air cond

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 temperature 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. Double.

In relation to the Cross Bleed valve and its operation: It is a valve that operates pneumatically. It has two electrical motors, one for manual and other for auto operation. It has one electrical motor, for auto and manual operation.

Fuel Tank Inerting System (FTIS), How isthe temperature of the system air controlled?. The temperature of the aireas already been treated and controlled in the pneumatic system of the airplane. By a dedicated heat exchanger installed in the ram air duct of the air conditioning pack. 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 the 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 is possible todo it only on ground. It is possible to do it only in flight. It can be done in flight or on ground.

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.

Which Slats are protected by the wing anti ice system?. Only the SLATS 1 and 2. All the SLATS. Only the SLATS 3-4-5.

Where can the "SYSTEM REPORT/TEST" be done to the Avionic Equipment Ventilation?. On the "ELECTRIC" page on CFDS. On the "PNEUMATICS" page on CFDS. On the "AIRCONDITIONING" page on CFDS.

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

The Engine Low Pressure Valve is closed when... The Pressurization Switch is in the OUT position. The engine is shutdown or the Engine Fire 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)?. Most of the components are located just above the center fuel tank. On a pallet located in the left air conditioned pack compartment. On a pallet located very close to the mixing unit (fwd cargo compartment, rear area.

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

ENHANCED: In the air conditioning system, the flow control valve is controlled by: It is not controlled, it works independently. The Pilot. The air conditioning system controller (ACSC).

The wing anti ice valve is limited on ground by.... Temperature. Over pressure. Time delay.

When 80C are reached for the first time in a zone distribution duct, the zone controller: Closes the Pack Valve. Reduces the output pressure of the Trim Air Pressure Regulating Valve. Closes the Inlet Ram Air Door.

With respect to the Pressurization System: It is s a Semi Automatic system. it is necessary to select the landing field altitude before flight. it is fully automatic, no selection required.

With respect to the Blower / Extractor fans: They are different. They have only one position, not interchangeable. They are equal and interchangeable.

Air Conditioning: The Bypass Valve has a preferred position of: 21 Degrees. 90 Degrees. 10 Degrees.

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.

A320 Classic, How does the pack controller avoid over temperature in the compressor discharge?. By opening the ram air inlet door. By modulating the Flow Control Valve. By modulating the Hot Trim.

In the Avionic Equipment Ventilation System, the Temperature parameter is taken: From TAT sensor. From its own skin temperature 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 Inner tank booster pump will stop, and the center tank will supply fuel to the engines. The center tank fuel transfer system will stop, and the ooster pump will continue supplying fuel to the engines. The FRTT (fuel return to tank) valve will stop returning fuel from the engines to the tanks.

In flight, the bleed air can be obtained from: The Engines or APU. The APU only. Engines only.

Which computer controls the APU leak detectors?. Both BMCs. The BMC N 2. The BMC N 1.

Related to the fuel system in the A 320 NEO, 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 transter 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: The EC. Both EECs (ECUs). Two BMCs.

The normal maximum Cabin Altitude of the system is: About 6.000 ft. Up to 15.000 ft. or less. 8.000 ft.

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 compartement. The Adirus.

Se detectará el sobrecalentamiento neumático del ala (fuga) y se mostrarán advertencias si: Ambos lazos (A y B) detectan sobrecalentamiento (fuga). Solo un lazo detecta sobrecalentamiento (fuga) ya sea A o B. El bucle doble en el pilón detecta sobrecalentamiento (fuga).

The purpose of the fuel sequence valves 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 Overhead Fuel panel, the PB (push buttoon), MODE SELECTOR, controls the operation of the: Main tank fuel booster pumps. Center tank fuel transfer valves. Jet pumps.

A320 Classic, If Pack Controller is failed: The Pack Flow Control Valve closes. Pack oulet T goes to 15 C, by means of Anti Ice Valve. The Air Conditioning Pack is lost.

If one Air Conditioning Pack is inoperative: The A/C can fly normally. Is not possible for the A/C to continue the flight. The A/C is limited to fly up to 31.000 ft.

In order to obtain a specific pack temperature, What components are normally modulated by the Pack Controller?. Ram Air Inlet Door and Anti-ice Valve. Ram Air Inlet Door and the By-Pass Valve. By-Pass Valve and Mixer Flap Actuator.

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.