Transcript
Cessna 172 The Glass Cockpit
Presented by Ilampirai(TECHNICAL OFFICER)
Aircraft technology ranges from the simple wicker basket and sandbags of a hot-air balloon, to the carbon fibre and fully digital systems of modern jets.
TYPE OF AIRCRAFT CESSNA 152
CESSNA 172 RCESSNA 172R
GARMIN[G1000]
Cirrus SR 22Piper PA 34
CESSNA152Engine specification :No.of engine : 1Engine manufacturer : Textron LycomingEngine model no : o-235-N2CEngine type : normally aspirated, direct drive air-cooled, horizontally opposed, fuel injected Compression ratio : 8:5:1Magnetos : slick[4281 RH & LH]Spark plug : 18mm Torque : 390+ 30 Lb.InAlternator :28 volt,60-ampereRated horse power at RPM : 108 AT 2550
Propeller specification :
Propeller manufacturer : Mc cauley propellers systemPropeller model no :1c235/LF A7570No of blades :2Propeller diameter :7fixed pitchFuel capacity :56 gallonsOil capacitySump :6 U.S quartsTotal :7 5’’ Propeller type :U.S quarts
Electrical system :•Electrical energy for the aircraft is supplied by 28v ,direct current ,single wire ,negative ground electrical system•The battery is 24 volt and is approximately 17ampere hour capacity.•Landing and taxi light is located on the left side of the wing.•The navigation light are attached to the wing tips and the aft end of the vertical fin tip.
Port side –RED colorStar board side - GREEN colorRear side - WHITE color
•The flashing beacon is attached to the vertical fin tip, 45 flashes per min•Instrument flood light and dome light are installed in the overhead console•Compass and radio dial lighting are contained within the individual units.The control wheel map light is mounted on the lower side of the control wheel.
Power plant system :The o-235-N2C engine in the model 152 is delivered from Cessna with corrosion preventative engine oil which should be replaced with AD type oil and the oil filter element changed at the first 25 hrs . if during this operation addition of oil becomes necessary , only straight mineral oil conforming to MIL-L-6082 SHOULD be used.
The accessory equipment furnished with the engine is:• RADIO shielded spark plugs•Marvel-schebler float-type carburettor •Two [2] SLICK magnetos with impulse coupling
Fuel system :
•The system consists of two metal tanks [one in each wing] , a fuel shut-off valve ,fuel strainer, manual primer and associated plumbing.•Method- gravity fuel flow method•Fuel flows from tank to the fuel shut-off valve•Valve in ON position •Fuel continues through the main fuel strainer to the carburettor.
Cessna-172R :
No of engine : 1Engine manufacturer : Textron lycoming Engine model no: IO-360-L2AEngine type : normally aspirated, direct drive, air-cooled, fuel injected, horizontally opposed four cylinder engine with 360 cu.in displacementHorse power rating and engine speed :160 rate
GLASS COCKPIT :The G1000 system is an integrated flight control system that present flight instrument system , position , navigation , communication and identification information to the pilot through large format displays. The system consist of the following LINE REPLACE UNIT[LRU’s]
• GDU 1040/1044B primary flight display[PFD]•GDU 1040/1044B multi function display[MFD]•GIA 63/63W integrated avionics unit[IAU]•GDC 74A air data computer•GEA 71 engine air unit•GRS 77 attitude and heading reference system[AHRS] •GMU 44 magnetometer•GMA 1347 audio system with integrated marker beacon receiver•GTX 83 model transponder•GDL 90 ADS B data link transeceiver•GSA 81 AFCS servos•GSM 85 servo mount
GDU 1040/1044B It s used in C-172R and features are 10.4 inch LCD display1024×7resolution Left side display is configured as PDF and light display is configured as MFD. Both system works GDU’s 1040 link and display all function of the G1000 system during flight.
GIA 63/63W
GIA 63/63W:
It function as the main communication top linking all LRU’s with GPS receiver VHF COM/NAV/GS receiver as flight director and system integration microprocessor. The GIA 63W contains GPS receiver .each GIA is paired with a respective GDU 1040/1044B display through either net the GIA’s are not paired together and do not communicate with each other directly.
GARMIN DATA COMPUTERGDC 74A process data from the pilot static as well as the OAT probe this unit provides pressure attitude Airspeed , vertical speed and Oat information to the G1000 system and it communicates with the GIA 63/63 W , GDU 40/1044B and GRS 77 using ARINC 429 digital interface the GDC 744 also.
GARMIN ENGINE AIR FRAME
GEA 71 recieves and process signals from the engine and airframe sensor the unit communicates with both GIA 63/63 WS using an RS-485 digital interface
GARMIN ALTITUDE REFERENCE SYSTEM
information via ARINC 429 both the GDU 1040/1044B and GIA 63/63W the GRS 77 contains GRS 77 [1] provides aircraft attitude the heading advanced sensor [including accelerometer and rate sensor ] and interface with side on GMU 44 to obtain magnetic field information with the GDC744 to obtain air data and with both GIAS to obtain GPS information AHRS made of operation are disclosed later in this document.
GARMIN MAGNETO UNIT
GMU 44[1] measures local magnetic field data is sent to the GRS 77 for processing to determine aircraft magnetic heading . the unit receives power directly from the GRS 77 and communicates with the GRS 77 using RS-485 digital interface.
GARMIN MARKER AUDIO
integrates NAV/COM digital audio intercom system and marker b
GMA 1347 audio panel eacon controls the GMA 1347 also controls the manual display reversionary mode { red display back up bottom} and is installed between the MFD and PDF the GMA 1347 communication with both GIA 63/63 WS using an RS 232 digital interface.
GARMIN TRANSPONDER
GTX 33 is a solid state mode s transponder that provides modes A C and S operation . the GTX33 controlled through PDF and communicates with the GIA 63/63 WS through an RS 232 digital.
GARMIN DATA LINK
GARMIN DATA LINK:GLD 69A satellite radio receiver real time weather information to the G1000 MFD and indirectly to the inset map of the 69A communication with the MFD via HSPB connection a subscription to the satellite radio service is required to enable the GDC 69A capabilityGLD 90[1]: a digital data link trans receiver designed to transmit receive and decode ADS-B messages it broadcast aircraft position velocity projected track altitude and flight identification to other equipped aircraft in the vicinity as well as to FAA ground station.
GARMIN SERVO ACTUATOR
GSA 81 and GSM 85. The GSA 81 servo are used for automatic control of roll pitch and pitch trim , these units reference with each GIA 63/63W
GARMIN SERVO MOUNT
GARMIN SERVO MOUNT :
The GSM 81 servo mount is responsible for transferring the output torque of the GSA 81 servo actuator to the mechanical flight control surface
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