ATA 31,24,26

what is true relate to the window anti ice?. there are two controller N 1 for window 1L and 2R 3R, 2 for window 1R and 2L, 3L. controller 1 controls all the left window and if there is a fault the N2 takes over. there is only one main window heat controller for hall the windows, the other one is a back-up.

the purposes of BPSU are: control BITE and monitoring. BITE functions for trouble shooting only. control of external power interlock only.

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

how is the DC electrical power generated ?. from the main AC busses by means of trasformer/rectifiers. By the Static inverter. using curret differential transformers and AC power.

what is the purpuse of the program switching 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 some selected flight parameters for the last 25 hours. to make a record of any maifuction ocurren in the last 30 minutes of flight. to record all the VHF and HF voice comunications.

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).

what are the Bus tie breakers position with bolt engines running and the IDGs supplying power to the main AC buses?. bolth BTBs are in the open position. both BTBs are closed while both IDGs are supplying. both BTBs are closed to provide back up power.

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

airplane FLYING, what happens to the cargo Fire Exitinguishing bottles when the FWD CARGO FIRE is armed and the BOTTLE DISCHARGE switch was pressed ?. Bottle 1 will be discharged immediately ´´ Bottle 2 and 2A are reserved for aft Cargo. All the three Bottles will be discharged immediately. Bottle 1 will be discharged immediately Bottle 2 and 2A will discharge 30 minutes later or when the aiplene touches down.

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

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. the compacted mode must be selected wilt the ENGINE switch. automatic EICAS computers switchover occurs.

which are the operation modes of the main Battlery Charger?. Charge mode and transformed Rectifier mode. Charging mode on ground and TR in flight. charge mode only.

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

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 swirches a manual reset must be performed. The lights extinguishes after a successful FIRE TEST. At the AFOLTS CARD 6 a manual Reset must be performed.

the total air Temperature (TAT) probe... On Graund with Engines running the heater power is 28 Vdc but in the Air 115 Vac is used. 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.

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

How can the emergency lights be tested ?. You must press the test switch in every Battery pack. The only way to do it is setting the emergency light switch on P5 in armed. from the test swicht on panels P21, FWD attd, p22,aft attd or p40 APU GND control panel.

what causes the DRIVE light to illuminate on the electrical power panel p5?. the IDG underspeed signals. the IDG high oil temperature or IDG low oil pressure. the IDG high oil pressure.

What happen when the EVENT RECORD ( DSP PANEL) pushbutton is pressed?. it signals to Eicas to stores all 4 system pages in a on volatil memory. maintenance pages are sequentially shown as far as the switch still pressed. A summary of all status messages are shown in the lower display.

When an EICAS maintenance page is displayed, the upper display normally is in: the maintenance page. Compac full format. primary engine parameters only.

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

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

Which are the operation modes of the Main Battery Charger?. Charge mode and transformer rectifier mode. charging mode ok ground and TR in flight. charge mode only.

which bus is automatically powered when external power is available ?. Battery Bus. Ground servise Bus. Ground hadling Bus.

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 buses can be supplied by the HMG ?. both AC-XFER Buses CPT´s FLT-instrument -XFER Bus HOT BAS BUS. left and right Main AC- busses. left and right DC-Buses and the AC-STBY Bus.

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. Do a BIT / VERIFY test on the window Heat controller. activate the window/probe heat test switch (P61) and then EICAS will display which side window caused the ´´INOP´´ light.

pressing the test awitch on the maintenance control panel, will initiate an EICAS test : then the test pattern is displayed fot two minutes and then changes to primary and secondary engines displays. any time the test switch is possed, the EICAS test is initiated. when the aircraft in on ground and the parking braking brake is set.

the EICAS BYPASS Sw. is an alternative procedure to: Change information on S.E.I from punds to kilos or vice. have the EICAS maintenance panel available in flight or when jacks. switch to the left or right computer.

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

failure of the window temperature sensor will requiere whitch maintenance action?. the failed sensor to be disconnected and the spare sensor to be connected at the terminal block in the main equipment center. the window must be replaced. a new sensor must be glued to the window.

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.

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

what makes the amber light ´´ CAPT PITOT´´ illuminates during flight ?. An overheated CAPT PITOT probe. interrupted heater current to the CAPT PITOT probe. CAPT PITOT probe control switch in OFF position.

when the pitot probes are heated?. 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. when there is power on the aircraft.

the IDG AIR/OIL HEAT EXCHANGER VALVE is: controlled from the BPSU. Failsafe closed. Failsafe open.

how can the low pressure switch of the engine fire extinguishing bottle be checked?. by pressing the FIRE TEST SWITCH at the p8 panel. through a TEST PUSHBUTTON at the LOW PRESSURE SWITCH on the bottle. through a test switch at the p61 maintenance panel.

what controls load shedding?. GCUs only. Static invert. BPSU, Relays,and circuit interlocks.

the ´´SYS FAIL´´ light will illuminate in case of.. Bolt loops at ENG, APU or CARGO fail. the AFOLTS cards detect single ENG , APU or CARGO loop fail. the system detects a FIRE condition.