pneumatic system
DESCRIPTION
sistema neumatico del avionTRANSCRIPT
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PNEUMATIC SYSTEM
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STIVEN PINZÓN
PRESENTADO POR:
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Generalidades
El propósito del sistema neumático es suministrar aire comprimido para:
• Aire acondicionado
• Presurización
• Arranque de los motores
• Sistema anti-ice térmico para las alas
• Presurización del sistema hidráulico y agua
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Generalidades
• El aire es obtenido del sangrado del compresor, APU o planta externa y e conducido dentro del sistema neumático principal
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Generalidades
• El aire comprimido es obtenido principalmente de la 8va etapa del compresor
• También se toma de la 13v etapa si no satisface los requerimientos dl sistema de aire acondicionado
• El sistema controla la presión, temperatura y limpia el aire
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Generalidades
• La energía eléctrica es necesaria para control, indicación y avisos durante la operación del sistema
• The pneumatic system operates pneumatically and is monitored by 2 Bleed Monitoring Computers (BMC 1 & 2).
• There is one BMC for each engine bleed system.• Both BMCs exchange data. If one BMC fails, the
other BMC takes over most of its monitoring functions.
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APU BLEED/EXTERNAL AIR
The left and right bleed systems are connected by a crossbleed duct.(ducto del multiple aire sangrado)A crossbleed valve enables their interconnection or isolation (aislamiento).The APU can also be used for bleed air supply. This is usually doneon the ground for air conditioning and for engine start.However, APU BLEED air could also be used in flight, dependingon altitude. The APU bleed supply is connected to the left side of thecrossbleed duct.On the ground, a HP ground power unit can be connected to the leftside pneumatic system. The right side may be supplied by openingthe crossbleed valve.
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LEAK DETECTION
Leak detection loops (bucles) are installed along the hot air supply ducts ofthe pneumatic system. The loops are made of multiple sensingelements connected in series. The leak detection loops are connectedto the BMCs. If a leak is detected, a signal is sent to the BMC 1 or 2which automatically isolates (aislara) the affected area by closing the crossbleedvalve and shutting off (apagando) the engine bleed on the affected side. The leakdetection system is organized into three loops. Here are the loops andthe protected areas: - pylon: from the precooler to the wing leadingedge,- wing: wing leading edge including the wing air inlet supply duct).- APU: APU aft supply duct (left hand side of the fuselage) from APUfirewall to wheel well area.
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CONTROL & INDICATING
• This section highlights the control panels and indications for the pneumatic system.
CONTROL PANEL
• Controls for the pneumatic system are part of the AIR COND panel, located on the overhead panel.
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CONTROL & INDICATING
ECAM INDICATION
• The pneumatic system indications are displayed on the lower part of the ECAM BLEED page.
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COMPONENT LOCATION
The main components of the fuel system are located on the engines and
in the pylons
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• PRESSURE REGULATION COMPONENTS
The pressure regulation components are located on the engines:
- the Engine High Pressure Valve (HPV),
- the Engine BLEED PRV,
- the OPV.
• TEMPERATURE REGULATION COMPONENTS
The temperature regulation components are located on the engines
and in the pylons:
- the FAV,
- the Precooler
COMPONENT LOCATION
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COMPONENT LOCATION
OTHER COMPONENTS
The crossbleed valve is located in the forward section of the lower
fuselage belly fairing area.
Get access to the HP ground connector through a small access door located on the lower fuselage belly fairing.
The APU bleed valve is located on the APU.
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SAFETY PRECAUTIONS
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AIR CONDITIONING, VENTILATION ANDPRESSURIZATION INTRODUCTION
The basic airflow through the pressurized part of the fuselage starts with the pneumatic system.Hot, high pressure air is supplied to two packs. The packs are responsible for basic temperature regulation.From the packs the air is distributed throughout the aircraft.The pressurization system controls the airflow overboard to maintain the cabin pressurization within safe limits.
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BASIC AIR CONDITIONING SYSTEM INTRODUCTION
The pneumatic system supplies air to each pack. The packs are responsible for BASIC temperature regulation.At the mixer unit, the air is mixed with air re-circulated from the maincabin. This reduces the overall bleed demand and saves fuel.From the mixer, the air is distributed to the cockpit and the forward andaft cabin zones.Some of the air from the pneumatic system is used for the OPTIMIZEDtemperature regulation system. This hot air is mixed with the air fromthe mixer to adjust the temperature in each zone independently.The air is distributed throughout the cabin and finally, dischargedoverboard through the outflow valve to maintain pressurization
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ZONE TEMPERATURE REGULATION SYSTEMINTRODUCTION
The packs supply the mixer unit. Three separate aircraft zones are suppliedfrom the mixer unit:- cockpit,- forward cabin,- aft cabin.Two cabin recirculation fans are installed to reduce the bleed air demand and therefore save fuel.These fans establish a recirculation flow of air from the cabin zones to the mixer unit. In normal operation, there are no ECAM indications associated with the cabin fans.The ZC controls and monitors the temperature regulation system for thecabin zones. On the overhead AIR COND panel, the flight crew selectsthe desired individual compartment temperature
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CONTROL AND INDICATING
This section will highlight the control panels and indications for the air
conditioning system.
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CONTROL PANELS
On the overhead panel, the AIR COND panel is used by the pilot to control the air conditioning system. This panel contains the PACK switches, the zone temperature selectors, the PACK FLOW control, and the HOT AIR control switch.
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CONTROL AND INDICATING
ECAM PAGESBasic temperature regulation is accomplished by the packs. Packparameters, such as pack flow and bypass valve position are found on the upper section of the ECAM BLEED page.The ECAM AIR COND page contains the optimized temperatureregulation parameters, such as duct temperature, zone temperature and trim air system indications.The ECAM CRUISE page also contains zone temperature indications.
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COMPONENT LOCATION
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MAINTENANCE/TEST FACILITIES
The ZC is the interface between the PCs and the Centralized Fault Display Interface Unit (CFDIU) for test purposes and fault reporting. The ZC test
on the Multipurpose Control and Display Units (MCDUs) initiates a complete air conditioning test including the packs.
The ACSC are connected to the CFDIU for test purposes and fault reporting, available on the MCDU.
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