Electrical System, Fire Protection And Detection System

23 Questions | Total Attempts: 105

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Electrical Quizzes & Trivia

The electrical system for an airliner is a very sensitive subject and a mechanic must ensure there are no possibilities for a fire occurring due to electrical wiring problems, as it can be catastrophic. The quiz below is designed to test out how much you know about wiring a Boeing 737. Give it a shot!


Questions and Answers
  • 1. 
    What does the illumination of the “elec” light on the electrical panel indicate:
    • A. 

      A fault has been detected in the AC or standby power system.

    • B. 

      A fault has been detected in the DC or standby power system.

    • C. 

      A fault has been detected in the DC and standby power system.

    • D. 

      A fault has been detected in the AC and standby power system.

  • 2. 
    How is the main battery charger powered:
    • A. 

      By the DC ground service bus 2

    • B. 

      By the AC ground service bus 1

    • C. 

      By the DC ground service bus 1

    • D. 

      By the AC ground service bus 2

  • 3. 
    With the standby power switch in the AUTO position, what will cause automatic switching to the Alternate power source:
    • A. 

      AC transfer bus 1 or DC bus 2 loses power

    • B. 

      AC transfer bus 1 or DC bus 1 loses power

    • C. 

      DC transfer bus 1 or DC bus 2 loses power

    • D. 

      DC transfer bus 1 or DC bus 1 loses power

  • 4. 
    After a generator drive disconnect, can the drive be re-engaged:
    • A. 

      Yes, in flight

    • B. 

      Only on the ground (by maintanance)

    • C. 

      Yes on ground (by flight crew)

    • D. 

      No

  • 5. 
    What is the normal supply to the battery bus:
    • A. 

      By the AC ground service bus 1

    • B. 

      By the DC ground service bus 1

    • C. 

      By the AC ground service bus 2

    • D. 

      By the DC ground service bus 2

  • 6. 
    When will the switched hot battery bus be powered by a functional battery:
    • A. 

      With APU running

    • B. 

      When Ground Power is connected

    • C. 

      Always

    • D. 

      When the battery switch is selected to ON

  • 7. 
    What does illumination of the “GND Power Available” light indicate:
    • A. 

      That DC ground power is connected

    • B. 

      That AC ground power is connected and meets airplane power quality standards

    • C. 

      That Ground power can be requested

    • D. 

      That the power is 3 phased and grounded

  • 8. 
    In flight, what does illumination of the “TR UNIT” light indicate:
    • A. 

      TRU1 or TRU2 and TRU3 have failed.

    • B. 

      TRU1 Failed

    • C. 

      TRU2 Failed

    • D. 

      All TRU's Failed

  • 9. 
    In flight, the output from no1 IDG fails. How is power AC transfer bus 1 restored:
    • A. 

      Via power x-feed switch

    • B. 

      Manually from AC transfer bus 2 via the AC tie bus.

    • C. 

      Automatically from AC transfer bus 2 via the AC tie bus.

    • D. 

      Automatically from the battery

  • 10. 
    Following the loss of an IDG, with a single generator operating, which loads are initially shed:
    • A. 

      Galley A

    • B. 

      Galley B

    • C. 

      Galley bus A + B (shed from transfer bus 1)

    • D. 

      Galley bus A + B (shed from transfer bus 2)

  • 11. 
    What are the normal AC volts and frequancy for the 2 engine driven generators and the APU generator:
    • A. 

      115 v (+/- 5 v) and 400Hz (+/- 10 Hz)

    • B. 

      220 v (+/- 5 v) and 400Hz (+/- 10 Hz)

    • C. 

      115 v (+/- 5 v) and 600Hz (+/- 10 Hz)

    • D. 

      220 v (+/- 5 v) and 600Hz (+/- 10 Hz)

  • 12. 
    What is the battery voltage:
    • A. 

      24 volts DC. Range is 22 to 30 volts and supplies standby power for 30 minutes (single battery)

    • B. 

      24 volts DC. Range is 22 to 30 volts and supplies standby power for 60 minutes (single battery)

    • C. 

