Term
| The purpose of the AC ground service bus is to power: |
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Definition
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Term
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Definition
| 115 volts AC to 28 volts DC |
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Term
| Which is the power source for the AC standby bus? |
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Definition
| Transfer bus 1 under normal conditions |
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Term
True/False
If the AC source powering a transfer bus fails, the transfer bus will remain unpowered. |
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Definition
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Term
True/False
A high oil temperature in the IDG would cause an automatic disconnect of the IDG. |
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Definition
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Term
| The TR3 cross bus tie relay automatically opens at glide slope capture to: |
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Definition
| Prevent a single bus failure from affecting both navigation receivers and Flight Control Computers (FCCs) |
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Term
| In flight, if the APU is supplying both AC Transfer busses, positioning the BUS TRANS switch to OFF will: |
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Definition
| Cause AC Transfer bus No.2 to lose power |
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Term
| The TR3 Disconnect Relay: |
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Definition
| Automatically opens at glide slope capture during a Flight Director or Autopilot ILS approach |
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Term
| The Engine Integrated Drive Generators (IDGs): |
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Definition
| Allow the generator to maintain a constant speed throughout the normal range of operation |
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Term
| After the loss of all generators, a fully charged battery can furnish power to the STANDBY Bus equipment for a minimum of: |
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Definition
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Term
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Definition
| Opens up if BUS TRANSFER switch is moved to OFF |
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Term
| Illumination of the GND POWER AVAILABLE light indicates: |
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Definition
| Ground power is connected and meets airplane power quality standards |
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Term
| For ground service, a ground service switch is placed: |
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Definition
| On forward attendant's panel |
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Term
| The GROUND POWER AVAILABLE light will extinguish when: |
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Definition
| The AC ground power cart has been disconnected |
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Term
| One basic principle of operation for the B737 electrical system is: |
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Definition
| There is no paralleling of the AC power sources |
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Term
True/False
Because engine generators power the transfer busses directly, and transfer busses are connected by a bus tie system, the loss of an engine driven generator will not necessarily result in the loss of any bus(ses). |
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Definition
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Term
True/False
The modified DC system architecture resulted in the TR3 disconnect relay found in the B737-300 thru 500 being replaced with a cross bus tie relay. The cross bus tie relay opens automatically under the same circumstances as did the TR3 disconnect relay. |
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Definition
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Term
| The SOURCE OFF light will illuminate: |
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Definition
When the source selected to power the transfer bus has failed and the automatic bus transfer function has closed the BTBs to power the transfer bus from another source
When the source selected to power the Transfer bus and the automatic transfer function have both failed resulting in the transfer bus being. unpowered
When the TRANSFER BUS OFF light is illuminated |
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Term
| When the STANDBY POWER Switch is OFF: |
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Definition
| The STANDBY PWR OFF light will be illuminated |
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Term
| Illumination of the BAT DISCHARGE light indicates: |
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Definition
| Excessive battery discharge is detected with the battery switch ON |
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Term
| In the event that the airplane battery is depleted, the APU can be started using DC external power. |
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Definition
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Term
| Illumination of the blue GEN OFF BUS light indicates: |
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Definition
| The IDG is not supplying power to its associated transfer bus |
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Term
| When the aircraft batteries is the only source of power: |
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Definition
| The captain's inboard and outboard displays operate until the battery is discharged |
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Term
| Illumination of the GEN BUS OFF light indicates: |
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Definition
| The IDG is not supplying power to its associated Transfer bus |
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Term
True/False
It is possible to power one transfer bus with external power and the other transfer bus with the APU. |
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Definition
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Term
| The crew fails to properly accomplish normal procedures and takes off with the APU powering both Transfer busses (SELECT THE INCORRECT STATEMENT) |
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Definition
| Both Main busses may become inoperative above 400 feet RA or after 12 sec. from lift-off |
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Term
True/False
AC amperage can be observed on the AC ammeter for the source selected by the AC meter selector. |
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Definition
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Term
| During cruise, one engine driven generator drops off-line. Indications that the crew should see include: |
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Definition
| A SOURCE OFF light and a GEN OFF BUS light |
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Term
| Illumination of the DRIVE light indicates: |
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Definition
IDG failure or
IDG automatic disconnect due to high oil temperature or
IDG disconnected through the drive disconnect switch |
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Term
| Both AC Transfer busses can be powered simultaneously by: |
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Definition
A single IDG on the ground or inflight
The APU generator while on the ground or inflight |
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Term
| On the ground, with the battery switch OFF and STANBY POWER Switch in AUTO, the Battery Bus is: |
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Definition
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Term
| The TR UNIT will illuminate in flight if: |
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Definition
| TR1 fails or TR2 and TR3 fail |
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Term
| The ELEC light will illuminate in flight if: |
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Definition
| The ELEC light only operates on the ground |
