ELECTRICS (737-3/4/500 Only)Multiple-choice exercise

Top of Form1The STANDBY PWR OFF light (amber) illuminated means

 The Battery Bus is inactive.The DC standby bus is inactive.The AC standby bus is inactive.

2Generator Drive Disconnect switch when operated Disconnects the Generator Drive from the engine in the event of a Generator Drive malfunction.Disconnects the Generator Drive from the generator in the event of a Generator Drive malfunction.Disconnects the Generator Drive from the engine in the event of a Generator Drive malfunction, only if the engine has been shut down first.

3Recoupling of the Generator Drive drive shaft to the engine may be accomplished Only on the ground.At any time in flight provided the Generator Breaker and the Generator Control Relay have previously been tripped.At any time on the ground or in flight.

4After operating the Generator Drive Disconnect switch the Generator Drive HIGH OIL TEMP (if illuminated) will Immediately extinguish as the power to the light comes from the Generator Drive Disconnect Switch.Flash repeatedly indicating successful Generator Drive uncoupling.Remain on, until the Generator Drive oil has cooled.

5The Generator Drive LOW OIL PRESSURE lights are Amber lights on the forward overhead panel which will illuminate when Generator Drive oil pressure is below minimum operating limits.Red lights on the forward overhead panel which will illuminate when Generator Drive oil pressure is below minimum operating limits.Amber lights on the forward overhead panel which will flash repeatedly when Generator Drive oil pressure is below minimum operating limits.

6One of the basic principles of the electrical system is There is no paralleling of the AC sources of power.The AC sources of power can be connected in parallel if necessary.The AC sources of power are always connected in parallel.

7The AC STANDBY BUS power can be supplied from The APU or engine generators only.The APU or engine generators, external power or directly from the Hot Battery Bus.The APU or engine generators, external power or the battery through the Static Inverter.

8A Generator Breaker can be closed At any time the engine is running at or above idle power.When power quality from the generator is correct.Irrespective of power quality from the generator.

9Should a Generator Drive develop a fault and be disconnected from the engine, before corrective action is taken by the pilots A few non-essential electrical systems ( loads ) will be lost.No electrical systems ( loads ) supplied by that generator will be lost as the Bus Transfer systems supplies all the aircraft's electrical systems ( loads ).All electrical systems ( loads ) supplied by that generator will be lost.

10When both engines are running with external power connected then External power must be selected OFF before the engine generators are brought on-line.External power will automatically disconnect when both engine generators are brought on line.External power will automatically disconnect when either engine generator is brought on-line.

11When the Generator Drive Temperature switch is selected to RISE, a higher than normal generator drive oil temperature indicates An excessive generator load or inadequate cooling of the engine oil.An excessive generator load or poor condition of the Generator Drive.Inadequate cooling of the Generator Drive oil.

12Under normal flight, if the Battery switch is selected to OFF then The Battery Bus loses power.The Battery Bus is automatically connected to the Hot Battery Bus.The Battery Bus is automatically connected directly to the Battery.

13 If the No. 2 TRU fails in the cruise The Master Caution and ELEC annunciator lights would illuminate.There would be no immediate indication.The Battery Ammeter would show a discharge.

14The auxiliary 28V DC power receptacle is situated At the AC power receptacle.Near the Battery in the electronic compartment.Externally, forward of the E & E bay door.

15A fully charged battery has sufficient capacity to provide power for a minimum of 30 minutes.45 minutes.20 minutes.

16The Switched Hot Battery Bus is powered from The Battery Bus whenever the Battery Switch is OFF.The Hot Battery Bus whenever the Battery Switch is ON.The Battery whenever the Battery switch is OFF.

17The APU can power both Generator Busses On the ground or in flight.On the ground only.In flight only.

18The T.R. voltage range is 26 - 35 volts.28 - 30 volts.24 - 30 volts.

19The battery voltage range is 26 - 28 volts.24 - 28 volts.22 - 30 volts.

20The maximum Generator Drive oil temperature / temperature rise is 157C / 20C157C / 30C215C / 11C

21The Transfer Buses supply The Essential Loads.The Non Essential and Heavy Loads.The Non Essential Loads.

22With 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 Will trip both engine generators and connect external power to both generator busses.Will trip the right engine generator only and connect external power to the right generator bus.Will trip the left engine generator only and connect external power to the left generator bus.

23 If, in flight, both engine generators fail, the APU generator should be connected to Both No. 1 and No. 2 Generator Busses.The No. 1 Generator Bus.The No. 2 Generator Bus.

