INDIAN AIR LINES INDIAN AIR LINES (IAL)(IAL)

INDIAN AIRLINESINDIAN AIRLINESIndian Airlines came into existence as a public sector undertaking on June 15th 1953. Indian Airlines came into existence as a public sector undertaking on June 15th 1953.

Indian Airlines is the member of International Air Transport Association (IATA).Indian Airlines is the member of International Air Transport Association (IATA).

Indian Airlines is also the member of International Civil Aviation Organization (ICAO).Indian Airlines is also the member of International Civil Aviation Organization (ICAO).

Offers about 220 services daily &links 59 destinations.Offers about 220 services daily &links 59 destinations.

Has 17 stations in the neighboring countries of Nepal, Pakistan, Afghanistan, Srilanka, Maldives, Has 17 stations in the neighboring countries of Nepal, Pakistan, Afghanistan, Srilanka, Maldives, Thailand, Bangladesh, Singapore, Oman, UAE, Kuwait, & Malaysia.Thailand, Bangladesh, Singapore, Oman, UAE, Kuwait, & Malaysia.

Maintenance carried out at four engineering bases equipped with hangers, modern workshops, Maintenance carried out at four engineering bases equipped with hangers, modern workshops, and test equipment located at Kolkata,Delhi, Mumbai & Hyderabad.and test equipment located at Kolkata,Delhi, Mumbai & Hyderabad.

Real time computer reservations system (CRS) established in March 1985.Real time computer reservations system (CRS) established in March 1985.

INDIAN AIRLINES AT GLANCEINDIAN AIRLINES AT GLANCE

BOEING B-737 12 BOEING B-737 12 AIRBUS A-320 30AIRBUS A-320 30 AIRBUS A-300 11AIRBUS A-300 11 Domestic destinations 69Domestic destinations 69 Over seas destination 17Over seas destination 17 Revenue (per year) 9974 millionRevenue (per year) 9974 millionPassengers carried (per year) 7.8 millionPassengers carried (per year) 7.8 millionCargo carried (per year) 94,000 tonnesCargo carried (per year) 94,000 tonnes

PRINCIPLEPRINCIPLE

The Bernoulli’s theory of VenturesThe Bernoulli’s theory of Ventures- - According to Bernoulli’s principle, which According to Bernoulli’s principle, which says that if air speeds up, the pressure is says that if air speeds up, the pressure is higher. Thus a wing generates lift because higher. Thus a wing generates lift because the air goes slower over the top creating a the air goes slower over the top creating a region of low pressure and air goes faster region of low pressure and air goes faster at the bottom, and thus lifts. at the bottom, and thus lifts.

CURVED SURFACE CURVED SURFACE CRITERIACRITERIA

Coanda effectCoanda effect Why should a fluid follow a curved Why should a fluid follow a curved

surface? The answer is viscosity; the surface? The answer is viscosity; the resistance to flow which also gives the air resistance to flow which also gives the air a kind of "stickiness". Viscosity in air is a kind of "stickiness". Viscosity in air is very small but it is enough for the air very small but it is enough for the air molecules to want to stick to the surface. molecules to want to stick to the surface.

ABOUT WINGSABOUT WINGS Lift can be accurately and exactly defined Lift can be accurately and exactly defined

by the relationship by the relationship Lift =1/2 pV2 S CLift =1/2 pV2 S CWhere, p is air density Where, p is air density

V is speed of aircraftV is speed of aircraft S plane area of wingS plane area of wing C lift coefficientC lift coefficient

The relationship of lift coefficient and the The relationship of lift coefficient and the angle of attack, which the lift coefficient angle of attack, which the lift coefficient depicts, is as under :- depicts, is as under :-

HOW THE AIRCRAFT HOW THE AIRCRAFT FLIES ?FLIES ?

