E a320

5.1. The engine generators and APU generator are rated at _____ KVA. A: 50. B: 70. C: 90. D: 110.

5.2. The number 1 AC bus channel normally supplies power to _____ and to the _____ bus which supplies power to the ______ bus. A: TR2 / AC ESS SHED / DC ESS SHED. B: TR1 / AC ESS SHED / DC ESS. C: TR1 / AC ESS / AC ESS SHED. D: TR1 / AC ESS / DC ESS SHED.

5.3. The normal priority for supplying electrical power to the AC busses is: A: External power, engine generators then APU. B: External power, APU, then engine generators. C: APU, external power then engine generators. D: Engine generators, external power then APU.

5.4. The BATTERY BUS is normally powered by: A: DC BUS 2. B: DC BUS 1 and DC BUS 2. C: DC bus 1 through a DC tie control relay. D: DC bus 2 through a DC tie control relay.

5.5. The A-320 has _______ batteries in its main electrical system. A: 1. B: 2. C: 3.

5.6. An AC ESS FEED switch located on the overhead panel shifts the power source for the AC ESS bus from: A: AC bus1 to AC bus 2. B: AC bus 1 to AC Grnd/Flt bus. C: AC bus 2 to AC bus 1.

5.7. Which of the following AC busses can be powered by the emergency generator?. A: AC bus 1. B: AC bus 2. C: AC ESS bus / AC ESS SHED bus.

5.8. After landing, in the emergency electrical configuration: the batteries automatically connect to the DC BAT bus when speed decreases below _______ knots. A: 50. B: 70. C: 90. D: 100.

5.9. The BAT FAULT light will illuminate when: A: Battery voltage is low. B: Charging current increases at an abnormal rate. C: Charging current decreases at an abnormal rate.

5.10. Do not depress the IDG DISCONNECT switch for more than _______ to prevent damage to the disconnect mechanism. A: 3 seconds. B: 7 seconds. C: 10 seconds. D: 15 seconds.

5.11. The IDG Fault light indicates: A: An IDG oil overheat. B: IDG low oil pressure. C: IDG low oil pressure or IDG oil overheat. D: IDG has been disconnected.

5.12. If normal electrical power is lost; essential cockpit lighting is maintained for the: A: Captain’s instrument panel. B: Standby compass. C: Right dome light (provided the dome selector is not off). D: All of the above.

5.13. Having started the APU, how can you get the APU generator to power the electrical system?. A: The APU generator must be switch on. B: By pushing the EXT PWR pushbutton thus disconnecting the external power. C: By pushing the BUS TIE pushbutton. D: You are unable to as the APU power output is outside normal parameters.

5.14. Are there any limitations associated with disconnecting an IDG?. A: Never disconnect an IDG in flight, or push the IDG disconnect push button for more than 30 seconds. B: There is no limitation. C: Never disconnect an IDG in flight, or push the IDG disconnect push button for more than 5 seconds. D: Never disconnect an IDG unless the engine is running, nor push the IDG disconnect push button for more than 3 seconds.

5.15. The APU is supplying the electrical system. What is the order of priority for the different generators?. A: Engines, external power, APU. B: APU, engines, external power. C: External power, engines, APU. D: APU, external power, engines.

5.16. What is the significance of the green collared circuit breakers?. A: Green collared circuit breakers are pulled when flying on battery power only. B: Green collared circuit breakers are monitored by the ECAM. C: Green collared circuit breakers are not to be reset. D: Green collared circuit breakers are AC powered.

5.17. What is the minimum voltage when conducting a BATTERY CHECK?. A: 28 volts. B: Less than 60 amps in 10 seconds. C: Greater than 24 volts. D: Greater than 25 volts.

5.18. What is the function of APU GEN push button located on the overhead electrical panel?. A: Push this button to automatically start the APU. B: When selected to OFF the APU generator field is de-energized. C: Both are correct.

5.19. Is it possible to parallel generators?. A: Of course yes. B: Only with the RAT deployed. C: The electrical system will not allow “paralleling” of generators. D: Only one engine generator may be paralleled with the APU.

