Pump And Hydraulic Fluid Engineering Essay

Pump And Hydraulic Fluid Engineering EssayIntroductionThis assignment main(prenominal)ly talks about the hydraulic corpse in an aircraft. The hydraulic frame in an aircraft is use for operating various services such as set down cant, tramp brakes and power f wake controls etc. Each system has its own hydraulic circuit within the system. These independent circuits are connected to the common draw and return lines of the hydraulic power circuit. A complete power hydraulic system consists of the followingA power or delivery circuit,A repress of service circuits,Emergency circuits.Below is the diagram of basic hydraulic systemhttp//www.ustudy.in/sites/default/files/images/hydraulic-system.gif line TwoPumpPump provides pressurise hydraulic suave to the system by comprising the smooth which comes from the reservoir. Pump back tooth pressurise the unsound up to 5000 psi. depends on different heart and souls.Pressure Reducing ValveThe Pressure Reducing valve reduces the syste m output storm to a squash suitable for operating a specific system or component.Pressure Relief ValveWhenever there is excessive pull in the system the wedge relief valve reliefs the extra shove.ReservoirThe function of reservoir in the hydraulic system is to store the hydraulic fluid and delivers the hydraulic fluid to the fondness which then gives the pressurise fluid to the system. The reservoir also pressurise the fluid up to 40psi in disposition to not get cavitation. getThe function of Motor is to help in engaging the pump and also help in plumping the system.StrainerStrainer is a filter. It filters out the dirt before the fluid goes to the pump. There are high and low pressures strainers, normally the high pressure strainer are after the pump and low pressure are before the pump.Task ThreeB767hydraulicS SYSTEMSINTRODUCTIONThis airplane has three independent hydraulics systems which are left wing Hydraulic systemThis hydraulics system powers theFlight controlsLeft sid e locomotive engine Thrust reversalIt consists ofReservoir,Engine Driven pump, andElectric labor determined pumpRight Hydraulic systemThis system is alike(p) to Left hydraulic system and it consists of equalReservoir,Engine driven pump, andElectric motor driven pumpThis system powers theFlight controls,Right side engine Thrust reversal,Normal brakes, andPitch enhancementCentre hydraulics systemThe system consists ofReservoir,Two Electric motor driven pumps,An Air driven contend pump, andRAT (Ram Air Turbine) pumpIt powers theFlight controls,Nose wheel steering,Flaps and slats,Alternate brakes,Landing gear,Hydraulic driven generator, andTail dislocateSo essentially the hydraulic system of this aircraft powers theFlight controls,Leading edge slats,Trailing edge flaps,Landing gear,Wheel brakes,Nose wheel steering,Autopilot servos,Thrust reversals, andTail skidFlight control system components are distributed so that any hydraulic system can provide commensurate airplane control lability. All hydraulic reservoirs supplies fluid to pumps and these pumps pressurized the system and the reservoirs are pressurized by bleed air system.Below figure shows three independent system what they consist of and to what they power. It also display there switches in the cockpit.HYDRAULIC SYSTEM SCHEMATICSFLUID SUPPLYHydraulic fluid is supplied to each pump from a reservoir. Reservoirs are pressurized from bleed air system.There is fluid bar measured device in all the reservoirs which provides information on EICAS status display. When RF illuminates on the EICAS status page then the reservoirs requires refilling prior to dispatch. reasonable only when airplane is on ground with twain engines shutdown or after landing with flaps up during taxi-in. As shown in figure down the stairsThe QTY (1) light illuminates and the EICAS advisory subject e.g. L HYD QTY displays which means that left side reservoir fluid quantity is low. SYS PRESS (2) illuminates when the system pressu re is less.ENGINE drive PUMPThe primary hydraulic system pump is engine driven pump. As there are deuce engines on this aircraft it has two engines driven pump left and right. It runs with the engine and pressurized the system.When the pump output pressure is low the primary pump PRESS light illuminates on the hydraulic overhead panel and a warning display on the EICAS e.g. (if it is right side) R HYD PRIM PUMP. When the pump temperature is high OVHT light illuminates on the hydraulic overhead panel and again a warning display on the EICAS e.g. (if its left side) L PRIM HYD OVHTELECTRIC MOTOR DRIVEN PRIMARY PUMPThe two centre electric motor driven primary pumps are identical to the left and right systems electric motor driven pumps. The C2 pump may be load shed mechanically to reduce electrical loads. As you can see the figure above it has also the same PRESS low pressure and over heat OVHT warnings on hydraulic overhead panel. The associated EICAS messages for low output pressure C HYD PRIM 1 or C HYD PRIM 2 and for over heat C HYD 1 OVHT or C HYD 2 OVHT.ELECTRIC MOTOR DRIVEN DEMAND PUMPAn electric motor driven pack pump