Primary Systems 2 Exam | Questions and Answers (Complete Solutions)

Primary Systems 2 Exam | Questions and Answers (Complete Solutions) Which of the following are correct major components of the electrical system? A. External power receptacle, starter/generator, and backup alternator B. Starter/generator, external power receptacle, and AC/DC power converter C. Starter/generator, 24 VDC battery, and backup 28 vdc battery pack D. Starter/generator, 24 VDC auxiliary battery True/False: The aircraft electrical system includes a 28 VDC 300 amp starter/generator, 24 VDC lead acid battery, 24 VDC auxiliary battery, and an external power receptacle True True/False: The aircraft electrical system includes a 28 VDC 300 amp starter/generator, 28 VDC battery, 28 VDC auxiliary battery, and an external power receptacle False The primary aircraft electrical power is powered by the ________ A. Alternator B. Auxiliary Battery C. Main Battery D. Generator The generator output provides ________ VDC, and is capable of supplying __________ amps A. 24; 300 B. 24; 1000 C. 28; 300 D. 28; 1000 The starter/generator is regulated and monitored by a _________ located under a panel in the aft cockpit A. Voltage regulator B. Power Management Unit C. Generator Control Unit D. Generator over voltage regulator Generator power is controlled by the ________ switch located on the right forward switch panel in each cockpit A. Generator Control (GEN) B. Auxiliary Battery (AUX BAT) C. Bus Tie (BUS TIE) D. Generator Reset (GEN RESET) When the occupant of either cockpit moves the generator control switch to ON, the switch in the other cockpit (if already selected ON) _________ A. Remain in the ON position B. Is locked in its current position C. Is tripped to the OFF position D. Trips the GEN SW circuit breaker The ability to control the generator control switch is:________ A. Transferable between cockpits B. Permanently assigned to the rear cockpit C. Permanently assigned to the front cockpit D. Transferred automatically if either cockpit control fails Under normal operating conditions, aircraft electrical power is distributed across the ________ and the __________ A. Standby bus; external power bus B. External power bus; battery bus C. Generator Bus; battery bus D. Standby bus; generator bus The BUS TIE switch on the right forward switch panel in the front cockpit is used to _______ A. Tie the battery bus and generator bus together for emergency operation B. Tie the battery bus and generator bus together for normal operation C. Control the power from the generator D. Connect the power for all the avionics and radio systems in both cockpits Circuit breakers labeled FWD AVI and AFT AVI control front and rear avionics buses and are located on front cockpit ______ A. Right forward switch panel B. Generator bus circuit breaker panel only C. Battery bus and generator bus circuit panels D. Battery bus circuit breaker panel only The battery powers select aircraft systems if the generator is not available, and provides power for _______ A. Charging the auxiliary battery B. Engine Starts C. The Auxiliary Generator D. Starting the generator prior to engine start The aircraft battery is rated to provide _______ VDC A. 18 B. 22 C. 24 D. 28 The _______ switch must be set to ON for external power to be available to the aircraft A. Generator B. Auxiliary battery C. Battery D. Avionics master External aircraft lighting for the aircraft is controlled by four individual switches which are the _________ switches located on the trim control panel in the front cockpit A. LDG, NAVY, STROB, and FLOOD B. LDG, STROB, FLOOD and NAV C. LDG, TAXI, STROB, and FLOOD D. LDG, TAXI ANTI-COL and NAV The landing light will come on _______ A. Only when the LDG and taxi switches are both on and the landing gear are down and locked B. Automatically when there is low ambient light C. Anytime the LDG switch is on D. Only when the LDG switch is on and the landing gear are down and locked True/False: Knee board lights mounted on the front of each forward and aft glareshield, intensity for these lights are controlled by the FLOOD light rheostat on the trim control panel in each cockpit False When using the primary T-6B refueling method, the aircraft fuel system provides approximately _________ of usable fuel (JP-8) A. 1000 pounds B. 1100 pounds C. 1200 pounds D. 2100 pounds When using the primary refueling method, the maximum fuel quantity for one wing tank is ________ A. 500 pounds B. 530 pounds C. 560 pounds D. 620 pounds True/False: The aircraft can hold a maximum of 1200 pounds of usable fuel (JP-8) stored between the left and right wing tanks as well as a collector tank. True What is the primary method of refueling for the aircraft A. Combat refueling B. In-flight refueling C. Single point pressure refueling D. Over the wing gravity refueling Which method of refueling allows the wing tanks to be filled simultaneously? A. Tanker refueling B. Over the wing gravity refueling C. Combat refueling D. Single point pressure refueling True/False: The collector tank normally remains full since most flights will not use the total volume of fuel. However, during ground refueling operations, if it is depleted; fuel will gravity feed to the collector tank from the wing tanks. True The ___________ provides fuel for initial engine start and acts as a backup to the engine-driven low pressure fuel pump A. Electric boost pump B. Engine-driven