Aircraft systems and Instrumentation

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Aircraft systems and Instrumentation

• AE 2252

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• FLIGHT CONTROL SYSTEMS
• PRIMARY FLIGHT CONTROL SRUFACES
• ELEVATOR
• AILERON
• RUDDER
• SECONDARY FLIGHT CONTROL SYSTEMS.
• 1. TABS
• 2. FLAPS
• 3. SPOILERS
• 4. SPEED BRAKES

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PURPOSE 1.TO ENABLE THE PILOT TO EXERCISE CONTROL
OVER THE AIRCRAFT DURING ALLL PORTIONS OF
FLIGHT. 2.IT ALLOWS TO MANOEUVRES IN
PITCH,ROLL AND YAW. METHODS 1.
PUSH-PULL CONTROL ROD SYSTEM 2. CABLE AND PULLY
SYSTEM
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FLIGHT CONTROL SYSTEM COMPONENTS 1. CABLES 2.
PULLEYS 3. TURNBUCKLES 4. PUSH PULL RODS 5. BELL
CRANKS 6. QUANDRANTS. 7. TORQUE TUBES 8. CABLE
GURARDS
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FLY BY WIRE (FBW) IT IS ONE IN WHICH WIRE
CARRYING ELECTRICAL SIGNALS FROM THE FLIGHT
CONTROLS BY REPLACING MECHANICAL LINKAGES.
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ADVANTAGES OF FBW 1. WEIGHT SAVING 2. REDUCED
MAINTENANCE TIMES 3. LESS SPACE 4. IMPROVED
HANDLING
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AUTOPILOT SYSTEM ACTIVE CONTROL
TECHNOLOGY AUTOPILOT IS A SYSTEM OF AUTOMATIC
CONTROLS WHICH HOLDS THE ARICRAFT ON ANY
SELECTED MAGNETIC HEADING AND RETURNS THE
ARICRAFT TO THAT HEADING WHEN IT IS DISPLACED
FROM IT. PURPOSE TO REDUCE THE WROK STRAIN AND
FATIQUE OF CONTROLLING THE AIRCRAFT IN FLIGHT
BY THE PILOT.
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COMPONENTS 1. GYROS (TO SENSE WHAT AIRPLANE IS
DOING) 2. SERVOS (TO MOVE CONTROL SURFACES) 3.
AMPLIFIER (TO INCREASE THE STRENGTH OF GYRO
SIGNALS TO OPERATE SERVOS) THREE CHANNELS. 1.
RUDDER CHANNELS 2. AILERON CHANNES. 3. ELEVATOR
CHANNELS
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COMMUNICATION SYSTEMS 1. H F 2. VHF 3.
UHF NAVIGATIONAL AIDS 1. VOR (VHR OMNIRANGE) 2.
DME (DISTANCE MEASURING EQUIPMENT) 3. ADF
(AUTOMATIC DIRECTION FINDING)
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INSTRUMENT LANDING SYSTEM 1. RUNWAY LOCALISER 2.
GLIDESLOPE SIGNAL 3. MARKER BEACONS MIRCROWAVE
LANDING SYSTEMS (MLS) MLS OPERATES IN THE
FREQUANCY BAND OF 5031MHZ-5190.7MHZ. IT HAS WIDE
FIEL D VIEW OF 40 DEGRESS IN AZIMUTH AND UPTO 20
DEGREES ELEVATION. THE COVERAGE IS UPTO 20NM FOR
NORMAL APPROACH.
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NON DIRECTIONAL BEACON (NDB) NDB IS GROUND BASED
.IT IS NON-DIRECTIONAL BECAUSE NO PARTICULAR
DIRECTION IS FAVOURED. THE NDB RADIATES
IDENTICAL ELECTROMAGNETIC ENERGY IN ALL
DIRECTIONS. FREQ RANGE 200-415KHZ.
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AIRCRAFT SYSTEM HYDRAULIC SYSTEM HAS TWO MAJOR
PARTS 1. POWER SECTION WHICH PROVIDES FLUID
FLOW AND REGULATES 2. ACTUATING SECTION WHICH
OPERATES FLAPS, LANDING GEAR ETC
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MAIN COMPONENTS 1. RESERVOIR 2. HAND PUMP 3.
ENGINE DRIVEN PUMP (EDP) 4. CHECK VALVE 5.
ACCUMULATOR 6. BRAKE 7. PRESSURE GUAGE 8. FLAP 9.
LANDING GEAR CYLINDER 10. RELIEF VALVE 11. FILTER
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PNEUMATIC SYSTEM AIRCRAFT PNEUMATIC SYSTEM USED
PRIMARILY AS EMERGENCY SOURCES OF PRESSURE. The
AIR WHICH IS CLEAR AND DRY ARE STORED IN HIGH
PRESSURE BOTTLE. LANDING GEAR THE LANDING GEARO
AN AIRPLANE PERFORMS VERY IMPORTANT FUCTIONS.IT
SUPPORTS FOR LANDING AND TAKE OFF.IT ALSO
DAMPENS VIBRATIONS WHILE LANDING.
