Cessna 1978 Skyhawk 172N Operating Handbook Download

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Summary of Contents for 1978 Skyhawk 172N

Page 1: ... PILOT S OPERATING HANDBOOK lEssna 1977 Skyhawk CESSNA MODEL 172N b I ...

Page 2: ...ns Us le F el Time 4 HRS RATE OF CLIMB AT SEA LEVEL OFPM SERVTCECEXLII TG 14 200 FT TAKEOFF PERFORMANCE Grqrnd Roll 80b FT Totd Distance Over 50 Ft Obstacle 1440 FT IA fDb 3 PENFORMANCE Grourd Roll 520 FT Total Distance Over 50 Ft Obstacle 1250 FT STALL SPEED CAS PleFs Up Power Off 50 KNOTS fhps Dwn Power Off 44 KNOTS IATTMUM WEXGHT 23OO LBS STAh DARDEMPTY WEIGHT Sk3rha k 1379 LBS Sk vhawkII 1403 ...

Page 3: ...OT S OPERATING HANDBOOK SKYHAWK 1977 MODEL 172N Serial No Regis tration No THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY CAR PART 3 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA ...

Page 4: ...ailable at Cessna Dealers worldwide Specificbenefits and provisions of warranty plusother importantbenefits for you arecontained in your Customer CareProgram book sup pliedwith your airplane Warrantyservice is available to you at authorized Gessna Dealers throughoutthe world uponpresentation of your Customer CareCardwhich establishes your eligibility underthe warranty FACTORYTRAINEDPERSONNEL to pr...

Page 5: ... publishedby Cessna Aircraft Company These are distributed to CessnaDealersand to those who subscribe through the Owner Follow Up System lf you are not receiving subscriptionservice you will want to keep in touch with your CessnaDealerfor information concerning the changestatusof the handbook Subsequentchangeswill be made in the form of stickers Theseshould be examined and attachedto the appropria...

Page 6: ...ne Weights Cabin and Entrv Dimensions BaggageSpaceand 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 L 7 Airplane Performance and Flight Planning Terminology l 7 Weight and Balance Terminology l 7 Page l 2 1 3 1 3 1 3 1 3 1 3 l 4 1 5 1 5 1 5 1 1 ...

Page 7: ...erghtshownwrth nose geardepressed all trres and nose strut properly Inflated and flashrng beaconInstalled 3 Wheelbaselengthts 65 4 Propellergroundclearance s 11 3 4 5 Wingareats 174 square feet 6 Minrmumturntngradius ptvot polnt to outboardwtng ttp rs 27 5lz PIVOT POINT l Figure 1 1 1 2 Three View ...

Page 8: ... ENGINE Number of Engines 1 Engine Manufacturer Avco Lycoming Engine Model Number O 320 HZAD Engine Type Normally aspirated direct drive air cooled horizontally opposed carburetor equipped four cylinder engine with 320 cu in displacement Horsepower Rating and Engine Speed 160 rated BHP at 27O0RPM PROPETLER Propeller Manufacturer McCauley Accessory Division Propeller Model Number 1C160 DTM7557 Numb...

Page 9: ... hours has accumulated or oil consumption has stabilized NOTE The airplane was delivered from the factory with a corro sion preventive aircraft engine oil This oil should be drained after the first 25 hours of operation MIL L 22851 Ashless Dispersant Oil This oil must be used after first 50 hours or oil consumption has stabifZ6 Recommended Viscosity For Temperature Range MIL L 6082 Aviation Grade ...

Page 10: ...inedweight capacity for baggageareas 1 and 2 is 120 lbs Weight in BaggageCompartment Utility Category In this category baggage compartment and rear seat must not be occupied STANDAR D AIRPTANE WEIGHTS Standard Empty Weight Skyhawk Skyhawk II 897 lbs 1379lbs 1403lbs 621lbs 597 lbs CABIN AND ENTRY DIfrlENSIONS Detailed dimensions of the cabin interior and entry door openingsare illustrated in Sectio...

Page 11: ...ng flaps in a prescribed extendedposition Ma imumStruchrral Cruising Speedis the speedthat should then only with caution Never Exce gdSpeedis the speed limit that may not be ex ceededat any time Stalling Speedor tlgminimum steady lJight peed at which the airplane is controllable Stalling Speedor the nginimum steady flight speed at which the airplane is controllable in the landing configuration at ...

Page 12: ...cross strated e control of the airplane Crosswind during takeoff and landing was acfually demonstrated during Velocitv certification tests The value shown in not considered to be Iimiting Usable Fuel Unusable Fbel GPH NMPG Usable F rel is the fuel available for flight planning Unusable Fuel is the quantity of fuel that can not be safely GaA in Titrfri Gallons Per Hour is the amount of fuel in gall...

Page 13: ... total weight C G C nt of G ityli are the extreme center of gravity Limits airplane must be operated at a given weight StandardSt istheweightofastandardairpIane Empty fuII operating fluids and full engine Weight oil Basic Empty Basic Empty Weight is the standard empty weight plus the Weight weight of optional equipment Useful Useful Load is the difference betweentakeoff weight and the Load Effipit...

Page 14: ...tnrment Markings Weight Limits Normal Cbtegory Utility Ch tegory Center of Gravity Limits Normal Cbtegory Utility Category Page 2 3 2 4 2 5 2 5 2 6 2 6 2 6 z 7 2 7 2 7 2 7 2 7 2 7 2 7 2 8 2 8 2 8 2 9 2 9 2 LO Maneuver Limits Normal Ca tegory Utitity Category Flight Load Factor Limits Normal Category Utility Category Kinds of Operation Limits FueI Limitations Placards 2 t 2 2 blank ...

Page 15: ...iated with optional systems or equipment are included in Section 9 NOTE The airspeeds listed in the Airspeed Limitations chart 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 static source is being used ample margins should be observed to allow for the airspeed calibration varia...

Page 16: ...xceed this speed in any operation Vruo MaximumStructural Cruising Speed 126 128 Do not exceed this speed exceptin smoothair and thenonly with caution V4 Maneuvering Speed 2300Pounds 1950Pounds 1600Pounds 96 88 80 97 89 80 Do not make full or abrupt control movements above this speed Vre MaximumFlapExtended Speed 86 85 Do not exceed this speed with flaps down Maximum WindowOpen Speed 158 160 Do not...

Page 17: ...ximum Oil Temperature 118oC 245 F Oil Pressure Minimum 25 psi Maximum 100 psi Propeller Manufacturer McCauley Accessory Di vision Propeller Model Number 1C160 DTM7557 Propeller Diameter Maximum 75 inches Minimum 74 inches MARKING KIASVALUE OR RANGE SIGNIFICANCE WhiteArc 41 85 Full FlapOperating Range Lower lirnit is maximum weightVgo in landing configuration Upperlimit is maximumspeed permissible ...

Page 18: ...ressure Carburetor Air Temperature 25 psi 2200 27OO RPM 10oo 2450F 60 90 psi 150 to 5oC 27OO RPM 2450F 100psi Figure 2 3 Power Plant Instrument Markings WEIGHT LIMITS NORfrlAI CATEGORY Maximum Takeoff Weight 2300 lbs Ma imum Landing Weight 2300 lbs Maximum Weight in BaggageCompartment BaggageArea 1 or passengeron child s seat Station82 to 108 120 lbs Seenote below BaggageArea 2 Station 108 to 142 ...

Page 19: ...ches aft of datum at 2000lbs Aft 40 5 inches aft of datum at all weights Reference Datum Lower portion of front face of firewall MANEUVER LIMITS NOR IUAt CATEGOR Y This airplane is certificated in both the normal and utility catego ry The normal category is applicable to aircraft intended for non aerobatic operations These include any maneuvers incidental to nor mal flying stalls except whip stall...

Page 20: ...and will build up speedquickly with the nose down Proper speed control is an essential requirement for execution of any maneuver and care should always be exercised to avoid excessive speedwhich in turn can impose excessive loads In the execution of all maneuvers avoid abrupt use of controls Intentional spins with flaps ex tendedare prohibited FLIGHT LOAD FACTOR LIMITS NOR Y At CATEGO RY Flight Lo...

Page 21: ...ns is prohibited FUELTIMITATIONS 2 Standard Tanks 2I 5 U S gallons each Total FueI 43 U S gallons Usable Fuel all flight conditions 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 a11flight conditions 50 U S gallons Unusable Fuel 4 U S gallons NOTE To ensure maximum fuel capacity when refueling place the fuel selector valve in...

