Cessna 17273274 Pilot Operating Handbook Download Page 143 | Manualshive

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SECTION 7

AIRPLANE

&

SYSTEMS DESCRIPTIONS

CESSNA

MODEL 172N

interrupted and the switch will automatically move to the off position.

If

this occurs, allow the circuit breaker to cool approximately two minutes

before placing the switch in the ON position again.

If

the circuit breaker

opens again, do not reset it. The avionics power switch should be placed in
the off position prior to turning the master switch ON or off, starting the
engine, or applying an external power source, and may be utilized in place
of the individual avionics equipment switches.

AMMETER

The ammeter, located on the lower left 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. When the

engine is operating and the master switch is turned on. the ammeter

indicates the charging rate applied to the battery. In the event the
alternator is not functioning or the electrical load exceeds the output of the
alternator, the ammeter indicates the battery discharge rate.

ALTERNATOR CONTROL UNIT AND LOW-VOLTAGE WARNING

LIGHT

The airplane is equipped with a combination alternator regulator

high-low voltage control unit mounted on the engine side of the firewall

and a red warning light, labeled LOW VOLTAGE, on the left side of the

instrument panel below the ammeter.

In the event an over-voltage condition occurs, the alternator control

unit automatically removes alternator field current which shuts down the

alternator. The battery

will

then supply system current as shown by a

discharge rate on the ammeter. Under these conditions, depending on

electrical system load, the low-voltage warning light will illuminate when

system voltage drops below ,normal. The alternator control unit may be
reset by turning the master switch off and back on again.

If

the warning

light does not illuminate, normal alternator charging has resumed;
however, if the light does illuminate again, a malfunction has occurred,

and the flight should be terminated as soon as practicable.

7-26

NOTE

Illumination of the low-voltage light and ammeter dis

charge indications may occur during low RPM conditions

with an electrical load on the system, such as during a low

RPM taxi. Under these conditions, the light will go out at
higher RPM. The master switch need not be recycled since
an over-voltage condition has not occurred to de-activate
the alternator system.

1 July 1979

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Summary of Contents for 17273274

Page 1: ...ES I CESSNA AIRCRAFT COMPANY 1980 MODEL 172N Serial No 7l7 3 27 f Registration No IG 37 G THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY CAR PART 3 AND CONSTITUTES THE FAA APPROVED AIRPLANE FLIGHT MANUAL COPYRIGHT e 1979 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA I f Member of GAMA 1 JULY 1979 ...

Page 2: ...THIS MANUALWAS PROVIDED FOR THE AIRPLANE IDENTIFIED ON THE TITLE PAGE ON _____ SUBSEQUENT REVISIONS SUPPLIED BY CESSNA AIRCRAFT COMPANY MUST BE PROPERLY IN SERTED CESSNA AIRCRAFT COMPANY PAWNEE DIVISION ...

Page 3: ...rs worldwide Specific benefits and provisions of warranty plus other important benefits for you are contained in your Customer Care Program book supplied with your airplane Warranty serviceis available to you at authorized Cessna Dealers throughout the world upon presentation of your Customer Care Cardwhich establishes your eligibility under the warranty FACTORY TRAINED PERSONNEL to provide you wi...

Page 4: ...Obstacle LANDING PERFORMANCE Ground Roll Total Distance Over 50 Ft Obstacle STALL SPEED CAS Flaps Up Power Off Flaps Down Power Off MAXIMUM WEIGHT Ramp Takeoff or Landing STANDARD EMPTY WEIGHT Skyhawk Skyhawk II MAXIMUM USEFUL LOAD Skyhawk Skyhawk II BAGGAGE ALLOWANCE WING LOADING Pounds Sq Ft POWER LOADING Pounds HP FUEL CAPACITY Total Standard Tanks Long Range Tanks OIL CAPACITY ENGINE Avco Lyco...

Page 5: ...carry the revision number and date on the applicable page The following Log ofEffective Pages provides the dates ofissue for original and revised pages and a listing of all pages in the handbook Pages affected by the current revision are indicated by an asterisk preceding the pages listed LOG OF EFFECTIVE PAGES Dates of issue for original and revised pages are Original 1 July1979 Revision1 15 Nove...

Page 6: ...ON GENERAL 1 LIMITATIONS 2 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT BALANCE EQUIPMENT LIST 6 AIRPLANE SYSTEMS DESCRIPTIONS 7 AIRPLANE HANDLING SERVICE MAINTENANCE 8 SUPPLEMENTS Optional Systems Description Operating Procedures 9 1 July 1979 ...

Page 7: ...d Weights 1 5 Standard Airplane Weights 1 5 Cabin And Entry Dimensions 1 5 Baggage Space And Entry Dimensions 1 5 Specific Loadings 1 5 Symbols Abbreviations And Terminology 1 6 General Airspeed Terminology And Symbols 1 6 Meteorological Terminology 1 6 Engine Power Terminology 1 7 Airplane Performance And Flight Planning Terminology 1 7 Weight And Bala nee Terminology 1 8 1 July 1979 1 1 ...

Page 8: ......

Page 9: ...ed all tires and nose strut properly inflated and flashing beacon installed 3 Wheel base length is 65 4 Propeller ground clearance is 11 3 4 5 Wing area is 174 square feet 6 Minimum turning radius pivot point to outboard wing tip is 27 5 1 2 PIVOT POINT rt 36 0 l Figure 1 1 Three View 1 2 1 July 1979 ...

Page 10: ...t drive air cooled horizontally opposed carburetor equipped four cylinder engine with 320 cu in displacement Horsepower Rating and Engine Speed 160 rated BHP at 2700 RPM PROPELLER Propeller Manufacturer McCauley Accessory Division Propeller Model Number 1C160 DTM7557 Number of Blades 2 Propeller Diameter Maximum 75 inches Minimum 74 inches Propeller Type Fixed pitch FUEL Approved Fuel Grades and C...

Page 11: ...il Ashless dispersant aircraft engine oil must be used for all operat ing conditions NOTE Use a minimum of 75 power for cruise during the first 50 hours of operation or until oil consumption stabilizes Service the engine oil system with aviation ashless dis persant oil only Required Viscosity for Temperature Range MIL L 22851 Ashless Dispersant Oil SAE 20W 50 or SAE 15W 50 for all temperatures NOT...

Page 12: ...ge areas 1 and 2 is 120 lbs Weight in Baggage Compartment Utility Category In this category the baggage compartment and rear seat must not be occupied STANDARD AIRPLANE WEIGHTS Standard Empty Weight Skyhawk 1403 lbs Maximum Useful Load Skyhawk Skyhawk II Skyhawk II 1430 lbs Normal Category 904 lbs 877 lbs CABIN AND ENTRY DIMENSIONS Utility Category 604 lbs 577 lbs Detailed dimensions of the cabin ...

Page 13: ... Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position Maximum Structural Cruising Speed is the speed that should notbe exceededexcept in smooth air then only with caution Never Exceed Speed is the speed limit that may not be exceeded at any time Stalling Speed or the minimum steady flight speed at which the airplane is controllable Stalling Speed or the...

Page 14: ... is on the ground and stationary AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Demon strated Crosswind Velocity Usable Fuel Unusable Fuel GPH NMPG g 1 July 1979 Demonstrated Crosswind Velocity is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing was actually demon strated during certification tests The value shown is not considered...

Page 15: ...er of Gravity is the point at which an airplane or equipment would balance if suspended Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane Center of Gravity Arm is the arm obtained by adding the airplane s individual moments and dividing the sum by the total weight Center of Gravity Limits are the extreme center of gravity locations with...

Page 16: ... Landing Weight is the maximum weight ap proved for the landing touchdown Tare is the weight of chocks blocks stands etc usedwhen weighing an airplane and is included in the scale read ings Tare is deducted from the scale reading to obtain the actual net airplane weight 1 9 1 10 blank ...

Page 17: ...ility Cat gory Center Of Gravity Limits Normal Category Utility Category Maneuver Limits Normal Category Utility Category Flight Load Factor Limits Normal Category Utility Category Kinds Of Operation Limits Fuel Limitations Other Limitations Flap Limitations Placards 1 July 1979 SECTION 2 LIMITATIONS Page 2 3 2 4 2 5 2 5 2 6 2 6 2 6 2 7 2 7 2 7 2 7 2 7 2 7 2 7 2 8 2 8 2 8 2 9 2 9 2 9 2 9 2 10 2 1 ...

Page 18: ......

Page 19: ...erating Handbook for amended operating limitations operating procedures performance data and other necessary information for airplanes equipped with specific options NOTE The airspeeds listed in the Airspeed Limitations cha rt figure 2 1 and the Airspeed Indicator Markings chart figure 2 2 are based on Airspeed Calibration data shown in Section 5 with the normal static source If the alternate stat...

Page 20: ...not exceed this speed in any operation VNO Maximum Structural 126 127 Do not exceed this speed Cruising Speed except in smooth air and then only with caution VA Maneuvering Speed 2300 Pounds 91 97 Do not make full or abrupt 1950 Pounds 88 89 control movements above 1600 Pounds 80 80 this speed VFE Maximum Flap Extended Speed 10 Flaps 110 110 Do not exceed this speed 10 40 Flaps 87 85 with flaps do...

Page 21: ... Yellow Arc Red Line 127 158 Operations must be onducted with caution and only in smooth air 158 Maximum speed for all operations Figure 2 2 Airspeed Indicator Markings POWER PLANT LIMITATIONS Engine Manufacturer Avco Lycoming Engine Model Number O 320 H2AD Engine Operating Limits for Takeoff and Continuous Operations Maximum Power 160 BHP rating Maximum Engine Speed 2700 RPM NOTE The static RPM r...

