repaso

Overtemperature in the compressor area of the ACM is corrected by: closing the repective pack valve. closing the hot trim air. opening the pack anti-ice valve.

Where is the compressor outlet temperatura shown: on the bleed page. on the cond page. it is not shown.

the APU leak detection (s) loop(s) is: single. monitored (s) and controlled (s) by the ECB. bouble.

in relation to the cross bleed valve and its operation: it has two electrical motors, one for manual and other for auto operation. it has one electrical motor, for auto and manual operation. it is a valve that operates pneumatically.

fuel tank inerting system (FTIS),how isthe temperature of the system air controlled : By a dedicated heat exchanger installed in the ram air duct of the air conditioning pack. the temperature of the air has already been treated and controlled in the pneumatic system of the airplane. by means of the ozone converter and air separation module (ASM).

When is the LAV/ galley extract fan operating: As long as the aircraft is powered. when de LAV/galley extract pushbutton in the FAP is ON. When the LAV/galley extract pushbutton in the cockpit is ON.

with respect to the fuel transfer operation: it can be done in flight or on ground. it is possible to do it only on ground. it is possible to do it only in flight.

the operation of the conditioned air system is. fully automatic. mechanic /electric semiauto. manual only.

what is the purpose of the pack: to regulate basic temperature. to regulate hot air pressure. to adjust the temperature in the three zones.

wich slats are protected by the wing anti ice system: only the SLATS3-4-5. all the SLATS. Only the SLATS 1 and 2.

-.where can the “SYSTEM REPORT /TEST” be done to the avionic equipment ventilation: on the “AIRCONDITIONING” page on CFDS. on the "PNEUMATICS" page on CFDS. On the "ELECTRICS" page on CFDS.

The ice on the wing leading Edge slats is prevented by: hot air comming from the pneumatic system. opening the two electrically operated valves. hot air coming from the respective pack valve.

The engine low pressure valve is closed when: The engine is shutdown or the engine fire switch is in the OUT position. the pressurization switch is in the OUT position. the ELACs switch is in the normal position.

where are located the main components of the IGGS (inert gas generation system). On a pallet located in the left air conditioned pack comparment. most of the components are located just above the center fuel tank. on a pallet located very close to the mixing unit (fwd cargo comparment, rear area).

The engine fuel LP valve closes when : The engine is shut down or the eng fire pushbutton is released out. the fuel booster pump presure decreases. the engine fire detection system senses an engine fire.

ENHANCED in the air conditioning system, the Flow control valve is controlled by: the air conditioning system controlled (ACSC). the pilot. it is not controlled,it works independently.

The wing anti ice valve is limited on ground by: time delay. over pressure. temperature.

when 80C are reached for the first time in a zone distribution duct, the zone controller: Reduces the output pressure of the trim air pressure regulating valve. closes the pack valve. closes the inlet ram air door.

with respect to the pressurization system: It is fully automatic, no selection required. it is necessary to select the landing field altitude before flight. it is a semi automatic system.

with respect to the blower/ extractor fans: They are equal and interchangeable. they have only one position,not interchangeable. they are different.

-.air conditioning:The bypass valve has a preferred position of: 21 degrees. 90 degrees. 10degrees.

what is the function of the zone trim air valve: to optimize the zone temperature by adding hot air. to regulate the hot air pressure. to optimize the zone temperature by adding cold air.

A32O classic how does the pack controlled avoid over temperature in the compressor discharge: by modulating the hot trim. by opening the ram air inlet door. by modulating the flow control valve.

in the avionic equipment ventilation system,the temperature parameter is taken : from its own skin temperature sensor. from TAT sensor. from P2/T2 sensor.

what is the purpose of intermediate pressure and high pressure switching in the pneumatic system: to keep air bleed at a sufficient pressure at low engine speed. to regulate the output temperature depending on the pack valve position. to regulate the output pressure depending on fan air valve position.

what will happen if the FULL level sensor is in WET in the inner fuel tank : The center tank fuel transfer system will stop,and the booster pump will continue supplying fuel to the engine. the inner tank booster pump will stop,and the center tank will supply fuel to the engines. The FRTT (fuel return to tank) valve will stop retuning fuel from the engines to the tanks.

In flight the bleed air can be obtained from : the engine or APU. the APU only. engines only.

wich computers controls the APU leak detectors: The BMC N1. both BMCs. The BMC N2.

related to the fuel system in the A320NEO, to supply fuel to the engines,the system has: four booster pumps in the main tanks,and two jet pumps that supply fuel directly to the engines from the center tank. four (4)booster pumps two in each main tank,and two transfer valves in the center tank. six (6) booster pumps two in each main tank two in the center tank.

the pneumatic system is monitored by: two BMCs. the EC. both ECCs(ECUs).

the normal maximum cabin altitude of the system is: 8000ft. about 6000ft. up to 15000 ft or less.

pressurization,the CPC obtains the cabin altitud information from: a pressure sensor located in the CPC. a dedicated pressure switch located in the avionic equipment comparment. the adirus.

.the neumatic wing overheat (leak) will be detected and warnings will be shown if: both loops (A and B) detect an overheat (leak). Only one loop detects an overheat (leak), either A or B. The dual loop in the pylon detects an overheat (leak).

the purpose of the fuel sequence valve is: to reduce output pressure of the wing boost pumps. to reduce pressure on the APU boost pump. to reduce output pressure of the center boost pumps.

in the overheat fuel panel th PB (push buttoon) MODE SELECTOR,controls the operation of the: center tank fuel tranfer valves. main tank fuel booster tank. jet pumps.

A320 classic,if pack controlled is failed: pack outlet T goes to 15C,by means of anti ice valve. the pack flow control valve closes. the air conditioning pack is lost.

in order to obtain a specific pack temperatura, What components are normally modulated by the pack controlled: ram air inlet door and the by pass valve. by-pass valve and mixer flap actuator. ram air inlet door and anti-ice valve.

-.if one air conditioning pack is inoperative : The A/C is limited to fly up to 31000ft. is not possible for the A/C to continue the flight. the A/C can fly normally.

how is the refuel valve normally open: by energization of a solenoid and application of fuel pressure. by energization of a solenoid. only by pressing the manual command button.