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What is the main procedure for leveling the aircraft? ATA 8 LEVELING Y WEIGHING. Level indicator. Spirit leveler. ADIRS.

What zone relates to the upper fuselage? ATA Dimensions and areas. 100. 200. 800.

What will occur when the annunciator lights switch is set to TEST? ATA 33 LIGHTS. The ECAM display a test pattern. All LEDs show atest pattern. THhe cockpit lighting systems dims.

When will the emergency lights be supplied from EPSU batteries? ATA 33 LIGHTS. The EMER push-button on the forward attendant panel is depressed and the EMER Lt switch is ON. The EMER Lt switch is ARM, usual AC power and DC essential bus fails. The EMER Lt switch is ON and the DC essential bus is supplied.

What has to be done to recover the failed ND? ATA 31 INSTRUMENT SYSTEMS. ND image must be switched over to upper ECAM display. Nothing. ND image is recovered automatically by it’s associated DMC. Manually pressing PFD/ND transfer p/b.

What is the reconfiguration if the EWD fails? ATA 31 INSTRUMENT SYSTEMS. EWD is automatically transferred to lower ECAM display. No reconfiguration possible. EWD can be manually transferred to lower ECAM display.

When will the STAT INV operate in flight? ATA 24 ELECTRICAL POWER. AC buses and CSM/G not available. CSM/G available and RAT extended. CSM/G supplies AC ESS at slat extension.

What are the Main Electrical power sources? ATA 24 ELECTRICAL POWER. Integrated Drive Generators (IDGs), APU Generator and External Power. Integrated Drive Generators (IDGs), Back Up Generators (BUGs), Primary and Secondary External Power. Integrated Drive Generators (IDGs), APU generator, Back Up Generators (BUGs).

ATA 24 ELECTRICAL POWER What type are batteries?. Lead-acid. Nickel cadmium. Lithium-ion.

What is the effect if TR2 fails on ground with EXT PWR A connected and the MAINT BUS switch in ON position? ATA 24 Electrical power. DC BAT BUS is not available. DC SERVICE BUS is not available. TR1 will supply DC SERVICE BUS.

What supplies the AC BUS 1 and 2 if Engine 2 fails in flight and APU is operating? ATA 24 Electrical power. GEN 1supplies AC BUS 1 and 2. GEN 1 supplies AC Bus 1, APU GEN supplies AC BUS 2. AC BUS 2 will not be powered.

What is the effect if the BUS TIE P/BSW (13XU on 235VU) is set to OFF? ATA 24 Electrical power. BTC1, BTC 2 and SIC opens. BTC 1 and 2 opens, SIC closes. BTC1 and 2 closes, SIC opens.

What is the purpose of the Inadvertent Paralleling Trip function on an AC BUS? ATA 24 Electrical power. Prevents two different sources to be connected in parallel for more than 130 ms. Allows two different sources to be connected in parallel after 130 ms. Prevents two different sources to be connected in parallel for more than 80 ms.

How are the main and APU batteries ventilated? ATA 24 ELECTRICAL POWER. Dedicated fan below each battery. Equipment cooling and ventilation system. Differential pressure between cabin and the outside.

What is the supply priority for AC Bus 1XP? ATA 24 Electrical power. IDG 1/APU GEN/EXT PWR B/EXT PWR A/IDG 2. What is the supply priority for AC Bus 1XP?. IDG 2 /APU GEN/EXT PWR A/IDG1.

What are the characteristics of type 3 systems? ATA 45 Onbooard Maintenance System. They can be downloaded in flight and on ground. They can be uploaded in flight. They do not generate failure messages.

What are the type 1 system computers in CMS? ATA 45 Onboard maintemance System. system that can remember last 64 flight memories. system that can remember only last flight memory. system that do not have any memory.

Where are the ACARS functions In ATIMS? ATA 46 Information Systems. ATC menu. AOC menu. Communication menu.

What types of communication does ATIMS use for data-link communication? ATA 46 Information Systems. Radio Communication, Internet, and Satellite Communication. GPS, Cellular Data, and Radar. VHF Data Link, HF Data Radio, and Satellite Communication.

How do class 2 aircraft system failures show on ECAM? ATA 31 INDICATING AND RECORDING SYSTEMS. By a box on the failed system at lower part of the EWD. By system failures with underline in the EWD. On the ECAM status page.

When is the DFDRS usually powered? ATA 31 INDICATING AND RECORDING SYSTEMS. If one engine is started until 5 minutes after last engine shutdown. No.1 engine start until 5 minutes after first engine stop. At electrical power-up until 5 minutes after power down.

How many ECAM modes of operation let aircraft system operation and status data show on the SD? ATA 31 INDICATING AND RECORDING SYSTEM. 2 manual and 2 automatic. 3 manual and 1 automatic. 1 manual and 3 automatic.

What is the maximum number of aircraft parameters that can be viewed on MCDU by the alpha call up function?: ATA 31 INDICATING AND RECORDING SYSTEMS. 3000. 300. 30.

When a PFD fails where will the PFD data show? ATA 31 INDICATING AND RECORDING SYSTEM. The off-side inboard display. The related inboard display. The lower center display.

When does the EFIS SINGLE SOURCE 2 message on both PFDs comes on? ATA 31 INDICATING AND RECORDING SYSTEMS. When DMC1,2 and 3 have failed. When DMC 2 is driving all 6 DUs. When EFIS is in Single Mode.

How can a system page show on the EWD when ECAM is in single-display mode? ATA 31 Indicating and recording systems. Not able to see any system page. Press and hold any system page button on ECAM Control Panel. Press any system page button on ECAM Control Panel.

How many points on the structure are designated for the purpose of lifting the aircraft? ATA 7 lifting y shoring. 2. 4. 3.

What is the purpose of ATA 10-00 ? ATA 10 Parking and Storage. Parking and mooring. Parking only. Mooring only.