Page 22: ...wn 3 0 3 0 Normal Category No acrobatic maneuvers including spins approved Utility Category Baggagecompartment and rear seat must not be occupied NO ACROBATIC MANEWERS APPROVED EXCEPT THOSE LISTED BELOW Maneuver Recm Entry Speed Maneuver Recm Entry Speed G6iid es rc Spins ffi Lazy Eights 105 knots Stalls except SteepTurns 95 knots whip stalls Slow Deceleration Altitude loss in stall recovery 180 f...

Page 23: ...4 Near fuel tank filler cap standard tanks FUEL 1OO 130MIN GRADE AVIATION GASOLINE CAP 21 5U S GAL Near fuel tank filler cap long range tanks FUEL 1OO 130MIN GRADE AVIATION GASOLINE CAP 27 U S GAL BOTH 40 GAL LEFT 20 GAL RIGHT 20 GAL OFF ALL FLIGHT ATTITUDES LEVEL FLIGHT ONLY LEVEL FLIGHT ONLY BOTH 50 GAL LEFT 25 GAL RIGHT 25 GAL OFF ALL FLIGHT ATTITUDES LEVEL FLIGHT ONLY LEVEL FLIGHT ONLY 2 tL ...

Page 24: ...compartment 120 POUNDSIVIAXIMUM BAGGAGE AND OR ATIXIIJARY PASSENGER FORWARD OF BAGC AGEDOOR I ATCH 50 POUNDSMAXIMUM BAGGAGEAFT OF BAGGAGEDOOR I ATCH MAXIMUM 120 POUNDSCOMBINED FOR ADDITIONAL LOADING INSTRUCTIONS SEEWEIGHT AND BAI ANCE DATA 7 On the instrument panel near over voltage light HIGH VOLTAGE 2 t2 ...

Page 25: ... 4 Emergency Landing Without Engine Power 3 4 Precautionary Landing With Ergrne Power 3 4 Ditching 3 5 Fires 3 5 During Start On Ground 3 5 Engine Fire In Flight 3 6 Electrical Fire In Flight 3 6 Cabin Fire Wing Fire Icing Inadvertent Icing Encounter Static Source Blockage Erroneous Instrument Reading Suspected Landing With A Flat Main Tire Electrical Power SupplySystem Malfunctions 3 8 Over Volta...

Page 26: ...y Descent Through Clouds Recovery From A Spira1Dive Flight In Icing Conditions Static Source Bloeked 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 Page 3 10 3 10 3 11 3 11 3 11 3 L2 3 12 3 t2 3 13 3 14 3 14 3 14 3 14 3 14 3 15 3 1...

Page 27: ...d as necessary to correct the problem Emergency procedures associated with the ELT and other optional systems can be found in section g AIRSPEEDS FOR EMERGENCY OPERATION Engine Failure After Takeoff Wing Flaps Up Wing Flaps Down Maneuvering Speed 2300 Lbs 1950Lbs 1600Lbs Maximum Glide 2300 Lbs Precautionary Landing With Engine Power Landing Without Engine Power Wing Flaps Up Wing Flaps Down OPERAT...

Page 28: ...IAS flaps DOWN Mixture IDLE CUT OFF F rel Selector Valve OFF Ignition Switch OFF Wing Flaps AS REQUIRED 40 recommended Master Switch OFF Doors UNI ATCH PRIOR TO TOUCHDOIWN Touchdorvn SLIGHTLY TAIL LOW Brakes APPLY HEAVILY PRECAUIIONARY LANDING WITH ENGINE POWER 1 Wing Ftaps 20o Q AirsPeed 60 KIAS 3 SelectedField FLY OVER noting terrain and obstructions then retract flaps upon reaching a safe altit...

Page 29: ... 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 STARI ON GROUND 1 Cranking CONTINUE to get a start which would suck the flames and accumulated fuel through the carburetor and into the engine If engine star...

Page 30: ... as described in Emergency Land ing Without Engine Power ETECIRICATFIREIN FLIGHI 1 Master Switch OFF 2 All Other Switches except ignition switch OFF 3 Yents Cabin Air Heat CLOSED 4 Fire Extinguisher ACTWATE if available WARNING After discharging an extinguisher within a closed cabin ventilate the cabin If fire appears out and electrical power is necessary for continuance of flight 5 Master Switch ...

Page 31: ... to obtain murimum windshield defroster airflovv Adjust cabin air control to get ma imumdefroster heat and airflow 4 Openthe throttle to increase engine speedand minimize ice build up on propeller blades 5 Watch for signs of carburetor air filter ice and apply carburetor heat as required An unexplained loss in engine speed could be caused by carburetor ice or air intake filter ice Lean the mixture...

Page 32: ...menl Reoding Suspected 1 Alternate Static SourceValve PULL ON 2 Airspeed Consutt appropriate calibration tables in Section 5 LANDING WITH A FLAT MAIN TIRE 1 Approach NORI AL 2 Touchdown GOOD TIRE FIRST hold airplane off flat tire as long as possible ELECTR ICAL POWERSUPPLY SYSTEM MALFUNCTIONS OVER VOtIAGE TIGHT IttU N INATES 1 Master Switch OFF both sides 2 Master Switch ON 3 Over Voltage Light OF...

Page 33: ...ses the landing shonld be planned straight ahead with only small changes in direction to avoid obstmctions Altitude and airspeed are sel dom sufficient to execute a 180 gliding furn necessary to return to the runway The checklist procedures assume that adequatetime exists to secure the fuel and ignition systems prior to touchdown After an engine failure in flight the best glide speed as shown in F...

Page 34: ...surface LANDING WITHOUT ELEVATOR CONTR OL Trim for horizontal flight with an airspeed of approximately 60 KIAS and flaps set to 20 by using throttle and elevator trim control Then do not changethe elevatoi trim control settingl control the glide angle by adjusting power exclusively At flareout the nose down moment resulting from power reduction is an adverse factor and the airplane may hit on the ...

Page 35: ...ight by leveling the miniature air pIane 3 Check accuracy of the turn by observing the compass heading which should be the reciprocal of the original heading 4 If necessary adjust heading primarily with skidding motions rather than rolling motions so that the compass will read more accurately 5 Maintain altitude and airspeed by cautious application of eleva tor control Avoid overcontrolling by kee...

Page 36: ...e elevator trim control to maintain an 80 KIAS gtide 5 Keep hands off the control wheel using rudder control to hold a straight heading Adjust rudder trim if installed to relieve unbal anced rudder force 6 Apply carburetor heat 7 Clear engine occasionally but avoid using enough power to disturb the trimmed glide 8 Upon breaking out of clouds resume normal cruising flight FLIGHTIN ICING CONDITIONS ...

Page 37: ... the following recovery procedure should be used 1 RETARD THROTTLE TO IDLE POSITION 2 PLACE AILERONSIN NEUTRAL PGTTION 3 APPLY AND HOLD FULL RUDDER OPPOSITE TO THE DIREC TION OF ROTATI6 4 JUST AFTER THE RUDDERREACHESTHE STOP MOVE THE CONTROL WEEEL BRISKLY FORWARD FAR ENOUGH TO BREAK THE STALL FuU Effii ator may be required at aft center of gravity loadings to assure optimum recoveries 5 HOLD THESE...

Page 38: ... several min utes determine if a richer mixh rre setting will produce smoother opera tion 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 TVI AG N ETO VT A IFU NCTION A sudden engine roughness or misfiring is usually evidence of mag neto problems Switching from BOTH to either L ...

Page 39: ... However after thirty minutes of cnrising flight the ammeter should be indicating Iess than two needle widths of charging current If the charging rate were to remain above this value on a long flight the battery would overheat and evaporate the electrolyte at an excessive rate Electronic components in the electrical system could be adversely affected by higher than normal voltage if a faulty volta...

Page 40: ...ternator is not supplying power to the system and should be shut down since the alternator field circuit may be placing an unnecessary load on the system All nonessential equipment should be furned off and the flight terminated as soon as practical 3 16 ...

Page 41: ...dge 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 AMPLIFIED PROCEDURES Starting Engine 4 LL SECTION 4 NORMAL PROCEDURES CESSNA MODEL 172N Page 4 3 4 3 4 5 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 ...

Page 42: ...eoff 4 18 Power Check 4 13 Wing Flap Settings 4 L4 Short Field Takeoff 4 L4 Crosswind Takeoff 4 15 Enroute Ctimb 4 L5 Cruise 4 I5 Stalls 4 LT Spins 4 tz Landing 4 19 Normal Landing 4 19 Short Field Landing 4 2O Crosswind Landing 4 2O Balked Landing 4 2O CoId Weather Operation 4 20 Starting 4 2O Flight Operations 4 22 Hot Weather Operation 4 23 Noise Abatement 4 23 4 2 ...