Page 22: ...ARC NORMAL OPERATING 2100 2450 RPM 2100 2575 RPM 2100 2700 RPM 100 245 F 60 90 psi 4 5 5 4 in Hg YELLOW ARC CAUTION RANGE Figure 2 3 Power Plant Instrument Markings WEIGHT LIMITS NORMAL CATEGORY Maximum Ramp Weight 2307 lbs Maximum Takeoff Weight 2300 lbs Maximum Landing Weight 2300 lbs Maximum Weight in Baggage Compartment RED LINE MAXIMUM LIMIT 2700 RPM 245 F 115 psi Baggage Area 1 or passenger ...

Page 23: ...e variation to 35 5 inches aft of datum at 2000 lbs Aft 40 5 inches aft of datum at an weights Reference Da um Lower portion of front face of firewall MANEUVER LIMITS NORMAL CATEGORY This airplane is certificated in both the normal and utility category The normal category is applicable to aircraft intended for non aerobatic operations These include any maneuvers incidental to normal flying stalls ...

Page 24: ...up speedquicklywith thenose down Proper speed control is an essential requirement for execution of any maneuver and care should always be exercised to avoid excessive speed which in turn can impose excessive loads In the execution of all maneuvers avoid abrupt use of controls Intentional spins with flaps extended are prohibited FLIGHT LOAD FACTOR LIMITS NORMAL CATEGORY Flight Load Factors Maximum ...

Page 25: ...itions 40 U S gallons Unusable Fuel 3 U S gallons 2 Long Range Tanks 27 U S gallons each Total Fuel 54 U S gallons Usable Fuel all flight conditions 50 U S gallons Unusable Fuel 4 U S gallons NOTE To ensure maximum fuel capacity when refueling and minimize cross feeding when parked ona sloping surface place the fuel selector valve in either LEFT or RIGHT position Takeoff and land with the fuel sel...

Page 26: ...Utility Category are contained in the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual Normal Category No acrobatic maneuvers including spins approved Utility Category No acrobatic maneuvers approved except those listed in the Pilot s Operating Handbook Spin Recovery Baggage compartmentand rear seat must not be occupied Opposite rudder forwardelevator neutralize controls Flight i...

Page 27: ...LL 100 MIN GRADE AVIATION GASOLINE CAP 21 5 U S GAL Near fuel tank filler cap long range tanks FUEL 100LL 100 MIN GRADE AVIATION GASOLINE CAP 27 U S GAL 4 Near wing flap switch AVOID SLIPS WITH FLAPS EXTENDED 5 On flap control indicator 10 to 40 1 July 1979 Partial flap range with blue color code and 110 kt callout also mechanical detent at 10 Indices at thesepositionswithwhite color code and 85 k...

Page 28: ... AFT OF BAGGAGE DOOR LATCH MAXIMUM 120 POUNDS COMBINED FOR ADDITIONAL LOADING INSTRUCTIONS SEE WEIGHT AND BALANCE DATA 7 A calibration card is provided to indicate the accuracy of the magnetic compass in 30 increments 8 On oil filler cap 9 On control lock OIL 6QTS I CONTROL LOCK REMOVE BEFORE STARTING ENGINE 10 Near airspeed indicator MANEUVER SPEED 97 KIAS 2 12 1 July 1979 ...

Page 29: ...art On Ground Engine Fire In Flight Electrical Fire In Flight Cabin Fire Wing Fire Icing Inadvertent Icing Encounter Static Source Blockage Erroneous Instrument Reading Suspected Landing With A Flat Main Tire Electrical Power Supply System Malfunctions Ammeter Shows Excessive Rate of Charge Full Scale Deflection Low Voltage Light Illuminates During Flight Ammeter Indicates Discharge AMPLIFIED PROC...

Page 30: ...15 3 16 3 16 3 16 3 16 3 16 3 17 3 17 3 17 Emergency Descent Through Clouds Recovery From A Spiral Dive Inadvertent Flight Into Icing Conditions Static Source Blocked Spins Rough Engine Operation Or Loss Of Power Carburetor Icing Spark Plug Fouling Magneto Malfunction Low Oil Pressure Electrical Power Supply System Malfunctions Excessive Rate Of Charge Insufficient Rate Of Charge 3 2 1 July 1979 ...

Page 31: ... this section should be considered and applied as necessary to correct the problem Emergency procedures associated with ELT and other optional systems can be found in Section 9 AIRSPEEDS FOR EMERGENCY OPERATION Engine Failure After Takeoff Wing Flaps Up Wing Flaps Down Maneuvering Speed 2300 Lbs 1950 Lbs 1600 Lbs Maximum Glide Precautionary Landing With Engine Power Landing Without Engine Power Wi...

Page 32: ...CY LANDING WITHOUT ENGINE POWER 1 Airspeed 65 KIAS flaps UP 60 KIAS flaps DOWN 2 Mixture IDLE CUT OFF 3 Fuel Selector Valve OFF 4 Ignition Switch OFF 5 Wing Flaps AS REQUIRED 40 recommended 6 Master Switch OFF 7 Doors UNLATCH PRIOR TO TOUCHDOWN 8 Touchdown SLIGHTLY TAIL LOW 9 Brakes APPLY HEAVILY PRECAUTIONARY LANDING WITH ENGINE POWER 1 Wing Flaps 20 2 Airspeed 60 KIAS 3 Selected Field FLY OVER n...

Page 33: ...s available approachat65KIASwithflapsup or at 60 KIAS with 10 flaps Cabin Doors UNLATCH 7 Touchdown LEVEL ATTITUDE AT ESTABLISHED RATE OF DESCENT 8 Face CUSHION at touchdown with folded coat 9 Airplane EVACUATE through cabin doors If necessary open window and flood cabin to equalize pressure so doors can be opened 10 Life Vests and Raft INFLATE FIRES DURING START ON GROUND 1 Cranking CONTINUE to g...

Page 34: ...inguished increase glide speed to find an airspeed which will provide an incombustible mixture 6 Forced Landing EXECUTE as described inEmergencyLanding Without Engine Power ELECTRICAL FIRE IN FLIGHT 1 Master Switch OFF 2 Avionics Power Switch OFF 3 All Other Switches except ignition switch OFF 4 Vents Cabin Air Heat CLOSED 5 Fire Extinguisher ACTIVATE if available I WARNING I After discharging an ...

Page 35: ...h if installed OFF NOTE Perform a sideslip to keep the flames away from the fuel tank and cabin and land as soon as possible using flaps only as required for final approach and touchdown ICING INADVERTENT ICING ENCOUNTER 1 Turn pitot heat switch ON if installed 2 Turn back or change altitude to obtain an outside air temperature that is less conducive to icing 3 4 5 Pull cabin heat control full out...

Page 36: ...ive ness 9 Open left window and if practical scrape ice from a portion of the windshield for visibility in the landing approach 10 Perform a landing approach using a forward slip if necessary for improved visibility 11 Approach at 65 to 75 KIAS depending upon the amount of the accumulation 12 Perform a landing in level attitude STATIC SOURCE BLOCKAGE Erroneous Instrument Reading Suspected 1 Altern...

Page 37: ...ght willgo outat higher RPM The master switchneed not be recycled since an over voltage condition has not occurred to de activate the alternator system 1 Avionics Power Switch OFF 2 Alternator Circuit Breaker CHECK IN 3 Master Switch OFF both sides 4 Master Switch ON 5 Low Voltage Light CHECK OFF 6 Avionics Power Switch ON If low voltage light illuminates again 7 Alternator OFF 8 Nonessential Radi...

Page 38: ......

Page 39: ...ssary to return to the runway The checklist procedures assume that adequate time exists to secure the fuel and ignition systems prior to touchdown After an engine failure in flight the bestglide speedasshown infigure 3 1 should be established as quickly as possible While gliding toward a suitable landing area an effort should be made to identify the cause of the failure If time permits an engine r...

Page 40: ...g height over a water surface LANDING WITHOUT ELEVATOR CONTROL Trim for horizontal flight with an airspeed of approximately 60 RIAS and flaps set to 20 by using throttle and elevator trim controls Then do not change the elevator trim control setting control the glide angle by adjusting power exclusively At flareout the nose down moment resulting from power reduction is an adverse factor and the ai...

Page 41: ...ight by leveling the miniature airplane Check accuracy of the turn by observing the compass heading which should be the reciprocal of the original heading If necessary adjust heading primarily with skidding motions rather than rolling motions so that the compass will read more accurately Maintain altitude and airspeed by cautious application ofelevator control Avoidovercontrolling by keeping theha...

Page 42: ...ator back pressure to slowly reduce the airspeed to 80 KIAS 4 Adjust the elevator trim control to maintain an 80 KIAS glide 5 Keep hands off the control wheel using rudder control to hold a straight heading Adjust rudder trim if installed to relieve unbalanced rudder force 6 Apply carburetor heat 7 Clear engine occasionally but avoid using enough power to disturb the trimmed glide 8 Upon breaking ...

Page 43: ...ains within 50 feet of normal SPINS Should an inadvertent spin occur the following recovery procedure should be used 1 RETARD THROTTLE TO IDLE POSITION 2 PLACE AILERONS IN NEUTRAL POSITION 3 APPLY AND HOLD FULL RUDDER OPPOSITE TO THE DIREC TION OF ROTATION 4 JUST AFTER THE RUDDER REACHES THE STOP MOVE THE CONTROL WHEEL BRISKLY FORWARD FAR ENOUGH TO BREAK THE STALL Full down elevator may be require...

Page 44: ...l minutes determine if a richer mixture setting will produce smoother operation If not proceed to the nearest airport for repairs using the BOTH position of the ignition switch unless extreme roughness dictates the use of a single ignition position MAGNETO MALFUNCTION A sudden engine roughness or misfiring is usually evidence of magneto problems Switching from BOTH to eitherLor R ignition switch p...

Page 45: ... usage at low engine speeds such as extended taxiing the battery condition will be low enough to accept above normal charging during the initial part of a flight However after thirty minutes of cruising flight the ammeter should be indicating less than two needle widths of charging current If the charging rate were to remain above this value on a long flight the battery wouldoverheat and evaporate...