Straight and Level FlightStraight and Level Flight For an airplane to fly straight and level, For an airplane to fly straight and level,

the following relationships must be true: the following relationships must be true: Thrust = Drag Thrust = Drag Lift = Weight Lift = Weight If, for any reason, the amount of drag If, for any reason, the amount of drag

becomes larger than the amount of becomes larger than the amount of thrust, the plane will slow down. If the thrust, the plane will slow down. If the thrust is increased so that it is greater thrust is increased so that it is greater than the drag, the plane will speed up. than the drag, the plane will speed up.

ABOUT FUEL AND FUEL ABOUT FUEL AND FUEL PUMPSPUMPS

THE MAXIMUM FUEL CARRYING THE MAXIMUM FUEL CARRYING CAPACITY IS=19000 LT.CAPACITY IS=19000 LT.

THE FUEL IS KNOWN AS THE FUEL IS KNOWN AS “ A.T.F ”.“ A.T.F ”. THERE ARE “6” FUEL PUMPS.THERE ARE “6” FUEL PUMPS. 2-ARE LOCATED IN LEFT WING2-ARE LOCATED IN LEFT WING 2-ARE LOCATED IN RIGHT WING 2-ARE LOCATED IN RIGHT WING 2-ARE LOCATED AT THE CENTER 2-ARE LOCATED AT THE CENTER ELECTRICAL SUPPLY=200 V,400 HZ.ELECTRICAL SUPPLY=200 V,400 HZ. CURRENT CONSUMPTION=8 A. CURRENT CONSUMPTION=8 A.

AIRCRAFT PARTSAIRCRAFT PARTS

AILERONAILERON They are used to control the aircraft in roll.They are used to control the aircraft in roll. Two Interconnected ailerons so that one goes down when the other goes up.Two Interconnected ailerons so that one goes down when the other goes up. The downgoing aileron increases the lift on its wing while the upgoing aileron reduces The downgoing aileron increases the lift on its wing while the upgoing aileron reduces

the lift on the other wing, producing a rolling moment about the aircraft's longitudinal the lift on the other wing, producing a rolling moment about the aircraft's longitudinal axis. axis.

AIRCRAFT PARTSAIRCRAFT PARTS

RUDDERRUDDER

Usually attached to the fin (or vertical stabilizer).Usually attached to the fin (or vertical stabilizer).

Allows the pilot to control yaw in the horizontal axis, i.e. Allows the pilot to control yaw in the horizontal axis, i.e. change the horizontal direction in which the nose is change the horizontal direction in which the nose is pointing. pointing.

SPOILERSSPOILERS

Device intended to reduce lift in an aircraft.Device intended to reduce lift in an aircraft.

These are plates on the top surface of a wing which can be These are plates on the top surface of a wing which can be extended upward into the smooth airflow.extended upward into the smooth airflow.

AIRCRAFT PARTSAIRCRAFT PARTS

LANDING GEARLANDING GEAR The landing gear is essential during take-off and landing. The landing gear is essential during take-off and landing.

Horizontal and Vertical Stabilizers

FLIGHT DYNAMICSFLIGHT DYNAMICS

•An aircraft is free to rotate around three axes which are perpendicular to each other and intersect at the plane's center of gravity (CG). •To control position and direction a pilot must be able to control rotation about each of them.

Vertical - The vertical axis passes through the plane from top to bottom. Rotation about this axis is called yaw.

Longitudinal - The longitudinal axis passes through the plane from nose to tail. Rotation about this axis is called bank or roll.

Lateral - The lateral axis passes through the plane from wingtip to wingtip. Rotation about this axis is called pitch.

SELCAL SYSTEMSELCAL SYSTEM The SELCAL system alerts the flight crew that a ground station is calling The SELCAL system alerts the flight crew that a ground station is calling

the Airplane. The SELCAL (selective call) system receives SELCAL codes the Airplane. The SELCAL (selective call) system receives SELCAL codes from the airplane communication receivers called the Call sign. from the airplane communication receivers called the Call sign.

When the assigned airplane code is received, the SELCAL system alerts When the assigned airplane code is received, the SELCAL system alerts the flight crew with visual and signals.the flight crew with visual and signals.