Page 43: ...ropriate to the particular weight must be used Takeoff Flaps Up Normal Climb Out 70 80KIAS Short Fietd Takeoff Flaps Up Speed at 50 Feet 59 KIAS Enroute Climb Flaps Up Normal Sea Level 75 85 KIAS 70 80KIAS Normal 10 000Feet Best Rate of Climb Sea Level Best R ateof Climb 10 000Feet Best Angle of Climb Sea Level Best Angle of Climb 10 000Feet Landing Approach Normal Approach Flaps Up 60 70KIAS Norm...

Page 44: ... In cold weather remove even small accumulations of frost ice or snow from wing tail and control surfaces Also make sure that eontrol surfaces contain no internal accumulations of ice or de ris If a night flight is planned check operation of all lights and make sure a flashlight is avaiUfte 4 4 Figure 4 1 Preflight Inspection ...

Page 45: ... Tire CHECK for proper inflation 3 Before first ffight 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 4 FueI Quantity CHECK VISUALLY for desired level 5 Fuel Filler Cap SECURE nosr 1 Engine Oil Level CHECK Do not operate with less than four quarts F1II to six quarts for ext...

Page 46: ... drain valve to check for water sediment and proper fuel grade 3 Fuel Quantity CHECK VISUALLY for desired level 4 Fuel FiIIer Cap SECURE Q tEFr wtNG Leodins Edge 1 Pitot Tube Cover REMOVE and check openingfor stoppage 2 Fuel Tank Vent Opening CHECK for stoppage 3 Stall Warning Opening CHECK for stoppage To check the sys tem place a clean handkerchief over the vent opening and apply zuc tion a soun...

Page 47: ... 6 Mixture RICH below 3000 feet 7 Elevator Trim and Rudder Trim if installed TAKEOFF 8 Throttle 1700RPM a Magnetos CHECK RPM drop should not exceed 125 RPM on either magneto or 50 RPM differential between magnetos b Carburetor Heat CHECK for RPM drop c Engine Instruments and Ammeter CHECK d Suction Gage CHECK 9 Radios SET 10 Autopilot if installed OFF 11 Flashing Beacon Navigation Lights and or St...

Page 48: ...5KIAS NCITE If a murimum performance climb is necess yr use speeds shown in the Rate Of Climb chart in Section 5 2 Throttle FULL OPEN 3 Mixture RICH above 3000 feet LEAN to obtain maximum RPM cRursE 1 Power ZOO 2200 RPM no more than SVois recommended 2 Elevator and Rudder Trim if installed ADJUST 3 Mixture LEAN DESCENT 1 Mixture ADJUST for smooth operation full rich for idle pow er 2 Power AS DESI...

Page 49: ...NDING 1 Airspeed 60 70KIAS flaps UP 2 Wing Flaps FULL DOWN 40 3 Airspeed 60 KIAS until flare 4 Power REDUCE to idle after clearing obstacle 5 Touchdown MAIN WHEELS FIRST 6 Brakes APPLY HEAVILY 7 tittU Flaps RETRACT _ BATKED TANDING 1 Throttle FULL OPEN 2 Carburetor Heat COLD 3 Wing Flaps 20o immediately 4 Climb Speed 55 KIAS 5 Wing Flaps 10o until obstacles are cleared RETRACT after reaching a saf...

Page 50: ...SECTION 4 NORMAL PROCEDIIRES 3 Mixture IDLE CUT OFF prlled tuIl out 4 Ignition Switch OFF 5 Master Switch OFF 6 Control Lock INSTALL CESSNA MODEL 172N 4 10 ...

Page 51: ...iming If the engine is underprimed most likely in cold weather with a cold engine i 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 show pressure within 30 seconds in the zummertime and about twice that long in very cold weather stop engine and investi...

Page 52: ...arp braking when the airplane is in thip attitude Use the steerable nose wheel and rudder to maintain direction wrNDDmECrroN USE UP AILERON ON LH WING AND NEUTRAL ELEVATOR USE UP AILERON ON RH WING AND NEUTRAL ELEVATOR USE DOWN AILERON ON LH WING AND DOWN ELEVATOR USE DOWN AILERON ON RH WING AIVD DOWN ELEVATOR 4 12 Figure 4 2 Taxiing Diagrarn ...

Page 53: ...n RPM drop should not exceed 125 RPM on either magneto or show greater than 50 RPM differential betweenmagnetos If there is a doubt concerning opera tion of the ignition system RPM checks at higher engine speedswill usu ally 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 th...

Page 54: ... Prior to takeoff from fields above 3000 feet elevation the mixture shotrld be leaned to give mardmum RPM in a full throttle static runup After full throttle is applied adjust the throttle friction lock clock wise 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 throt...

Page 55: ... the drift an gle immediately after takeoff The airplane is accelerated to a speed slightty higher than normal then pulled off abruptly to prevent possible settling back to the runway while drifting When clear of the ground make a coordinated furn into the wind to correct for drift ENROUTE CLI MB Normal climbs are performed with flaps up and full throttle and at speeds 5 to 10 knots higher than be...

Page 56: ...most favorable wind conditions and the use of low power set tings are significant factors that should be considered on every trip to reduce fuel consumption To achieve the recommended lean mixture fuel consumption figures shown in Section 5 the mixture should be leaned until engine RPM peaks and drops 25 50RPM At lower powers it may be necessary to enrichen the mixture slightly to obtain smooth op...

Page 57: ... aft c g lnsitions are presented in Section b SPINS Intentional spins are approvej i1 this airplane within certain restrict iri fft spinswith baggase loadines o J rpiedrear JG arenot However before attempting to perfor_m spins several items should be be caretully considered b a qafe fiight No spins shourd be at_ tempted withcmt first ta ing received auar instruction both in spin entries and spin r...

Page 58: ...erons in the direction of the desired spin and the use of power at the entry will assure more consistent and positive entries to the spin As the airplane begins to spin reduce the power to idle and return the ailerons to neutral Both elevator and rudder controls should be held full with the spin until the spin recovery is initiated An inadvertent relur ation of either of these controls could resul...

Page 59: ...Intentional spins with flaps extended are prohibited since the high speeds which may occur during recovery are potentially damaging to the flap wing stmcture LANDING NOR UAt TANDING Normal landing approaches can be made with power on or power off with any flap setting desired Surface winds and air turbulence are usual ly the primary factors in determining the most comfortable approach speeds Steep...

Page 60: ...th full rudder deflection some elevator oscillation may be felt at normal approach speeds However this does not affect control of the airplane Although the crab or combination method of drift correction may be used the wing Iow methodgives the best control After touch down hold a straight course with the steerable nose wheel and occasional braking if necessary The ma imumallowable crosswind veloci...

Page 61: ...ing an external power source the position of the mas ter switch is important Refer to Section 7 under Ground Seryice plug Receptaclefor operating details Cold weather starting procedures are as foll ows With Preheat tl with ignition switch oFF and throtile closed prime the engine four to eight strokes as the propeller is being turned over by hind NOTE use heavy strokes of primer for best atomizati...

Page 62: ...s attempted Pumping the throttle may cause raw fuel to accumulate in the intake air duct creating a fire hazard in the event of a bacldire If this occurs maintain a cranking action to suck flames into the engine An outside attendant with a fire extinguisher is advised for cold starts without pre heat During cold weather operations no indication will be apparent on the oil temperafure gage prior to...

Page 63: ...al and park areas and other noise sensitive areas should make every effort to fly not less tlwn 2 000 feet above the surface weather permitting even though flight at a lower level may be consistent with the provisions of government regulations 2 During deprfure from or approach to an airport climb after taleoff and descent for landing should be made so as to avoid pro longedflight at low altihde n...

Page 64: ...re 5 6 Figure 5 7 Figure 5 8 Figure 5 9 Airspeed Calibration Normal Static Source Airspeed Calibration Alternate Static Source Temperature Conversion Chart Stall Speeds Takeoff Distance Takeoff Distance 2300Lbs 2100Lbs and 1900Lbs Rate of Climb Range Profile 40 Gallons FueI Range Profile 50 Gallons Fuel Endurance Profile 40 Gallons Fuel Endurance Profile 50 Gallons Fuel Figure 5 10 Landing Distanc...

Page 65: ...ropeller condition and air turbulence may account for varia tions of LOVo or more in range and endurance Therefore it is impor tant to utilize aII available information to estimate the fuel required for the particular flight USEOF PERFORMANCE CHARTS Performance data is presented in tabular or graphical form to illus trate the effect of different variables Sufficiently detailed information is provi...

