ATA 24 EXAMEN AVIANCA

the STATIC INVERTER operates. when the emergency generator runs. permanently. when no AC sources are available.

the battery coupling is controlled by the. electrical contactor management unit ECMU. battery charge limiter BCL. generator control unit GCU.

after differential pressure indicator DPI pops out you have to. replace the integrated drive generator IDG in any cases. drain and do no replace the integrated drive generator IDG. follow the trouble shooting manual TSM alternative differential pressure indicator DPI reset procedure.

one of the following situations does not trigger the IDG p/b fault legend. a too low pressure in the IDG oil system. a too high temp in the IDG oil system. a too low oil level in the IDG oil system.

aircraft on ground an APU generator oil overheat causes. illumination of the fault legend on the APU gen p/b sw and automatic isolation of the APU generator. an immediate APU shutdown performed by the electronic control box ECB. illumination of the fault legend on the APU gen p/b sw requiring manual isolation of the APU generator.

external power overvoltage is detected by the. GAPCU at CT current transformer. ground and auxiliary power unit GAPCU at POR point of regulation. electrical contactor management units ECMU at por.

constant speed motor/generation CSM/G speed is regulated by the CSM/G GCU through inputs to the CSM/G. solenoid control valve. servo valve. permanent magnet generator (PMG).

the DC GND SERVICE DC GND/FLT bus is powered. from ext power through TR1. from ext power through TR2. from APU power through TR1.

The BATTERIES are protected from complete discharge by automatic opening of their respective contactors with aircraft. on ground and the battery voltage is lower than 23 volts for 15 seconds. in flight and the battery voltage is lower than 20 volts for 1 seconds. in flight or on ground and the battery voltage is lower than 23 volts for 15 seconds at any time.

a commercial off message displayed on the elec ac ECAM page indicates. all galleys are no longer supplied. only non essential cabin system have been loadshed. all galleys and commercial buses are no longer supplied.

main batteries are mainly used to. help at APU starting and emergency configuration. supply the entire network in emergency. refueling operations.

in the IDG the cooler bypass valve is used by the system. is an oil to air heat exchanger. a fuel management system. in low oil temperature.

the emergency generator EMER GEN is A. IDG 115 VAC/400 HZ single phase generator. tru 28 VDC generator. CSM/G 115 VAC/400HZ triple phase generator.

when an ac bus 2 has failed the ac essential bus is supplied from. ac ess bus. ac bus 1. ac bus 2.

who control the battery contactor. GCL controlled by the GCU. BCL battery charge limiter. P/B of each battery.

the APU generator can supply the entire ac electrical system. in flight or on ground. in flight only. on ground only.

conditions for the constant speed motor / generator CSM/G to start are. any time after manual activation of the ac ess p/bsw. automatically in case of main AC buses failure in flight. automatically in case of single generator failure to reduce the remaining generators workload.

the IDG oil is cooled by means of. an oil to air heat exchanger. a fuel to oil heat exchanger. an oil to oil heat exchanger.

ground power unit GPU connected and maintenance bus off, in this case. ac and dc gnd flt buses energized. ac and dc ess busses energized. ac and dc gnd flt buses not energized.

the supply priorities for ac bus 1-2 are. external power then the apu generator then the onside IDG then the opposite IDG. the onside IDG then the opposite IDG and then external power and the APU generator. the onside IDG the external power, then the apu generator and then the opposite IDG.

which are the conditions for RAT automatic deployment. air speed >100 kts ac bus 1 off + ac buss 2 off. air speed > 500 kts dc bus 1 off + ac buss 2 off. ac bus 1 off + ac bus 2 off.

aircraft on ground elec ac bus 1 fault and ground power unit connected so, the ac ess bus will be supplied from. ac bus 2. external power contactor. TR 2 transformer rectifier.

in normal flight configuration each generator supplies its own distribution network via its. electrical contactor management unit ECMU. battery charge limiter BCL. generator line contactor GLC.

in flight in case of total loss of all the main generator and before the emergency generator connection wich source will supply the ac ess bus. battery 1 via the static inverter. battery 2 via the static inverter. constant speed motor generator CSM/G via the static inverter.

wich one of the following situation does not trigger the IDG p/b fault legend. a too low pressure in the IDG oil system. a too high temp in the IDG oil system. a too low oil level in the IDG oil system.

when the speed is lower than 100 knots the emergency generator is deactivated the batteries supply the AC and DC ess buses, and when the speed drops below 50 knots the ac ess bus. disconnects from the static inverter. dicsonnects from the AC ess bus. disconnects from the AC bus 1.

IDG cooling system the purpose of the IDG oil cooler bypass valve is to protect the IDG oil from. overheating. overcooling. overvoltage.

IDG monitoring sys aircraft in flight and according to the system logic oil pressure lower than 140 psi + engine 1 running so. automatic disconnection of IDG 2. IDG 1 P/BSW fault light illuminates. IDG 2 P/BSW fault light does not illuminate.

the DC GND SERVICE DC GND/FLT bus is powered. from ext power through TR1. from ext power through TR2. from APU power through TR 1.

each generator control unit GCU is supplied by the permanent magnetic generator PMG from its related IDG and as a back up through the. generator line contactor GLC 1. point of regulation POR. battery bus 301 pp.

a high oil temperature on the APU generator oil outlet port leads to. an immediate automatic shutdown of the APU via the electronic control box ECB. an immediate manual shutdown of the APU via the electronic control unit ECU. an immediate manual shutdown of the APU via the electronic control box ECB.

the condition for an automatic thermal disconect of IDG is. IDG oil outlet temperature of 200°. IDG oil inlet temperature of 200°. IDG on outlet temperature less than 185°.