Each country has a set of alphabetic or numeric International Each country has a set of alphabetic or numeric International Telecommunication Union-designated prefixes with which their call signs Telecommunication Union-designated prefixes with which their call signs must begin. For example:must begin. For example:

India uses India uses ATAT––AWAW, , VTVT––VWVW, and , and 8T8T––8Y8Y.. Brazil uses Brazil uses PPPP––PYPY and and ZVZV––ZZZZ.. Russia uses Russia uses RR and and UAUA––UIUI.. The United Kingdom uses The United Kingdom uses GG, , MM, , VSVS, , ZBZB––ZJZJ, , ZNZN––ZOZO, , ZQZQ, and , and 22.. The United States uses The United States uses KK, , WW, , NN, and , and AAAA––ALAL..

TRAFFIC COLLISION AVOIDANCE TRAFFIC COLLISION AVOIDANCE SYSTEMSYSTEM

The Traffic alert and Collision Avoidance System (or TCAS) is a The Traffic alert and Collision Avoidance System (or TCAS) is a computerized avionics device which is designed to reduce the danger of computerized avionics device which is designed to reduce the danger of mid-air collisions between aircraft mid-air collisions between aircraft

It monitors the airspace around an aircraft warns pilots of the presence of It monitors the airspace around an aircraft warns pilots of the presence of other aircraft which may present a threat of mid air collision (MAC).other aircraft which may present a threat of mid air collision (MAC).

It is an implementation of the Airborne Collision Avoidance System It is an implementation of the Airborne Collision Avoidance System mandated by International Civil Aviation Organization to be fitted to all mandated by International Civil Aviation Organization to be fitted to all aircraft over 5700 kg or authorised to carry more than 19 passengers. aircraft over 5700 kg or authorised to carry more than 19 passengers.

Each TCAS-equipped aircraft "interrogates" all other aircraft in a Each TCAS-equipped aircraft "interrogates" all other aircraft in a determined range about their position determined range about their position (via the 1030 MHz frequency).(via the 1030 MHz frequency).

TCAS system builds a three dimensional map of aircraft in the airspace, TCAS system builds a three dimensional map of aircraft in the airspace, incorporating their bearing, altitude and velocity, it determines if a incorporating their bearing, altitude and velocity, it determines if a potential collision threat exists.potential collision threat exists.

Versions of TCASVersions of TCASTCAS ITCAS I TCAS IITCAS II TCAS IIITCAS III

HIGH FREQUENCY (HF) HIGH FREQUENCY (HF) SYSTEMSYSTEM

The HF communication system provides long range communication between The The HF communication system provides long range communication between The Aircraft and Ground Stations.Aircraft and Ground Stations.

The Aircraft and other AircraftThe Aircraft and other Aircraft

• The system operates in the 2 to 30 MHz frequency range.

• The HF communication provides a reliable way to transmit and receive Flight Information, Landing Instruction and Voice Communication

•Two HF communication systems HF-1 and HF-2 installed in the aircraft.

VERY HIGH FREQUENCY SYSTEM VERY HIGH FREQUENCY SYSTEM (VHF)(VHF)

DESCRIPTIONDESCRIPTION

The Aircraft and Ground Stations.The Aircraft and Ground Stations. The Aircraft and other Aircraft.The Aircraft and other Aircraft. OPERATES ATOPERATES AT 27.5 VDC 27.5 VDC Frequency range for commercial aviation VHF communication isFrequency range for commercial aviation VHF communication is

118.00 to 136.975 MHz.118.00 to 136.975 MHz. Also sends an audio signal to the SELCAL system to alert the flight Also sends an audio signal to the SELCAL system to alert the flight

crew of an incoming call.crew of an incoming call.