high-pressure fuel pump C. Primary jet pump D. Transfer jet pump Fuel is directed to the collector tank from each wing tank by _________, keeping the collector tank pressurized A. The electric boost pump B. A primary jet pump C. Two transfer jet pumps D. The collector tank pressure pump Fuel is directed from the collector tank to engine driven low pressure fuel pump by _________ A. Collector tank pressure pump B. Transfer jet pump C. Primary jet pump D. Fuel management unit True/False: The fuel is pumped through the engine feed line to the fuel filter, which prevents contaminants from reaching the main fuel pumps or engine. If the filter becomes restricted the engine will flame out due to fuel starvation. False During operation of the fuel system, fuel routed from the engine-driven low pressure pump down the motive flow line is used to drive the ________ and ________ A. Primary jet pump; endings-driven high pressure pump B. Transfer jet pumps; engine-driven high pressure pump C. Electric boost pump; transfer jet pumps D. Primary jet pump; transfer jet pumps A pressure switch in the motive flow line activates the ________ anytime fuel pressure drops below 10psi. A. Transfer jet pumps B. Primary jet pump C. Engine-driven high pressure pump D. Electric boost pump The fuel gauging system uses seven fuel probes inside the fuel tanks to __________ A. Send a signal to the engine indicating and Crew Alerting System (EICAS) for visual display of fuel quantity B. Reduce corrosion within the fuel tank C. Transmit the fuel from the wing tanks to the collector tank D. Send a signal to the AEDD for visual display of fuel flow The left and right fuel quantity tanks on the EICAS turn yellow when indicated fuel quantity is the respective tank is below________ A. 75 pounds B. 110 pounds C. 150 pounds D. 175 pounds True/False: The fuel low level sensors light the "L FUEL LO" or "R FUEL LO" messages on the EICAS when the fuel level falls below 150 pounds in the respective tank. False Display of the FUEL BAL message may indicate an imbalance exceeding _________ pounds for more than two minutes between the left and right fuel tanks, or a failure of the autobalance system A. 20 B. 30 C. 50 D. 70 the fuel system incorporates an auto balance system which maintains the fuel load in each wing tank to within ______ pounds of the other wing A. 30 B. 70 C. 20 D. 50 The fuel balance switch has two positions; _________ or ___________ and is located ______ A. OFF or NORM; right front side in forward cockpit B. OFF or NORM; right front side in rear cockpit C. MAN/RESET or AUTO; right front side in forward cockpit D. MAN/RESET or AUTO; right front side in rear cockpit True/False: Wing tanks are vented to the atmosphere as well as each other through vent lines which provide vacuum and pressure relief for the tanks True If a fuel imbalance is detected by the _______ of 20 pounds or more for more than 30 seconds, the appropriate transfer (solenoid) valve is activated to close the motive flow line to the lighter tank A. Fuel Management Unit (FMU) B. Engine Data Manger (EDM) C. Power management unit (PMU) D. Fuel data manager (FDM) If the auto balance system shuts off without reducing fuel imbalance to 30 pounds or less, the auto balance system may be reset to provide an additional ________ to balance the fuel load A. 20 seconds B. 30 seconds C. 1 minute D. 2 minutes What three elements are necessary for engine operations? A. Fuel, oil, and heat B. Air fuel, and heat C. Air, oil, and fuel D. Heat, smoke and fire The engine cowling performs all of the following functions except _________ A. Protect the engine components B. Provide an engine air intake C. Decreases drag D. Secure engine to aircraft airframe What are the two major components of the propulsion system? A. Propeller and reduction gearbox B. PCL and engine C. Engine cowling and PCL D. Engine and propeller What are the three sections of the engine? A. Accessory compartment, compression section, and combustion section B. Compression, combustion, and reduction areas C. Compression, combustion, and power sections D. Accessory compartment, gas generation section, and power turbine section After combustion occurs in the combustion chamber, the expanding gases_________ A. Drive the reduction turbine B. Reverse direction C. Drive the compressor turbine, then the power turbine D. Drive the power turbine, then the compressor turbine The aircraft is equipped with a free turbine, reverse flow design turboprop engine, what is meant by the term "free turbine"? A. Air flow the compressor does not drive the power turbine, as they are physically connected B. Air flow from the compressor drives the power turbine, as they are not physically connected C. This is where the free air temperature is measured D. Air flow from the lower air inlet cowling drives the power turbine When starting the aircraft, the power control lever (PCL) should be ____________ A. Pushed forward to the IDLE position B. Pushed forward to the START/IDLE/ detent is reached C. Pushed forward until a green ST READY message is illuminated on the EICAS display D. Pushed towards until a green IGN SEL message is illuminated on the EICAS display True/False: Friction control settings made to the front cockpit power control lever (PCL) has no effect on the rear cockpit PCL. False The front cockpit power control lever (PCL) is _______ connected to the fuel management unit (FMU) by