provides an extra hydraulic power either on demand or continuously for periods of high system demand. The demand pump also provides a backup hydraulic power source for the engine driven primary pumps.To reduce electrical load, the electric demand pump is inhibited on the ground during engine start of either engine, when only one electrical generator is operating. The demand pump PRESS and SYS PRESS lights illuminates when starting engines on the ground. As shown in the figure at a lower place the overhead hydraulic panel with warnings. The warnings will also display on the EICAS e.g. R HYD DEM PUMP.AIR DRIVEN DEMAND PUMPAn air driven demand pump also provides additional hydraulic power either on demand or continuously for periods of high system demand. This pump provides the backup hydraulic power for electric motor driven primary pumps. As shown in picture above it shows the warnings on the hydraulic panel PRESS when its low pressure and OVHT when the pump come over heat. The warning can also be seen in EICAS.RAT (RAM AIR TURBINE) PUMPThis pump is used in collar conditions it provides hydraulic power to the flight control portion of the centre hydraulic system. The RAT provides satisfactory hydraulic power at the speed above one hundred thirty knots. In flight, the RAT deploys automatically when both engine fails. The RAT is inhibited from auto deployment on the ground.The RAT can be deployed manually by energy the RAT switch. The UNLKD light illuminates and the EICAS advisory message RAT UNLOCKED displays when the RAT is not stowed and locked. Once the RAT is producing the pressure the PRESS lights illuminates. The SYS PRESS light lighted if RAT is only the source of centre system pressure. Once the RAT is deployed then it cannot be stowed in flight.SYSTEM PRESSURE INDICATIONSThe SYS PRESS lights illuminates and the EICAS caution message e.g. ( for left hydraulic system) L HYD SYS PRESS when the left side hydraulic system pressure is low same for the right side and centre system.HYDRAULIC DRIVEN GENERATORHydraulic driven generator is automatically powered by the centre system when electrical power is lost from both main AC buses. The centre air demand pump then operates continuously to ensure sufficient hydraulic pressure to drive the generator.HYDRAULIC PANEL transcription Pressure (SYS PRESS) LightsIlluminated (amber) system pressure is low.Reservoir Low Quantity (QTY) LightsIlluminated (amber) reservoir quantity is low.Left/Right Engine (L/R ENG) thugital Pump SwitchesON the engine driven hydraulic pump pressurized when engine rotates.OFF (ON not visible) the engine driven hydraulic pump is turned murder and depressurized.Pump Pressure Lights (PRESS) Illuminated amber Pump output pressure is low.Pump Overheat (OVHT) LightsIlluminated amber pump temperature is high.Centre 1/ 2 Electric (C1/2 ELEC) Primary Pump SwitchesON the electric motor driven pump pressurized the centre hydraulic system.OFF the electric motor driven pump is turned rack up and is not pressurizing the system.Left/Right Electric and Centre Air ( L/R ELEC and C AIR) Demand Pump SelectorsON continuous operationAUTOLeft/Right electric pumps operate when engine pump pressure is low.Centre air demand pump operates when both centre electric pump pressure is low.Centre AIR demand pump operates when heavy load items are selected.OFF Pumps are turned offLANDING tiltIntroductionThe airplane has two main landing gear and single nose gear. The nose gear is a steerable with two wheel unit. Each main gear has four wheels in tandem pairs.Hydraulic power for retraction, addition, and steering is supplied by the centre hydraulic system. An alternative extension system is also provided.Below is the schematic of the landing gear systemAir Ground Sensing SystemThe air ground percept system receive s air ground logic signals from tilt sensors located on each main landing gear. These signals are used to configure the airplane system to the leave air or ground status.A nose air ground system receives signals from nose gear strut compression sensors. These signals are for controlling perish warning and portions of the caution and warning system.LANDING GEAR UNDER NORMAL OPERATIONThe landing gears are normally controlled by the landing gear lever.On the ground, the lever is held in DN position by an automatic lever lock controlled by the main gear tilt sensor.The lever lock can manually overridden by pushing and holding the landing gear lever LOCK OVRD switch. In flight, the lever lock is automatically released by the air ground sensing of main gear tilt sensor.Landing pitch RetractionWhen the landing gear lever is positioned to UP, the tilted landing gear begins to retract. The landing gear doors control surface and the gear retract to up position. Automatic wheel braking oc curs during gear retraction. The landing gear lever is placed in the OFF position to depressurize the landing gear system.Landing Gear ExtensionWhen the landing gear level is propeld to DN, the landing gear door opens, the gear are unlocked, and the GEAR and DOORS light illuminates.The gears are hydraulically powered to the