Page 46: ...o reactivate the alternator system To do this turn the avionics powerswitchoff check that the alternator circuit breaker is in then turn both sides of the master switch off and then on again If the problem no longer exists normal alternator charging will resume and the low voltage light will go off The avionics power switch may then be turned back on If the light illuminates again a malfunction is...

Page 47: ...Leading Edge Left Wing Trailing Edge Before Starting Engine Starting Engine Before Takeoff Takeoff Normal Takeoff Short Field Takeoff Enroute Climb Cruise Descent Before Landing Landing Normal Landing Short Field Landing Balked Landing After Landing Securing Airplane Starting Engine Taxiing 1 July 1979 AMPLIFIED PROCEDURES Page 4 3 4 3 4 5 4 5 4 5 4 5 4 5 4 6 4 6 4 6 4 6 4 6 4 7 4 7 4 8 4 8 4 8 4 ...

Page 48: ...ise CESSNA MODEL 172N Leaning With A Cessna Economy Mixture Indicator EGT Page 4 13 4 13 4 13 4 13 4 13 4 13 4 14 4 15 4 15 4 15 4 17 4 17 4 17 4 19 4 19 4 20 4 20 4 20 4 21 4 21 4 23 4 23 4 23 Stalls Spins Landing Normal Landing Short Field Landing Crosswind Landing Balked Landing Cold Weather Operation Starting Flight Operations Hot Weather Operation Noise Abatement 4 2 1 July 1979 ...

Page 49: ...must be used Takeoff Flaps Up Normal Climb Out Short Field Takeoff Flaps 10 Speed at 50 Feet Enroute Climb Flaps Up Normal Sea Level Normal 10 000 Feet Best Rate of Climb Sea Level Best Rate of Climb 10 000 Feet Best Angle of Climb Sea Level Best Angle of Climb 10 000 Feet Landing Approach Normal Approach Flaps Up Normal Approach Flaps 40 Short Field Approach Flaps 40 Balked Landing Maximum Power ...

Page 50: ... snow from wing tail and controlsurfaces Also makesure that control surfaces contain no internal accumulations of ice or debris Priorto flight check thatpitot heater if installed is warm totouch within 30 seconds with battery and pitot heat switches on If a night flight is planned check operation of all lights and make sure a flashlight is available Figure 4 1 Preflight Inspection 1 July 1979 ...

Page 51: ...ropeller to rotate 6 Fuel Quantity Indicators CHECK QUANTITY 7 Master Switch OFF 8 Static Pressure Alternate Source Valve if installed OFF 9 Baggage Door CHECK lock with key if child s seat is to be occupied EMPENNAGE 1 Rudder Gust Lock REMOVE 2 Tail Tie Down DISCONNECT 3 Control Surfaces CHECK freedom of movement and security RIGHT WING Trailing Edge 1 Aileron CHECK freedom of movement and securi...

Page 52: ... and Tire CHECK for proper inflation 7 Nose Tie Down DISCONNECT 8 Static Source Opening left side of fuselage CHECK for stop page LEFT WING 1 Main Wheel Tire CHECK for proper inflation 2 Before first flight of the day and after each refueling use sampler cup and drain small quantity of fuel from fuel tank sump quick drain valve to check for water sediment and proper fuel grade 3 Fuel Quantity CHEC...

Page 53: ...Propeller Area CLEAR 7 Ignition Switch START release when engine starts 8 Oil Pressure CHECK 9 Flashing Beacon and Navigation Lights ON as required 10 Avionics Power Switch ON 11 Radios ON BEFORE TAKEOFF 1 Parking Brake SET 2 Cabin Doors and Window s CLOSED and LOCKED 3 Flight Controls FREE and CORRECT 4 Flight Instruments SET 5 Fuel Selector Valve BOTH 6 Mixture RICH below 3000 feet 7 Elevator Tr...

Page 54: ...t 55 KIAS 5 Climb Speed 70 80 KIAS SHORT FIELD TAKEOFF 1 Wing Flaps 10 2 Carburetor Heat COLD 3 Brakes APPLY 4 Throttle FULL OPEN 5 Mixture RICH above 3000feet LEANto obtain maximum RPM 6 Brakes RELEASE 7 Elevator Control SLIGHTLY TAIL LOW 8 Climb Speed 53 KIAS until all obstacles are cleared ENROUTE CLIMB 4 8 1 Airspeed 70 85 KIAS NOTE If a maximum performance climb is necessary usespeeds shown i...

Page 55: ... Mixture RICH 4 Carburetor Heat ON apply full heat before reducing power 5 Autopilot if installed OFF 6 Air Conditioner if installed OFF LANDING NORMAL lANDING 1 Airspeed 60 70 KIAS flaps UP 2 Wing Flaps AS DESIRED 0 10 below 110 KIAS 10 40 below 85 KIAS 3 Airspeed 55 65 KIAS flaps DOWN 4 Touchdown MAIN WHEELS FIRST 5 Landing Roll LOWER NOSE WHEEL GENTLY 6 Braking MINIMUM REQUIRED SHORT FIELD LAND...

Page 56: ...es are cleared CESSNA MODEL 172N RETRACT after reaching a safe altitude and 60 KIAS AFTER LANDING 1 Wing Flaps UP 2 Carburetor Heat COLD SECURING AIRPLANE 1 Parking Brake SET 2 Avionics Power Switch Electrical Equipmeµt Autopilot if installed OFF 3 Mixture IDLE CUT OFF pulled full out 4 Ignition Switch OFF 5 Master Switch OFF 6 Control Lock INSTALL 4 10 1 July 1979 ...

Page 57: ...st likely in cold weather with a cold engine it will not fire at all and additional priming will be necessary As soon as the cylinders begin to fire open the throttle slightly to keep it running After starting if the oil gage does not begin to showpressurewithin 30 seconds in the summertime and about twicethat long inverycold weather stop engine and investigate Lack of oil pressure can cause serio...

Page 58: ...ESSNA MODEL 172N Strong quartering tail winds require caution Avoid sudden bursts of the throttle and sharp braking when the airplane is in this attitude Use the steerable nose wheel and rudder to maintain direction Figure 4 2 Taxiing Diagram 4 12 1 July 1979 ...

Page 59: ...ither magneto or show greater than 50 RPM differen tial between magnetos If there is a doubt concerning operation of the ignition system RPM checks at higher engine speeds willusually confirm whether a deficiency exists An absence of RPM drop may be an indication of faulty grounding of one side of the ignition system or should be cause for suspicion that the magneto timing is set in advance of the...

Page 60: ...ould be leaned to give maximum RPM in a full throttle static runup After full throttle is applied adjust the throttle friction lockclockwise to prevent the throttle from creeping back from a maximum power position Similar friction lock adjustments should be made as required in other flight conditions to maintain a fixed throttle setting WING FLAP SETTINGS Normal takeoffs are accomplished with wing...

Page 61: ... and may be leaned above 3000 feet for smoother operation or to obtain maximum RPM For maximum rate of climb use the best rate of climb speeds shown in the Rate of Climbchart in Section 5 If an obstruction dictates the use of a steep climb angle the best angle of climb speed should be used with flaps up and maximum power Climbs at speeds lower than the best rate of climb speed should be of short d...

Page 62: ... than 75 power themixture should not be leaned more than is required to provide peak RPM Carburetor ice as evidenced by an unexplained drop in RPM can be removed by application of full carburetor heat Upon regaining the original RPM with heat off use the minimum amountofheat by trial and error to prevent ice from forming Since the heated air causes a richer mixture readjust the mixture setting whe...

Page 63: ...re 4 4 As noted in this table operation at peak EGT provides the best fuel economy This results in approximately 4 greater range than shown in this handbook accompanied by approximately a 3 knotdecrease in speed Under some conditions engine roughness may occur while operating at peak EGT In this case operate at the Recommended Lean mixture Any change in altitude or throttle position will require a...

Page 64: ... 6000 feet above ground level In any case entries should be planned so that recoveries are completed well above the minimum 1500 feet above ground level required by FAR 91 71 Another reason for using high altitudes for practicing spins is that a greater field of view is provided which will assist in maintaining pilot orientation The normal entry is made from a power off stall As the stall is appro...

Page 65: ... THE RESULTING DIVE NOTE If disorientation precludes a visual determination of the direction of rotation the symbolic airplane in the tum coordinator may be referred to for this information Variations in basic airplane rigging or in weight and balance due to installed equipment or right seat occupancy can cause differences in behavior particularly inextendedspins These differences are normal and w...

Page 66: ...approach speedby lowering the nose of the airplane Touchdown should be made with power off and on the main wheels first Immediately after touchdown lower the nose wheel and apply heavy braking as required For maximum brake effectiveness retract the flaps hold the control wheel full back and apply maximum brake pressure without sliding the tires CROSSWIND LANDING When landing in a strong crosswind ...

Page 67: ...nal I preheater and an external power source are recommended whenever possible to obtain positive starting and to reduce wear and abuse to the engine and electrical system Pre heat will thaw the oil trapped in the oil cooler which probably will be congealed prior to starting in extremely cold temperatures When using an external power source the position of the master switch is important Refer to S...

Page 68: ...ter engine hasstarted Leave on until engine is running smoothly 12 Primer LOCK NOTE If the engine does not start during the firstfewattempts or if engine firing diminishes in strength it is probable that the spark plugs have been frosted over Preheat must be used before another start is attempted CAUTION Pumping the throttle may cause raw fuel to accumulate in the intake air duct creating a fire h...

Page 69: ...pilots to minimize the effect of airplane noise on the public We as pilots can demonstrate our concern for environmental im provement by application of the following suggested procedures and thereby tend to build public support for aviation 1 Pilots operating aircraft under VFR over outdoor assemblies of persons recreational and park areas and other noise sensitive areas should make every effort t...

Page 70: ...and avoid other aircraft The certificated noise level for the Model 172N at 2300 pounds maxi mum weight is 73 8 dB A No determination has been made by the Federal Aviation Administration that the noise levels of this airplane are or should be acceptable or unacceptable for operation at into or out of any airport 4 24 1 July 1979 ...

