Mfe - 2A651 Vol 5 Unit Review

100 Questions | Total Attempts: 33

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Electrical Quizzes & Trivia

Questions and Answers
  • 1. 
    After reviewing the aircraft/engine forms, where should you begin troubleshooting?
    • A. 

      Discuss problem with other journeymen in the shop.

    • B. 

      Check each part of every system.

    • C. 

      Examine the most complex unit.

    • D. 

      Observe gauge indications.

  • 2. 
    All of the options listed below are proper troubleshooting practices except
    • A. 

      Checking the applicable trouble areas.

    • B. 

      Understanding the function of each engine unit.

    • C. 

      Performing easy checks, then going to more difficult checks.

    • D. 

      Inspecting other areas after isolating the trouble between points.

  • 3. 
    Aircraft power plant and engine intermediate maintenance technical orders (TO) contain information on troubleshooting. This information is presented in the form of
    • A. 

      Fix-it diagrams.

    • B. 

      Power plant charts.

    • C. 

      Mechanical drawings.

    • D. 

      Troubleshooting charts.

  • 4. 
    To become an expert troubleshooter, you must
    • A. 

      Be a 7-level.

    • B. 

      Have at least 5 years experience.

    • C. 

      Attend college courses in troubleshooting techniques.

    • D. 

      Understand the function of each unit within each system.

  • 5. 
    The F100-PW–220 engine monitoring system component that acquires fault data from the digital electronic engine control (DEEC) and logs the faults with the time of their occurrence is the
    • A. 

      Data collection unit (DCU).

    • B. 

      Ground station unit (GSU).

    • C. 

      Engine analyzer unit (EAU).

    • D. 

      Engine diagnostic unit (EDU).

  • 6. 
    An understanding of the operating principles of engine instruments will help you decide
    • A. 

      If an engine should be removed from an aircraft.

    • B. 

      If the engine should be sent to the test cell.

    • C. 

      The meanings of the instrument readings.

    • D. 

      What tools are required for maintenance.

  • 7. 
    Most engine monitoring gauges and instruments require some type of
    • A. 

      Electrical valve to the indicator.

    • B. 

      Metal tubing for electron flow.

    • C. 

      Radio frequency transmitter.

    • D. 

      Transmitter and indicator.

  • 8. 
    Which jet engine temperature is not measured?
    • A. 

      Exhaust gas.

    • B. 

      Turbine inlet.

    • C. 

      Combustion inlet.

    • D. 

      Fan turbine inlet.

  • 9. 
    A typical jet engine exhaust gas temperature (EGT) indicating system contains thermocouples, leads, an indicator, and
    • A. 

      Resistor.

    • B. 

      Turbine inlet.

    • C. 

      Control valve.

    • D. 

      Exhaust duct.

  • 10. 
    The engine fuel-flow indicating system of most jet powered aircraft contains a fuel-flow
    • A. 

      Transmitter and a float valve.

    • B. 

      Control valve and a float valve.

    • C. 

      Transmitter and a fuel-flow indicator.

    • D. 

      Control valve and a fuel-flow transcriber.

  • 11. 
    The fuel system component of a jet engine that operates by using a water wheel concept is the
    • A. 

      Fuel-flow generator.

    • B. 

      Fuel-flow indicator.

    • C. 

      Fuel-flow transmitter.

    • D. 

      Fuel remaining counter.

  • 12. 
    The fuel-flow indicator indicates the rate of fuel-flow as
    • A. 

      Pounds per hour.

    • B. 

      Gallons per hour.

    • C. 

      Pounds per minute.

    • D. 

      Gallons per second.

  • 13. 
    Two units that work together to indicate that the oil system is operating correctly are the oil pressure
    • A. 

      Transmitter and indicator.

    • B. 

      Relief valve and indicator.

    • C. 

      Relief valve and transmitter.

    • D. 

      Synchronous unit and indicator.

  • 14. 
    The oil pressure indicator receives an electrical signal from the
    • A. 

      Gyro.

    • B. 

      Transmitter.

    • C. 

      Hydraulic unit.

    • D. 

      Synchronous unit.

  • 15. 
    The two primary units of the tachometer indicating system are the tachometer generator and tachometer
    • A. 

      Indicator.

    • B. 

      Fuse panel.

    • C. 

      Transformer.

    • D. 

      Thermocouple.

  • 16. 
    The N2 tachometer generator is usually driven from the tachometer drive located on the
    • A. 

      Engine accessory section.

    • B. 

      Engine turbine section.

    • C. 

      Combustion case.

    • D. 

      Fuel control.

  • 17. 
    The tachometer indicator is
    • A. 

      An electric direct-drive type instrument.

    • B. 

      An electric-magnetic-drag-type instrument.

    • C. 

      A mechanical direct-drive-type instrument.

    • D. 

      A mechanical-magnetic-drag-type instrument.

  • 18. 
    The exhaust nozzle position indicating system found on engines with afterburners is important because it
    • A. 

      Helps the pilot determine engine power.

    • B. 

      Helps the pilot determine fuel consumption.

    • C. 

      Gives the pilot indications of electrical failures.

    • D. 

      Aids the pilot in selection of proper altitude levels.

  • 19. 
    On engines with afterburners, the position of the exhaust nozzle is converted into an electrical signal by a
    • A. 

      Rheostat.

    • B. 

      Rectifier.

    • C. 

      Transducer.

    • D. 

      Transformer.

  • 20. 
    One type of overheat detector unit used on aircraft engines consists of a hollow stainlesssteel tube that covers
    • A. 

      One gold contact.

    • B. 

      Two silver contacts.

    • C. 

      Three bronze contacts.

    • D. 

      Four copper contacts.

  • 21. 
    What is used to indicate the amount of thrust a dual-compressor engine is producing?
    • A. 

      Engine pressure ratio (EPR).

    • B. 

      Exhaust gas temperature (EGT).

    • C. 

      Revolutions per minute (RPM).

    • D. 

      Turbine inlet temperature (TIT).

  • 22. 
    The pressures used in the operation of the engine pressure ratio (EPR) system are the
    • A. 

      Engine inlet total pressure and exhaust total pressure.

    • B. 

      Exhaust total pressure and turbine inlet total pressure.

    • C. 

      Inlet total pressure and compressor discharge total pressure.

    • D. 

      Compressor discharge total pressure and turbine inlet total pressure.

  • 23. 
    Inlet pressure (Pt2) is transmitted from its sensing point
    • A. 

      Electrically.

    • B. 

      Mechanically.

    • C. 

      Hydraulically.

    • D. 

      Through tubing.

  • 24. 
    The direct oil pressure gauge on a test cell is connected to an engine oil pressure line. This configuration will indicate oil pressure without using wiring, indicator, or
    • A. 

      Engine transformer.

    • B. 

      Aircraft transformer.

    • C. 

      Engine transmitter.

    • D. 

      Aircraft transmitter.

  • 25. 
    The test cell exhaust gas temperature (EGT) selector allows selection of
    • A. 

      The EGT parameter for transit speeds.

    • B. 

      Accuracy check switch during adjustment.

    • C. 

      The EGT indicator to be read in digital or analog.

    • D. 

      Individual thermocouple inputs or an average of these inputs.

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