down and lock position. The down locks are powered to the lock position, all hydraulically actuated gear door close, and the main gear trucks hydraulically tilt to the flight position.When all gears are down and locked, the gear down light illuminates and the GEAR and DOOR light extinguish.Landing Gear Alternative ExtensionThe alternative landing gear extension system uses an electric motor to trip the locking mechanism for each gear. Selecting DN on the ALTN GEAR EXTEND switch releases all the door and gear up locks, the landing gear then free fall to the down and locked position.TASK FOUR health SAFETY REGULATIONIntroductionThe Workplace (Health, Safety and W elfare) Regulations 1992 cover a wide range of basic health, safety and welfare issues and apply to most studys (with the excommunication of those fitplaces involving construction work on construction sites, those in or on a ship, or those below ground at a mine). They are revise by the Quarries Regulations 1999, the Health and Safety (Miscellaneous Amendments) Regulations 2002, the Work at Height Regulations 2005, and the Construction (Design and Management) Regulations 2007.These Regulations aim to ensure that workplaces meet the health, safety and welfare needs of all members of a workforce, including people with disabilities. Several of the Regulations require things to be suitable.Followings are the Health and safety regulations which should be followed in the working placeHEALTHVentilationWorkplaces need to be adequately ventilated. Fresh, clean air should be drawn from a source outside the workplace, uncontaminated by discharges from flues, chimneys or other assist outle ts, and be circulated through the workrooms. Ventilation should also remove and dilute warm, humid air and provide air movement which gives a sense of freshness without causing a draught. If the workplace contains process or heating equipment or other sources of dust, fumes or vapours, more fresh air will be needed to provide adequate ventilation. Windows or other openings may provide sufficient ventilation but, where needed, mechanical ventilation systems should be provided and regularly obligeed.Temperatures in indoor workplacesEnvironmental factors (such as humidity and sources of heat in the workplace) combine with personalisedised factors (such as the clothing a worker is wearing and how physically demanding their work is) to influence what is called someones thermal comfort. Individual personal preference makes it difficult to specify a thermal environment which satisfies everyone. For workplaces where the activity is mainly sedentary, for example offices, the temperature should normally be at least 16 C. If work involves physical effort it should be at least 13 C (unless other laws require lower temperatures).Work in hot or coolness environmentThis includes risk to workers health from working in either a hot or cold environment needs to consider both personal and environmental factors. Personal factors include body activity, the amount and type of clothing, and duration of exposure. Environmental factors include ambient temperature and radiant heat and if the work is outside, sunlight, wind velocity and the presence of rain or snow.LightingLighting should be sufficient to enable people to work and move about safely. Lighting and light fittings should not create any hazard. Automatic emergency lighting, powered by an independent source, should be provided where sudden loss of light would create a risk.Cleanliness and waste tangibleEvery workplace and the furniture, furnishings and fittings should be kept clean and it should be possible to keep th e surfaces of floors, walls and ceilings clean. Cleaning and the removal of waste should be carried out as necessary by an effective method. Waste should be stored in suitable receptacles.Room dimensions and spaceWorkrooms should have enough free space to allow people to move about with ease.Workstations and seatingWorkstations should be suitable for the people using them and for the work they do. People should be able to leave workstations swiftly in an emergency. If work can or must be done sitting, seats which are suitable for the people using them and for the work they do should be provided. Seating should give adequate support for the lower back, and footrests should be provided for workers who cannot place their feet flat on the floor.SAFETYMaintenanceThe workplace, and certain equipment, devices and systems should be maintained in efficient working order (efficient for health, safety and welfare). Such maintenance is required for mechanical ventilation systems equipment and d evices which would cause a risk to health, safety or welfare if a fault occurred and equipment and devices think to prevent or reduce hazard.The condition of the buildings needs to be monitored to ensure that they have appropriate stability and solidity for their use. This includes risks from the normal running of the work process (e.g. vibration, floor loadings) and foreseeable risks (e.g. fire in a cylinder store).FloorThe surfaces should not have holes or be uneven or slippery, and should