine driven pump pressure falls below limits
- ARichtig
- BFalsch
112Can the standby hydraulic pump operate the thrust reversers?
- ANo. They are pneumatically powered
- BYes, at the normal rate
- CNo. There is no backup source of power for the thrust reversers
- DYes, but more slowly than normal operation
113When both the crossfeed switch and the crossfeed valve are open, the CROSSFEED VALVE OPEN light will:
- ABe extinguished
- BIlluminate dim blue
- CIlluminate bright blue
114For a FUEL annunciator and MASTER CAUTION light to illuminate, two fuel LOW PRESSURE lights must be illuminated in the same wing tank.
- ARichtig
- BFalsch
115When the landing gear is up and locked, all Landing Gear Indicator lights will be extinguished when the Landing Gear Lever is placed in what position?
- AUP
- BOFF
- CDown
116The maximum fuel imbalance for landing is?
- A1500
- B1300
- C1200
- D1000
117What does the illumination of a fuel FILTER BYPASS light indicate?
- ASolid contaminants
- BIcing
- CImpending filter bypass
- DFuel temp 0 degrees or less
118Wing tanks #1 and #2 must be full if the center tank contains more than what amount?
- A2000
- B1000
- C1500
- D1300
119The warning horn will sound when landing gear is not down and locked, flaps greater than 15 and the Thrust Levers are at IDLE; it cannot be silenced.
- ARichtig
- BFalsch
120Air/Ground Safety Sensors are located on what gear?
- AThe left main gear
- BThe right main gear
- CThe nose gear
121The engine fuel shutoff valve is:
- ADC powered (hot battery bus) and controlled by the engine start lever and/or the engine fire switch
- BPowered from the STBY BUS and controlled by the engine fire switch
- CPowered by XFER BUS and controlled by the engine start lever
- DPowered by XFER BUS and controlled by the engine fire switch
122What ensures proper fuel flow direction and prevents transfer of fuel between tanks?
- ACrossfeed valve
- BPositive pressure from the fuel boost pumps
- CCheck valves
123What is the Maximum airspeed for extending the landing gear?
- A220
- B230
- C250
- D270
124The purpose of the single point fueling system is to allow:
- ARapid fueling
- BGround fuel transfer
- CDefueling
125Is it possible to service the center tank without single-point fueling?
- ANo
- BYes, by the use of ground transfer
126If both “A” & “B” hydraulic systems failed could any of the primary flight controls be hydraulically powered?
- AYes, the elevator by STBY hydraulics
- BYes, the rudder thru the STBY rudder power control unit powered by the STBY hydraulic system
- CYes, the ailerons by the STBY hydraulics
- DNone by the hydraulics but they can be moved manually
127With the loss of all generators, both center tank boost pumps are inoperative and the fuel in the center tank is no longer usable.
- ARichtig
- BFalsch
128Where does the Auto mode of the pressure controller receive its barometric reference?
- AFrom the First Officer's altimeter
- BDirectly from the pitot/static probes
- CFrom the BARO selectors through the ADIRUs
- DFrom the ADC
129Yaw damper operation occurs only when what hydraulic system is operational?
- AB system
- BA system
- CSTBY system
130Where does the ALTN mode get its barometric reference?
- AFrom the BARO selectors through the ADIRUs
- BDirectly from the pitot/static probes
- CFrom the Captain's altimeter
- DFrom the ADC
131If the trailing edge flaps were extended and retracted by the alternate method, according to procedure; how long would it be before you could extend the trailing edge flaps again?
- A25 minutes
- B15 minutes
- C5 minutes
- D2 minutes
132Which outflow valve motor does the AUTO mode use?
- AThe AC motor
- BA DC motor
- CThe pneumatic motor
- DThe DC motor through the TR
133If the cowl valve fails to agree with the position of the Engine Anti-ice switch, what will the indication be?
- AThe COWL VALVE OPEN light will extinguish
- BThe COWL VALVE OPEN light will be dim blue
- CThe COWL VALVE OPEN light will be bright blue
- DThe COWL ANTI ICE light will illuminate
134In AUTO mode, where does the controller derive its altitude information?