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Term
| What is the significance of an illuminated ELEC light? |
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Definition
| The DC system or standby system equipment has failed |
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Term
| With external DC power connected to the external DC power receptacle: |
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Definition
| There is no external DC power receptacle |
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Term
| Illumination of the STANDBY POWER OFF light indicates: |
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Definition
The AC Standby Bus is unpowered or
The DC Standby Bus is unpowered or
The Battery Bus is unpowered |
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Term
| With the STANDBY switch in the AUTO position, the loss of all engine or APU electrical power results in the automatic switching from the normal power source to the alternate source for standby power: |
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Definition
| Either inflight or on the ground |
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Term
| In flight if APU is the only source of electrical power: |
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Definition
| All galley busses are automatically shed |
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Term
True/False
With the STANDBY POWER switch in AUTO (guarded position). In flight, or on the ground, loss of all AC power. AC Standby bus is powered by battery through static inverter & DC Standby bus is powered by battery. |
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Definition
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Term
| DC voltage and amperage may be read on the DC voltmeter and ammeter for the battery and each of the 3 TRs. The Standby power and battery bus displays only Dc voltage. Normal indication is : ______ volts |
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Definition
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Term
True/False
The purpose of the static inverter is to convert 24 volt DC power from the battery to 115V AC power to supply the AC standby bus during the loss of normal electrical power. |
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Definition
True
The power supply to the inverter is controlled by the standby power switch and the battery switch on the overhead panel |
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Term
| The two nickel-cadmium batteries can provide standby power for a minimum of _____ minutes (if fully charged). |
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Definition
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Term
| DC busses powered from the battery following a loss of both generators are: |
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Definition
Battery bus
DC Standby bus
Hot battery bus & Switched hot battery bus
Switched hot battery bus is powered whenever the battery switch is ON |
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Term
True/False
If the TR UNIT light is illuminates in flight, it indicates that one or more TR\'s have failed and you are supposed not to use the AFDS approach mode. |
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Definition
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Term
True/False
An illuminated TR UNIT light while on the ground indicates that at least two TRs have failed. |
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Definition
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Term
| What is the purpose of the GROUND SERVICE switch? |
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Definition
Provide manual control of ground service busses
Enables servicing airplane using external power without activating AC transfer busses. |
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Term
| Either generator or the APU can power both transfer buses. In the event a power source fails, what is required for that transfer bus to be powered by the opposite transfer bus power source? |
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Definition
| The BUS TRANS switch must be in the AUTO position |
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Term
| Normal AC voltmeter indication for the APU generator with the AC busses loaded: |
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Definition
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Term
| Illumination of the STANDBY POWER OFF light indicates: |
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Definition
|
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Term
| 53. DC voltage and amperage may be read on the DC voltmeter and ammeter for the battery and each of the three TRs. The standby power and battery bus displays only DC voltage. Normal indication is: |
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Definition
26 +/- 4 volts
During primary charge cycle operation battery voltage can be as high as 30 +/- 3 volts |
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Term
True/False
Both On the ground and in flight a amber ELEC light comes on to indicate that a fault exists in DC power system or standby power system. |
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Definition
False
The ELEC light is inhibited in flight |
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Term
| Galley busses are powered from: |
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Definition
|
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Term
| How many TRs are required to power the entire DC system? |
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Definition
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Term
| What is the source of power for TR3? |
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Definition
|
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Term
| What is the source of power for TR2? |
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Definition
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Term
| The switched hot battery bus is powered whenever: |
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Definition
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Term
| The purpose of the cross tie relay is to: |
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Definition
| Isolate DC bus 1 from DC bus 2 |
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Term
| What is the source of power for TR1? |
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Definition
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Term
| On the ground, with the BATTERY switch OFF and STANDBY POWER Switch in BAT, the switched hot battery bus is: |
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Definition
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Term
| The main battery charger is powered through: |
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Definition
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Term
| Which bus supplies electrical power to the auxiliary battery charger? |
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Definition
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Term
True/False
The auxiliary battery operates in parallel with the main battery when the battery is powering the standby bus. |
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Definition
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Term
| The electrical system incorporates an automatic load shedding feature. What is the first bus that is shed? |
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Definition
| Galleys on transfer bus 2 are shed first |
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Term
| The electrical system incorporates an automatic load shedding feature. What is the second bus that is shed? |
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Definition
| Galleys on transfer bus 1 |
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Term
| After an overload situation has been resolved, how do you recover the galley buses? |
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Definition
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Term
True/False
Once disconnected, the IDG can be reconnected in flight. |
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Definition
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