Page 66: ...keoff distance informa tion presented for a weight of 2300 pounds pressure altitude of 2000 feet and a temperature of 30oC should be used and results in the following Ground roll 1075 Feet Total distance to clear a 50 foot obstacle 1915 Feet These distances are well within the available takeoff field length However a correction for the effect of wind may be made based on Note 3 of the takeoff char...

Page 67: ...500 feet yields a predicted range of 523 nautical miles with no wind The endu ranee profile chart figure 5 9 shows a corresponding 4 2 hours The range figure of 523 nautical miles is corrected to account for the expected 10 knot headwind at 5500 feet This indicates that the trip can be made without a fuel stop using ap proximately 65Vo power The cruise performance chart figure 5 7 is entered at G0...

Page 68: ...e due to the lower rate of climb In this case assuming a temperature 16oC above standard the correction would be 9 9 rovo l6vo Increase 100c With this factor included the fuel estimate would be calculated as fol Iows Fuel to climb standard temperature 1 3 Increase due to non standard temperature 1 3 tGVo O 2 Corrected fuel to climb 1 5 Gallons Using a similar procedure for the distance to climb re...

Page 69: ...and the corres ponding fuel required to complete the trip with ample reserve LANDING A procedure similar to takeoff should be used for estimating the landing distance at the destination airport Figure 5 10 presents land ing distance information for the short field technique The distances corresponding to 2000 feet and 30oC are as follows Ground roll 590 Feet Total distance to clear a 5O footobstac...

Page 70: ...AAALSTATICSOURCE Figure 5 1 Airspeed Calibration Sheet1 of 2 FLAPS UP KIAS KCAS 40 50 60 70 80 90 100 110 120 130 140 49 55 62 70 80 89 99 108 118 128 138 FLAPS1OO KIAS KCAS 40 50 60 70 80 85 49 55 62 71 80 85 FLAPS 4OO KIAS KCAS 40 50 60 70 80 85 475462718186 5 8 ...

Page 71: ...ENAND WINDOWS CLOSED FLAPSUP NORMALKIAS ALTERNATEKIAS 40 50 60 70 80 90 100 110 120 130 140 36 48 59 70 80 89 99 108 118 128 139 FLAPS1OO NORMALKIAS ALTERNATEKIAS 40 50 60 70 80 85 38 49 59 69 79 84 FLAPS 4OO NORMALKIAS ALTERNATEKIAS 40 50 60 70 80 85 34 47 57 67 77 81 WINDOWS OPEN FLAPSUP NORMALKIAS ALTERNATEKIAS 40 50 60 70 80 90 100 110 120 130 140 26 43 57 70 82 93 103 113 123 133 143 FLAPS1OO...

Page 72: ...SECTION 5 PERFORMANCE CESSNA MODEL 172N L LU I z LIJ E I fl40 LU LU t tn t o20 TEMPERATURECONVERSION CHART 20 0 20 40 DEGREES CELSIUS Figure 5 2 Temperature Conversion Chart 5 10 ...

Page 73: ...ORWARD CENTEROF GRAVIIY WEIGHT LBS FLAP DEFLECTION ANGLEOF BANK oo 300 450 600 KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS 2300 UP loo 400 42 38 36 50 47 M 45 40 38 54 51 47 50 45 43 59 56 52 59 54 51 71 66 62 WEIGHT LBS FLAP DEFLECTION ANGLEOF BANK go 3oo 450 600 KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS 2300 UP 100 400 47 44 41 53 51 47 51 47 M 57 55 51 56 52 49 63 61 56 66 62 58 75 72 66 Figure 5 3 S...

Page 74: ... z WEIGHT LBS TAKEOFF SPEED KIAS PRESS ALT FT 00c 100c 2ooc 300c 4ooc GRND ROLL TOTAL TO CLEAR 50 FT OBS GRND ROLL TOTAL TO CLEAR 50 FT OBS GRND ROLL TOTAL TO CLEAR 50 FT OBS GRND ROLL TOTAL TO CLEAR 50 FT OBS GRND ROLL TOTAL TO CLEAR 50 FT OBS LIFT OFF AT 50 FT 2300 52 59 SL 1000 2000 3000 4000 5000 6000 7000 8000 720 790 865 950 1045 1150 1265 1400 1550 1300 1420 1555 1710 1880 2075 2305 2565 28...

Page 75: ...85 1070 1165 1270 1390 1525 1680 1850 2050 2275 865 940 1025 1115 1220 1340 1470 1620 1790 630 690 755 830 910 1000 1100 1215 1345 505 550 605 660 725 795 875 965 1065 1140 1245 1360 1490 1640 1805 1990 2210 2460 920 1005 1095 1195 1305 1435 1575 1740 1925 680 740 810 890 980 1075 1185 1310 1450 540 590 645 710 780 855 940 1035 1145 1220 1330 1455 1595 1755 1935 2140 2380 2655 985 1070 1170 1275 1...

Page 76: ...ned above 3000feetfor maximumRPM Figure 5 5 Rate of Climb WEIGHT LBS PRESS ALT FT CLIMB SPEED KIAS RATEOF CLIMB FPM 200c 00c 200c 400c 2300 S L 2000 4000 6000 BOOO 10 000 12 000 73 72 71 7Q 69 68 67 875 765 655 545 440 335 230 815 705 600 495 390 285 180 755 650 545 440 335 230 695 590 485 385 280 5 14 ...

Page 77: ...d temperature 4 Distances shownarebased on zerowind WEIGHT LBS PRESSU RE ALTITUDE FT TEMP oc CLIMB SPEED KIAS RATEOF CLIMB FPM FROMSEALEVEL TIME MIN FUELUSED GALLONS DISTANCE NM 2300 S L 1000 2000 3000 4000 5000 6000 7000 8000 9000 10 000 11 000 12 000 15 13 11 9 7 5 3 1 1 3 5 7 9 73 73 72 72 71 71 70 69 69 68 68 67 67 770 725 675 630 580 535 485 440 390 345 295 250 200 o 1 3 4 6 8 10 12 15 17 21 ...

Page 78: ...3 5 8 8 5 7 6 6 8 6 1 5 6 8 1 7 2 6 5 5 9 5 5 8 6 7 7 6 9 6 2 5 7 8 5 8 1 7 3 6 5 6 0 5 6 7 7 6 9 6 3 5 8 5 5 75 67 60 53 47 75 71 64 57 51 46 75 67 60 54 49 44 75 71 64 58 52 47 71 68 61 55 50 45 64 58 53 48 44 116 111 105 100 94 118 115 110 105 99 93 120 t15 109 104 98 92 122 120 114 109 103 97 122 119 114 108 102 96 118 113 107 101 95 8 4 7 5 6 7 6 1 5 6 8 4 LO 71 6 4 5 9 5 5 8 4 7 6 6 8 6 2 5 ...

Page 79: ...limb as shown rn figure5 6 2 Reservefuel is basedon 45 minutesal 45o o BHP and rs 4 1 gallons 12 OOO 10 ooo 8000 F uJ t u IL I ur 6000 o F F d 4ooo 2000 S L 11 TASr t4l 1 Ogz KTAS F 9 f LYT l8A _t_ I 1q llll 94 KTAS tf 1 r115 J KTAS ttl 1OGKTAS tttl KTAS_ ttl tf llil 103KTAS r I I r 1111I I i ii rL E Itu l 3 l o rI s LO s I t1 1ttt 0 t r c i ffi I I ls ft to lltr I I l e ol l3l KTASI lllll zlqo KT...

Page 80: ...mb as shown rn figure 5 6 2 Reservefuel rs basedon 45 mtnutesat 45 BHPand rs 4 1 gallons 12 000 10 ooo 8000 IIJ ut lJ I H 6000 3 t t 2000 S L T J 1Oer KTAS 96 KTAS tltl ffc 118 KTAS lttl Jff llll 94 KTAS 1122KTAS ttttl 115 KTAS tttt 106 KTAS llll rltll 118 KTAS 1 tlr 1 KTAS lllr 103 KTAS la T ui E Lr l o o be rol sfl gz rtRS ttll lC a e _ro ol fFl lNl 1 lff rttl 1OOKTAS rttl 90 KTAS 4 ii i 1Q 7 lt...

Page 81: ...refor Cruise StandardTemperature NOTES 1 This chart allowsfor the fuel usedfor enginestart taxi takeoffand climb and the time during climb as shown rn figure 5 6 2 Reservefuel is basedon 45 mrnutesat 45o o BHPand is 4 1 gallons 12 OOO 10 000 F SOOO UJ UJ l I H 6000 l tr F 2000 sr 5 456 ENDURANCE HOURS Figure 5 9 Endurance Profile SheetI of 2 5 19 ...

