(HPA) B737-NG 48 Hour - Master Question File Flashcards
- What system is used to open the forward cargo (baggage) door?
a. Battery
b. Standby DC.
c. External AC.
d. Manual (Michanical).
d. Manual (Mechanical)
1. 40.31
- The designation of the engine on the 737-NG is CFM International CFM56-7B26.
a. True
b. False
a. True
7. 1.11
- With the emergency light switch in the “armed” position under normal power, what condition will cause the lights to illuminate automatically?
a. Loss of transfer buses.
b. Loss of #1 DC bus or AC power is turned off.
c. Loss of a main generator bus.
d. Loss of the #1 TR.
b. Loss of #1 DC bus or AC power is turned off.
1. 30.7
- In flight, when the gear horn sounds, under what conditions can it be silenced?
a. Flaps > 15, both Thrust Levers any position.
b. Flaps 15, both Thrust Levers at idle.
c. Flaps 1-10, Thrust Levers at any position.
d. Flaps 30, Thrust Levers full forward.
c. Flaps 1-10, Thrust Levers at any position.
1. 20.6
- What warning inhibits are available in the GPWS system?
a. Glide Slope
b. Excessive Descent
c. Flaps Config, Gear Config, and Terrain
d. Sink On Go Around
c. Flaps Config, Gear Config, and Terrain
15. 10.8
- How are the bleed valves operated?
a. Pneumatically controlled and operated
b. Electrically controlled and pneumatically operated
b. Electrically controlled and pneumatically operated
2. 20.1
- A reactive windshear alert inhibits all others?
a. False
b. True
b. True
15. 20.1
- Can the engines be started with the engine Bleed Valve switches in the “OFF” position?
a. Yes
b. No
a. Yes
7. 20.11
- With loss of system A hydraulic pressure, nose wheel steering:
a. Automatically operates from system B by a shuttle valve
b. Is not available
c. Is manually selectable to system B hydraulics
d. None of the above
c. Is manually selectable to system B hydraulics
14. 10.8
- What causes a bleed trip?
a. Excessive bleed pressure
b. Excessive bleed temperature
c. Both a and b
d. None of the above
c. Both a and b
2. 20.1
- How many fuel measuring sticks are used to check the center tank quantity?
a. 1 only
b. 2
c. 1 each side
d. 4
d. 4
12. 10.10
- What does a duct overheat light indicate?
a. Any time the DUCT OVERHEAT light illuminates.
b. Any time the air mix valves go full cold.
c. Bleed air temperature in related duct exceeds limits.
d. When the bleed valve closes
c. Bleed air temperature in related duct exceeds limits.
2. 10.6
- What is the function of the EEC?
a. It calculates power setting via the FMC.
b. N1 is used by the EEC to set thrust in three control modes: Normal and two alternates.
c. EEC uses thrust lever inputs to automatically control forward and reverse thrust.
d. Both b and c
d. Both b and c
7. 15.6 and 7.20.5
- Where is the engine oil pressure measured?
a. On the outlet side of the engine driven oil pump, prior to the fuel filter.
b. Prior to the fuel/oil heat exchanger
c. On the outlet side of the engine driven oil pump, prior to engine lubrication.
d. In the oil tank
c. On the outlet side of the engine driven oil pump, prior to engine lubrication.
(7. 20.9)
- What is the purpose of the isolation valve?
a. Allows separation of the bleed valves from the packs when required
b. Allows separation or connection of the left and right pneumatic systems when required
c. Isolates the hydraulic system from the pneumatic system during servicing
d. Isolates air conditioning system from the anit-ice system
b. Allows separation or connection of the left and right pneumatic systems when required
(2. 20.2)
- What are the in-flight operating limits of the APU?
a. Up to 10,000’ - Pneumatic and Electrical load
b. Up to 17,000’ - Pneumatic load only
c. Up to 41,000’ - Electrical load only
d. All of the above
d. All of the above
L.10.8
- When should the starter automatically cutout?
a. 20% N2
b. 25% N2
c. 35% N2
d. 56% N2
d. 56% N2
7. 20.11
- What are the power sources of igniters?
a. Left, respective AC Transfer Bus and Right Standby AC Bus
b. Left GEN BUS and Right Main Bus
c. Left AC Transfer bus and Battery Bus
d. Hot Batt Bus and Right AC Transfer Bus
a. Left, respective AC Transfer Bus and Right Standby AC Bus
7. 20.12
- Will the APU fire detection system automatically discharge the fire bottle?
a. Yes, but only if AC power is on the aircraft
b. No, it only shuts the APU down
c. No, you will only get the fire warning
d. Nothing will happen
b. No, it only shuts the APU down
8. 20.4
- What requirements must be met before Reverse is available?
a. Fire switch down
b. Either radio Altimeter sensing less than 10 feet, or the Air/Ground Sensor in the Ground Mode
c. Hydraulic pressure and battery power available
d. All of the above and Reverse selected
d. All of the above and Reverse selected
7. 20.14
- What is the purpose of the landing gear transfer unit?
