Maravilloti

When does the bus tie switch ISLN light illuminate?. The bus tie breaker is open during center bus transfer. The generator circuit breaker is tripped/open. The bus tie breaker is open because of a fault.

if the right TRU fails, the right DC bus will be supplied by: L TRU through the DC Tie Relay (automatically). DC Standby Bus. Ground Handling TRU.

Airplane FLYING, what happens to the Cargo Fire Extinguishing Bottles when the FWD CARGO FIRE switch is armed and the BOTTLE DISCHARGER switch was pressed?. Bottle 1 will be discharged immediately. Bottle 2 and 2A will discharge 30 minutes later or when the Airplane touches down. Bottle 1 will be discharged immediately. Bottle 2 and 2A are reserved for Aft Cargo. All the three Bottles will be discharged immediately.

what makes the amber light CAPT PITOT, illuminates during flight?. Interrupted Heater current to the CAPT PITOT probe. CAPT PITOT probe control switch in OFF position. An Overheated CAPT PITOT probe.

what is the purpose of the FDR?. To record some selected flight parameters for the last 25 hours. To record all the VHF and HF voice comunications. To makes a record of any malfunction ocurred in the last 30 minutes of flight.

what are the conditions to turn on the nose gear landing light?. The nose landing light switch ON. The nose gear light landing light switch ON and the landing gear down and locked. The nose landing light switch ON and the nose gear in UP.

what controls load shedding?. BPCU, Relays, and Circuit interlocks. GCUs only. Static invert.

A side window INOP light is illuminated. How can you find out which window caused the INOP light (number 2 or number 3 side window?. The EICAS will display on its CRT which window caused the INOP light. Activate the window/probe heat test switch (P61) and then EICAS will display which side window caused the INOP light. Do a BIT/VERIFY test on the window heat controller.

if the upper EICAS display unit fails, how the primary and secondary engine parameters will be displayed?. The compacted mode must be selected with ENGINE switch. The full compacted mode automatically appears on the lower display. Automatic Eicas computers switchover occurs.

what are the Bus Tie Breakers position with both engines running and the IDGs supplying power to the main AC buses?. Both BTBs are closed to provide back up power. Both BTBs are in the open position. Both BTBs are closed while both IDGs are supplying power.

A fire in the FWD cargo compart, Has been estinguished. After landing all bottles had been replaced and correct connected, but the bottle Discharger light still illuminated, so... The lights extinguishes after a successful FIRE TEST. At the AFOLTS CARD 6 a Manual Reset must be performed. At the FWD Discharge Line Pressure Switches a Manual Reset must be performed.

in autoland approach CAT 3, from where the C AC BUS takes power?. Static inverter. L AC BUS. R AC BUS.

when an EICAS maintenance page is displayed, the upper display normally is in: Primary engine parameters only. Compact Full format. The maintenance page.

A STATUS cue appears on the EICAS lower display for a new: Advisory message. Status message. Caution message.

which are the operation modes of the main battery charger?. Charger mode only. Charger mode and Transformer Rectifier mode. Charging mode on ground and TR in flight.

which buses can be supplied by the HMG?. Left and Right DC-Buses and the AC-STBY Bus. Left and Right Main AC-Busses. Both AC-XFER Buses, CPT´s FLT-Instrument-XFER Bus, HOT BAT BUS.

What is the purpose of the EVENT READ pushbuttons?. To erase the NVM. To set the EICAS ON. To read an AUTO EVENT or a MANUAL EVENT.

where are located the AFOLTS cards?. Behind the FIRE/OVHT test panel on P8. In the P54 card file. In the P51 card file.

which bus is automatically powered when external power is available?. Ground Handling Bus. Battery Bus. Ground service Bus.

The IDG AIR/OIL HEAT EXCHANGER VALVE is: Failsafe closed. Controlled from the BPCU. Failsafe open.

what is the purpose of the Program Switching Modules (PSMs)?. The PSM DIP switches allow to program the EICAS Computers to display Maintenance formats in Air mode. The PSMs allow programming of Engine and Airframe options. The PSMs allow programming of Display options.