Page 82: ...ES 1 Thts chart allowsfor the fuel usedfor engtnestart taxi takeoffand climb and the trme durrngclimb as shown in figure b 6 2 Reservefuel rs basedon 45 minutesal 4s BHp and rs 4 1 gallons 12 OOO 10 ooo F 8000 uJ t t 3 6000 l F F J 2000 s L r rr1 rt rll l tt tl l l b6789 ENDURANCE HOURS Figure 5 9 Endurance profile Sheet Z ot Z Jl I l Ill _LE lo to R T o Jt H 1 d t ir t 1 o 1 d 5 20 ...

Page 83: ... ROLL TOTAL TO CLEAR 50 FT OBS GRND ROLL TOTAL TO CLEAR 50 FT OBS GRND ROLL TOTAL TOCLEAR 50FTOBS GRND ROLL TOTAL TOCLEAR 50FTOBS 2300 60 S L 1000 2000 3000 4000 5000 6000 7000 8000 495 510 530 550 570 590 615 640 665 1205 1235 1265 r300 1335 1370 1415 1455 1500 510 530 550 570 590 615 640 660 690 1235 1265 1300 1335 1370 1415 1455 1495 1540 530 550 570 590 615 635 660 685 710 1265 1300 1335 1370 ...

Page 84: ... 172N SECTION 6 WEIGHT BALANCE EQUIPMENT LIST SECTION 6 WEICHT BALANCE EQUIPMENT LIST TABLEOF CONTENTS Page Introduction 6 3 Airplane Weighing Procedures 6 3 Weight and Balance 6 6 Equipment List 6 13 6 r a zblank ...

Page 85: ...g to drain all fuel c Remove oil sump drain plug 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 Leveling a Place scales under each wheel minimum scale capacity 500 poundsnose 1000poundseach main b Deflate the nose tire and or lower or raise the nose strut to properly center the bubble...

Page 86: ...ft Wheel L Right Wheel R Nose Wheel N Sumof NetWerghts AsWerghed W X ARM A N x B X W tN x Item Moment 1000 Weight Lbs X C G Arm ln Lbs ln Airplane Weight From ltem 5 page6 6 Add oit No Oil Filter 6 Otsat 7 5 Lbs Gal With Oil Filter 7 Qtsat 7 5 Lbs Gal t4 0 14 O Add Unusable Fuel Std Tanks 3 Galat 6 Lbs Gal L R Tanks 4 Galat 6 Lbs Gal 46 0 46 0 Equipment Changes Airplane Basic Empty Weight 6 4 Figu...

Page 87: ... ry s z trl h dE t EF KEds E H z t o FJ ts ZA O AB4 E Ct Ot I ctl AIRPLANE MODEL SERIAL NUMBER PAGENUMBER DATE ITEMNO DESCRIPTION OFARTICLEOR MODIFICATION WEIGHTCHANGE RUNNING BASIC EMPTY WEIGHT ADDED REMOVED I ln Out wt rb Arm ln Moment 1000 wt fib Arm ln Moment 1000 wt ilb Moment 1000 Figure 6 2 Sample Weight and Balance Record ...

Page 88: ...fuselagestation is also shown but need not be used on the Sample Loading Prob lem The moment which is shown must be divided by 1000and this value used as the moment 1000 on the loading problem Use the Loading Graph to determine the moment 1000 for each addi tional item to be carried then list these on the loading problem NOTE Loading Graph information for the pilot p uisengers and baggageis based ...

Page 89: ... of gravity on adjustable seats positloned for avetage occupant Numbers rn pareD theses rndicate forward ard aJt Umits of occupant center of gravity range arm measued to the center of the areas shown NOTE The rear cabin vall appronmate station 108 or aJt baggage wall appro omate stauon 142 can be uged as convenent tntenor reference pornts for determrrung the location of baggage uea fuselage statio...

Page 90: ...0 30 WIDTH I HEIGHI Borroil I rRoNr HEIGHI REAR CABIN OOOR BAGGAGE DOOR 4t 21 MEASUR EMENTS I REARDOORPOST BULKHEAD T 21Y2 l cABrN I SIAIIONS O c G AR r S TIJ tl 90 loo I 80 tl 40 50 I llo I 120 I 130 ll lt42 t40 6 5 3 AFI BAGGAGE AREA DOOR OPENING DIMENSIONS 37 I oo st t 22 t lt r o 37 t t xZ9Vt l 3 tL l i i_ ri i __ _ _ i 1 1t 6 B Figure 6 4 Internal Cabin Dimensions ...

Page 91: ...on 34 to 46 RearPassengers Baggage Area 1 or Passenger on Child s Seat Station82 to 108 120 Lbs Max Bagg g Area2 Station 108 to 142 50 Lbs Max 3 4 5 6 145 57 6 240 11 5 340 12 6 170 12 4 96 9 1 7 TOTALWEIGHT AND MOMENT 2300 103 2 8 Locatethis point 2300at 103 2 on the Centerof GravityMomentEnvelope andsincethis point fallswithin the envelope the loadingis acceptable NOTE Th maximumatlowable combin...

Page 92: ...SECTION 6 WEIGHT BALANCE EQUIPMENT LIST CESSNA MODEL 172N r bo Fl I t a ho h 6 10 ...

Page 93: ...CESSNA MODEL 172N SECTION 6 WEIGHT BALANCE EQUIPMENT LIST q a o d F r f k O t I o h t bD ft 6 11 ...

Page 94: ... 2r FIH r u nz o e a A z p o A E o F ts Fr rI U 2300 2200 2100 2000 1900 1800 1 00 1600 1500 34 35 3 38 AIRCRAFT 1 HO Htr g tul sz z 36 40 4t 42 43 44 45 LOCATION INCHES AFT OF DATUM 39 46 47 Figure 6 8 Center of Gravity Limits ...

Page 95: ...ification S standardequipment items O optional equipment items replacingrequired or standarditems A optional equipmentitemswhich are in addition to requiredor standard items A referencedrawing column providesthe drawing number for the item NOTE lf additionalequipmentis to be installed it must be done in accord ancewith the referencedrawing accessorykit instructions or a separateFAA approval Column...

Page 96: ...E FTID SPINNER EULKHEAD AFT SPINNER BULKHEAD VACUUHSYSTEIIIINSTALLATION DnV Vaeu0u PUttP Av lr oF 4 TYPESI F IL TER VACUUI GAUGE RELIEF VALVE REGULATOR PRIMER SYSTEII NGINE THREECYLINDER OIL QUTCKDRAIN VALVE NET CHANGEI LEFTI I RTGHTT EACHI l HEELT BRAKE 6 T IRE ASsYr 6 oox6 IIHEEL ASSY I ICCAULEY ERAKE ASSY r I ICCAUL EY BRAKE ASSY T I ICCAUL EY TIREr 4 PLY BLACKIJAIt o55031 c2e45t0 030 I c 6l t ...

Page 97: ... ONr OlilN I FLASH 8EAC0N BEACONLIGHT ON FIN TIP FLASHER POHERSUPPLY RESI STOR TEHCOR I LTGHT INSTATLATIONI I ING TTP STROEE FLASHER POTER SUPPLY SET OF 2IN I INGI STROBELIGHTT I ING TIP SET OF 2I L IGHT INSTALLATIONT COI L HOUNIEDLANDING L Al l P 25O ATT l G E I L IGHTS T DUAL COT LI IOUNTED LANDING LAHPr 250 HATT G E t EACH INSTALLATIONT IHEEL FAIRING hIHEELFAIRING TUBE IHEEL 6 I HEEL TIRET TUBE...

Page 98: ...LECTRIC COI IPAS S HAGNET I C INSTALLAT ION INSTRUI ENTCLUSTERTLH 6 RH FUEL QUANTITY INSTRUHENTCLUSTERI OIL PRESSTOIL TEMP GYROSTATTITUDE E DIRECTIONAL INDICATORS NON NAV O XAIIC DIRECTIONAL INDTCATOR AV OF 4I ATTITUDE INDICATOR AV OF 3 GYRO I NSTALTATION TSI14IIAR TO D64 S E XCEPT DIRECTIONAL INDICATOR HAS A I4OVEABLE HEADING POINTER IINDICATOR NET CHANGEI GYRO INSTALTATIBN FOR 3OOA NAV O MATIC D...

