test 010

What happen to the master caution and warning lights if the FWC 1 fails?. The Capt. master and warning lights are inop. Only the Master caution on the Captain side is inop. Half of the Master Warning and Caution lights on the Capt and F/O are inop.

Where are the class 3 failures shown?. They are shown on the ECAM EW/D. The flight crew can see them on the status page. They are available on the MCDU.

How can you see the avionics status page?. In flight only. Either on ground or flight. On the MCDU on ground only.

Airplane with a speed over 100 knots and it loose both AC busses, then ... The RAT is extended automatically and the Emergency Generator begins to operate. The crew must extend the RAT manually, then the emergency generator begins to operate. The Static Inverter supplies both AC busses.

When released out, what does the GEN 1 LINE pushbutton enable?. To close GLC 1 and supply the fuel pumps from the AC NORMAL BUS. To open GLC 1 and supply the fuel pumps from GEN 1. To close the BTC and supply the fuel pumps from the AC NORMAL BUS.

A BITE type 3 system is connected to the CFDIU by. a discrete input and an ARINC 429 output. a discrete input and a discrete output. an ARINC 429 input and an ARINC 429 output.

When are the "Runway Turn Off" lights turned off. The lights illuminate only at night, automatically after landing. When the nose landing gear is retracted. When the nose landing gear is downlocked.

In normal operation in flight no annunciator light is illuminated on the cockpit panels. This is known as ... Lights out philosophy. Forward facing philosophy. Glass cockpit philosophy.

What is the meaning of the STS cue in the upper ECAM display?. The status page is not empty. There are information comming from FWC # 1. There are more caution messages stored on the upper ECAM display.

What is the purpose of the Wing & Scan Light?. To examine the wing leading edge and the engine nacelle in flight and on ground. To show the wing tip to avoid the collision possibilities. To identify the aircraft during ground operations.

In normal condition, the DC ESS BUS is supplied by ... the Hot bus 1. the ESS TR. the DC BAT BUS.

Where are Class 2 messages in MEL?. At the head of each ATA chapter. In Annex CAT II/III components. In section ECAM / Warning MEL entry.

What is the correlation principle on the PFR?. It is the correlation based on the GMT and the ATA chapter. It is the correlation between the internal and external failures. It is the correlation between the source and identifiers.

The purpose of the Emergency Lighting system is... To provide illumination always. To provide the illumination in case of emergency condition. To provide single illumination at night.

The static inverter operates: Permanently. When one engine generator fails. When on batteries only.

What is the "Funtional Item Number" (FIN)?. It's the zone and sub-zone denomination. It is a fault isolation notice. It's the identification for any part or equipment on the aircraft.

Where are the Flights Phases generated?. In the DMC. In the DFDR System. In the FWC.

Eventually, to solve a failure via AIRBUS TSM we should follow .... a fault isolation procedure. crew decision about returning to the maintenance base. dispatch the aircraft without further action.

Which component monitors the current charge of the battery?. A voltage sample from the DC BAT BUS. The Battery Shunt. The Battery Charge Limiter (BCL).

In normal condition the AC ESS BUS is supplied by ... the Static Inverter. the AC Bus 2. the AC Bus 1.

Some of the advantages of composite materials are: High resistance to extreme temperatures. High corrosion resistance and lower weight. Low cost.

How is the IDG oil cooled?. Through an Air/Fuel heat exchanger. Through one Fuel/Oil heat exchanger. Through an Air/Oil heat exchanger.

The main construction materials of the airplane are: Metallic and Composite Materials. Glass and Aluminum Materials. Wood and Plastic Materials.

TR 2 was disconnected from DC BUS 2 because of overheat. How do you return the system to normal?. RESET via BATT P/B 1 or 2 OFF then ON. RESET via CFDS (MCDU) or RESET P/B on panel 103 VU. The TR 2 returns automatically to normal operation after cool down.

A BITE type 1 system is connected to the CFDIU by ... an ARINC 429 input and an ARINC 429 output. a discrete input and a discrete output. a discrete input and an ARINC 429 output.

Enhanced: What happens if DMC 1 fails?. DMC 3 takes over PFD1, ND1, E/WD and SD automatically. DMC 3 automatically replaces DMC 1. DMC 2 takes over E/WD and SD automatically.

How many types of failures can you see on the E/WD?. Independent, Primary and Secondary failures. Isolated and recorded failures. Passive and inactive failures.

What is the meaning of the ECAM message "CB TRIPPED ON OVHD PNL"?. A monitored circuit breaker (C/B) on the overhead panel is pulled/tripped. Any C/B on the overhead panel is pulled/tripped. monitored C/B on the overhead panel is tripped only automatically.

What is a type 1 system charasteristic?. They can memorize failures occurred in the last 64 flight legs. They are interfaced with the CFDIU by discrete signals only. They can memorize failures.

The BITEs are located: in the CFDIU. in each aircraft system computer which is connected to the CFDIU. in the FWD Avionics Compartment.

What Class of failures are shown on the Post Flight Report?. Class 1 and 3.Insertar respuesta. Class 2 and 3. Class 1 and 2.

What's typical for a primary failure presented on ECAM?. Asterisk in front of failure. Underlined ECAM message. Boxed ECAM message.