a. Allows landing gear retraction in the event of a #1 engine failure
b. Allows the lowering of the gear in the event of a #1 engine failure
c. Allows both a and b
d. Allows for steering in the event of a system A hydraulic failure
a. Allows landing gear retraction in the event of a #1 engine failure
(13. 20.4)
- What are the temperature limits of the APU?
a. Start: 760˚C, No max continuous
b. Start: 760˚C, Max continous: 710˚C
c. Start: 710˚C, Max: 660˚C
d. Maximum limits are not displayed but are set by the ECU
d. Maximum limits are not displayed but are set by the ECU
7. 30.3
- What are the electrical sources for the 737?
a. Engine driven generators (2)
b. APU
c. Ground Power
d. Battery for Standby Bus
e. All of the above
e. All of the above
6. 10.13
- How are the primary flight controls normally powered?
a. “A” hydraulic system only
b. “B” hydraulic system only
c. By hydraulic systems “A” and “B”
d. Electro/mechanical only
c. By hydraulic systems “A” and “B”
9. 10.2 and 9.10.17
- How could the STBY RUDDER be activated manually?
a. Placing either or both system “A” and “B” flight control switches to STBY RUDDER
b. Placing the STBY hydraulic switch to “ON”
c. Placing the rudder switch to STBY
d. Both b and c
a. Placing either or both system “A” and “B” flight control switches to STBY RUDDER
(13. 20.4)
- Under what conditions would a IDG disconnect (either manually or automatically) be necessary when low lil is sensed by a DRIVE amber caution light?
a. High oil temperature
b. IDG Failure
c. Fire
d. Both a and b
d. Both a and b
6. 10.7
- Can the STBY hydraulic pump be activated by any additional method?
a. Yes placing eh STBY hydraulic switch to on
b. Yes placing the elevator switch to STBY
c. Yes placing the aileron switch to STBY
d. Yes by selecting the ALTERNATE FLAP MASTER switch to ON
d. Yes by selecting the ALTERNATE FLAP MASTER switch to ON
9. 20.22
- Which buses supply the “essential” loads?
a. The STANDBY buses
b. The TRANSFER buses
c. The ESSENTIAL buses
d. The MAIN buses
a. The STANDBY buses
6. 20.16
- What is the minimum fuel to operate the electric hydraulic pumps on the ground?
a. 1,675 lbs in each wing tank
b. 1,675 lbs in the right tank only
c. 1,676 lbs in the left tank only when the “B” system pumps are on
a. 1,675 lbs in each wing tank
13. 20.3
- Why is there a minimum fuel requirement to operate the electric hydraulic pumps?
a. To have enough fuel for thrust during flight control maneuvering
b. To keep the hydraulic pumps submerged for cooling
c. To prevent sloshing during ground taxi
d. The “A” and “B” system heat exchangers are located in the main tanks
d. The “A” and “B” system heat exchangers are located in the main tanks
(13. 20.3)
- What are the primary and the backup sources of power for the XFER BUSES?
a. Primary: Respective IDG. Backup: Opposite XFER BUS
b. Primary: Respective IDG. Backup: MAIN BUS
c. Primary: Respective MAIN BUS. Backup: STBY BUS
d. Primary: Respective MAIN BUS. Backup: STBY GEN.
a. Primary: Respective IDG. Backup: Opposite XFER BUS
6. 20.5
- At what degree of control wheel displacement does flight spoiler deployment begine to assist the airlerons in roll control?
a. 8 degrees
b. 12 degrees
c. 15 degrees
d. 10 degrees
d. 10 degrees
9. 20.5
- Does aileron trim physically effect control wheel position?
a. Yes. The control wheel position directly indicates the amount of aileron trim applied.
b. No. The control wheel will remain in the same position.
a. Yes. The control wheel position directly indicates the amount of aileron trim applied.
(9. 20.4)
- What is the function of a TR?
a. Convert 28 Vdc power to 115 Vac power
b. Convert 115 Vac power to 28 Vdc power
c. Provides power to the battery
d. Allows APU to power the buses
b. Convert 115 Vac power to 28 Vdc power
6. 20.1
- What is the voltage output of the TRs?
a. 28 Vdc
b. 115 +/- 5 volts
c. 22-28 volts
d. 400 +/- 10 volts
a. 29 Vdc
6. 20.10
- If the trailing edge flaps are extended by the alternate method, what flap protections are available.
a. None
b. Asymmetry but not skew
c. Skew but not asymmetry
d. Both skew and asymmetry
a. None
9. 20.22
- What powers the trailing edge flap down with the Alternate Flaps system selected?
a. System “A” hydraulic pressure
b. Standby hydraulic system pressure
c. An electric motor
d. The PTU (Power Transfer Unit)
c. An electric motor
9. 20.22
- When is the automatic Standby Power feature available?
a. When the STBY power switch is in the BAT position
b. It’s never automatic.
c. Always. It functions the same on the ground as in the air
d. Any time there is power on the aircraft
c. Always. It functions the same on the ground as in the air
(6. 10.8)
- Which of the following is not on the Hot Battery Bus?
a. APU and ENGINE fire bottle discharge
b. Fuel Shutoff Valves
c. External Power Control
d. Standby Rudder Shutoff Valve
d. Standby Rudder Shutoff Valve
6. 20.21
- If the system “B” electric pump or lines develop a leak, what would the indictions be?
a. System “B” quantity would decrease to approximately 1.84 gal.
b. System “B” quantity would decrease to approximately 1/2 full.
c. The quantity indications would go to zero. But sufficient fluid would be available to operate the power transfer unit.
d. System “B” quantity would remain full due to the blocking valve in the pump
c. The quantity indications would go to zero. But sufficient fluid would be available to operate the power transfer unit.
