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141 Cards in this Set
- Front
- Back
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During the STBY power test, in BAT, the Stdby AC, Stdby DC and Bat buses should go to their alternate power sources.
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True.
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Which of the following is FALSE concerning the lights that should be on during the STBY POWER Test (OFF position)?
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IRS ON DC light OFF.
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A fully charged battery has sufficient capacity to provide power for a minimum of
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30 minutes.
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The auxiliary 28V DC power receptacle is situated
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Near the Battery in the electronic compartment.
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The auxiliary 28V DC power receptacle is situated
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Externally, forward of the E & E bay door.
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If the No. 2 TRU fails in the cruise
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There would be no immediate indication.
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Under normal flight, if the Battery switch is selected to OFF then
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The Battery Bus loses power.
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When the Generator Drive Temperature switch is selected to RISE, a higher than normal generator drive oil temperature indicates
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An excessive generator load or poor condition of the Generator Drive.
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When both engines are running with external power connected then
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External power will automatically disconnect when both engine generators are brought on line.
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A Generator Breaker can be closed
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When power quality from the generator is correct.
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What happens automatically when you raise the landing gear following a loss of the #1 engine during takeoff?
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Stby hydraulic pump transfers.
B/C transfers. Shed the galley and the transfer bus switches. |
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One of the basic principles of the electrical system is
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There is no paralleling of the AC sources of power.
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The Generator Drive LOW OIL PRESSURE lights are
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Amber lights on the forward overhead panel which will illuminate when Generator Drive oil pressure is below minimum operating limits.
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After operating the Generator Drive Disconnect switch the Generator Drive HIGH OIL TEMP (if illuminated) will
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Remain on, until the Generator Drive oil has cooled.
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Recoupling of the Generator Drive drive shaft to the engine may be accomplished
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Only on the ground.
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Generator Drive Disconnect switch when operated
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Disconnects the Generator Drive from the engine in the event of a Generator Drive malfunction.
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The STANDBY PWR OFF light (amber) illuminated means
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The AC standby bus is inactive.
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What happens if the Bus Transfer switch is OFF and GEN 1 loses power?
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The DC isolation relay is opened.
Transfer Bus 1 is unpowered. TR1 is unpowered. |
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When does the AC and DC Stby buses go to their alternate power source?
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Whenever Transfer bus 1 loses power or DC bus 1 loses power in flight.
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What can cause the DC Isolation relay to open?
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The Bus Transfer switch is placed to OFF.
GS capture with the F/D engaged. GS capture with the A/P engaged. |
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With the Bus Transfer Switch OFF, will the STBY HYD pump transfer?
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The Bus Transfer switch has no effect on the standby hydraulic pump.
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Should a Generator Drive develop a fault and be disconnected from the engine, before corrective action is taken by the pilots
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A few non-essential electrical systems ( loads ) will be lost.
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The T.R. voltage range is
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24 - 30 volts.
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How can you tell under normal conditions if the Field Relay is open?
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Select the respective generator on the AC selector switch. If the Field Relay is closed, you can read volts and frequency.
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After operating the Generator Drive Disconnect switch
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The APU should be started and the APU generator selected on-line.
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Under normal conditions the Standby AC bus is energised from the
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115-volt Transfer bus No. 1.
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The blue GRD POWER AVAILABLE light when illuminated indicates
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That the External Power Bus is powered by the ground power supply. Light remains illuminated as long as ground power is connected.
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What is the backup power source for the Bat Bus?
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Hot Bat Bus.
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You can read a voltage reading on a generator when you manually trip the Generator Breaker.
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False.
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If, in flight, both engine generators fail, the APU generator should be connected to
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The No. 2 Generator Bus.
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What is the back up power source for the Stby Bus AC?
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Bat through inverter.
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With the aircraft on the ground (both engine generators on-line) and external power connected up to the aircraft, momentarily positioning the Ground Power switch to ON
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Will trip both engine generators and connect external power to both generator busses.
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The Transfer Buses supply
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The Essential Loads.
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During the STBY POWER TEST, you should ensure that....
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Fueling is not in progress
The IRU's alignment is completed. |
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The battery voltage range is
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22 - 30 volts.
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What happens following the loss of engine #2?
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Transfer bus transfers and galley is shed.