Page 71: ...version Chart Figure 5 3 Stall Speeds Figure 5 4 Takeoff Distance 2300 Lbs Takeoff Distance 2100 Lbs and 1900 Lbs Figure 5 5 Maximum Rate Of Climb Figure 5 6 Time Fuel And Distance To Climb Figure 5 7 Cruise Performance Figure 5 8 Range Profile 40 Gallons Fuel Range Profile 50 Gallons Fuel Figure 5 9 Endurance Profile 40 Gallons Fuel Endurance Profile 50 Gallons Fuel Figure 5 10 Landing Distance P...

Page 72: ......

Page 73: ...peller condition and air turbulencemay account for variations of 10 or more in range and endurance Therefore it is important to utilize all available information to estimate the fuel required for the particular flight USE OF PERFORMANCE CHARTS Performance data is presented in tabular or graphical form to illus trate the effect of different variables Sufficiently detailed information is provided in...

Page 74: ...off distance information presented for a weight of 2300 pounds pressure altitude of 2000 feet and a temperature of 30 C should be used and results in the following Ground roll Total distance to clear a 50 foot obstacle 1045 Feet 1885 Feet These distances are well within the available takeoff field length Howev er a correction for the effect of wind may be made based on Note 3 of the takeoff chart ...

Page 75: ... nearly corres pond to the planned altitude and expected temperature conditions The engine speed chosen is 2500 RPM which results in the following Power True airspeed Cruise fuel flow 64 114 Knots 7 1 GPH The power computer may be used to determine power and fuel consump tion more accurately during the flight FUEL REQUIRED The total fuel requirement for the flight may be estimated using the perfor...

Page 76: ...ted to be 114 10 i04 Knots Therefore the time required for the cruise portion of the trip is filQ Nautical Miles _ 3 0 H 104 Knots ours The fuel required for cruise is 3 0 hours x 7 1 gallons hour 21 3 Gallons The total estimated fuel required is as follows Engine start taxi and takeoff Climb Cruise Total fuel required 1 1 1 5 21 3 23 9 Gallons Once the flight is underway ground speed checks will ...

Page 77: ... A correction for the effect of wind may be made based on Note 2 of the landing chart using the same procedure as outlined for takeoff DEMONSTRATED OPERATING TEMPERATURE Satisfactory engine cooling has been demonstrated for this airplane with an outside air temperature 23 C above standard This is not be to considered as an operating limitation Reference should be made to Section 2 for engine opera...

Page 78: ... RPM dive FLAPS UP KIAS 40 50 60 70 KCAS 50 56 63 71 FLAPS 10 KIAS 40 50 60 70 KCAS 49 55 62 71 FLAPS 40 KIAS 40 50 60 70 KCAS 48 55 63 72 80 90 80 89 80 90 80 90 80 85 82 87 100 99 100 99 110 109 110 108 120 119 130 129 CESSNA MODEL 172N 140 139 150 149 160 160 Figure 5 1 Airspeed Calibration Sheet 1 of 2 5 8 1 July 1979 ...

Page 79: ...ORMAL KIAS 40 50 ALTERNATE KIAS 36 48 FLAPS 10 NORMAL KIAS 40 50 ALTERNATE KIAS 38 49 FLAPS 40 NORMAL KIAS 40 50 ALTERNATE KIAS 34 47 FLAPS UP NORMAL KIAS 40 50 ALTERNATE KIAS 26 43 FLAPS 10 NORMAL KIAS 40 50 ALTERNATE KIAS 25 43 FLAPS 40 NORMAL KIAS 40 50 ALTERNATE KIAS 25 41 60 70 80 90 59 70 80 89 60 70 80 90 59 69 79 88 60 70 80 85 57 67 77 81 WINDOWS OPEN 60 70 80 90 57 70 82 93 60 70 80 90 5...

Page 80: ...CTION 5 PERFORMANCE CESSNA MODEL 172N 5 10 TEMPERATURE CONVERSION CHART I w r z w a I u w w a w 60 40 20 J 40 _ _ _ _ _ 40 20 0 20 40 60 DEGREES CELSIUS Figure 5 2 Temperature Conversion Chart 1 July 1979 ...

Page 81: ... BANK WEIGHT FLAP oo 30 45 LBS DEFLECTION KIAS KCAS KIAS KCAS KIAS KCAS UP 39 50 42 54 47 59 2300 100 38 47 40 51 45 56 400 31 44 33 47 37 52 MOST FORWARD CENTER OF GRAVITY ANGLE OF BANK WEIGHT FLAP oo 30 45 LBS DEFLECTION KIAS KCAS KIAS KCAS KIAS KCAS UP 44 53 47 57 52 63 2300 100 44 51 47 55 52 61 40 33 47 35 51 39 56 Figure 5 3 Stall Speeds 1 July 1979 60 KIAS KCAS 56 71 54 66 45 62 500 KIAS KC...

Page 82: ... LIFT AT FT GANO OFF 50FT ROLL 2300 48 53 S L 695 1000 760 2000 835 3000 920 4000 1010 5000 1115 6000 1235 7000 1370 8000 1520 r Jc 10 c 20 c TOTAL TOTAL TOTAL TO CLEAR GANO TO CLEAR GANO TO CLEAR GRNO 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS ROLL 1250 745 1340 805 1440 865 1370 820 1475 880 1585 950 1510 900 1625 970 1750 1045 1670 990 1800 1070 1940 1150 1850 1090 2000 1180 2165 1270 2060 1205 22...

Page 83: ...25 1070 1975 1155 2135 1095 2040 1185 2210 1280 2400 1215 2295 1315 2495 1420 2720 450 820 480 880 52 0 940 490 895 525 96 0 565 1025 535 980 580 1050 620 1120 590 1070 635 1150 680 1230 645 1175 695 1260 750 1355 710 1295 765 1390 82 5 1495 785 1430 845 1540 910 16 55 865 1585 935 1710 10 05 18 45 955 1765 1030 1905 1115 2060 Figure 5 4 Takeoff Distance Sheet 2 of 2 700 765 840 925 1020 1125 1245...

Page 84: ...ve 3000 feet for maximum RPM WEIGHT PRESS CLIMB RATE OF CLIMB FPM LBS 2300 5 14 ALT SPEED FT KIAS 20 c o0c S L 73 875 815 2000 72 765 705 4000 71 655 600 6000 70 545 495 8000 69 440 390 10 000 68 335 285 12 000 67 230 180 Figure 5 5 Maximum Rate of Climb 20 c 755 650 545 440 335 230 4o0c 695 590 485 385 280 1 July 1979 ...

Page 85: ...rature 4 Distances shown are based on zero wind PRESSURE CLIMB RATE OF FROM SEA LEVEL WEIGHT TEMP LBS ALTITUDE oc SPEED CLIMB TIME FUEL USED 2300 1 July 1979 FT KIAS FPM MIN GALLONS S L 15 73 770 0 0 0 1000 13 73 725 1 0 3 2000 11 72 675 3 0 6 3000 9 72 630 4 0 9 4000 7 71 580 6 1 2 5000 5 71 535 8 1 6 6000 3 70 485 10 1 9 7000 1 69 440 12 2 3 8000 1 69 390 15 2 7 9000 3 68 345 17 3 2 10 000 5 68 ...

Page 86: ...8 5 5 STANDARD TEMPERATURE KTAS GPH BHP 75 116 8 4 67 111 7 5 60 105 6 7 53 100 6 1 47 94 5 6 75 118 8 4 71 115 8 0 64 110 7 1 57 105 6 4 51 99 5 9 46 93 5 5 75 120 8 4 67 115 7 6 60 109 6 8 54 104 6 2 49 98 5 7 44 92 5 4 75 122 8 4 71 120 8 0 64 114 7 2 58 109 6 5 52 103 6 0 47 97 5 5 71 122 8 0 68 119 7 6 61 114 6 8 55 108 6 2 50 102 5 8 45 96 5 4 64 118 7 2 58 113 6 5 53 107 6 0 48 101 5 6 44 9...

Page 87: ...g climb 1 w w LL w 0 I J 1 July 1979 ___ _ __ __ _ _x A i 1 1 1 _ _ 1 l I 8000 t t 1 1 I I _ 122 1 KTAS 1 1 4 1 1 1 a 1 1 1 J j_ j I I 6000t kt tkt W kl l l l t 120 113 93 KTAS KTAS KTAS I 4000 11M 11 i 1 1 105 1 3 3 _3 _ KTAS 1 1 1 0 0 0 0 l 1 a 0 a a 1 4 1 I I ft 1 4 1 I 2000 e m m __ fl l 1 1 1 1 I I t 1 i 11 114 107 _ 100 90 t t KTAS KTAS1 _ KTAS _ _ KTAS___ _____ _____ S L _ I _i I I I I _ i ...

Page 88: ...the distance during climb 5 18 12 000 T T r T T r r r r 1 1 1 T T 1 t t t 1 Jllt l t t r t t t 1 r r 96 __ f t v 118 t I _ KTAS t t 1 10 y l I 8 1 t J _ 122 KTAS 1 H 1 t t I I w 0 I J 6000 1 I I 113 I l 120 105 93 _____ __ _KTAS KTAS t KTAS KTAS 4000 fE irl l t r t fE fE11 1 i 3 3 _3 o 1 2 2J l I 2000 tR t 114 1 KTAS 107 S L 550 I I I I 600 I KTAS I I I 650 I 100 90 1 KTAS KTAS I 1 1 I I 700 750 8...

Page 89: ... for Cruise Standard Temperature NOTE This chart allows for the fuel used for engine start taxi takeoff and climb and the time during climb I w UJ LL UJ a I 1 July 1979 12 000 I tJ 10 000 St Q 8000 6000 a I a a w UJ w UJ i 3 t o 0 0 0 0 0 0 4000 f f It It It It 0 LO 2000 S L 3 4 5 6 ENDURANCE HOURS Figure 5 9 Endurance Profile Sheet 1 of 2 7 5 19 ...