?
(12.20.3)
- If you lost all Standby system hydraulic fluid, would there be a cockpit indication?
a. Yes, but only if the Standby pump was operating at the time.
b. Yes. The Standby LOW QUANTITY light would be illuminated and System “B” reservoir would read between 1/2 and RFL.
c. No. However, you may notice lower quantity in the other reservoirs.
b. Yes. The Standby LOW QUANTITY light would be illuminated and System “B” reservoir would read between 1/2 and RFL.
(13. 20.8)
- What activates the Standby hydraulic pump?
a. Placing either flight control switch to STBY RUDDER
b. Placing the alternate flap switch to ARM
c. The 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 kts.
d. All of the above and activation of the FFM.
e. a and b only
d. All of the above and activation of the FFM.
13. 20.4
- What is the power source for APU start?
a. AC power if available
b. Main Battery only if AC not available
c. a and b
d. It is a pneumatic starter
c. a and b
7. 30.3
- Will the AUTOBRAKE DISARM light normally illuminate after takeoff with RTO selected?
a. Yes
b. No
b. No
14. 20.5
- When selected, at what speed is RTO available?
a. Above 60 kts
b. Above 80 kts
c. Above 90 kts
d. Above 110 kts
c. Above 90 kts
14. 20.4
- What is the maximum airspeed for retracting the landing gear?
a. 250 kts
b. 200 kts
c. 225 kts
d. 235 kts
d. 235 kts
Forward Instrument panel placard
- When is the fuel heated?
a. The fuel is constantly heated by a fuel/oil heat exchanger.
b. When you turn on the Fuel Heater switch
c. Automatically when the Fuel temperature is below 0 degrees
d. There is no requirement for fuel heat on this aircraft.
a. The fuel is constantly heated by a fuel/oil heat exchanger.
(7. 20.9)
- When retracting the high lift devices using the alternate method, will the LED’s return to the retracted position?
a. Yes
b. No
b. No
9. 10.4
- What are the two sources of power for the Ground Service Bus?
a. Transfer Bus #1
b. Main Bus #2
c. Ground power via the Ground Service switch on the F/A panel
d. Both a and c
e. Both b and c
d. Both a and c
6. 20.2
- When are the Ground Service Buses powered?
a. When external power is available and the Ground Service switch is ON, or both TRANSFER BUSES are powered.
b. When the Battery Switch is ON and the STBY Power Switch is in NORMAL
c. When the Battery Switch is ON or GEN BUS #1 is powered.
d. Automatically when the ground power is plugged in to the aircraft
a. When external power is available and the Ground Service switch is ON, or both TRANSFER BUSES are powered.
(6. 20.2)
- When is the latest you should wait for oil pressure to be indicated?
a. By the time the START VALVE OPEN light illuminates
b. By the time the OIL PRESSURE LOW light extinguishes.
c. By idle rpm
d. 25% N2
c. By idle rpm
NP.21.34
- The APU has an overheat warning system.
a. True
b. False
b. False
7. 30.3
- Must the Battery switch be on to operate the APU?
a. Yes, to provide fire detection when unattended
b. No, it’s not required
c. Yes, on the ground and in-flight
d. No, Battery is only required for starting.
c. Yes, on the ground and in-flight
7. 30.2
- Can the APU be started without the battery?
a. Yes, using the external DC receptacle
b. Battery is required for start on the ground but not in-flight
c. No, the battery is required
d. Yes using external AC power
c. No, the battery is required
7. 30.2
- What actuates the thrust reversers?
a. Hydraulic pressure
b. Electrical signal
c. Pneumatic pressure
d. All of the above
a. Hydraulic pressure
7. 20.15 and 13.20.1
- What do the Start Levers control?
a. Fuel
b. Hydraulics
c. ignition
d. Both a and c
d. Both a and c
7. 15.7
- How long should you operate teh APU before using it as a bleed air source?
a. one minute
b. Two minutes
c. No time requirement
d. None of the above
a. one minute
7. 30.3
- The EGPWS get position information from:
a. GPS position
b. Both FMCs
c. XM satellite
d. The multi-mode receivers through the DME/DME triangulation.
a. GPS position
15. 20.11
- When are the Aux and Main batteries tied together?
a. When selected in parallel
b. Never
c. At all times
d. When the batteries are the only source of power (except during start)
d. When the batteries are the only source of power (except during start)
(6. 20.1)
- What is the primary source for DC power?
a. Battery
b. APU
c. Three Transformer Rectifiers (TRs) and a ground service TR
d. XFER BUS
c. Three Transformer Rectifiers (TRs) and a ground service TR
(6. 20.10)