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The APU can power both Generator Busses
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On the ground only.
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The Switched Hot Battery Bus is powered from
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The Hot Battery Bus whenever the Battery Switch is ON.
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You lose both generators during takeoff, above V1. At what point will you get all instruments associated with the STBY buses?
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At lift off.
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What voltage are you reading with external powering the aircraft and the DC selector to Bat?
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B/C voltage.
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When you get STBY power during lift off, will you regain your EADI and EHSI?
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Only if you get the transfer buses repowered somehow.
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What happens when the APU GB switch is placed to ON?
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Closes the Field Relay.
The GCU checks the acceptability of the APU power. Closes the associated APU generator Breaker. |
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Which of the following is FALSE concerning this situation: In flight, the aircraft starts filling with smoke. The procedure tells you to turn the Bus Transfer Switch OFF and Galley Power Switch OFF. Which of the following is TRUE?
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You isolated the L and R electrical systems.
You can further isolate sections of the electrical system by turning off the Generator Breakers. The field relays will stay closed. The STBY and BAT buses are still available. |
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Can the Transfer bus be unpowered with the TRANSFER BUS OFF light off?
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Yes, if the Norm Transfer Bus or Alt Transfer bus circuit breaker behind the FO is pulled.
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Which of the following is TRUE concerning TR failures?
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On TR3, both volts and amps would be zero.
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When the Generator Control Unit senses an under (or over) frequency, the Generator Breaker and Field Relay both trip.
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False.
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The maximum Generator Drive oil temperature / temperature rise is
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157C / 20C
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Placing the BUS TRANS switch to 'OFF' inflight with both generators operating and connected
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Isolates the transfer busses by preventing operation of the bus transfer relay, opens the TR 3 disconnect relay and prevents connection of the battery charger to its alternate power source ( Main Bus 2 ).
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The first action to be taken in the event of electrical failure of a generator (BUS OFF light illuminated) is
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Select the associated Generator switch to ON.
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The normal power source for the Battery Charger is the AC Ground Service Bus, with provisions for automatic switching to
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The No. 2 Main Bus.
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Pulling up an engine fire handle will
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Trip the associated Generator Control Relay and Breaker.
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If the Battery switch is selected OFF, the airstairs can be lowered from the outside
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By using the STANDBY system.
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To have all three Generators (APU and engines) on-line simultaneously
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Is not possible.
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With an engine Generator switch selected OFF and the associated engine is running, the voltage of that generator will read
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Residual volts when the residual volts switch is pressed.
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To connect the External Ground power to the aircraft's Generator busses
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The Battery switch must be ON.
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The APU is running and you close the Right APU GB. How many buses are NOT powered?
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3
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Failure of the No. 1 Generator Bus will
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Will cause failure of the System B Electric hydraulic pump.
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The Battery Switch is ON and the GRD PWR is connected to the aircraft's Busses. If the Battery Switch is selected OFF then
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The GRD PWR switch will automatically disconnect.
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Which of the following statements is correct
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TR 3 normally backs up TR 1 and TR 2 provided that the BUS TRANS switch is in AUTO.
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Standby A.C. power is available on touch down after a total electrical failure providing
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The Standby Power switch is selected to BAT.
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The APU generator has
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No Generator drive unit since the APU itself is governed and will maintain a constant generator speed.
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If ground power is available and the Ground Service switch on the forward attendant's panel is switched on, then power is supplied to
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The Ground Service bus for utility outlets, cabin lighting and battery charger.
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An engine electrical generator is rated at
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45 KVA
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The T/R No. 3 disconnect relay automatically opens at glideslope capture to
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Prevent a single bus failure from affecting both the navigation receivers and flight control computers.
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After disconnecting a Generator Drive, its associated oil temperature indicator
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May show an increase on the IN scale and/or the RISE scale.
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The Battery Switch must be
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ON for the GRD PWR Switch to be operable.
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Standby D.C. power is normally supplied from
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DC Bus No. 1.
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Which buses are not powered with the APU running and the R APU GB closed?
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Gen Bus 1, Main Bus 1 & Ground Service Bus.
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With the APU running, you close the L APU GB. What is not powered?
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Gen Bus 2, Main Bus 2, TR3.
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At glide slope capture, the Captain's FD goes away. You execute a Go-Around and everything returns to normal. Which of the following is correct?