- AFrom the ADC
- BFrom the ADIRUs
- CFrom the AUX ports
135If unable to close the Engine Anti-ice valve in flight, what should the crew do?
- ARetard the thrust levers to IDLE
- BOpen the isolation valve
- CLimit the thrust on the affected engine to 80% N1 is TAT exceeds 10C
- DTurn off the bleed valve
136What does an illuminated COWL ANTI-ICE light mean?
- AThe cowl valve is open
- BAn over pressure condition exists in the cowl anti-ice duct
- CThe cowl valve has failed open
- DThe cowl valve is in transit
137The Engine Anti-ice should be turned on at what time?
- AAnytime the COWL ANTI-ICE light is on
- B0 degrees C or colder
- CTen minutes prior to departure
- DWhen icing conditions exist or are anticipated
138If an engine OVERHEAT light cannot be extinguished by using the recommended overheat procedures, which engine procedures should be followed?
- ABleed overheat
- BEngine failure, fire, severe damage, or separation
- CEngine overheat
- DEngine shutdown
139How many minutes prior to takeoff should window heat be turned on?
- A1
- B3
- C5
- D10
140With the Overheat Detector switch in NORMAL, which loops must sense an overheat or fire condition before an overheat or fire warning is activated?
- ABoth #1 and #2 loops
- BBoth the A and B loops
- COnly one loop for fire or one loop for overheat
- DOnly one loop of any kind
141A green window heat ON light illuminates:
- AWhen the switch is in the ON position
- BThe valve doesn't agree with the switch position
- CWhenever the window heat controller is applying heat to the associated window
- DWhen the window has already reached a predetermined temperature
142Pulling and rotating a FIRE warning handle will discharge the fire extinguisher selected even when the Battery switch is OFF.
- ARichtig
- BFalsch
143The results of pulling the APU Fire Warning handle are:
- AAPU fuel shutoff valve closes. Bleed air valve closes. Inlet door closes.
- BTrips the generator control relay. Arms the extinguisher.
144When the FLT/GRD switch is placed in the FLT position, what does the system do?
- AIt starts pressurizing the cabin to .125 psid
- BIt's a trick! There is no FLT/GRD switch
- CTemporarily switches to the STBY mode of pressure until takeoff
- DIt temporarily closes the MAIN OUTFLOW valve until takeoff roll
145APU fire detection loop failure is indicated by the illumination of which light?
- AAPU fire light
- BFault light
- CAPU DET INOP light
- DGreen squib light
146The FAULT light monitors which detector loops?
- AEngine #1 and Engine #2
- BFire loops #1 and #2
- COverheat loops #1 and #2
- DAPU overheat and fire loops
147How are the FIRE warning switches unlocked manually?
- ABy pressing the override release
- BBy conducting a FIRE test, then pulling the switch
- CNone of these
148If a flight attendant turns on the Emergency Exit lights on the aft panel, is there a cockpit indication and can the cockpit crew override the F/A switch?
- AA blue light illuminates, the pilot's switch will override the F/A switch
- BNo indication in the cockpit, the pilot's switch will not override the F/A switch
- CLight on the overhead panel, the pilot's switch will not override the F/A switch
149What does the green disk on the right side of the fuselage indicate? [No mention in text, but there’s one on every airplane.]
- AFire bottle intentional discharge
- BFire bottle thermal discharge
- CPortable water servicing disk
- DCrew oxygen thermal pressure relief disk
150If ground power is being supplied to the aircraft and APU power is put on one bus, does the ground power trip off the line?
- AYes, only the side powered by the APU will remain powered
- BYes, all power will be removed from all buses
- CNo, ground power will continue to power the other side until it is removed, or another power source powers that bus
Informationen
- Beschreibung
- Quiz am 737NG MQF Practice Test, erstellt von matt.velure am 30/08/2015.
- Autor
- matt.velure
- Sprache
- English
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- 0
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