Provides short-range (Line Of Sight) voice communication between:

EMERGENCY LOCATOR EMERGENCY LOCATOR TRANSMITTER (ELT)TRANSMITTER (ELT)

ARTEX ELT 110-406 is an automatic activated Emergency ARTEX ELT 110-406 is an automatic activated Emergency Locator Transmitter (ELT). It is a device to detect the aircraft Locator Transmitter (ELT). It is a device to detect the aircraft after it has been crashed.after it has been crashed.

During this time an encoded message is sent to the satellite. During this time an encoded message is sent to the satellite. The information contained in this message is shown below:The information contained in this message is shown below:

Serial number of the Transmitter.Serial number of the Transmitter. Country code.Country code. I.D. code.I.D. code. Position coordinates (optional).Position coordinates (optional).

DISTANCE MEASURING DISTANCE MEASURING EQUIPMENTEQUIPMENT

DME is aDME is a system combiningsystem combining Ground BasedGround Based andand Airborne Airborne Equipment to measure the distance of the aircraft from a ground Equipment to measure the distance of the aircraft from a ground station.station.

The airborne DME-RT computes the slant range (Line-Of-Sight) The airborne DME-RT computes the slant range (Line-Of-Sight) distance from the ground station as follows: -distance from the ground station as follows: -

D = {(T – 50 µs)/12.359}D = {(T – 50 µs)/12.359} Where, Where, D = Slant range distance in nautical miles from the D = Slant range distance in nautical miles from the

ground Station.ground Station. T = Time in µs b/w transmission of interrogation pulse T = Time in µs b/w transmission of interrogation pulse pair and reception of corresponding reply pulse pair.pair and reception of corresponding reply pulse pair. 50 µs = Delay at ground station b/w reception of DME 50 µs = Delay at ground station b/w reception of DME Interrogation & transmission of reply.Interrogation & transmission of reply. 12.359 =Time in µs for RF energy to travel one nautical 12.359 =Time in µs for RF energy to travel one nautical mile and return.mile and return. The distance is then sent to the distance indicator where it is The distance is then sent to the distance indicator where it is displayed for pilot’s use.displayed for pilot’s use.

GYROSCOPEGYROSCOPE A gyroscope is a rotating mass having freedom of rotation in one A gyroscope is a rotating mass having freedom of rotation in one

or more planes at right angles to the plane of rotation.or more planes at right angles to the plane of rotation. It possesses two fundamental characteristics:It possesses two fundamental characteristics:

Gyroscopic Inertia or Rigidity Gyroscopic Inertia or Rigidity && Precesion. Precesion.

The property by which a gyro resists any force tending to change the The property by which a gyro resists any force tending to change the plane of the rotor rotation is calledplane of the rotor rotation is called Rigidity Rigidity. .

Depends onDepends on : :1)Mass of the rotor,1)Mass of the rotor, 2) The speed of rotation & 2) The speed of rotation & 3) The distance at which the mass acts at the center i.e. 3) The distance at which the mass acts at the center i.e.

radius of gyration. radius of gyration.

Precesion Precesion is the angular change of direction of the plane of rotation, is the angular change of direction of the plane of rotation, under the action of an external force.under the action of an external force.

The gyro will move in a plane at right angles to the disturbing torque. The gyro will move in a plane at right angles to the disturbing torque.

CABIN PRESSURE CONTROLLERCABIN PRESSURE CONTROLLER

THE MAJOR FUNCTION OF CABIN PRESSURE CONTROLLER IS TO THE MAJOR FUNCTION OF CABIN PRESSURE CONTROLLER IS TO KEEP THE DESIRED CABIN PRESSURE BY UTILIZING THE KEEP THE DESIRED CABIN PRESSURE BY UTILIZING THE EXTERNAL AIRCRAFT INPUT AND INTERNAL LOGIC.EXTERNAL AIRCRAFT INPUT AND INTERNAL LOGIC.