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TR1 has failed.
At GS capture, the Disconnect Relay opens. TR3 can no longer power DC bus 1. |
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When starting the aircraft (first flight of the day), how can you verify the correct operation of the Transfer Relay?
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Put the right bus on first.
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What remains when you are down to STY buses?
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Comm1 radios; Stby Instruments; #1 IRS, Nav1 and ADF2; Igniters (R), fuel gauges, engine instruments, trust reversers with T/R, engine start valve open, low oil pressure lights, fire protection & detection.
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What is the minimum battery voltage?
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24 volts.
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The STANDBY PWR OFF light (amber) illuminated means
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The AC standby bus is inactive.
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Generator Drive Disconnect switch when operated
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Disconnects the Generator Drive from the engine in the event of a Generator Drive malfunction.
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Recoupling of the Generator Drive drive shaft to the engine may be accomplished
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Only on the ground.
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After operating the Generator Drive Disconnect switch the Generator Drive HIGH OIL TEMP (if illuminated) will
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Remain on, until the Generator Drive oil has cooled.
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The Generator Drive LOW OIL PRESSURE lights are
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Amber lights on the forward overhead panel which will illuminate when Generator Drive oil pressure is below minimum operating limits.
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One of the basic principles of the electrical system is
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There is no paralleling of the AC sources of power.
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The AC STANDBY BUS power can be supplied from
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The APU or engine generators, external power or the battery through the Static Inverter.
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A Generator Breaker can be closed
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When power quality from the generator is correct.
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Should a Generator Drive develop a fault and be disconnected from the engine, before corrective action is taken by the pilots
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A few non-essential electrical systems ( loads ) will be lost.
|
|
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When both engines are running with external power connected then
|
External power will automatically disconnect when both engine generators are brought on line.
|
|
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When the Generator Drive Temperature switch is selected to RISE, a higher than normal generator drive oil temperature indicates
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An excessive generator load or poor condition of the Generator Drive.
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Under normal flight, if the Battery switch is selected to OFF then
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The Battery Bus loses power.
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If the No. 2 TRU fails in the cruise
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There would be no immediate indication.
|
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The auxiliary 28V DC power receptacle is situated
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Near the Battery in the electronic compartment.
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A fully charged battery has sufficient capacity to provide power for a minimum of
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30 minutes.
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The Switched Hot Battery Bus is powered from
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The Hot Battery Bus whenever the Battery Switch is ON.
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The APU can power both Generator Busses
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On the ground only.
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The T.R. voltage range is
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24 - 30 volts.
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The battery voltage range is
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22 - 30 volts.
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The maximum Generator Drive oil temperature / temperature rise is
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157C / 20C
|
|
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The Transfer Buses supply
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The Essential Loads
|
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With the aircraft on the ground (both engine generators on-line) and external power connected up to the aircraft, momentarily positioning the Ground Power switch to ON
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Will trip both engine generators and connect external power to both generator busses.
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If, in flight, both engine generators fail, the APU generator should be connected to
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The No. 2 Generator Bus.
|
|
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The blue GRD POWER AVAILABLE light when illuminated indicates
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That the External Power Bus is powered by the ground power supply. Light remains illuminated as long as ground power is connected.
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Under normal conditions the Standby AC bus is energised from the
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115-volt Transfer bus No. 1.
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After operating the Generator Drive Disconnect switch
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The APU should be started and the APU generator selected on-line.
|
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The first action to be taken in the event of electrical failure of a generator (BUS OFF light illuminated) is
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Select the associated Generator switch to ON.
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The normal power source for the Battery Charger is the AC Ground Service Bus, with provisions for automatic switching to
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The No. 2 Main Bus.
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Pulling up an engine fire handle will
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Trip the associated Generator Control Relay and Breaker.
|
|
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If the Battery switch is selected OFF, the airstairs can be lowered from the outside
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By using the STANDBY system.
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To have all three Generators (APU and engines) on-line simultaneously
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Is not possible.
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|
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With an engine Generator switch selected OFF and the associated engine is running, the voltage of that generator will read
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Residual volts when the residual volts switch is pressed.
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To connect the External Ground power to the aircraft's Generator busses
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The Battery switch must be ON.
