test para examen de curso

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

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

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)?. Do a BIT/ VERITY test on the window heat controller. 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.

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

the IDG AIR / OIL HEAT EXCHANGER VALVE is: failsafe open. controlled from the BPCU. failsafe close.

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

What makes the amber light "CAPT PITOT", illuminates during flight?. interrupted Header current to the CAPT PITOT probe. CAPT PITOT probe control switch in OFF position. An Overheated CAPT PITOT probe.

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

How can the Emergency Lights be Tested?. 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. You must press the Test switch in every Battery Pack.

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

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

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

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

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

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

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.

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

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

Which bus is automatically powered when external power is available?. Ground handling Bus. Ground service Bus. Battery Bus.

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

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

What is true related to the window anti ice?. There are two controller Nº1 for window 1L and 2R , 3R, Nº 2 for window 1R and 2L ,3L. Controller 1 controls all the left window and if these is un fault the Nº2 takes over. There is only one main window heat controller for all the windows, the other one is a back-up.

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

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

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.

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

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

A fire in the FWD Cargo Compart. has been extinguished. After landing all Bottles had been replaced and correct connected, but the Bottle Discharge light stil illuminated, so ..... At the FWD Discharge Line Pressure Switches a Manual Reset must be performed. At the AFOLTS CARD 6 a Manual Reset must be performed. The lights extinguishes after a successful FIRE TEST.

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.

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

Airplane FLYING , what happen to the Cargo Fire Extinguishing Bottles when el FWD CARGO FIRE switch is armed and tha BOTTLE DISCHARGE switch was pressed?. Bottle 1 will be discharged immediately, Bottle 2 and 2A willdischarge 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.

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

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

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

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

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

Which are the operation modes of the Main Battery Charger?. Charge mode and Transformer Rectifier mode. Charging mode on ground and TR in flight. Charge mode only.

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

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

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