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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