5.20. What cockpit lighting is available during an emergency electrical situation?. A: Emergency path lighting only. B: Right side Dome light, main panel flood lights (left two columns only), and the standby compass light. C: Located on normal circuit breaker panels. D: Right side dome light, main panel flood lights, and the standby compass light.

5.21. What is the function of the GEN 1 LINE push button?. A: When selected OFF the avionics compartment isolation valves close. B: When selected OFF the #1 generator powers all AC busses. C: When selected OFF generator # 1 is removed from all busses but continues to power one fuel pump in each wing.

5.22. When does the RAT automatically deploy?. A: With the loss of two hydraulic systems. B: Electrical power to both AC BUS #1 & #2 is lost and the aircraft speed is above 100 knots. C: Both are correct.

5.23. How many times can you reset a circuit breaker?. A: Once. B: Once, if authorized by the procedures. C: Twice. D: Twice, if authorized by the procedures.

5.24. Can you reconnect an IDG in flight?. A: Yes, but only after contacting maintenance control. B: Yes, push and hold the IDG pb until the GEN fault light is no longer illuminated. C: No, it is not possible.

5.25. Which communication and navigation radios are operational in the Emergency Electrical Configuration with the EMER GEN powering the system?. A: ACP 1 and 2, VHF 1, HF, RMP 1, VOR 1, and ILS 1. B: VHF 1, RMP 1, VOR 1. C: RMP #1 & #2, VHF #1, HF (if equipped), ACP #1, VOR #1 and ILS #1. D: All radios are lost.

5.26. What is the meaning of the green AVAIL light?. A: External power is plugged in and parameters are normal. You must push the external power to connect it. B: External power is available to the batteries only. C: The external power panel door has been opened. D: External power is supplying the aircraft systems.

5.27. What does the blue EXT PWR ON light mean?. A: External power is plugged in and parameters are normal. B: External power is supplying the aircraft’s electrical system. C: There is a fault with the external power.

5.28. Is it possible to determine the source of power for aircraft busses. A: It is indicated on the electrical schematic overhead. B: No it is not possible. C: Yes, press the ECAM ELEC pb and view the electrical schematic on the ECAM. D: Only when operating in the Emergency Electrical Configuration.

5.29. Both batteries are charged by the external power unit. Approximately how long does the charging process take?. A: 10 minutes. B: 20 minutes. C: 30 minutes. D: Between 30 and 45 minutes.

5.30. The GALLEY FAULT light illuminates when any generator is exceeding 80% of its rated output. A: True. B: False.

5.31. What would cause the GALLEY fault light to illuminate?. A: The flight attendants have all the coffee makers and ovens on at once. B: The Main Galley has shed. C: The load on any generator is above 100% of its rated output. D: The Aft Galley has shed.

5.32. In normal electrical configuration, how is DC ESS bus supplied: A: From TR 1 via DC Bus 1 and DC Bat Bus. B: From ESS TR. C: From TR 2. D: From Bat 2.

5.33. What happens in case of total loss of main generators?. A: The RAT is automatically extended and powers the yellow system which drives the emergency generator. B: The RAT is automatically extended and powers the blue system which drives the emergency generator. C: The RAT has to be manually extended. D: The RAT is extended and mechanically connected to the emergency generator.

5.34. Normal minimum battery voltage before APU start is: A: No minimum. B: 27.5 Volts. C: 25.5 Volts. D: 22.5 Volts.

5.35. Where can the battery voltage be checked?. A: On the ECAM elec. Page only. B: On the elec. overhead panel and ECAM E/WD. C: On the elec. overhead panel only. D: On the Elec. overhead panel and ECAM Elec. Page.

5.36. In flight on batteries only, the AC ESS Shed bus and DC ESS Shed bus are lost. A: Yes. B: No. C: Only A/C ESS Shed Bus is lost. D: Only D/C ESS Shed Bus is lost.

5.37. If a TR fails: A: The other TR automatically replaces the faulty one and the ESS TR supplies the DC Ess Bus. B: The static inverter replaces the faulty TR. C: The DC Bus on the faulty side is lost. D: The Emergency generator supplies DC power on the faulty side.

5.38. If AC Bus 1 fails the AC ESS bus is supplied by: A: Emer Gen. B: The RAT. C: Static Inverter. D: AC Bus 2.