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CLASSIFICATION 1.UNABSORBING LANDING GEAR 2.
SHOCK ABSORBING LANDING GEAR SHOCK ABSORBING
LANDING GEAR SHOCK ABSORBING LANDING GEAR
DISSIPATES THE IMPACT OF ENERGY OF LANDING. THIS
IS ACHIEVED BY FORCING THE FLUID THROUGH A
RESTRICTED PASSAGE.
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TWO TYPES OF SHOCK ABSORBING LANDING
GEAR SPRING OLEO STRUTS IT CONSISTS OF
PISTON TYPE STRUCTURE AND A HEAVY COILED
SPRING. AIR OLEO STRUT DURING COMPRESSION OF
THE STRUT AT LANDING AN ORIFICE PROVIDES A
RESTRICTION OF AIR FLOW.
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RETRACTABLE GEAR IT WAS DEVELOPED TO ELIMINATE
THE DRAG. THE RETRACTION IS NORMALLLY
ACCOMPLISHED WITH HYDRAULIC POWER.EMERGENCY
SYSTEM IS PROVIDED TO ENSURE THAT THE LANDING
SYSTEM FAILURE. THE LANDING GEAR OF AN AIRPLANE
IS OF PRIMARY IMPORTANCE IN THE OPERATION OF AN
AIRCRAFT.
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SHIMMY DAMPERS 1.IT IS A HYDRAULIC SNUBBING
UNIT THAT REDUCES THE TENDENCY OF THE NOSE TO
OSCILLATE FROM SIDE TO SIDE. 2.SHIMMY DAMPERS
ARE USUALLY CONSTRUCTED IN ONE OF TWO GENERAL
DISIGNS a) PISTON TYPE b) VANE TPYES
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LUBRICATION SYSTEM 1.IT CARRIES HEAT FROM THE
ENGINE 2.IT PROVIDES CUSHOING BETWEEN MOVING
PARTS 3.IT REDUCES FRICTION BETWEEN MOVING
PARTS 4.IT ACTS AS A HEAT EXCHANGER BY HEATING
FUEL 5.DUE TO FLOWABILITY IT CARRIES
PARTICLS 6.IT PROVIDES FILTERING AND MAGNETICS
DETECTOR 7.IT ACTS AS SEAL BETWEEN AND PISTON AND
CYLINDER 8.OIL BREATHER PROVIDES TO REMOVE
VAPOUR 9.WARNING LIGHT ENSURES SAFE OPERTATION
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TYPES OF LUBRICATION SYSTEM 1.PRESSURE RELIEF
VALVE SYSTEM 2.FULL FLOW SYSTEM 3.TOTAL LOSS
SYSTEM
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JET ENGINE IGNITION AND STARTING 1.MUST BE ABLE
TO ROTATE COMPRESSOR AND TURBINE AT A SPEED AT
WHICH ADEQUATE AIR PASSESS INTO THE COMBUSTION
TO MIX WITH FUEL 2.IGNITION OF FUEL AIR MIXTURE
IN THE COMBUTION TO OCCUR IGNITION SYSTEM
COMPONENTS 1.EXCITER BOX 2.IGNITION
LEAD 3.LEAD
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STARTING SYSTEM FOR GAS TURBINE 1.AIR TURBINE
STARTERS(PNEUMATIC) a) LOW PRESSURE b) HIGH
PRESSURE 2.ELECTRIC STARTERS 3.FUEL AIR
COMBUSTION STARTERS
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AUXILIARY SYSTEMS 1.IT IS REQUIRED FOR SAFE
OPERATION OF AIRCRAFT 2.IT IS PROVIDED FOR
EMERGENGY SYSTEMS NOT ESSENTIAL FOR ACTUAL
OPERATION ARE CALLED AUXILIARY SYSTEMS. 1.ICE
AND RAIN PROTECTION 2.FIRE WARNING AND FIRE
EXTINGUISHERS 3.WATER AND WASTE SYSTEM 4.WARNING
SYSTEMS 5.AUXILIARY POWER UNITS(APU)
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TYPES OF FIRE AND OVERHEAT SYSTEMS 1.THERMAL
SWITCHES 2.THEROMCOUPLES 3.TUBULAR DETECTORS
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SMOKE AND FLAME DETECTORS TYPES 1.LIGHT
DETECTION 2.LIGHT REFRACTION DETECTOR 3.IONIZATI
ON TYPE SMOKE DETECTOR 4.SOLID STATE TYPE
CLASSIFICATION OF FIRE EXTINGUISHING
SYSTEM 1.CONVENTIONAL SYSTEM 2.HIGH RATE OF
DISCHARGE SYSTEM
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ICE PROTECTION SYSTEM AIRCRAFT OPERATES AT ALL
WEATHER CONDITIONS WHERE IS LIKELY TO BE FORMED
. AN ANTI-ICING SYSTEM PREVENTS THE FORMATION OF
ICE ON THE AIRPLANE AND THE DEICING SYSTEM