24The blue GRD POWER AVAILABLE light when illuminated indicates That either Generator Bus is powered by the ground power supply. Light remains illuminated as long as ground power is connected.That both Generator Busses are powered by the ground power supply. Light remains illuminated as long as ground power is connected.That the External Power Bus is powered by the ground power supply. Light

remains illuminated as long as ground power is connected.

25Under normal conditions the Standby AC bus is energised from the 115-volt Transfer bus No. 2.115-volt Transfer bus No. 1.The Static Invertor.

26After operating the Generator Drive Disconnect switch The Standby Power switch should be selected to BAT.The APU should be started and the APU generator selected on-line.The Generator switch should be momentarily held to OFF to trip the Generator Control Relay.

27The first action to be taken in the event of electrical failure of a generator (BUS OFF light illuminated) is Start the APU (if available) and select it on line.Select the associated Generator switch to OFF.Select the associated Generator switch to ON.

28The normal power source for the Battery Charger is the AC Ground Service Bus, with provisions for automatic switching to The No. 2 Main Bus.The No. 1 Main Bus.Either Transfer Bus.

29Pulling up an engine fire handle will Trip the associated Generator Control Relay and disconnects the Generator Drive.Trip the associated Generator Control Relay and Breaker.Trip the associated Generator Control Relay only.

30 If the Battery switch is selected OFF, the airstairs can be lowered from the outside By using the STANDBY system.By using the NORMAL system with ground power plugged in.By using the STANDBY system, but can only be raised again by use of the NORMAL system.

31To have all three Generators (APU and engines) on-line simultaneously Is not possible.Is possible on the ground only.Is possible in flight only.

32With an engine Generator switch selected OFF and the associated engine is running, the voltage of that generator will read 115 volts.Residual volts when the residual volts switch is pressed.Approximately 3 volts.

33To connect the External Ground power to the aircraft's Generator busses The Battery switch must be ON.The Battery switch must be OFF.The Bus Transfer switch must be in the AUTO position.

34Standby D.C. power is normally supplied from The Hot Battery Bus.DC Bus No. 1.The Battery Bus.

35Failure of the No. 1 Generator Bus will Have no effect on either electric hydraulic pump.Will cause failure of the System B Electric hydraulic pump.Will cause failure of the System A Electric hydraulic pump.

36Placing the BUS TRANS switch to 'OFF' inflight with both generators operating and connected Isolates the transfer busses by preventing operation of the bus transfer relay and opens the TR 3 disconnect relay only.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 ).Isolates the transfer busses by preventing operation of the bus transfer relay, opens the TR 1 and 2 disconnect relays and prevents connection of the battery to the Static Invertor.

37Which of the following statements is correct TR 3 backs up TR 2 only.TR 3 normally backs up TR 1 and TR 2 provided that the BUS TRANS switch is in OFF.TR 3 normally backs up TR 1 and TR 2 provided that the BUS TRANS switch is in AUTO.

38Standby A.C. power is available on touch down after a total electrical failure providing The Standby Power switch is selected to AUTO.The Standby Power switch is selected to BAT.The Battery switch is selected to ON and the Standby Power switch is selected to AUTO.

39The APU generator has A Generator drive unit which will disconnect when the APU Generator drive disconnect switch is activated from the flight deck.No Generator drive unit since the APU itself is governed and will maintain a constant generator speed.A Generator drive unit which will automatically disconnect when its oil temperature is high.

40 If ground power is available and the Ground Service switch on the forward attendant's panel is switched on, then power is supplied to The Ground Service bus for utility outlets, cabin lighting and battery charger.All the aircraft electrical busses.The Ground Service bus for utility outlets and cabin lighting only.

41An engine electrical generator is rated at 45 KVA55 KVA35 KVA

42The 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.

Provide backup power to the Standby DC bus.Off-load the battery charger from the 115V AC GND SERVICE Bus.

43After disconnecting a Generator Drive, its associated oil temperature indicator May show an increase on the IN scale and/or the RISE scale.Will immediately show a decrease in temperature.Will maintain the same temperature reading.

44The Battery Switch must be ON or OFF for the GRD PWR Switch to be operable.OFF for the GRD PWR Switch to be operable.ON for the GRD PWR Switch to be operable.

45The Battery Switch is ON and the GRD PWR is connected to the aircraft's Busses. If the Battery Switch is selected OFF then The GRD PWR switch will not automatically disconnect.The GRD PWR switch will automatically disconnect.The GRD POWER AVAILABLE light will extinguish.