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CESSNA:152A INFORMATION MANUAL
Cessna A –152 is two place side seating, high wing – monoplane of all metal, semimonocoque construction
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It is powered by AVV-LYCOMING – 0 – 235 – N2C, four cylinder, horizontally
opposed, normally as paired air cooled engine, driving al all metal, fire pitch propeller
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: Down 30°
:Right 23°

Wing flap
Rudder

Elevator Trim Tab

Elevator
Down 18°
: Up 10°
: Down 20°

5) Power plant
Number of engine
:One
Manufacturer
:AVCO Lycoming
Model No
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3 displacement
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Power loading
:15
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5 lbs / Sq
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of blades
Propeller diameter
Type
Model No
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:One
:Two
:69”
:Fixed pitch
:1 A 103 / TCM 6958

:Two (One in each wing)
:By gravity
:26 U
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gallons (13 U
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gallons in each tank)
:24
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S
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5 U
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gallons

b) Long range tanks (VT-EMM & VT-EMM is fitted with these tanks)
Number of tanks
:Two (One in each wing)
Fuel flow
:By gravity
Usable fuel
:37
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5 US gallons
Quantity fuel
:39 US gallons
Fuel Quantity indicator gauge
:magnetic type, used in conjunction with flout
Operated variable resistance transmitter
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Grade :MJI –L- 6082 Aviation grade straight mineral
Oil
a) Temperature

b) Pressure

9) LANDING GEARS:
Type
a)

:Minimum 25 PSI
Normal 60 to 90 PSI
:Maximum 115 PSI

:Tri –cycle type with stcerable nose wheel
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00 x 6
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:minimum 100° F
: Maximum 245° F

b) NOSE WHEEL
Tire size
Tire size
Shock absorber
Nose steering

10) Break System
Type
Parking brakes

11) Weight
Ramp
Take-off
Landing
Standard empty weight
Maximum useful load
Baggage area I
Baggage area II
Max total weight allowed
For I & II
Datum

:5
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4- ply rated
:30 PSI
:Air / Oil shock strut
:max
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:Operated by knob on lower left side of
Instrument panel
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:1670 lbs
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:1131 lbs
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: 120 lbs
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:120 lbs
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WINGS: Externally traced wings are constructed of a front and rear with formed sheet
ribs doublers and stringers and entire structure is covered with aluminum skin
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The
ailerons are constructed of for ward spar containing balance weight, formed sheet metal ribs and “V” type
corrugated, aluminum skin join together at the trailing edge
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EMPENNAGE: It consists of a conventional vertical stabilizer, rudder horizon stabilizer and elevator
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The top of the rudder incorporates a leading edge extension, which
contains a balance weight
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The horizion stablizer also contains the elevator-trim tab actuator
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Leading edge
of both the elevator tip incorporates extension which contains balance weights
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and
elevator control surface
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Elevator trimming is accomplished through the
elevator trim tab by utilizing the vertically mounted trim control wheel
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INSTRUMENT PANEL:
The instrument panel is designed to place the primary flight instruments directly in front of the pilot
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To the left of these instruments are air speed indicator, and turner co-ordinator
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Avionics instrument is stacked approximately on the centerline of the panel, with space for
additional equipment on the lower right side of instrument panel
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The left switch and control panel, under the primary instruments panel, contains the fuel,
quantity indicators and engine instrument position below the pilots control wheel the electrical switched
panek and radio light rheostat knob ignition and master switches primary and parking brake controls are
located around these instruments
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Directly below these controls are the elevator trim control wheel, trim position indicator, microphone and
circuit breakers
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GROUND CONTROL:
Effective ground control is accomplished through nose wheel steering by using the radar pedals,
left radar pedals to steer left, and right radar pedals to steer tight
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8
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By applying either left or right brake, the degree of turn may be
increased upto 30° each side of center
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If a tow bar is not available, or pushing is required, use the wing struts as pushing points
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If the airplane has to be towed by vehicle,
even turn the nose wheel more than 30° either side or center or structural damage to the nose gear would
result
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25ft
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WING FLAP SYSTEM:
The electrically operated wing flaps are to the single slot type with a maximum deflection of 30°
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Panel to the
desired flap deflection position
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A scale and pointer on the left side of the switch lever indicates flap travel on degrees
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LANDING GEAR SYSTEM:

The landing gear is of the tricycle type with a steerable nose wheel and two main wheels
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Shock absorption is provided by the tubular spring-steel
main landing gear struts and the air oil nose shock struts
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BAGGAGE COMPARTMENT:
The baggage compartment consists of the area from the back of the pilot and passenger’s seats to
the aft cabin bulkhead
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A
baggage not with six die-down straps is provided for securing baggage and is attached by tying the straps to
die-down air provided in the airplane
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For baggage area dimensions refer to section
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The
pilot’s and passenger’s seats are available two designs and six-way adjustable
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To position either
seat, left the lever under the inboard corner of the seat, slide the seat into position, release the lever and
check that the seat is locked in place
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To return the seat to the upright position
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The seat back and seat bottom
cushions on the pilot’s and passenger’s seats are removable accommodate the usage of parachutes aerobatic
flight
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To replace the cushions, position and place
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SEAT BELTS:
The seat belts used with the pilot’s and passengers seats are attached fitting on the floorboard
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To use the pilot’s and passenger’s seat belts, position the seats as desired, and then lengthen the
latch and link halves approximately on equate by grapping the narrow release and pulling on the end of the
below
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Tight belt halves evenly to a
snug fit
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HOULDER HARNESS:
Each shoulder harness is attached by a stirrup and cable to structure in the car of the cabin
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length and leave to as connected,
lengthen the harness straps as required by pulling down on harness and loose while pulling up on the narrow
release straps
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Rotate the hook position, connect the
link to the latch, and rotate the looking arm close until it engages the locking detent
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Also the pilot with want freedom to reach all controls easily
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To remove the shoulder harness
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ENTRANCE DOORS AND CABIN WINDOWS:

Entry to, and exit from the airplane is airplane is accomplished through either two-jettisionable
entry doors, one on each side of the cabin
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A ring on each
forward doorpost serves as an emergency release control for doors
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Grasp the forward edge of the hand and pull out
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Both cabin doors should be checked of security prior to
flight, and should not be opened intentionally during flight
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The best procedure is to set up airplane in a trimmed condition at approximately 65 KIAS,
momentarily shove the door
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To lock the airplane, lock the right cabin at from the inside by inside by lifting up on the lever
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Both cabin doors are equipped with openable windows
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To open either window
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The windows equipped with a spring-loaded rotating arm, which will help, rotate the window
outward and hold it there
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The rest
aide window, near windows and cabin top windows are the fixed type and cannot be opened
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The lock consists of a pin shaped, steel rod, and
flag
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To install the
control lock, align the hole in the top of the pilot’s control wheel shaft within hole in the top of the shaft
collar on the instrument panel and insert the rod into the aligned holes
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The control lock and any other type
of locking device should be removed prior to starting the engine
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the throttle operates in a conventional manner, in the full forward position, the throttle is open and in
the full aft position, it is closed
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The mixture control mounted above the right points corner of the control pedestal, it is red
knob with raised points around the circumference and is equipped with a lock button in the end if the knob
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For
rapid or large adjustments, the knob may be moved forward or aft by depressing the lock buton in the end of
the control, and then positioning the control as desired
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The oil pressure gauge, located on the left switch and control panel, is operated by oil
pressure
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Gauge marking indicate that minimum idling pressure is 26 PSI (red line), the normal operating range is 60
to 90 PSI (Green line) and maximum pressure is 115 PSI (red line)
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is indicated by a gauge located on the left switch and control
Panel
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Gauge markings indicate the normal creating range
(Green line) , which is
100° F (38° C) to 245° F (118° C) and the maximum (Red line), which is 245° F (118°C)
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The instrument is calibrated in increments of 100 RPM and indicates both engine and
propeller speed
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The upper end of the engine is stepped to indicated approximate RPM
for 75% engine power at level (2350 RPM) at 4000 feet (2450 RPM) and at 8000 feet (2500 RPM)
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A thermocouple probe in the muffler to pipe measures exhaust temperature and transmits
it to the indicator
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Exhaust gas
temp
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However, the difference between the peak EGT and the
cruise mixture setting
is essentially constant and used fuel learning aid
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ENGINE LUBRICATION SYSTEM:
The engine utilizes a full pressure, wet sump-type system with aviation grade oil used as
lubricant
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is six quart’s (One
additional quarts is required for the full flow oil filter
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The filter
cap dipstick is accessible through an access door in the engine cowling
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To minimise loss of oil through the breather, fill to five quarts for normal
flights of less than three hours
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For engine oil
grade specifications
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The right magnets fire the lower left and upper right spark plugs
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Ignition and starter operation is controlled by a rotary type of switch located on the left side of
the switch and control panel
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T
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Then engine should be operated
on both magnetos (Both position) except for magnet checks
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When the switch is rotated to the spring-loaded START position, (with the master
switch in the ON position), the starter contactor is energized and the starter will crank the engine
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AIR INDUCTION SYSTEM:
The engine air induction system receives the air through an air intake in the lower portion of
the engine cowilg
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Airflow passing through the filter enters an airbox, after passing
through the airbox, induction air enters the inlet in the carburater which is under the engine, and is then
inducted to the engine cylinders through the air intake manifold tube
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List of full
carburater at full throttle will result in a loss of approx
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EXGAUST SYSTEM:
Exhaust gas front each cylinder passes through raiser assembles to a muffler and tailpipe on
underside of engine
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CARBURETTOR AND PRIMING SYSTEM:
The engine is equipped with a n updraft, float-type, fixed jet carburater mounted on the
bottom of the engine
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ELECTRICAL SYSTEM:
The airplane is equipped with a 28-volt direct current electrical system
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Alternator to maintain the battery’s state of charge
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This power to all the circuits except the engine ignition system, clock, and flight hour
recorder (if installed)
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All avionics equipment
should be turned off prior to starting the engine or using an external power source to prevent harmful
transient voltage from damaging the transistors in this equipment
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The right half of the switch is labeled “RAT” side of the switch should be
turned separately to check equipment while on the ground
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With this switch in the OFF position, the
entire electrical load is placed on the battery
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AMMETER:
The ammeter dedicated on the upper right side of the instrument panel, indicates the amount of
current in amperes, from the alternator to the battery or from the battery to the airplane electrical system
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In the event the altimeter is not functioning or the electrical load exceeds the out-put
of the alternator, the ammeter indicates the battery discharge rate
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In the event an over voltage control occurs, the altimeter control unit automatically removes
alternator field current which shut’s down the alternator