REMOVES THE ICE THAT HAS ALREADY FORMED . PARTS
THAT ICE LIKELY TO BE FORMED 1.WINDSHILED 2.WING
LEADING EDGE 3.PROPELLERS 4.ENGING AIR
INLETS 5.TAIL AIRFOIL LEADING EDGE 6.PITOT
TUBES 7.WATER DRAINS
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PNEUMATIC MECH DEICING SYSTEM INFLATABLE RUBBER
BOOTS FORMED AT THE LEADING EDGE OF WING,STRUTS
AND STABLISHERS. ANTI-ICING 1.THERMAL
ANTI-ICING SYSTEM 2.PROBE ANTI-ICING WIND
SHIELD ICE CONTROL 1.HEATING WINDSHIELD a) BY
HEATING ELEMENT b) BLOWING HOT AIR BETWEEN
SHEILDS 2.BY SPRAYING FLUID ON THE WINDSHIELD
SURFACE
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RAIN REMOVAL SYSTEMS TO HAVE CLEAR VIEW OF THE
AIRPORT WHEN TAXING AND ALLOW THE PILOT TO SEE
APPROACH PATHS WHEN TAKING OFF OR
LANDING. 1.REPELLANT SYSTEM 2.PNEUMATIC RAIN
REMOVAL SYSTEM
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CABIN COOLING SYSTEMS AIRCRAT COOLING SYSTEMS
ALSO CALLED AIRCONDTIONING SYSTEM ARE USED TO
REDUCE THE TEMPERATURE INSIDE FOR COMFORT OF
CREW AND PASSENGER. TWO METHODS USED TO REDUCE
THE TEMPERATURE 1.VAPOUR CYCLE
MACHING 2.AIRCYCLE MACHINE
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CABIN PRESSURISATION SYSTEM TO MAINTAIN A
COMFORTABLE ENVIRONMENT FOR OCCUPANTS AT HIGH
ALTITUDE. TO MAKE IT COMFORTABLE ,THE CABIN MUST
NORMALLY BE PRESSURIED TO MAINTAIN THE CABIN AIR
PRESSURE AT THE LEVEL REACHED AT NOT HIGHER THAN
8000FT.THIS ENABLES CREW AND PASSENGER TO
FUNCTION WITHOUT THE USE OF SUPPLLEMENTARY
OXYGEN AND WITH ADJUSTMENT OF THE CABIN AIR
TEMP,ALLOWS THAM TO BE IN A SHIRSLEEVE
ENVIRONMENT.
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OXYGEN SYSTEMS TYPE OF OXYGEN
SYSTEMS CLASSIFIED ACCORDING TO THE SOURCE OF
SUPPLY 1.STORED GAS 2.CHEMICAL OR SOLID
STATE 3.LIQUID OXYGEN
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INSTRUMENTS INSTRUMENTS ARE CLASSIFIED ACCORDING
TO THE FUNCION . THREE PRINCIPLE
CATEGORIES 1.POWER PLANT INSTRUMENTS 2.FLIGHT
AND NAVIGATIONAL INSTRUMENTS 3.SYSTEMS
INTRUMENTS.
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PURPOSE OF INTRUMENTS 1.SAFETY OF AIRCRAFT
,CREW AND PASSENGER DEPENDS ON THE PROPER
INSTALLATION AND CORRECT OPERATION OF
INSTRUMENTS 2.POWER PLANT INSTRUMENTS FOREWARN
THE PILOT ABOUT ENGINE FAILURE. 3.FLIGHT
INSTRUMENTS INDICATE ANY IRRUGULARITY OF
FLIGHT ATTITUDE OR DIRECTION .
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POWER PLANT INSTRUMENTS 1.OIL PRESSURE
INDICATOR 2.OIL TEMPERATURE INDICATOR 3.ENGINE
PRESSURE RATIO GAUGE 4.FUEL QUANTITY
INDICATOR 5.TACHO METER 6.EXHAUST GAS
TEMPERATURE(EGT) 7.MANIFOLD PRESSURE
GAUGE(PISTON ENGINE)
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FLIGHT INSTRUMENTS 1.ALTIMETER 2.AIRSPEED
INDICATOR 3.ANGLE OF ATTACK INDICATOR 4.MACH
METER 5.VERTICAL SPEED INDICATOR(RATE OF CLIMB
INDICATOR) 6.HEADING INDICATOR 7.HORIZONTAL
SITUATION INDICATOR 8.TURN AND BANK
INDICATOR(TBI) 9.ACCELEROMETER 10.MAGNETIC COMPASS
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Magnetic Compass
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Radio Magnetic Indicator
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T-6 Arrangement of basic Instruments
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Turn Coordinator
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Vertical Speed Indicator
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