Page 99: ... 9 J ZZ F JUJ lf J If JO a Fl aJZZ4 FO OOo Hclc T tt r JJ lo Hx4 Ztn tn UJU I HFO I EI F o o Jlclt ufo tt cJ uJ vv m U tf J Ju JN I l J r f FUJ F tr1 Ze tl F F I ll OUJ _O l i c r ut y JdJur I cfu IF ott urt J UJ J F O 9C Z L LlJ F F oJ tOq UTzlJFCZCUJUJ gJ09 cOcO oJ dd llJ vd Z4 nF YuJ uFuJtlJI d J Y 2Z 906 33 d f drr J LJ tftw IO tOptrJUr qz b6 uJl Q rd Qu Ot txx r UI HOUJ IO OdI tuJ d llf uJ o ...

Page 100: ...TGHT VFR IFR PLAEARD OPERATIONALLI14ITATIONS DAY VFR FLOATPL ANE PLACARO dPENATIONAL LITTITATIONS DAY NIGHT VFR FLOATPLANE PLA hiiO 6FENATTOI IAIL I I IITATIONS DAYNI6HT VFR IFR FLOATPLANE NOTE lxe ABOVE PLACAR0S ARE INSTALLED ACEORDiNGTO AIRCRAFT EQUIPHENT INOICATOnT lUDI6le PNEUI IATIeSTALL t ARNING OVENVOIT IiARNING LIGHTI ALTERNATOR SIOE 6 REAR STOXED I USE t BOXEO USE EI DUAT CARBUR ETOR STEI...

Page 101: ...CHANGEI H AVTONICS E AUTOPILOTS CESSNA3OO ADF INSTALLATION coNstsTs oF RECEIVER IIITH BFO R 5468I INOICATOR IN 346AI SENSE ANTENNAINSTALLATION LOOP ANTENNAINSTALLATION RECEIVER TJIOUNT HIRES ANO I IISC ITEHS DI E INSTALLATIONT NARCO RECE MR D lE l90l MOUNTINGBOX ANTENNA T CESSNA4OO GLIDESLOPE RECEIVER R 438 I 0l o2 050101I c42t ool 01 c42lo0l 0t 0513 t5 0501008 055201I O552L32 Lt o552132 t r 05520...

Page 102: ... uJ z zQ Ll I uJ Z UJ H r D aiF a r t HtsC ZhO OllJE ld lZ UJUJ UJ IJ tllJ UJF Ul I Ul I E JF o In J F lfi FrnoL I I e hZ Z fl1 ZJ qZ UJO t tlx Z Ztn H t z f oQ o O J Hg J O Ogt lJ CJ r Ul il lltz cJ tt O a o c f Z Z t co d r u Z6 uJZ ZVrg tsvr O 03 O F r O O Z l UJ JOZ F Our rZH a ddO I J J xJO uJ J dIcOH OJHd v v uJu uJ FoF hJ J q tl Ui yc Fd tt lJr iu d ur OZ 6Orn uJ lZ4 nuJ tr tn 2 E J I XuIZ ...

Page 103: ...LATION COM IUN ICATION ANTENNACABLE C FAX I OMN T ANTENNACAELE OI NI ANTENNAINSTALLATION COHTUNICATIONS SPIKE ANTENNAINSTL ESSNA 300 NAV COI I 720 CHr F IRST UNIT IITTH VOR LOC REC EIVER TRANSI II TTER RT 328Tt VOR LOC INDICATOR I TN 5I48 I INSTL COI IPONENTS SIHTLAR TO H2Z A I ESSNA 30O NAV COf lr 20 CHr F IRST UNIT I TTH VOR ILS 3el 0128 21 41470 l t t 4 1530 oool 391 055 7 31390 l 114 3e30152 t...

Page 104: ... ANTENNA AV O iATlc 2004 ogs ai t rUnn cooRo tr ArQR trEI_c ANqE I Tlnn cdoRDlNAToR NEr cHNGI G 300Al I ING INSTALLAT TOT sEHVo illT PA 2e58 NAY O ilATtc3qlA lAF395t contnoltER AnPLI EIER a quNf 661JA 2_6VN6 IRSTAfLAIION INEI qUNEEt 6sd it I i0Rn eodnoINAToR tNET cHANGEI IITNGINSTALLATIOi SeFVd UNtr I tPA ze5Bl RELAYINSTALLATION AvIai ICS 6Filo D NAY o flATIE INE BQV iiiKE iHEAosEi eoreo Nsrr tttE...

Page 105: ...ER RT 359I LOATPLANEFUSETAGESTRUCTURAL I IODTF ICA TIONS 6 FITTINGS OPTION C I LOATPLANECOI TOECK V BRACE INSTALLEDT sTol EDI LOATPLANEAILERON RUODERI NTERCONNECT FLOATPLANEONLY I INSTALTEDI sTor ED t TETS JIO A 6 JI3 A ARE ALSO APPROVED FOR LANOPLANEOPERATIONS OOEL 89A2OOOFLOATS E 502 ATTACHI ENTS NET CHANGEBETh EENSIANDARDLANDING GEAR ITEI NOS BOI Rr 8O4 Rr BIO S ANO BRAKE 6 NOSE IJHEET STEERTNG...

Page 106: ...t 117 UJ Ot alaTF tu JZZJW J Z 1 r uJc r rlx uJ t lQq Zz uruJo z q IUJS iHJ rvf F UJO h UJ ry E cl EJrr le gOl l tuJd Z q9O F ut tut O lF tuJ O G ZIUJ urFO ZZ 1 SJFO F tur UJFA u E Jo CutrJurFa JoH uJ JtJ yrFz d Jotal o UJ x AFI uJdH r llJ xiF OE QZ tcv o qqZ1tLd no Z n Ei aO t vtJ 9O urH O JF clCt urxrp JO itjJrcO J xftr QddJJO I FlJ r r OC JJO I Ftl Z JJ Ft Vur Jqa o Og U t Jda o cto J O OC J F ...

Page 107: ...sses Integrated Seat Belt Shoulder Harnesses With Inertia Reels Entrance Doors and Cabin Windows Control Locks Engine Engine Controls Engine Instmments New Engine Break in and Operation Engine Oil System Ignition Starter System Air Induction System Exhaust System Carburetor and Priming System Cooling System PropeIIer Fuel System Brake System Electrical System Master Switch Ammeter 7 tl 7 t2 7 L2 7...

Page 108: ...ng and Defrosting System 7 29 Pitot Static System and Instruments 30 Airspeed Indicator 31 Rate of Climb Indicator 31 Altimeter 31 Vacuum System and Instruments 31 Attitude Indicator 33 Directional Indicator 33 Suction Gage 33 Stall Warning System 7 33 Avionics Support Equipment 7 34 Audio Control Panel 7 34 Transmitter Selector Switch 7 34 Automatic Audio Selector Switch 7 34 Audio Selector Switc...

Page 109: ...n spars Conventional hinged ailerons and single slot type flaps are attached to the trailing edge of the wings The ailerons are constructed of a forward spar containing a balance weight formed sheet metal ribs and V type corrugated alum inum skin joined together at the trai ling edge The flaps are construct ed basically the same as the ailerons with the exception of the balance weight and the addi...

Page 110: ...SECTION 7 AIRPLANE SYSTEMS DESCRIPTIONS CESSNA MODEL 172N AILERON COI IITROLSYSTEM RUDDER AND RUDDER TRIM CONTROL SYSTEMS 7 4 Figure 7 1 Flight Control and Trim Systems Sheet 1 of 2 ...

Page 111: ...SECTION 7 AIRPLANE SYSTEMS DESCRIPTIONS ELEVATOR CONTROL SYSTEM ELEVATOR TRIM CONIROL SYSTEM 1 i C q 1 r l h Figure 7 1 Flight Control and Trim Systems Sheet2 ot 2 7 5 ...

Page 112: ...ON 7 AIRPLANE SYSTEMS DESCR IPTIONS CESSNA MODEL 172N GI C et N cl GC CE lt l c lt GI ct l ctlt er 6 1 N r C l 6a c lt C 6a t l 1 G C CI c t 6a CE ar t ct CE c c r 6a 6 Figure 2 Instrument Panel SheetI of 2 ...

Page 113: ...Mirror Audio Control Panel Radios Autopilot Control Unit Additional Instrument Space ADF Radio Flight Hour Recorder Additional Radio Space 23 Map Compartment 24 Cabin Heat and Air Control Knobs 25 Cigar Lighter 26 Wing Flap Switch and Position Indicator 27 Mixture Control Knob 28 Throttle With Friction Lock 29 Static Pressure Alternate Source Valve 30 Instrument and Radio DiaI Light Rheostats 31 M...