Page 90: ...Standard Temperature NOTE CESSNA MODEL 172N This chart allows for the fuel used for engine start taxi takeoff and climb and the time during climb 12 000 10 000 8000 UJ u UJ 6000 0 4000 2000 S L 5 20 i RI 4 i J a a a a w UJ U I 3 3 3 0 0 0 0 ll ll ll LO LO ID LO 4 5 6 7 8 ENDURANCE HOURS Figure 5 9 Endurance Profile Sheet 2 of 2 9 1 July 1979 ...

Page 91: ...GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS 2300 59 S L 495 1205 510 1235 530 1265 545 1295 1000 510 1235 530 1265 550 1300 565 1330 2000 530 1265 550 1300 570 1335 590 1370 3000 550 1300 570 1335 590 1370 610 1405 4000 570 1335 590 1370 615 1410 635 1445 5000 590 1370 615 1415 635 1450 655 1485 6000 615 1415 640 1455 660 1490...

Page 92: ......

Page 93: ...ECTION 6 WEIGHT BALANCE EQUIPMENT LIST SECTION 6 WEIGHT BALANCE EQUIPMENT LIST TABLE OF CONTENTS Introduction Airplane Weighing Procedures Veight And Balance Equipment List 1 July 1979 Page 6 3 6 3 6 6 6 13 6 1 6 2 blank ...

Page 94: ......

Page 95: ... to drain all oil d Move sliding seats to the most forward position e Raise flaps to the fully retracted position f Place all control surfaces in neutral position 2 Leveling a Place scales under each wheel minimum scale capacity 500 pounds nose 1000 pounds each main b Deflate the nose tire and or lower or raise the nose strut to properly center the bubble in the level see figure 6 1 3 Weighing a W...

Page 96: ... 6 3 Add Oil No Oil Filter 6 Ots at 7 5 Lbs Gal With Oil Filter 7 Ots at 7 5 Lbs Gal Add Unusable Fuel Std Tanks 3 Gal at 6 Lbs Gal L R Tanks 4 Gal at 6 Lbs Gal Equipment Changes Airplane Basic Empty Weight Tare Weight Lbs X CESSNA MODEL 172N Level at upper door sill or leveling screws on left side of tailcone Symbol Net Weight L R N w IN Moment 1000 X C G Arm In Lbs ln 14 0 14 0 46 0 46 0 Figure ...

Page 97: ... Balance I SERIAL NUMBER I PAGE NUMBER WEIGHT CHANGE DESCRIPTION ADDED REMOVED OF ARTICLE OR MODIFICATION Wt Arm Moment Wt lb In 1000 lb Figure 6 2 Sample Weight and Balance Record Arm Moment In 1000 RUNNING BASIC EMPTY WEIGHT Wt Moment lb 1000 a i 0 t rj t I Cl t rj Cl t 4 z 1 1 z t rj t rj 0 I d a go a IJj rJl tx 1 t_ i j z t 4 i o 3 o 3 zs oz rJl t j o 3 c ...

Page 98: ...loading problem Use the Loading Graph to determine the moment 1000 for each additional item to be carried then list these on the loading problem NOTE Loading Graph information for the pilot passengers and baggage is based on seats positioned for average occu pants and baggage loaded in the center of the baggage areas as shown on the Loading Arrangements diagram For loadings which may differ from t...

Page 99: ...ES 1 The usable fuel C G arm for standard and long range tanks is located at station 48 0 2 The rear cabin wall approximate station 108 or aft baggage wall approximate station 142 can be used as convenient interior reference points for determining the location of baggage area fuselage stations STATION STATION C tARM C G ARM 37 37 34 to 46 34 to 41 73 73 BAGGAGE 95 AREA 1 96 108 108 123 BAGGAGE BAG...

Page 100: ...G DIMENSIONS IWIDTH TOP CABIN DOOR I 32 BAGGAGE DOOR 1S I WIDTH IHEIGHT I HEIGHT BOTTOM FRONT REAR 3 7 I 40 I 4 1 1S 22 21 CABIN WIDTH MEASUREMENTS WIDTH LWR WINDOW LINE CABIN FLOOR INSTRUMENT PANEL REAR DOORPOST B ULKHEAD I 39 I 34 I I I I I I STATIONS 0 10 20 30 40 50 I 11 60 70 80 90 100 110 120 130 140 C G ARMS 6 8 6S 3 Figure 6 4 Internal Cabin Dimensions 1 July 1979 ...

Page 101: ... Lbs Max 7 RAMP WEIGHT AND MOMENT 8 Fuel allowance for engine start taxi and runup 9 TAKEOFF WEIGHT AND MOMENT Subtract Step 8 from Step 7 Weight lbs 1454 240 340 170 103 2307 7 2300 10 Locate this point 2300 at 103 6 on the Center of Gravity Moment Envelope and since this point falls within the envelope the loading is acceptable Moment lb ins 1000 57 6 11 5 12 6 12 4 9 8 103 9 3 103 6 YOUR AIRPLA...

Page 102: ... so i t iO GAL 300 11 1 89 3 LITERS ii _ __ r 50 11 l LOAD MOMENT 1000 POUND INCHES NOTE Line representing adjustable ts shows the pilot or passenger center of gravity on adjustable seats positioned for an average occupant Refer to the loading Arrangements diagram for forward and aft limits of occupant C G range Figure 6 6 Loading Graph 12 5 en E a C g i2 C w 3 0 g t rl E rn D l2 l t r j C H H O t...

Page 103: ...2100 2000 1900 1800 1700 1600 1500 45 CENTER OF GRAVITY MOMENT ENVELOPE 50 55 I I I 4 v 0 o v if 60 65 70 75 r r 00 85 NORMAL ii CATEGORY l il 90 95 100 105 110 LOADED AIRPLANE MOMENT 1000 POUND INCHES Figure 6 7 Center of Gravity Moment Envelope I 1050 1000 950 900 850 800 750 700 a a o trJ t I rn trJ rn t z z a C1 0 J i2 J C1 w 3 w z J a a 0 w 0 0 J trJ 1 4 t 2 0 ei a tc rn t 2 trJ z t a t z 0 1...

Page 104: ... 35 36 I I I I I I I CENTER OF GRAVITY UTIUTY CATEGORY 37 38 39 40 LIMITS I I I I I I NORMAL I CATEGORY I I I I 41 42 43 44 45 AIRPLANE C G LOCATION INCHES AFT OF DATUM STA 0 0 Figure 6 8 Center of Gravity Limits 46 I 47 t_ rj s Cf g t_ r jt_ rj c 0 1 1 0 1 3 C tt a 1 3 0 t_ r j z z l I 0 1050 t 3 t j t i V 1 1 t l 1000 a 0 C t_ r j 0 950 I I 900 Q w 1 w 850 5 a 800 w 0 750 g 700 0 t J 0 t r l t_ ...

Page 105: ...standard equipment items 0 optionalequipment itemsreplacing required or standard items A optional equipment items which are in addition to required or standard items A reference drawing column provides the drawing number for the item NOTE If additional equipment is to be installed it must be done in accordance with the reference drawing accessory kit instruc tions or a separate FAA approval Column...

Page 106: ...TCK OAAlN VALVE NET CHA GE 13 LA nt GEA ACCESSORIES I WHF F L OAKE r TIPE ASSY 6 00X6 AI N 2t W EFL ASSV MCCAULEY BRAKE ASSV MCCAULEY LEFT ARAK ASSY MCCAULEY RIGHT TIRE 4 PLY 8LACKWALL EACH Tlll F EACH WH EL f TIRF ASSY 5 H X5 NOSE WHEEL ASSY MCCAULEY I REF DRAWING I WT LBS I I 550333 269 5 294510 0301 o s C6l l503 1102 11 7 0550333 3 3 l l599A 2 1 511 6 2 5 Cl6l Ol 13l 34 6 1Cl61 DT 7 i57 30 l C4...

Page 107: ...EACON BEACON LIGHT ON FIN TIP FLASHER POWFQ SUPPLY Rf SISTOR ME COR LIGHT INSTALLATIGN WING TIP STROBE FLASHER POWER SUPPLY SET OF 2 IN WING STRnijE LIGHT WING TIP SET Of 2 LIGHT lNSTALLATICN COWL MOUNTED LANDING LAMP 250 WATT G E t LJr HTS DUAL COWL MOUNTEO LANDING LAMP 2 0 WATT CG E EACH D NSTRUMENTS lN1TCATOR AJqSPEEr IN ICATQR TRUE AIRSPEED REF DRAWING 262003 11 2 C262023 IJ101 0541225 1 C6140...

Page 108: ...J 11IRECTIONAL INDICATOR ATTITUDE INOICATOR GYRO INSTALLATION FOR 300 NAV 0 MATtC OIRECTIONAL INDICATOR ARCI ATTITUOE INDICATOR RfCORDER INSTALLATION FLIGHT HOUR r AGF OUTSIDE AIR TEMPEPATURE TACHO ETEP INSTALLATICN ENGINE RECOR8TNG TACH INDICATOR JNJICATOR TURN COROINATOR 28 VOLT ONLY tN ICAT Q TUqN COOPOINATOR 10 30 VOLT IN ICATOR TURN COOROINATGR FOR USE WITH NAV 0 MATIC 20 A ANO 300A IN1ICATOR...

Page 109: ... WlTH Esq A l OR AR h 21 9FVfQ4f E CUP HOLOER YfAORfST 1ST RO WT EACHt E O EST ND Rnw WT EACH U 1 V ISl IR S SET CF 2 nnws TINTEn CABIN NET CHANGE I IET CHA 1 GI r AGC t GF NFT Rl GS CARGO TIE DOWN STCWE USE R AS lNSTALLEn WITH CARGO cnNTQOlS TNST LLATION DUAL QlJf f R TR IM VSTEM CA3IN I CONDITIONING SVSTE CH ILLED AIR COMOO SSOR ASSE RLY FVAPORATnR LOCAT O ABOV AF T ijAGf AGE cm 111ENSOR LOCAT E...