a flexible cable as well as ________ connected to the FMU by way of the power management unit (PMU) A. Electrically; pneumatically B. Mechanically; hydraulically C. Mechanically; electrically D. Hydraulically; electrically The PMU performs the following functions, except: a. maintains engine and propeller within operating limits b. keep fuel balance within limits c. determines available power and provides a near linear response between PCL idle and max positions d. fine tunes the power request and sends an electronic signal to the FMU The primary power source for the PMU comes from the ________ A. Permanent Magnet Alternator (PMA) B. Generator bus C. Battery bus D. Engine data manager (EDM) The power management unit (PMU) ____________ A. Processes all data for the EICAS display in each cockpit B. Displays available oil pressure in each cockpit C. Records all flight data D. Keeps the engine and propeller within operating limits The starter/ generator ___________ until the engine starts and is able to sustain itself A. Turns the propeller B. Turns the power turbine C. Provides fuel D. Turns the compressor True/False: Once the engine is started, and the ignition switch is in the ON position, igniters are automatically energized and de energized by the PMU. False Once the engine start sequence is completed, the starter functions _________ A. As a 28VDC generator B. as a backup to start automatically in case of failure C. As the main to drive to the accessory gear box D. As a 28VDC alternator The oil system provides filtered oil to all of the following systems, except ____________ A. Reduction gears B. Wheel brakes C. Propeller D. Engine bearings True/False: Scavenge pumps are designed to return oil from the engine bearings, reduction gears, accessory drives and propeller back to the main oil tank. This scavenged oil is first routed through an oil cooler before the oil is returned True During steady state conditions, normal oil pressure should be between __________ (green area on the gauge) A. 120-200 B. 40-90 C. 90-120 D. 40-130 psi With a loss of oil pressure to the pitch change mechanism, the __________ and ___________ move the propeller to feather A. Airflow; feathering spring B. Feathering spring; torque probe C. Airflow; counterweights D. Counterweights; feathering springs Which propeller position will the propeller be in during most flight conditions? A. Low propeller pitch B. Feather position C. High propeller pitch D. Thrust position The ________ and the ___________ control propeller speed to maintain a constant propeller speed of 2000RPM and achieve varying levels of thrust by automatically adjusting propeller pitch A. Feathering spring; regulator unit B. Toque probe; scavenge unit C. Fuel flow regulator; fly weights D. PMU; propeller interface unit The engine data manager performs all of the following, except ____________ A. Monitors and processes engine operating parameters B. Provides discreet alerts to each IAC when necessary C. Drives the engine instrument display D. Monitors and processes AOA data True/False: All of the functions performed by the engine data manager (EDM) are engine related False The engine data manager (EDM) also performs non-engine related functions such as _____________ A. Fuel balancing and fuel quantity indications B. Determination and display of DC volts and amps C. Determination and display of cockpit pressure altitude and differential pressure D. All of the above The engine indication and crew alerting display provides _________ with a visual indication of _________ A. Each cockpit; primarily flight data information B. The front cockpit only; endings and auxiliary instrument information C. Each cockpit; engine and auxiliary instrument information D. The rear cockpit only; primary flight data information The engine and crew alerting system (EICAS) ___________ A. Transmits engine data to air data computer B. Records engine data for aircraft analysis C. Governs engine operating parameters D. Provides each cockpit with a visual indication of engine operations On the engine indication and crew alerting system (EICAS) display, △P measures _____________ A. The difference between cockpit altitude and outside altitude B. The fuel difference between wing tanks C. The difference between optimal and actual hydraulic pressure D. The difference between cockpit pressure and outside pressure The middle column of the engine indication and crew alerting system (EICAS) display contains what information? A. Torque B. Interstate turbine temperature (ITT) C. Gas generator speed (N1) D. All the above The right side (column) of the engine indication and crew alerting system (EICAS) display contains all the following information, EXCEPT ___________ A. Oil pressure B. Oil temperature C. Fuel flow D. Hydraulic pressure The left side (column) of the engine indication and crew alerting system (EICAS) display contains what information? A. B. Fuel quantity, bingo, fuel flow, indicated outside air temperature, current amperage draws, bus voltage, oil temperature, oil pressure, and hydraulic C. Fuel quantity, bingo, fuel flow, indicated outside air temperature, current amperage draw, bus voltage, cockpit altitude and differential pressure D. Torque, interstate turbine temperature (ITT), and gas generator speed (N1) In the event of an out of limits torque indication, the EICAS display will warn the pilot by all of the following methods, EXCEPT