ATA 31

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

What is true related to the window anti ice?. A) Controller 1 controls all the left windows and if there is a fault the Nº 2 takes over. There is only one main window heat controller for all the windows; the other one is a back-up. C) There are two controllers: Nº 1 for window 1L and 2R, 3R; Nº 2 for Window 1R and 2L, 3L.

At power up, the EICAS Display will show: A) The Test configuration. B) The Engine Primary and Secondary Displays. C) The Engine Primary Display and Status page.

What are the conditions to turn on the nose gear landing light?. A) The nose gear light landing light switch ON and the landing gear down and locked. B) The nose landing light switch ON and the nose gear in UP. C) The nose landing light switch ON.

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

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

How can the Low Pressure Switch of the Engine Fire Extinguishing Bottle be checked?. Through a TEST PUSHBUTTON 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.

Which statement concerning to the WEU is correct?. 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. The WEU controls the Master Warning Light and the Aural Warning Speakers.

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.

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 with the ENGINE switch. Automatic EICAS computers switchover occurs.

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.

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

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.

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

The Total Air Temperature (TAT) probe: Is not heated because of a temperature influence between the heater and the sensor element. 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 115 Vac.

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

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

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

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

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

The "SYS FAIL" light 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.

What controls load shedding?. Static Invert. - GCUs only. BPCU, Relays and circuit interlocks.

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.

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/ VERIFY test on the Window heat controller. Activate the window / Probe heat test switch (P61) and the EICAS will display which side window caused the “INOP” light. The EICAS will display on its CRT which window caused the “INOP” light.

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

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 switch on panels P21, Fwd Attd, P22 Aft Attd or P40 APU GND Control panel.

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

Airplane FLYING, what happens to the cargo fire extinguishing bottles when the FWD CARGO FIRE Switch is armed and the BOTTLE DISCHARGE switch was pressed?. - Bottle 1 will be discharged immediately. “ Bottle 2 and 2A are reserved for AFT cargo. Bottle 1 will be discharged immediately. Bottle 2 and 2A will discharge 30 minuted later or when the Airplanes touches down. All three Bottles will be discharged immediately.

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

EICAS level B or C messages are removed from the display unit by pressing the. Recall (RCL) switch on the captain’s pael. ERASE switch on the EICAS maintenance panel. Cancel ( CANC) switch on the captain’s panel.

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.

When the pitot Probes are heated?. - 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. When the aircraft is powered and the control switch is in ON.

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

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

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.

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 AFOLTS CARD 6 a Manual Reset must be performed. At the FWD Discharge Line pressure Switches a Manual Reset must be performed. The lights extinguishes after a successful FIRE TEST.

What are the bus Tie breakers position with both engines running and the IDGs supplying power to the main AC Busses?. 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.

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

The EICAS BYPASS sw, is an alternative procedure to. Switch to the left or right computer. Change information on S.E.I from pounds to kilos or viceversa. Have the EICAS Maintenance Panel available in flight or when jacks.

Which buses can be supplied by the HMG?. Left and Right main AC buses. Left and Right main AC buses. Both AC-XFER Buses, CPT’s FLT-instrument-XFER Bus, HOT BAT BUS.