IT COMPARES THE DESIRED PRESSURE TO THE ACTUAL SENSED IT COMPARES THE DESIRED PRESSURE TO THE ACTUAL SENSED CABIN PRESSURE & IF A DIFFERENCE EXISTS ,THEN IT VARIES CABIN PRESSURE & IF A DIFFERENCE EXISTS ,THEN IT VARIES THE OUTFLOW VALVE POSITION & COMMANDS SIGNAL TO THE THE OUTFLOW VALVE POSITION & COMMANDS SIGNAL TO THE ELECTRONIC BOX UNTIL THE PRESSURE DIFFERENCE EQUALS TO ELECTRONIC BOX UNTIL THE PRESSURE DIFFERENCE EQUALS TO ZERO. ZERO.

SOLID STATE COCKPIT VOICE SOLID STATE COCKPIT VOICE RECORDERRECORDER

Use large capacity computer memory chips.Use large capacity computer memory chips. Much cheaper to maintain.Much cheaper to maintain. It has CSMU crash survival memory unit. Underwater It has CSMU crash survival memory unit. Underwater

locator device mounted on the front of CSMU.locator device mounted on the front of CSMU.

MAGNETIC COCKPIT VOICE RECORDERMAGNETIC COCKPIT VOICE RECORDER Endless loop tape device that records all voice signals Endless loop tape device that records all voice signals

transmitted or received by aircraft crew members for a transmitted or received by aircraft crew members for a maximum period of 2 hours of continuous operation.maximum period of 2 hours of continuous operation.

Housed in an international orange colored short Housed in an international orange colored short equipment case and consists of a tape recorder and an equipment case and consists of a tape recorder and an electronic chassis electronic chassis

AIR TRAFFIC AIR TRAFFIC CONTROL(A.T.C)CONTROL(A.T.C)

Air traffic control system contains airborne Air traffic control system contains airborne components controlled by the ground facilities components controlled by the ground facilities to identify the flight number & altitude of to identify the flight number & altitude of airplane.airplane.

In addition to this ,the ground facilities In addition to this ,the ground facilities monitor’s the airplane’s location & direction of monitor’s the airplane’s location & direction of travel.travel.

The power requirement is 115 V.The power requirement is 115 V. Transmit frequency is (1090+/-3) MHzTransmit frequency is (1090+/-3) MHz

&&

Receive frequency is (1030+/-0.2) MHzReceive frequency is (1030+/-0.2) MHz

RADARRADAR

THE RADAR RANGE IS UPTO THE RADAR RANGE IS UPTO 300 MILES .300 MILES .

POWER REQUIREMENT IS 115 POWER REQUIREMENT IS 115 V,400HZ.V,400HZ.

TRANSMITTER TRANSMITTER FREQUENCY=9375 MHZ.FREQUENCY=9375 MHZ.

RECEIVER RECEIVER FREQUENCY=9375+/-40 MHZ.FREQUENCY=9375+/-40 MHZ.

AIRSPEED INDICATORAIRSPEED INDICATOR

DESCRIPTION :DESCRIPTION :

Contains a capsule operated mechanism which measures the Contains a capsule operated mechanism which measures the static pressure and provides airspeed indication in terms of knots, static pressure and provides airspeed indication in terms of knots, up to altitudes of 50,000 feet. up to altitudes of 50,000 feet.

The pressure-sensitive capsule expands and contracts in response The pressure-sensitive capsule expands and contracts in response

to change in the static pressure .to change in the static pressure .

The capsule deflection is transmitted via the rocking shaft, to the The capsule deflection is transmitted via the rocking shaft, to the sector which converts the linear motion to rotary movement of the sector which converts the linear motion to rotary movement of the pointer.pointer.

ACTUATORACTUATOR

Electromechanical unit with 2 ends of travel positions: Electromechanical unit with 2 ends of travel positions: Retracted and Extended.Retracted and Extended.

IT IS USED TO OPERATE THE DOOR OF AIR IT IS USED TO OPERATE THE DOOR OF AIR CONDITIONING SYSTEM.CONDITIONING SYSTEM.