Page 110: ...D t CCQP nlNG TC AIRCRAFT EOUIP ENT INOICI TOR AUDIBLE PNEUMATIC STALL WARNING LOW VOLTAGE WARNING LIGHT ALTE Nt TO PlLrT s OPER TING HANORO K ANO FAA APPQnvfn PnLANE FLIG T ANUhl G AU I LIARY EOUIPMENT l GS A JRP L h E HOISTING CARIN TOPI r riqROSinN P r FING INTERNAL STATIC ISCHAqGfQS STA ILIZE AR SlON ACOTS rrw 9A CST0WE0 ATNT ovcRALL EXTF P IOR OVFQ Ll RA F HITE COLO S TR T PF CARL S COQROSION...

Page 111: ...LLATION RECEIVER UNT WIRES AND MISC ITE S 404 A l MC INSTALLATION NARCO TRANSCl 1 Vf DME 1q 1 MCUNT ASSY I NT INA H A FPSTER R NAV 511 RF Cr lVFP OUNT 511 H A CES A 4n GLl ESLOPE INCLUOES VO lLS l DT aTnR NET CHANGE FOR VCR LOC Rf CETVfR 43Rl T NNA Ll T 0 UPP R WINDSHIELD V R lLS lN lCATOR IN 33 A IN CAT R WT FT CHA GE ACTUA L T IS 1 7 LBS HOA A 1 dtTO Rl lAL CCf HERING INDICAHlR ARC LOCI REF DRAW...

Page 112: ...UNIT RF JUlRES 434 A TO BE CPERATIO lAL RFC IVER TQANSCFTVER RT 3 5AI VOR LOC IN11CATOR 1N 385A au T W RING MISC ITEMS H 1 ICESSNA n NAV COM 720 CH COM 2ND UNIT R l JIIIRES H37 A rr RE CPERATIONALl RF CF IVF R TQ NSCEIVER RT 3R5hl vn l JC IN l lCATnR lN 38 iA MOUNT WIRTNG E M SC JTfMS H q A 1 IE ERGF NCY tOCHOR TPANSMITTEQ T A S ITTFq J O ELT 6 1 RH DRAWING 40960 120 4636 1 1 l 391019l 46 961 220 ...

Page 113: ...EL I NSTL NTFNNA f cnuPLF R KIT REQUIRED WITH 2ND UNIT NdV CC FACTORY INSTALLATICN AVIONICS QPTtnN O NAV 0 ATtC WING PROV T E H AOSET cn BINATION HEADSET STOWED csrnw 9 Q SHOwN REOUl ES E89 0J PAQDEO HEADPHONES ICRCPHONE REQUIRES FqQ n hLL nuooosE CONTROL WHEEL J SPECl L CPTICN PACKAGES SKYH WK Tl CUIPMENT CONSISTS OF ITEMS REF DRAWING C589511 0ll l9 n47041q 4 589511 01 l3 C5895ll lJ109 3911162 1 ...

Page 114: ...GE AETWEEN STANOARO LANDING GFAO CITF NCS B1t R 814 R B11 S AND A 0 AKE F NCSE WH El TEFRING SYSTF S ANr FLOATPLANE KIT lTE NO JV I A 11 TS APPROXIMATELY 155 l 3S AT q 3 TN THE CORR ECT VALUES OF WT AO CHA E FOD WT BALANCE CALCULATIONS APE TO BE nETERMINEn FQO THE ACTUAL lNSTt LLATTC l l l 1 l IFLOI TPLANE FOIJIPMFNT KlT i ITl f PRGP CHANGE ANO COR O TON PROOFING CONSISTS QF A 1 1 PQ PFLLER FLOATP...

Page 115: ...ELING Jl A FUSELAGE MODIFICATIONS Jl3 A CO L DECK V BRACF INSTALLED Jl5 A INTERCONNECT SYSTEM INSTALLED COWL ASSY FLOATPLANE NET CHGI FL ATPLANF EQUIPMENT KIT ITH NO PROP CHANGE oo CORROSION PPOOFING USED PRI ARtlY N CANADA G 7 A Rl GS AIRPLANE HOISTING G5B A STEP f HANDLE REFUELING Jl A FU5F LAGE MOOIFICATIONS Jl3 A COWL nECK V BRACE INSTALLED Jl5 A INTFRCGNNECT SYSTEM STOWEDJ CCWL ASSY FLCATPLAN...

Page 116: ......

Page 117: ...houlder Harnesses With Inertia Reels Entrance Doors And Cabin Windows Control Locks Engine Engine Controls Engine Instruments New Engine Break In And Operation Engine Oil System Ignition Starter System Air Induction System Exhaust System Carburetor And Priming System Cooling System Propeller Fuel System Brake System Electrical System Master Switch Avionics Power Switch 1 July 197 9 Page 7 3 7 3 7 ...

Page 118: ......

Page 119: ...tor Altimeter Vacuum System And Instruments Attitude Indicator Directional Indicator Suction Gage Stall Warning System Avionics Support Equipment Audio Control Panel Transmitter Selector Switch Audio Selector Switches Com Auto Audio Selector Switch Com Both Audio Selector Switch Auto Audio Selector Switch Annunciator Lights Brightness And Test Switch Sidetone Operation Microphone Headset Installat...

Page 120: ...ibs doublers and stringers The entire structure is covered with aluminum skin The front spars are equipped with wing to fuselage and wing to strut attach fit tings The a ft spa rsa reequippedwith wing to fuselageattachfittings and a re partial span spars Conventional hingedailerons and single slot type flaps are attached to the trailing edge of the wings The ailerons are constructed of a forward s...

Page 121: ...NA MODEL 172N AIRPLANE SYSTEMS DESCRIPTIONS _ ___ _ __ 1 _ _ 7 _ RUD RIM 7 4 f p r n s I C i l _ __ _ _ _ _ _ _ _ _ _ _ ___ _ _ f ii _ _ _ _ __ _ __ Figure 7 1 Flight Control and Trim Systems Sheet 1 of 2 1 July 1979 ...

Page 122: ...TION 7 AIRPLANE SYSTEMS DESCRIPTIONS ELEVATOR CONTROL SYSTEM _ _ _ _ _ _ l 1 1 ELEVATOR TRIM CONTROL SYSTEM _ j y i f l l f f _ l i ___ t rr 0 _ _ w _ Figure 7 1 Flight Control and Trim Systems Sheet 2 of 2 1 July 1979 7 5 ...

Page 123: ...SECTION 7 AIRPLANE SYSTEMS DESCRIPTIONS 7 6 Figure 7 2 Instrument Panel Sheet 1 of 2 CESSNA MODEL 172N 1 July 1979 ...

Page 124: ... Controls a a 11 Course Deviation Indicators 32 Fuel Selector Valve Handle ij CD 12 Transponder 33 Rudder Trim Control Lever ts 13 Magnetic Compass 34 Elevator Trim Control Wheel 14 Marker Beacon Indicator 35 Carburetor Heat Control Knob ts Lights and Switches 36 Electrical Switches 15 Audio Control Panel 37 Circuit Breakers Autopilot Control Unit 38 Parking Brake Handle en en 16 i t 17 Radios 39 ...

Page 125: ...nsist ofa rudder pedal face two spacers and two spring clips To install an exten sion place the clip on the bottom of the extension under the bottom of the rudder pedal and snap the top clip over the top of the rudder pedal Check that the extension is firmly in place Toremovethe extensions reverse the above procedures TRIM SYSTEM A manually operated elevator trim system is provided a rudder trim s...

Page 126: ... switch and control panel in front of the pilot Fordetails concerning the instruments switches circuit breakers and controls on this panel refer in this section to the description of the systems to which these items are related GROUND CONTROL Effective ground control while taxiing is accomplished through nose wheel steering by using the rudder pedals left rudder pedal to steer left and right rudde...

Page 127: ...e stop and position it as desired A scale and pointer on the left side of the switch lever indicates flap travel in degrees The wing flap system circuit is protected by a 15 ampere circuit breaker labeled FLAP on the left side of the switch and control panel LANDING GEAR SYSTEM The landing gear isof the tricycle type with asteerablenosewheel two main wheels and wheel fairings Shock absorption is p...

Page 128: ...ow the center of the seat frame slide the seat into position release the handle and check that the seat is locked in place The seat back angle is controlled by a cylinder lock release button which is spring loaded tothelocked position The release button is locatedon theright side below the forward corner of the seatcushion Toadjusttheangleof theseat back push up on the release button posftion the ...

Page 129: ... headrest apply enough pressure to it to raise or lower it to the desired level The headrest may be removed at any time by raising it until it disengages from the top of the seat back SEAT BELTS AND SHOULDER HARNESSES All seat positions are equipped with seat belts see figure 7 4 The pilot s and front passenger s seats are also equipped with separate shoulder harnesses shoulder harnesses are avail...

Page 130: ...ATSHOWN FREE END OF HARNESS Pull down to tighten SEAT BELT SHOULDER HARNESS WITH INERTIA REEL r l j FREE END OF SEAT BELT Pull to ti hten I I l f f r I 1 j I I f i i I I l ff I f 1 I I l z t f t r _ _ _ _ i level pull link and harness down _ _ ward to connect to seat belt buckle i s L 0 Figure 7 4 Seat Belts and Shoulder Harnesses 1 July 1979 7 13 ...

Page 131: ...tud on the seatbelt link Inan emergency the shoulder harness may be removed by releasing the seat belt first and allowing the harness still attached to the link half of the seat belt to drop to the side of the seat INTEGRATED SEAT BELT SHOULDER HARNESSES WITH INERTIA REELS Integrated seat belt shoulder harnesses with inertia reels are availa ble for the pilot and front seat passenger Theseat belt ...

Page 132: ...CK The handle is spring loaded to the CLOSE up position When the door has been pulled shut and latched lock it by rotating the door handle forward to the LOCK position flush with the arm rest When the handle is rotated to the LOCK position an over center action will hold it in that position Both cabin doors should be lockedprior to flight and should not be opened intentionally during flight NOTE A...