be kept free of obstructions and from any article or substance which may cause a person to slip, trip or fall. Criteria for defects such as subsidence, unevenness, pot holes, hookup of surface water, cracks and ruts should be determined and set, and maintenance systems developed to undertake repair when these limits are exceeded.WindowsOpen able windows, skylights and ventilators should be capable of being opened, closed or adjusted Safely and, when open, should not pose any undue risk to anyo ne.FATIGUE TESTING MACHINEFatigue testing machine test and determines the efficacious working life of a component which is subjected to repeated load. Fatigue testing machine applies pre-defined loads or alternating loads to the sample component and records dig life indicated by the number of cycles required to product failure.Health Safety IssueFollowings are the health and safety issues with fatigue testing machineAs Fatigue-testing machines produce heavy vibration so it requires a strong foundation.Safety guidelines provided by the metal fatigue-testing equipment manufacturers should be followed before starting a fatigue test. square-toed controls and accessories should be installed for fatigue-testing machine to prevent accidents.Task FiveMaintenance Procedure for Landing GearLanding Gear is the most rugged part of an aircraft and should be maintain properly in order not have accidents.In order to increase the life span and minimising the accidents regularly inception should be do for inspecting the landing gear because of the force hitting the runway upon landing stresses the entire system no matter how gentle the landing is.Following is the procedure to maintain the landing gearPlace the aircraft on jacks in the approved manner as detailed in the manufacturers maintenance manual.Interconnect a manual pump (complete with a one gallon reservoir and a 3000 p.s.i. pressure gauge) into the system at the service tee fitting. This fitting is located downstream of the pump check valve.Deactivate the pump and motor by disconnecting the plug on the pressure switch.Disconnect the pressure relief valve and the thermal relief valve from the system and cap off the lines.Disconnect the accumulator from the system and cap off the line.Pressurise the system to 3000 p.s.i.When the pressure reaches 3000 p.s.i., the system must remain within 50 p.s.i. of this pressure for one fleck without additional pumping.Reconnect the THERMAL relief valve and pressurise the system until the valve opens. The cracking pressure of the valve should be 2200 + or 50 p.s.i.*With the gear doors disconnected, select gear up and retract using the hand pump. Take the gear up slowly and check the flex lines for clearance and signs of chafing.When the gear reaches the up position, increase the pressure to 3000 p.s.i. The system must again remain within 50 p.s.i. of this pressure for one minute.Pull the 5 amp L/G control breaker, reconnect the pressure switch plug and reset the 5 amp breaker. Extend the gear with the normal system.Reconnect the pressure relief valve and pressurise the system until the valve opens. The cracking pressure for this valve is the same as the thermal relief valve, 2200 + or 50 p.s.i.*Disconnect manual pump from service tee and cap tee.Check emergency nitrogen feeding bottle is charged to 1500 p.s.i.With gear in down position and system pressurised, open manual nitrogen valve in the cockpit and check for leaks in the midst of the valve and th e actuators. Maximum leakage rate, 50 p.s.i. in ten minutes.Close the manual nitrogen valve and bleed off the pressure in the emergency system by loosening the line at the bleed valve in the nose wheel well. Prior to re-connecting the line, check that the bleed valve is open. Blow air gently into the bleed valve fitting and check the top of the valve for a flow of air.Charge the accumulator to 1250 p.s.i. Re-connect to the system.Recharge the emergency nitrogen bottle to 1500 p.s.i.http//www.business.com/images/divider.gifTasksYesNoJack is placed on right positionAircraft is put on jack according to maintenance manualConnect manual pump into the system at service tee fitting. Fill it to one gallon reservoir with 3000 psi.Pump De-activatedPressure relief valve and thermal valve dis-connectedAccumulator dis-connectedPressurise till 3000 psiSystem remain at 50 psi for a minuteThermal relief valve re-connected and system pressurise until the valve opensGear doors dis-connectedGear up se lectedRetract using the hand pump and check the flex lines for clearance and signs of chafing.On the gear reaches the up position, increase the pressure to 3000 p.s.i. The system must again remain within 50 p.s.i. of this pressure for one minute.System remained within 50 p.s.i. for one minute.5 amp L/G control breaker pulled.Pressure switch plug reconnected and reset the 5 amp breaker resetGear extended with the normal system.Pressure relief valve reconnected and pressurise the system until the valve opensManual Pump dis-connectedEmergence Bottle checkLeakage check between the valve actuatorEmergency system checkEmergency Bottler recharge to 1500 psi.