Posted at 11.28.2018
This report represents analysis and analyzes Airbus A318 pneumatic system. Alternatively, aeroplanes pneumatic systems will be lay-out in this survey. The resources of supply in this technique both main and standby may also be mention. The past is the pressure and temperatures control in this technique will be analysed.
The reason for this article is to analyzing Airbus A318 pneumatic systems and the function of pneumatic systems in Airbus A318.
The function Pneumatic system is employed to provide High pressure (Horsepower) for air-conditioning, pressurization, pressurization and anti-icing. Engine bleed, APU and exterior ground service are used to create HP.
The engine motor bleed air is the environment taken within the engine compression stage when pressure and temps regulated prior. RUTHLESS Compressor (HPC) levels, intermediate Pressure (IP) levels and HP stages will be the place where in fact the air is bled.
When the engine in low vitality condition, the RUTHLESS Bleed Valve (HPV) will function and offer air to the systems. But, when the pressure inside the IP bleed is sufficient, HPV will closes.
HP VLV is switch ON when the IP stage is not a enough pressure for pneumatically systems (when engine at low swiftness). The pressure supply is between 8 to 36 psi. Horsepower VLV is push to close when PRV is closed down because Horsepower VLV pressure should no more than PRV pressure. In the event the sense line on the limitation, the machine will over pressure and cause malfunction.
The function of Bleed Monitoring Computer (BMC) is to keep up HP VLV sealed during the airfare.
The HP VLV solenoid will active by BMC when:
The engine unit is higher than Idle and pressure is over 80psi.
When the Wing Anti Ice (WAI) is OFF condition
The altitude is over 15, 000 feet
The pack configuration is act normal.
When solenoid is de-energized, this suggest the HP VLV will open up. This problem is restrained.
IP check valve can be used to avoid the ventilation in the anti-direction. Once the HP VLV starts, IP check valve will make sure hit air at IP level wouldn't flow back again to the engine.
The goal PRV is used to keep up the bleed pressure between 44 psi. Thermal fuse can be used to causes the PRV to close when the engine's case temps was around 450C.
The CTL SOL is located downstream from the precooler. The reason is to regulate PRV pressure will going to bleed out. These systems are handled by pneumatic and electric.
The CTL solenoid will energize by BMC when:
Over temperature of the precooler
Over pressure of the PRV
Leak detection encircling area
APU bleed valve not close
Starter Valve not closed
This valve is generally open up condition, close when pressure is apply upon this valve. This valve closes at 75psi and fully shut down at 85. It will start around 35psi.
It is act as a transducer. It really is connected to both BMCs and analyzes the pressure from PRV.
This element is also same function as regulated pressure. Nonetheless it is used to learn from HPV and PRV.
It is employed to control the fan airflow to the precooler and keep maintaining bleed air heat at 200C.
Act as exterior servo-control. It is located downstream from the precooler.
It is utilized to reduce the temperature engine motor bleed air.
This part is connected to both BMCs. It really is use to regulate heat downstream from the precooler.
APU is utilized to bleed air source for air- conditional and engine start when the aeroplanes was on the ground. On the other hand, APU also use to provide electrical power to supply the electrical power systems. APU bleed act as a backup vitality for both systems. The both bleed systems are fastening along by a combination bleed duct.
External air can also be use during in air travel, depend on the high of the airplane. When in flight, the APU bleed supply only given by the left hands side of the cross bleed duct.
APU bleed valve can be used to provide APU is jogging. The valve is handled by electrically by the Electrical Control Field (ECB) solenoid and pneumatic. When air pressure and electrical power are unavailability, valves spring and coil -packed will shut down.
It is use to monitor the pressure and closes or starts the APU bleed valve.
The function of X-Bleed system is to interconnection of kept and right bleed air are system. In the systems, it includes shut-off valve controlled by electronic two DC motors. Primary electric motor will function in Vehicle mode. The position of the shut down valve is manipulated by the (BMC) in line with the APU bleed settings. Secondary engine will be utilized to over dominate the Vehicle mode. The positioning of the valve is manipulated by X-bleed selector.
It is utilized so resource air by a floor air cart and linked to the HP ground connector. When floor air cart is connected, only the left hand part of the bleed systems has source. Left hand aspect and right palm side bleed system will nourish with earth air resource when X-bleed valve selector will be select in the wild position.
SYSTEMS Guide - Engine unit BLEED & APU BLEED/ Alternative AIR
(From MAINTENANCE COURSE BOOK - T1 (CFM56-5B/Me personally Name: Pneumatic Level) Site 3
Airbus A318 pneumatic systems are supply by engine unit bleed, APU and the bottom air supply. Engine bleed are used provide air pressure when aircraft engine is low electric power condition. The pressure is control by the Horsepower valve. Following the pressure inside the IP bleed is sufficient, high pressure valve (HPV) will turn off.
APU can be used as standby pneumatic system. It is used to provide electrical power to function the electrical and environment systems. It can be used when the airplane on the ground. APU also used when in flight condition with respect to the altitude of the plane.
It is used so source air by way of a floor air cart and connected with HP floor connector. Air only was resource to left hands aspect of bleed system. So, crossbleed valve use to feed air systems to the right side aspect of the bleed system.