Page 133: ...talled over the vertical stabilizer a nd rudder The control lock and any other type of lockingdevice shouldbe removed prior tostartingthe engine ENGINE The airplane is powered by a horizontally opposed four cylinder overhead valve air cooled ca rbureted engine with a wetsump oil system The engine is a LycomingModel O 320 H2AD and is ratedat 160 horsepow er a t 2700 RPM Major accessories include a ...

Page 134: ...rating range green arc which is 1 F 38 C to 245 F 118 C and the maximum red line which is245 F 118 C The engine driven mechanical tachometer is located on the instrument panel to the left of the pilot s control wheel The instrument is calibrated in increments of 100 RPM and indicates both engine and propeller speed An hour meter in the lower section of the dial records elapsed engine time in hours...

Page 135: ...sory housing and into aflexible hose leading to the oil cooler on the right rear engine baffle Pressure oil from the cooler returns to the accessory housing where it passes through the pressure strainer screen full flow oil filter if installed The filter oil then enters a pressure relief valve which regulates engine oil pressure by allowing excessive oil to return to the sump while the balance of ...

Page 136: ...e When the switch is released itwillautomati cally return to the BOTH position AIR INDUCTION SYSTEM The engine air induction system receives ram air through an intake in the lower front portion of the engine cowling The intake is covered by an air filter which removes dust and other foreign matter from the induction air Airflow passing through the filter enters an airbox After passing through the ...

Page 137: ...penings in the frontofthe engine cowling The cooling airis directed aroundthe cylinders and other areas of the engine by baffling and isthen exhausted through an opening at the bottom aft edge of the cowling No manual cooling system control is provided A winterization kit is available for the airplane Details of this kit are presented in Section 9 Supplements PROPELLER The airplane is equipped wit...

Page 138: ...el quantity transmitters one in each tank and indicated by two electrically operatedfuel quantity indicators on the left side of the instrument panel An empty tank is indicated by a red line and the letter E When an indicator shows an empty tank approximately 1 5 gallons remain in a standard tank and 2 gallons remain in a long range tank as unusuable fuel The indicators cannot be relied upon for a...

Page 139: ...LECTRICAL CONNECTION VALVE FUEL QUANTITY INDICATORS 11 SELECTOR VALVE FUEL QUANTITY TRANSMITTER SELECTOR VALVE DRAIN PLUG FUEL STRAINER CARBURETOR FUEL STRAINER DRAIN CONTROL 0THROTTLE CONTROL f_ O TO ENGINE TO ENSURE MAXIMUM FUEL CAPACITY WHEN REFUELING ANO MINIMIZE CROSS FEEDING WHEN PARKED ON A SLOPING SURFACE PLACE THE FUEL SELECTOR VALVE IN EITHER LEFT OR RIGHT POSITION Figure 7 6 Fuel System...

Page 140: ...op of either the left pilot s or right copilot s set of rudder pedals which are interconnected When the airplane is parked both main wheel brakes may be set by utilizing the parking brake which is operated by a handle under the left side of the instrument panel To apply the parking brake set the brakes with the rudder pedals pull the handle aft and rotate it 90 down For maximum brake life keep the...

Page 141: ... BATTERY GROUND SERVICE PLUG RECEPTACLE FLIGHT HOUR RECORDER Figure 7 7 Electrical System CESSNA MODEL 172N TO PITOT HEAT SYSTEM TO DIGITAL CLOCK TO IGNITION SWITCH TO OIL TEMPERATURE GAGE AND CYLINDER HEAD TEMPEAATURE GAGE TO LOW VOLTAGE WARNING LIGHT TO FUEL QUANTITY INDICATOAS ANO CAA8URETOR AIR TEMPERATURE GAGE TO DOOR POST MAP LIGHT TO DOME AND COURTESY LIGHTS TO INSTRUMENT RADIO MAGNETIC COM...

Page 142: ...used simultane ously however the BAT side of the switch could be turned on separatelyto check equipment while on the ground To check or useavionics equipment or radios while on the ground the avionics power switch must also be turned on The ALT side of the switch when placed in the off position removes the alternator from the electrical system With this switch in the off position the entire electr...

Page 143: ...e is equipped with a combination alternator regulator high low voltage control unit mounted on the engine side of the firewall and a red warning light labeled LOW VOLTAGE on the left side of the instrument panel below the ammeter In the event an over voltage condition occurs the alternator control unit automatically removes alternator field current which shuts down the alternator The battery will ...

Page 144: ...are protected by fuses mounted adjacent to the battery GROUND SERVICE PLUG RECEPTACLE A groundserviceplug receptacle may be installed to permitthe use of an external power source for cold weather starting and during lengthy maintenance work on the electrical and electronic equipment Details of the ground service plug receptacle are presented in Section 9 Supple ments LIGHTING SYSTEMS EXTERIOR LIGH...

Page 145: ...ide direct lighting To use post lighting move the slide switch in the overhead console labeled PANEL LIGHTS to the POST position and rotate the outer knob on the light dimming rheostat labeled PANEL LT clockwise to obtain the desired light intensity When the PANEL LIGHTS switch is placed in theBOTH position the flood lights and post lights will operate simultaneously The engine instrument cluster ...

Page 146: ...odor turn offthelight switch oftheaffected lights reset the breaker and turn the switch on again If the breaker opens again do not reset it CABIN HEATING VENTILATING AND DEFROSTING SYSTEM The temperature and volume of airflow into the cabin can beregulated by manipulation of the push pull CABIN HT and CABIN AIR control knobs see figure 7 8 For cabin ventilation pull the CABIN AIR knob out To raise...

Page 147: ...TLET 2 CABIN HEAT u _1 CONTROL fr f REAR CABIN AIR OUTLETS ADJUSTABLE VENTILATORS CESSNA MODEL 172N HEATER VALVE VENT LATING AIR DOOR CABIN AIR CONTROL CODE RAM AIR FLOW 7 VENTILATING AIR _ HEATED AIR BLENDED Affi MECHANICAL CONNECTION Figure 7 8 Cabin Heating Ventilating and Defrosting System 7 30 1 July 1979 ...

Page 148: ...trol panel When the pitot heat switch is turned on the element in the pitot tube is heated electrically to maintain proper operation in possible icing conditions Pitot heat should be used only as required A static pressure alternate source valve may be installed on the switch and control panel below the throttle and can be used if the external static source is malfunctioning This valve supplies st...

Page 149: ...plane altitude is depicted by a barometric type altimeter A knob near the lower left portion of the indicator provides adjustment of the instrument s barometric scale to the current altimeter setting VACUUM SYSTEM AND INSTRUMENTS An engine driven vacuum system see figure 7 9 providesthesuction necessary to operate the attitude indicator and directional indicator The system consists of a vacuum pum...

Page 150: ...CUUM PUMP VACUUM SYSTEM AIR FILTER t O O t _ 0 0 0 I O O t 0 0 0 _ 0 0 0 t 0 0 0 0 0 0 ATTITUDE INDICATOR i SUCTION I GAGE ___ ii l l t OVERBOARD VENT LINE I VACUUM RELIEF VALVE INLET AIR t lttd VACUUM r 4J DISCHARGE AIR Figure 7 9 Vacuum System 1 July 1979 7 33 ...

Page 151: ...irplane is equippedwith a pneumatic type stall warning system consisting of an inlet in the leading edge of the left wing an air operated horn neartheupperleft comerof thewindshield and associatedplumbing As the airplane approaches astall the lowpressure on the upper surface of the wings moves forward around the leading edge of the wings This low pressure creates a differential pressure in the sta...

Page 152: ... associated with that transmitter to provide speaker audio For example if the number one transmitter is selected the audio amplifier in the number one NAV COM is also selected and is used for ALL speaker audio In the event the audio amplifier in use fails as evidenced by loss of all speaker audio selecting an alternate transmitter will reestablish speaker audiousing the alternate transmitter audio...

Page 153: ...111 1 1 l 110 1 11 J TRANSMITTER SELECTOR SWITCH TRANSMITTER SELECTOR SWITCH 7 36 ACCESS XMTR 1 _ ___ ____SPEAKER 1 I ANN LTS 0 COM AUTO AUDIO SELECTOR AUDIO SELECTOR SWITCHES SWITCH DME ANNUNCIATOR LIGHTS BRIGHTNESS AND TEST SWITCH USED WITH THREE TRANSMITTERS SPEAKER 3 AUTO NAV COM I 2 3 AUTOMATIC AUDIO SELECTOR AUDIO SELECTOR SWITCHES SWITCH Figure 7 10 Audio Control Panel ADF 2 OFF I AUDIO SEL...

Page 154: ... the other transmitter auto matically switches the other communications receiver audio to the speaker This automatic audio switching feature may alsobe utilized when listening on a headset by placing the COM AUTO switch in the down PHONE position If automatic audio selection is not desired the COM AUTO selector switch should be placed in the center OFF position COM BOTH AUDIO SELECTOR SWITCH The a...

Page 155: ...r OFF position NOTE If the NAV COM audio selector switch corresponding to the selected transmitter is in the PHONE position with the AUTO selector switch in the SPEAKER position all audio selector switches placed in the PHONE position will automatically be connected to both the airplane speaker and any headsets in use ANNUNCIATOR LIGHTS BRIGHTNESS AND TEST SWITCH The audio control panel used with ...

Page 156: ...tches Adjust ment of speaker and headset sidetone volume can only beaccomplished by adjusting the sidetone potentiometers located inside the audio control panel NOTE Sidetone is not available on HF Transceivers TypesPT10 A and ASB 125 when installed MICROPHONE HEADSET INSTALLATIONS Three types of microphone headset installations are offered The standard system provided with avionics equipment incl...

Page 157: ...es of the wings rudder elevator propeller tips and radio antennas can result in loss of usable radio signals on all communications and navigationradioequipment Usually the ADF is first to be affected and VHF communication equipment is the lastto be affected Installation of static dischargers reduces interference from precipita tion static but it is possible to encounter severe precipitation static...