      28 volts DC. Range is 22 to 30 volts and supplies standby power for 30 minutes (single battery)

    • D. 

      28 volts DC. Range is 22 to 30 volts and supplies standby power for 60 minutes (single battery)

  • 13. 
    DC power is supplied by 3 TR units. What is the output Voltage:
    • A. 

      28 volts DC.

    • B. 

      24 volts DC

    • C. 

      24 volts AC

    • D. 

      28 volts AC

  • 14. 
    Where does TRU no 2 receive its AC power from:
    • A. 

      AC transfer bus 2

    • B. 

      AC transfer bus 1

    • C. 

      From hot battery bus

    • D. 

      From battery bus

  • 15. 
    The aircraft is on the ground on stand, with engines running, and both generators on line. External power is available. What will positioning the ground power switch to ON do:
    • A. 

      Trip both engine generators and APU

    • B. 

      Connect external power and keep generators running.

    • C. 

      Trip both engine generators and connect external power and connect external power to the transfer busses.

    • D. 

      Ground power can not be connected with engines running.

  • 16. 
    With AC power on the bus bars, no system faults, and OVHT DET switches in NORMAL, selecting OVHT/FIRE on the test switch will illuminate wich lights:
    • A. 

      Master FIRE WARNING lights

    • B. 

      Master caution lights

    • C. 

      Master FIRE WARNING lights, ENG1+ENG2 and APU fire switch lights, and WHEEL WELL FIRE light, Plus the MASTER caution lights, OVHT/DET annunciator and the ENG+ENG OVERHEAT lights.

    • D. 

      OVHT/DET Lights

  • 17. 
    With the OVHT/DET switch in the normal position, and both loobs servicable, when will engine fire warning be activated:
    • A. 

      If one loop detects a fire or a overheat condition.

    • B. 

      When both loops detect a fire condition.

    • C. 

      When both loops detect a overhead condition

    • D. 

      When both loops detect a fire condition or an overheat condition

  • 18. 
    Illumination of the FAULT light on the Overheat/Fire detection panel indicates what:
    • A. 

      With the Overheat Detector in the NORMAL position, one loop has failed

    • B. 

      With the Overheat Detector in the NORMAL position, Both loops have failed.

    • C. 

      With the Overheat Detector in the AUTO position, Both loops have failed.

    • D. 

      With the Overheat Detector in the AUTO position, one loop has failed.

  • 19. 
    If a malfunction in one fire loop occurs, with the OVHT DET switch in the normal position, do you still have detection availiable:
    • A. 

      No, if a malfunction occurs, system is not availiable for the rest of the flight.

    • B. 

      Yes. The defective loop is removed, and the remaining loop continues functioning as a single loop detector.

    • C. 

      Yes, but the switch must be put in ALTN selection

    • D. 

      Yes, but a amber OVHT light wil illuminate for the rest of the flight.

  • 20. 
    The power source for the APU fire extinguishing system is the:
    • A. 

      DC transfer bus 2

    • B. 

      The hot battery bus (28v DC)

    • C. 

      Ground power

    • D. 

      DC transfer bus 1

  • 21. 
    The power source for the ENG Overheat and Fire Protection detection system is:
    • A. 

      Battery bus (28v DC)

    • B. 

      Hot battery bus

    • C. 

      Transfer bus 1

    • D. 

      Transfer bus 2

  • 22. 
    When the extinguisher test switch is held in the 1 or 2 position, 3 green lights should illuminate. What does this indicate:
    • A. 

      The associated bottle discharge circuits for all 3 extinguisher bottles are normal.

    • B. 

      That wheel extinguishers are tested and ok

    • C. 

      The bottles are armed and have surficient contense

    • D. 

      The three wheel well areas are tested for overheat.

  • 23. 
    The engine fire warning switch lock mechanism is automatically unlocked when:
    • A. 

      It is put in AUTO mode.

    • B. 

      Either the fire warning or overheat light illuminates.

    • C. 

      When aircraft is in flight.

    • D. 

      Engine ignition key is put in

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