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Standby D.C. power is normally supplied from
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DC Bus No. 1.
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Failure of the No. 1 Generator Bus will
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Will cause failure of the System B Electric hydraulic pump.
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Placing the BUS TRANS switch to 'OFF' inflight with both generators operating and connected
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Isolates the transfer busses by preventing operation of the bus transfer relay, opens the TR 3 disconnect relay and prevents connection of the battery charger to its alternate power source ( Main Bus 2 ).
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Which of the following statements is correct
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TR 3 normally backs up TR 1 and TR 2 provided that the BUS TRANS switch is in AUTO.
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Standby A.C. power is available on touch down after a total electrical failure providing
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The Standby Power switch is selected to BAT.
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The APU generator has
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No Generator drive unit since the APU itself is governed and will maintain a constant generator speed.
|
|
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If ground power is available and the Ground Service switch on the forward attendant's panel is switched on, then power is supplied to
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The Ground Service bus for utility outlets, cabin lighting and battery charger.
|
|
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An engine electrical generator is rated at
|
45 KVA
|
|
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The T/R No. 3 disconnect relay automatically opens at glideslope capture to
|
Prevent a single bus failure from affecting both the navigation receivers and flight control computers.
|
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After disconnecting a Generator Drive, its associated oil temperature indicator
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May show an increase on the IN scale and/or the RISE scale.
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The Battery Switch must be
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ON for the GRD PWR Switch to be operable.
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The Battery Switch is ON and the GRD PWR is connected to the aircraft's Busses. If the Battery Switch is selected OFF then
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The GRD PWR switch will automatically disconnect.
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What happens in the event the Bus Transfer switch is in the OFF position and GEN 1 falls?
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DC isolation relay open, DC bus 1 is also unpowered
L and R electrical systems isolated No transfer of AC Transfer Bus therefore T/R1 to be without powered. or Battery Charger |
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How can you tell if the Generator Field Relay is open?
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Select AC selector switch
Read voltage and frequency, field relay is closed. |
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TR1 indicates VOLTS but zero AMP reading. Is this normal?
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TR1 has failed.
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What is the indication that TR3 has failed?
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ZERO volts and amps.
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What is avail. when operating on STBY busses?
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1- COMM 1 radios
2-STBY instruments 3-#1 IRS, 1# NAV, and ADF2 4-R igniters, fuel gauges, certain eng. instruments (all on EIS aircraft), thrust reversers, engine start valve open, low oil pressure lights, and fire protection and detection. 5-Manual DC pressurization. |
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What can cause the DC isolation relay open?
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GS capture with either F/D or A/P engaged
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The # 1 GEN fails in flight and there is no backup.Which buses are lost?
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1-GEN BUS 1
2-MAIN BUS 3-GROUND service bus |
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What would cause the field relay to open?
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Any problem other than frequency
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Is it possible for the Transfer Bus to be unpowered without an illuminated TRANSFER BUS OFF light?
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YES
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What equipment transfers to a different power source in the event you loose an engine?
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STBY Hyd pump (eng 1)
BATT charger (eng 1) Transfer bus (both engines) |
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How do you verify the correct operation of the Transfer Relay
after starting the APU? |
Put the right Bus on first, next bring the left bus on.
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What voltage is read in the battery position while external power is connected?
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BATT CHARGER voltage.
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What is the normal output of the engine driven generators?
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115 VOLTS
400 HZ |
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What prevents a generator from supplying unacceptable power to the electrical system?
|
GCU
Genrator Control Unit |
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What can the APU generator directly supply?
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Both GEN Busses
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How is the APU generator output controlled?
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By controlling the APU RPMs
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Which of the following is true concerning the TR3 disconnect relay?
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Isolates DC BUS 1 from DC BUS 2
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How long can a fully charged battery supply the essential equipment?
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:30 Minutes
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What temperature is measured when the CSD temperature switch is in the rise position?
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The difference between the CSD oil outlet temperature and the CSD oil inlet temperature.
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What does the bus transfer switch do in the auto position?
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It allows main bus 2 to provide backup power to the battery charger.
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What does the bus transfer switch do in the auto position?
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It allows main bus 2 to provide backup power to the battery charger.
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What does the ground power available light indicate?
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Ground is plugged in.
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What is the normal TR output?
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24-30 volts
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