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Page 159: ... Progressive Care Cessna Customer Care Program Pilot Conducted Preventive Maintenance Alterations Or Repairs Ground Handling Towing Parking Tie Down Jacking Leveling Flyable Storage Servicing Engine Oil Fuel Landing Gear Cleaning And Care Windshield Windows Painted Surfaces Propeller Care Engine Care Interior Care 1 July 1979 Page 8 3 8 3 8 3 8 3 8 4 8 5 8 5 8 6 8 6 8 7 8 7 8 7 8 7 8 8 8 8 8 8 8 9...

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Page 161: ... and Type Certificate Number TC can be found on the Identification Plate located on the lower part of the left forward doorpost Located adjacent to the Identification Plate is a Finish and Trim Plate which contains a code describing the interior color scheme and exterior paint combination of the airplane The code may be used in conjunction with an applicable Parts Catalog if finish andtrim informa...

Page 162: ...items many of which he keeps on hand He will be happy to place an order for any item which is not in stock NOTE A Pilot s Operating Handbook and FAA Approved Air plane Flight Manual which is lost or destroyed may be replaced by contacting your Cessna Dealer or writing directly to the Customer Services Department Cessna Aircraft Company Wichita Kansas An affidavit con taining the owner s name airpl...

Page 163: ...hat these items plus the Pilot s Checklists Power Computer Customer Ca re Program book and Customer Care Card be carried in the airplane at all times AIRPLANE INSPECTION PERIODS FAA REQUIRED INSPECTIONS As required by Federal Aviation Regulations all civil aircraft of U S registry must undergo a complete inspection annual eachtwelvecalend ar months In addition to the required ANNUAL inspection air...

Page 164: ...ly worked out by the factory and are followed by the Cessna Dealer Organization Your Cessna Dealer can assistyou in selecting the inspection program mostsuitable for your type of aircraft and operation The complete familiarity of Cessna Dealers with Cessna equipment and factory approved procedures pro vides the highest level of serv ce possible at lower cost to Cessna owners Regardless of the insp...

Page 165: ...ld refer to the regulations of the country of certifica tion for information on preventive maintenance that may be performed by pilots A Service Manual should be obtained prior to performing any preven tive maintenance to ensure that proper procedures are followed Your Cessna Dealer should be contacted for further information or for required maintenance which must be accomplished by appropriately ...

Page 166: ...rope or chain to a ramp tie down 4 Install a pitot tube cover JACKING When a requirement exists to jack the entire airplane off theground or when wing jack points are used in the jacking operation refer to the Service Manual for specific procedures and equipment required Individual main gear may be jacked by using the jack pad which is incorporated in the main landing gear strut step bracket When ...

Page 167: ...ed in flyable storage status Every seventh day during these periods the propeller should be rotated by hand through five revolutions This action limbers the oil and prevents any accumulation of corrosion on engine cylinder walls I WARNING I For maximum safety check that the ignition switch is OFF the throttle is closed the mixture control isintheidle cut off position and the airplane issecured bef...

Page 168: ... various flight operations your local Government Aviation Agency may require additional service inspections ortests For these regulatory requirements owners should check with local aviation officials where the airplane is being operated For quick and ready reference quantities materials and specifica tions for frequently used service items are as follows ENGINE Oil GRADE AND VISCOSITY FOR TEMPERAT...

Page 169: ... oil at least every 6 months even though less than the recommended hours have accumulated Reduce intervals for pro longed operation in dusty areas cold climates or when short flights and long idle periods result in sludging conditions NOTE During the first 25 hour oil and filter change a general inspection of the overall engine compartmentis required Items which are not normally checked during a p...

Page 170: ...sation in the tanks FUEL ADDITIVES Strict adherence to recommended preflight draining instructions as called for in Section 4 will eliminate any free water accumulations from the tank sumps While small amounts of water may still remainin solution in the gasoline it will normally be consumed and go unno ticed in the operation of the engine One exception to this can be encountered when operating und...

Page 171: ...uel stream issuing from the fueling nozzle 2 An alternate method that may be used is to premix the complete alcohol dosage with some fuel in a separate clean container approximately 2 3 gallon capacity and then transferring this mixture to the tank prior to the fuel operation Any high quality isopropyl alcohol may be used such as Anti Icing Fluid MIL F 5566 or Isopropyl Alcohol Federal Specificati...

Page 172: ... will result in a water buildup in the fuel which leeches out the additive An indication of this is when an excessive amount of water accumulates in the fuel tank sumps The concentration can be checked using a differential refractometer It is imperative that the technical manual forthe differential refractometer be followed explicitly when checking the additive concentration LANDING GEAR NOSE WHEE...

Page 173: ...A thin even coat of wax polished out by hand with clean soft flannel cloths will fill in minor scratches and help prevent further scratching Do not use a canvas cover on the windshield unless freezing rain or sleet is anticipated since the cover may scratch the plastic surface PAINTED SURFACES The painted exterior surfaces of your new Cessna have a durable long lasting finish and under normal cond...

Page 174: ...rvice Small nicks on the propeller particularly near the tips and on the leading edges should be dressedout as soonas possible since these nicks produce stress concentrations and ifignored mayresult in cracks Never use an alkaline cleaner on the blades remove grease and dirt with Stoddard solvent ENGINE CARE The engine may be cleaned with Stoddard solvent or equivalent then dried thoroughly CAUTIO...

Page 175: ... the manufacturer s instructions To minimize wetting the fabric keep the foam as dry as possible and remove it with a vacuum cleaner If your airplane is equipped with leather seating cleaning of the seats is accomplished using a soft cloth or sponge dipped inmildsoap suds The soap suds used sparingly will remove traces of dirt and grease The soap should be removed with a clean damp cloth The plast...

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Page 177: ...matic Autopilot Type AF 295B 15 300 ADF Type R 546E 16 300 Nav Com Type RT 385A 17 300 Transponder Type RT 359A And Optional Altitude Encoder Blind 18 300 Transponder Type RT 359A And Optional Encoding Altimeter Type EA 401A 19 300A Navomatic Autopilot Type AF 395A 20 400 Glide Slope Type R 443B 21 400 Marker Beacon Type R 402A 22 400 Transponder Type RT 459A And Optional Altitude Encoder Blind 23...

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Page 179: ...button type switches directly below the display control all time keeping functions These control functions are summarized in figures 2 and 3 The digital display features an internal light back light to ensure good visibility under low cabin lighting conditions or at night The intensity of the back light is controlled by the RADIO LT rheostat In addition the display incorporates a test function see...

Page 180: ...endar date appears numerically on the display with month ofyear tothe left of the colon and day of the month shown to the right of the colon The display automatically returns to the clock mode after approximately 1 5 seconds However if the RH button is pressed continuously longer than approximately two seconds the display will return from the date to the clock mode with the activity indicator colo...

Page 181: ...and stops timer timer starts from any previously accumu lated total Figure 3 Timer Mode selected by changing the position of an internal slide switch accessible through a smallholeonthebottomof the instrument case Notice that in the 24 hour format the clock mode indicator does not appear SETTING CORRECT DATE AND TIME The correct date and time are set while in the clock mode using the LH and RH pus...

Page 182: ...e LH button again and the clock returns to the normal time keeping mode without altering the minutes timing TIMER OPERATION The completely independent 24 hour elapsed timer see figure 3 is operated as follows press the center MODE push button until the timer mode indicator appears Reset the display to zero by pressing the LH button Begin timing an event by pressing the RH button The timer will beg...

Page 183: ...ch should be turned off If maintenance is required on the avionics equipment it is advisable to utilize a battery cart external power source to prevent damage to the avionics equipment by transient voltage Do not crank or start the engine with the avionics power switch turned on The battery and external power circuits have been designed to com pletely eliminate the need to jumper acrossthe battery...

Page 184: ...re is no change to the airplane emergency procedures when the ground service plug receptacle is installed SECTION 4 NORMAL PROCEDURES Just before connecting an external power source generator type or battery cart the avionics power switch should be turned off and the master switch on 2 I WARNING I When turning on the master switch using an external power source or pulling the propeller through by ...

Page 185: ...n the left switch and control panel and a5 amppush to reset circuit breaker also located on the left switch and control panel SECTION 2 LIMITATIONS Strobe lights must be turned off when taxiing in the vicinity of other airplanes or during night flight through clouds fog or haze SECTION 3 EMERGENCY PROCEDURES There is no change to the airplane emergencyprocedureswhen strobe lights are installed SEC...

Page 186: ...7 STROBE LIGHT SYSTEM MODEL 172N PILOT S OPERATING HANDBOOK SUPPLEMENT SECTION 5 PERFORMANCE The installation of strobe lights will result in a minor reduction in cruise performance 2 1 July 1979 ...

Page 187: ...at 10 000 feet The ELT supplied in domestic aircraft transmits on both distress frequen cies simultaneously at 75 mw rated power output for 50 continuous hours in the temperature range of 4 F to 131 F 20 C to 55 C The ELT unit in export aircraft transmits on 121 5 MHz at 25 mw rated power output for 50 continuous hours in the temperature range of 4 F to 131 F 20 C to 55 C The ELT is readily identi...

Page 188: ...R Removable for access to battery pack 3 ANTENNA RECEPTACLE Connects to antenna mounted on top of tailcone Figure 1 ELT Control Panel SECTION 3 EMERGENCY PROCEDURES Immediately after a forced landing where emergency assistance is required the ELT should be utilized as follows 2 1 ENSURE ELT ACTIVATION Turn a radio transceiver ON and select 121 5 MHz If the ELT can be heard transmitting it was acti...

Page 189: ...ON 4 NORMAL PROCEDURES As long as the function selector switch remains in the AUTO position the ELT automatically activates following an impact of 5g or more over a short period of time Following a lightning strike or an exceptionally hard landing the ELT may activate although no emergency exists To check your ELT for inadvertent activation select 121 5 MHz on your radio transceiver and listen for...

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