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Under these condition depending on electrical system load, and
low-voltage warning light will illuminate when system voltage drops below normal
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if the warning light does not illuminate
again a malfunction has occurred, and the flight should be terminated as soon as practical
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However circuit breakers protecting the
alternator out put and the radio cooling fan strope light (if installed) is protected by the MAV (DCME circuit
breaker 0 and fuse behind the instrument panel
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The circuitry are
protected by fuses mounted to the battery
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To assist the pilot in meeting
this requirement, a special spare fuses holder is an assortment of spare fuses to be used in the event an
installed fuse requires replacement
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LIGHTING SYSTEMS:
EXTERIOR LIGHTING:
Conventional navigation lights are located on the wing tips and top of the rudder, and dual
landing taxing lights are mounted in the left wing leading edge
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Details of
the strobe light system are presented in section 9 supplements
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The switch are
on in the up position and OFF in the down position
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and volume of airflow into the cabin can be regulated bumanipulation of the PUSHPULL cabin HT and cabin AIRCONTROL knobs
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Wind, shield defrost air is also supplied by a duct leading from the manifold to
a pair of outlets below the windshield
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To radio the air temp
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Additional heat is available by pulling the knob
out further, max
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after no heat is desired in, the CABIN HT knob is pushed full
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PITOT-STATIC SYSTEM AND INSTRIMENT:
The pitot-static system supplies RAM air pressure to the airspeed indicator and static pressure to
the air-speed indicator, vertical speed indicator and altimeter
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A heated pitot system may be installed and consists of a heating element in the pitot tube, a
rocker-type switch labeled PITOT HRT on the left switch and control panel, a 15 AMP
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When a pitot heat switch is turned
on the element in the pitot tube is heated electrically to maintain proper operation in all possible conditions
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AIRSPEED INDICATOR:
The airspeed indicator is calibrated in knots and Miles/hour limitation and RPM marling include
the white are 35 to 85 knots, green are 40 to 135 knots, yellow are 125 to 175 knots and a red line 172 knots
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The pointer
is actuated by atmospheric pressure changes resulting from changes of altitude as supplied as supplied by the
static source
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A knob near the lower left portion of
the indicator provides adjustment of the instruments barometric scale to the current altimeter setting
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The system consists of a vaccum pump mounted on the engine, a
vaccum relief valve and vaccum system air filter on the left side of the firewell below the instrument panel,
vaccum operated instruments, and a suction gauge and low vaccum warning light on the left side of the
instrument panel
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It is designed
to provide adequate vaccum in the event of failure of the engine driven pump
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Bank attitude is
presented by a pointer at the top of the indicator relative to the bank scale which has index marks 10°, 20°,
30°, 60° & 90° either side of the center marks
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The upper “
BLUE SKY” area and the lower “GROUND” area have arbitrary pitch reference lines useful for pitch
attitude control
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DIRECTIONAL INDICATOR:
A directional indicator is available and displays airplane readings on a compass card in relation to
fixed simulated airplane image and index
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Therefore the take-off and occasionally readjusted on extended flights
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The stall warning system should be checked during the pre-flight inspector by placing a clear
handkerchief over the vent opening and supplying section
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ACCELEROMETER:
An accelerometer may be mounted near the lower portion of the instrument panel and
continuously measures the forces imposed on the airplane
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“g”
measures from 5 to 10g, has three pointers
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The max
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CABIN FEATURES:
CABIN FIRE EXTINGUISHER:
A portable dry chemical (sodium Bi carbonate) fire extinguisher available for installation at the
right cabin wall where it would be accessible in case of fire
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C
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100 PSI) and the tamper tape is secure and carrying handle in the stored position is intact
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2) Max
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4) Max
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power left side
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All
other switched off
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-7°C
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Master
switch off
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S
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S)
10) Controls are operated

by cables- bell crank, push pull rods
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14) Operation of oil temp
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15) Pitot heat system should be warm
within
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17) Take & landing speeds recommended
take-off –65-75 KIAS 10° -56 KIAS
for flaps up down position landing –flaps up 60/70 KIAS 30° flaps
-55/56 KIAS
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Before the actual stall
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43 kts
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10°

22) Engine make-Number

AVCO Lycoming 0-235-N2C-108 BHP
rated 2550 RPM
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26) In the airspeed indication yellow
arc means

Operation to be made with caut in the
smooth air only
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28) Procedure to be followed for
engine fire on T-off

Refer question-8

29) Rate of climb

715 FPM at sea level

30) To check the generator whether
The battery is charging
Or not

Load the system with the landing lights elec
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31) Flap system is protected by

15 AMP fuse
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30° with brakes
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34) Movement of flaps

0°, 10°, 20°, 30°
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36) Where is the starter location

Ref Q5

37) Immediate action to be taken on
engine failure on take-off
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39) Green arc on oil pressure gauge

Normal operating limits

40) Location of Tachometer

Right/Co-pilot instrument panel
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43) Gyro instruments are located one above the other

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