4. CESSNA152
Engine specification :
No.of engine :1
Engine manufacturer : Textron Lycoming
Engine model no : o-235-N2C
Engine type : normally aspirated, direct drive
air-cooled,
horizontally opposed, fuel injected
Compression ratio : 8:5:1
Magnetos : slick[4281 RH & LH]
Spark plug : 18mm
Torque : 390+ 30 Lb.In
Alternator :28 volt,60-ampere
Rated horse power at RPM : 108 AT 2550
5. Propeller specification :
Propeller manufacturer : Mc cauley propellers
system
Propeller model no :1c235/LF A7570
No of blades :2
Propeller diameter :7fixed pitch
Fuel capacity :56 gallons
Oil capacity
Sump :6 U.S quarts
Total :7 5’’
Propeller type :U.S quarts
6. 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 color
Star board side - GREEN color
Rear 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.
7. 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
8. 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.
9. Cessna-172R :
No of engine :1
Engine manufacturer : Textron lycoming
Engine model no: IO-360-L2A
Engine type : normally aspirated, direct drive, air-
cooled, fuel injected, horizontally opposed
four cylinder engine with 360 cu.in displacement
Horse power rating and engine speed :160 rate
10. 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]
11. •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
12. GDU
1040/1044B
It s used in C-172R and
features are
10.4 inch LCD display
1024×7resolution
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.
13.
14. 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.
15. GARMIN DATA
COMPUTER
GDC 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.
16. 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
17. 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.
18. 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.
19. 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.
20. 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.
21.
22. 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 capability
GLD 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.
23. 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
24.
25. 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
…………………………………………………………………………………..