Page 114: ...rough a bungee connected to the rudder control system and a trim lever mounted on the control pedestal Rudder trimming is accomplished by lifting the trim lever up to clear a detent then moving it either left or right to the desired trim position Moving the trim lever to the right wiII trim the airplane nose right conversely moving the lever to the left will trim the airplane nose Ieft INSTRUMENTP...

Page 115: ... wheel through an arc of approxi mately 10 each side of center By applying either left or rightbrake the degree of turn may be increased up to 30 each side of center Moving the airplane by hand is most easily accomplished by attaching a tow bar to the nose gear stnrt If a tow bar is not available or pushing is required use the wing struts as pu shpoints Do not use the vertical or horizontal surfac...

Page 116: ...wheel two main wheels and wheel fairings Shockabsorption is provided by the tubular spring steel main landing gear struts and the air oil nose gear shock stntt Each main gear wheel is equippedwith a hydraulically actu ated disc type bral eon the inboard side of eachwheel and an aero dynamic fairing over eachbrake BAGGAGE COMPARTMENT The baggage compartment consists of two areas one extending from ...

Page 117: ... locked in place The seat backs will also fold full forward The six way seats may be moved fonvard or aft adjusted for height and the seat back angle is infinitely adjustable Position the seat by lift ing the tubular handle under the center of the seat bottom and slide the seat into position then release the lever and check that the seat is locked in place Raise or lower the seat by rotating a lar...

Page 118: ... of the belt as neededby grasping the sides of the link and pulling against the belt Insert and lock the belt Iink into the buckle Tighten the belt to a snug fit Seat belts for the rear seats and the child s seat if installed are used in the same manner as the belts for the front seats To release the seat belts grasp the top of the buckle opposite the link and pull outward SHOU DER HARNESSES Each ...

Page 119: ...K Snap onto retaining stud on seat belt link to attach barness SEAT BELT BUCKLE HALF SEAT BELT LINK HALF SEAT BEtT SHOUtDER HARNESS WITH INERTIA REEt AND SHOULDERHARNESS RETAINING STI ID FREE END OF SEAT BELT PuU to tighten SEAT BELT SHOULDERHARNESS ADJUSTABLE LINK Position tink Justbelow shoulder level pull link and harness down ward to connectto seat belt buckle SEAT BELT BUCKLE Non adjustable F...

Page 120: ... sudden deceleration they will lock automatically to protect the occupants NOTE The inertia reels are located for maximum shoulder har ness comfort and safe retention of the seat occupants This location requires that the shoulder harnesses cross near the top so that the right hand inertia reel serves the pilot and the left hand reel serves the front passenger When fastening the harness check to en...

Page 121: ...ir plane The best procedure is to set up the airplane in a trimmed condition at approximately 75 knots momentar ily shove the door outward slightly and forcefully close and lock the door Exit from the airplane is accomplished by rotating the door handle from the LOCK position past the CLOSE position aft to the OPEN posi tion and pushing the door open To lock the airplane Iock the right cabin door ...

Page 122: ...lternator mounted on the front of the engine and dual magne tos and a vacuum pump which are mounted on an accessory drivJpad on the rear of the engine Provisions are also made for a full flow oil filter ENGINE CONIROTS Engine power is controlled by a throttle located on the lower center portion of the instnrment panel The throttle operates in a conventional manner in the fuIl forward position the ...

Page 123: ... increments of 100 RPM and indicates both engine and propeller speed An hour meter below the center of the tachometer dial records elapsed engine time in hours and tenths In strument markings include a normal operating range green arc of 2200to 27OO RPM and a maximum red line of 2700RPM A carburetor air temperature gage may be installed on the right side of the instnrment panel to help detect carb...

Page 124: ...ated at the rear of the engine near the center The filler cap dipstick is accessible through an access door in the engine cowling The engine should not be operated on less than four quarts of oil To minimize loss of oil through the breather fill to five quarts for normal flights of less than three hours For extended flight fill to six quarts dipstick indication only For engine oil grade and specif...

Page 125: ...box operated by the carburetor heat control on the instrument panel Heated air from the shroud is obtained from an unfiltered outside source Use of full carburetor heat at full throttle will result in a loss of approximately 100 to 225 RPM EXHAUSTSYSTEftl Exhaust gas from each cylinder passes through riser assemblies to a muffler and tailpipe The muffler is constmcted with a shroud around the outs...

Page 126: ...rictive cover plate for the oil cooler air inlet in the right rear vertical engine baffle insulation for the crankcase breather line and a placard to be installed on the instrument panel This equipment should be installed for opera tions in temperatures consistently below 7 C 20 F Once installed the crankcase breather insulation is approved for permanent use in both hot and cold weather PROPELTER ...

Page 127: ...OR VALVE t t2 TO ENGINE Effi tl CODE FUEL SUPPLY VENT 7 21 ffi x M l l r__r r H MIXTURE CONTROL KNOB TO ENSUREMAXIMI M FUEL CAPACITY WHEN REFUELING PLACE THE FUEL SELECTORVALVE IN EITIIER LEFT OR RIGHT PGITION TO PREVENT CROSS TEEDING Figure 7 6 Fuel System Standardand Long Range ...

Page 128: ...he wing strut The right fuel tank filler cap is also vented Fuel quantity is measured by two float type fuel quantity transmit ters one in each tank and indicated by two electrically operated fuel 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...

Page 129: ...e under the left side of the instrument panel To apply the parking brake set the bral es with the mdder pedals prll the handle aft and rotate it 90 down For maximum brake life keep the brake system properly main tained and minirnize brake usage during taxi operations and landings Some of the symptoms of impending brake failure are gradual decrease in braking action after brake application noisy or...

Page 130: ...BNATOR 8US TO DOORPOSTMAP LIGHT TO DOMEAND COURT SY LIGHTS TO IGNITION SWITCH TO COMPASS INSTRUMENT ANO POSTLIGHTING TO CIGARLIGHTER WITHCIRCUITBREAKER TO LANDINGLIGHT S TO STROBE LIGHTS TO FLASHING BEACON TO NAVIGATIONLIGHTSAND CONTROL WHEELMAP LIGHT TO AUDIOMUTINGBELAY TO PITOTHEAT SYSTEM AUTO PILOT MASTEB SWITCH STARTER CONTACTOR STARTEB BATTERY CONTACTOR BATTE RY CODE o crRcutT SREAKER PUSH TO...

Page 131: ...h in the OFF position will reduce battery power low enoughto open the battery contactor remove power from the alternator field and pre vent alternator restart A N N ETER The ammeter indicates the flow of current in amperes from the al ternator to the battery or from the battery to the airplane electrical sys tem When the engine is operating and the master switch is turned on the ammeter indicates ...

Page 132: ...r starting and during tengthy maintenance work on the airplane electrical system with the exception of electronic equipment The receptacle is located behind a door on the left side of the fuselage near the aft edge of the cowling NOTE Electrical power for the airplane electrical circuits is pro vided through a split bus bar having all electronic circuits on one side of the bus and other electrical...

Page 133: ...are ON in the up position and OFF in the down position The flashing beacon should not be used when flying throtgh clouds or overcast the flashing light reflected from water droplets or particles in the atmosphere particularly at night can produce vertigo and loss of orientation The two high intensity strobe lights wiII enhanceanti collision protec tion However the lights shotrld be turned off when...

Page 134: ...nd is helpfuI when checking maps and other flight data during night operations To operate the light first turn on the NAV LT switch then adjust the map lightrs intensity with the knurled disk type rheostat control located at the bottom of the control wheel A doorpost map light is available and is located on the left forward doorpost It contains both red and white bulbs and may be positioned to ill...

Page 135: ...N AIR OUTLET ADJUSTABLE DEFROSTER OUTLET CABIN HEAT CONTROL SECTION 7 AIRPLANE SYSTEMS DESCRIPTIONS HEATER VALVE VENTILATING AIR DOOR CABIN AIR CONTROL I D v CODE A tl RAM AIR FLOW VENIILATING AIR HEATED AIR o SLENDED AIR MECHAMCAL CONNECTION 7 Figure 7 8 Cabin Heating Ventilating and Defrosting System 7 29 ...

Page 136: ... available for the rear cabin area to supply air to the rear seat passengers PITOT STATIC SYSTE M A ND INSTR UMENI S The pitot static system supplies ram air pressure to the airspeed indicator and static pressure to the airspeed indicator rate of climb indicator and altimeter The system is composed of either an unheated or heated pitot tube mounted on the lower surface of the left wing an external...