IT IS SINGLE PHASE ELECTIC MOTOR :IT IS SINGLE PHASE ELECTIC MOTOR :

VOLTAGE-115 VOLTS & 28 VDCVOLTAGE-115 VOLTS & 28 VDC

FREQUENCY-400 HZFREQUENCY-400 HZ

IT HAS TWO PORTS:IT HAS TWO PORTS: RAM AIR INLET(RAI)RAM AIR INLET(RAI) RAM AIR OUTLET(RAM)RAM AIR OUTLET(RAM)

IGNITION EXCITER IGNITION EXCITER

B-737-200 USING JT8D ENGINE.B-737-200 USING JT8D ENGINE. A-320,21 USING V-2500 ENGINE.A-320,21 USING V-2500 ENGINE. BOEING HAS 2-PLUG FIRE & BOEING HAS 2-PLUG FIRE &

OPERATES ON 28 VDC & GENERATES OPERATES ON 28 VDC & GENERATES (18-22) J OF ENERGY.(18-22) J OF ENERGY.

AIRBUS HAS 1-PLUG FIRE & AIRBUS HAS 1-PLUG FIRE & OPERATES ON 115 V,400HZ & OPERATES ON 115 V,400HZ & GENERATES (18-22)J OF ENERGY.GENERATES (18-22)J OF ENERGY.

EMERGENCY EXIT LIGHT POWER EMERGENCY EXIT LIGHT POWER SYSTEMSYSTEM

A self - contained unit made up of a package of six nickel - A self - contained unit made up of a package of six nickel - cadmium batteries and an electronic switching circuit with voltage cadmium batteries and an electronic switching circuit with voltage regulator.regulator.

The unit is used to supply power for emergency exit lighting.The unit is used to supply power for emergency exit lighting.

The unit is connected to the aircraft’s 28 volt D.C. power system The unit is connected to the aircraft’s 28 volt D.C. power system and controlled by a switch at the pilot’s cabin.and controlled by a switch at the pilot’s cabin.

Depending upon presence or absence of power supply and on the Depending upon presence or absence of power supply and on the pilot’s switch position; following different phenomenon occur in pilot’s switch position; following different phenomenon occur in batteries:batteries:

OFFOFF ONON

THERMOCOUPLETHERMOCOUPLE

A Thermocouple is an instrument used for A Thermocouple is an instrument used for measuring temperature. When installed on a measuring temperature. When installed on a brake thermocouple provides means of brake thermocouple provides means of checking the heat generated during brake checking the heat generated during brake applications.applications.

CHARACTERISTICSCHARACTERISTICS Weight - 120 kgWeight - 120 kg Probe - Probe -

Chromel, Alumel Chromel, Alumel Max. Operating temperature - 800 deg Max. Operating temperature - 800 deg

C C

GENERATORGENERATOR

Rating - 40 KVARating - 40 KVA Voltage - 120/208 VoltacVoltage - 120/208 Voltac Frequency - 380/420 HzFrequency - 380/420 Hz Current - 111 ACurrent - 111 A Phase - 3Phase - 3 Power factor - 0.75Power factor - 0.75 Speed - 5700/6300 Speed - 5700/6300

RPMRPM Maximum weight - 37 KgMaximum weight - 37 Kg

TAKE-OFF LIGHTTAKE-OFF LIGHT

Input voltage - 115 Volts Input voltage - 115 Volts Frequency - 400 HzFrequency - 400 Hz OPERATES AT 28 VOLTS BY STEP OPERATES AT 28 VOLTS BY STEP

DOWN 115 VOLTS.DOWN 115 VOLTS. Power - 600 Watts Power - 600 Watts

TAXIING LIGHTTAXIING LIGHT

Input voltage - 115 VoltsInput voltage - 115 Volts Frequency - 400 HzFrequency - 400 Hz OPERATES AT28 VOLTS BY OPERATES AT28 VOLTS BY

STEPPING DOWN 115 VOLTSSTEPPING DOWN 115 VOLTS Power - 450 WattsPower - 450 Watts