19.- what is true related to the window anti ice?. Controller 1 controls all the left windows and if there is a fault the N°2 takes over. There are two controller N° 1 for window 1L and 2R, 3R, N° 2 for window 1R and 2L, 3L. There is only one main window heat controller for all the windows, the other one is a back-up.

EICAS Level B or C messages are removed from the display unit by pressing the: Cancel ( CANC ) switch on the captain´s panel. Recall ( RCL ) switch on the captain´s panel. ERASE switch on the EICAS maintenance control panel.

There is fire in the APU, from where can I discharge the bottles?. Only from the cockpit. From P40 or from the cockpit. Only from the P40 (APU remote control panel).

how can the Low Pressure Switch of the Engine Fire Extinguishing Bottle be checked?. Through a Test Switch at the P61 Maintenance Panel. Through a TEST PUSHBUTTON at the LOW PRESSURE SWITCH on the bottle. By pressing the FIRE TEST SWITCH at the P8 Panel.

when the Hydraulic motor generator (HMG) start to operate?. Loss of power from both main DC buses. Loss of power from both main AC buses in flight. Failure of any electrical system generator.

pressing the Test switch on the maintenance control panel, will initiate an EICAS test: When the aircraft is on ground and the parking brake is set. Then the Test pattern is displayed for two minutes and then changes to primary and secondary engines displays. Any time the Test switch is pressed, the EICAS test is initiated.

how is the DC electrical power generated?. From the main AC busses by means of Transformer/Rectifiers. Using current differential transformers and AC power. By the Static inverter.

how can the emergeny lights be tested?. You must press the Test switch in every Battery Pack. From the Test switch on panels P21, Fwd Attd, P22 Aft Attd or P40 APU GND Control panel. The only way to do it is setting the Emergency light switch on P5 in armed.

when the Pitot Probes are heated?. When there is power on the aircraft. When the aircraft is powered and at least one Engine is started or the in Flight condition is adquired. When the aircraft is powered and the control switch is in ON.

what happen when the EVENT RECORD (DSP panel) pushbutton is pressed?. It signals to EICAS to stores all 4 system pages in a non volatil memory. A summary of all status messages are shown in the lower display. Maintenance pages are sequentially shown as far as the switch still pressed.

the SYS FAIL light will illuminate in case of... The system detects a FIRE condition. Both Loops at ENG, APU or CARGO fail. The AFOLTS cards detect Single ENG, APU, or CARGO Loop fail.

Failure of the window temperature sensor will require which maintenance action?. The window must be replaced. A new sensor must be glued to the window. The failed sensor to be disconnected and the spare sensor to be connected at the terminal block in the Main Equipment Center.

what causes the DRIVE light to illuminate on the electrical power panel P5?. The IDG high oil pressure. The IDG high oil temperature or IDG low oil pressure. The IDG underspeed signals.

The total air temperature (TAT) probe... Is not heated because of a temperature influence between the heater and the sensor element. This could cause a faulty TAT indication. Is heated in the Air and during the test only. Heater Power is 115 Vac. On Ground with Engines running the Heater Power is 28 Vdc but in the Air 115 Vac is used.

at power up, the EICAS Display will show: The Engine Primary and Secondary Displays. The Test configuration. The Engine Primary Display and Status page.

the purposes of BPCU are: BITE functions for trouble shooting only. Control, BITE and Monitoring. Control of external power interlock only.

the EICAS BYPASS Sw, Is an alternative procedure to: Have the EICAS Maintenance Panel available in flight or when jacks. Change information on S.E.I from Punds to kilos or vice versa. Switch to the left or right computer.

After IDG disconnection how can it be reconnected again?. Only on ground by pulling the reset ring with engine not running. On ground with engine in idle. In flight with engine not running and by pressing the Field Reset switch on P61.

Which statement concerning to the WEU is correct?. The WEU controls the Master Warning Light and the Aural Warning Speakers. The WEU controls the Master Warning Light, the Master Caution Light and the Aural Warning Speakers. When one SIREN/OWL module fails, the remaining one supplies both Aural Warning Speakers.