Page 137: ... the altimeter to 29 92 and read pressure altitude on the altimeter Be sure to return the altimeter barometric scale to the orig inal barometric setting after pressure altitude has been obtained Having set the ring to correct for altitude and temperature then read the airspeed shown on the rotatable ring by the indicator pointer For best accuracy this indication should be corrected to calibrated a...

Page 138: ...CODE l l TNLET AtR mffif vAcuuM n DtscHARGE AtR ATTITUDE INDICATOR SUCTION GAGE CESSNA MODEL 172N OVERBOARD VENTLINE VACUUMRELIEFVALVE l VACUUM SYSTEM AIR FILTER DIRECTIONAL INDICATOR o0c ooo ooo ooo ooo ooo oco 7 32 Figure 7 9 Vacuum System ...

Page 139: ... card should be set in accordance with the magnetic compass just prior to takeoff and oc casionally re adjusted on extended flights A knob on the lower left edge of the instmment is used to adjust the compass card to correct for precession SUCTION GAGE The suction gage is located on the left side of the instnrment panel and indicates in inches of mercury the amount of suction available for operati...

Page 140: ... transmitter rotate the switch to the number corres ponding to that transmitter The numbers 1 2 and 3 above the switch cor respond to the top second and third transceivers in the avionics stack An audio amplifier is required for speaker operation and is automati cally selected along with the transmitter by the transmitter selector switch As an example if the number 1 transmitter is selected the au...

Page 141: ...Oselector switchis in theOFF position the number1 NAV COMreceiver isin the PHONE position andthenumber1 ADF isin theSPEAKER position Withtheswitches setas shown the pilotwill transmiton the number1 transmitter andhearthenumber 1 NAV COMreceiver on a headset whilethepassengers arelistening to theADF audiothroughtheairplane speaker lf another audioselector slritchisplaced in either the PHONE or SPEA...

Page 142: ...anytime ADF audio is desired If the pilot wants only ADF audio for station identiJication or other rea sotls the AUTO selector switch if in use and all other audio selector switches should be in the OFF position If simuttaneous ADF and NAV coM audio is acceptable to the pilot no change in the existing switch positions is required Place the ADF 1 or 2 switch in either Ine SpneKER or PHoNE position ...

Page 143: ...result in loss of usable radio signals on all communications and navigation radio equipment Usually the ADF is first to be affected and VHF communication eguipment is the Iast to be affected Instaltation of static dischargers reduces interference from precipi tation static but it is possible to encounter severe precipitation static conditions which might cause the loss of radlo siglrls even with s...

Page 144: ...ions CessnaProgressive Care Flyable Storage Servicing Engine Oil Fuel Landing Gear Cleaning and Care Windshield Windows Painted Surfaces Propeller Care Engine Care Interior Care CessnaCustomer Care Program 8 6 Pilot ConductedPreventive Maintenance 8 Alterations or Repairs 8 7 Ground Handling 8 Towing 8 7 Parking 8 Tie Down 8 8 Jacking 8 8 Leveling 8 9 Page 8 3 8 3 8 3 8 3 8 4 8 5 8 5 8 6 8 9 8 10 ...

Page 145: ...r PC and Type Certificate Number TC can be found on the Identification Plate located on the lower part of the left forward door post Located adjacent to the Hentification Plate is a Finish and Trim Plate which contains a code describing the interior color scheme and ex terior paint combination of the airplane The code may be used in con junction with an applicable Parts Catalog if finish and trim ...

Page 146: ...g aII available items many of which he keeps on hand He wiII be happy to place an order for any item which is not in stock AIRPLANE FILE There are miscellaneous data information and licenses that are a part of the airplane file The following is a checklist for that file In addition a periodic check should be made of the latest Federal Aviation Regulations to ensure that aII data requirements are m...

Page 147: ...plete inspection every 100 hours of operation The FAA may require other inspections by the issuance of airworthi ness directives applicable to the airplane engine propeller and compo nents It is the responsibility of the owner operator to ensure compliance with all applicable airworthiness directives and when the inspections are repetitive to take appropriate steps to prevent inadvertent noncompli...

Page 148: ... accomplish all required FAA inspections ard most of the manufacturer recommended inspections CESSNA CUSIOfilER CARE PR OGRAffl Specific benefits and provisions of the CESSNAWARRANTY plus other imlrcrtant benefits for you are contained in your cusToMER CARE pRo GRAM book supplied with your airplane Ybu wiII want to thoroughly re view your Customer Care Program book and keep it in your airplane at ...

Page 149: ...TIONSOR REPAIRS It is essential that the FAA be contacted prior to any alterations on the airplane to ensure that airworthiness of the airplane is not violated Alterations or repairs to the airplane must be accomplished by licensed personnel GR OUNDHANDTING TOW ING The airplane is most easily and safely maneuvered by hand with the tow bar attached to the nose wheel When towing with a vehicle do no...

Page 150: ...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 Whenusing the individual gear strut jack pad flexibility of the gear strut will cause the main wheel to slide inboard as the wheel is raised tilting the jack The jack must then be lowered for a secondjacking operation Do not jack both main whe...

Page 151: ...iods the propeller should be rotated by hand through five revolu tions This action limbers the oil and prevents any accumulation of cor rosion on engine cylinder walls WARNING For maximum safety check that the ignition switch is OFF the throttle is closed the mixture control is in the idle cut off position and the airplane is secured before rotating the propeller by hand Do not stand within the ar...

Page 152: ...viously covered Dependingon various flight operations your local GovernmentAvia tion Agency may require additional service inspections or tests 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 OII GRAD...

Page 153: ...r at this time Refill sump with straight mineral oil and use until a total of 50 hours has accumulated or oil consump tion has stabilized then change to dispersant oil On airplanes not equipped with an oil filter driin the engine oil sump and oil cootF and clean the oil pressure screen each 50 hours thereafter On airplanes which have an oil filter the oil change interval may be extended to 100 hou...

Page 154: ...r anti ice fluid lacquer thinner or glass cleaner to clean the plastic These ma terials will attack the plastic and may cause it to craze Follow by carefully washing with a mild detergent and plenty of water Rinse thoroughly then dry with a elean moist chamois Do not rub the plastic with a dry cloth since this builds up an electrostat iE which attracts dust Waxing with a good commercial wur will f...

Page 155: ...ce removal with chemical liquids A 50 50 solution of isopropyl alcohol and water will satisfactorily remove ice accumulations without damaging the paint A solution with more than 50Vo alcohol is harmful and should be avoided While applying the de icing solution keep it away from the windshield and cabin windows since the alcohol will attack the plastic and may cause it to craze PR OPEttER CAR E Pr...

Page 156: ...r and test it on an obscure place on the fabric to be cleaned Never satu rate the fabric with a volatile solvent it may damage the padding and backing materials Soiled upholstery and carpet may be cleaned with foam type detergent used according to the manufacturerts instructions To minimize wetting the fabric keep the foam as dry as possible and remove it with a vacuum cleaner If your airplane is ...

Page 157: ...ures TABLE OF CONTENTS Introduction Supplements Emergency Locator Transmitter ELT 4 pages Updated Supplements SAF T STOP auxiliaryfront seatstops 2 pages GarminGMA340AudioPanel 12pages GarminGTN550GPS 35pages GarminSL30 NAV COM 2 pages GarminGTX327Transponder 8 pages STEC Autopilot reference autopilotPOH 9 1 ...

Page 158: ...tem wNch may be installed in the airplane Each zup plement contains a brief description and when applicable operating lim itations emergency and normal procedures and performance Other routinely installed items of optional equipment whose function and opera tional procedures do not require detailed instmctions are discussed in Section 9 2 ...

Page 159: ...ero Technologies SAF T STOP is installed in acc ordance with STC SA i 1966 L The information contained herein supplements or supersedes the information in the basic Flight Manual only in those areas listed For limitations procedures and performance information not contained in this supplement consult the basic Airplane Flight Manual 0fl FAA APPRO l E c Y 2CJJ2_ W F Horn Manager ACE 115C Chicago Ai...

Page 160: ...d aircraft adjust and lock seat using the aircraft s 1ocking mechanism pruv i ci ou i1c al a 71 l r 3 4 5 6 Insure that the aircraft s seat locking mechar ism is secur ly and properly locked accord1ng to th aircraft manufactu s dlrectio s Slide SAF T STOP up to approximatelv 1 4 to 1 2 inch of the seat rol1er See Figure 2 DO NOT HAVE THE SEAT ROLLER OR ANY PART OF THE SEAT STRUCTURE COME IN CONTAC...

Page 161: ...GMA 34O Audio Panel pilot s guide ...

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Cessna 1978 Skyhawk 172N, Operating Handbook

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