Cessna Skyhawk 172N 1980 Information Manual Download Page 58

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Summary of Contents for Skyhawk 172N 1980

Page 1: ...INFORMATION MANUAL lg80 MODEL 172N SKYHAwK _ Lessna...

Page 2: ......

Page 3: ...OK AND FAA APPROVED AIRPLANE FI IGHT MANUAL AND S TO BE USED FOR GENERAL PURPOSES ONLY IT WILL NOT BE KEPT iunRENT AND THEREFORE CANNOT BE USED AS A SUBSTITUTE FOR THE OFFICIAL PILOT S OPERATING HANDB...

Page 4: ...I Total Distance Over 50 Ft LANDING PERFORMANCE 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...

Page 5: ...1979 CESSNA AIRCRAFT COMPANY W CHITA KANSAS USA THE REPRINTING OF THIS MANUAL INCORPO RATES INFORMATION ISSUED IN REVISION 1 DATED 15 NOVEMBER 1979 FROM THE PILOT S OPERATINC HANDBOOK AND FAA APPROVE...

Page 6: ...ertificated 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 S5rmbols Abbreviations And Terminology 1 6 General Air...

Page 7: ...slrobe lights installed 2 Maximum h ighl shown wilh nose gEar depre ed all tires and nose srut properlv in lated and flashing beacon rnstalled Whel ba length as 65 Prorller qround clearance is 1 1 3...

Page 8: ...ive air cooled horizontally opposed carburetor eguipped four cylinder engine with 320 cu in displacement Horsepower Rating and Engine Speed 160 rated BHP at ZZ00 RpM PROPELLER Propeller Manufacturer M...

Page 9: ...nt aircraft engine oil must be used for all operat ing conditions NOTE Use a minimtrr of 75Vo power for cruise during the first 50 hours of operation or until oil consumption stabilizes Service the en...

Page 10: ...e 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 Sk...

Page 11: ...eed permissible with wing flaps in a prescribed extended position Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air then only with caution Never Exceed Sp...

Page 12: ...ngine Revolutions Per Minute is engine speed Static RPM is engine speed attained during a full throttle engine runup when the airplane is on the ground and stationary Demonstrated Crosswind Velocity i...

Page 13: ...1 S 1 10 blank I JuIv 19 9 l...

Page 14: ...nding llleight is the maximum weight ap proved for the landing touchdown Tare is the weight of chocks blocks stands etc used when weighing an airplane and is included in the scale read ings Tare is de...

Page 15: ...t Markings 2 6 Weight Limits 2 6 NormaL Category 2 6 Utility Category 2 7 Center Of Gravity Limits 2 7 Normal Category 2 7 Utility Category z Maneuver Limits 2 7 Normal Category 2 7 Utility Category 2...

Page 16: ...AS R EMAR KS Vrur Never Exceed Speed 158 158 Do not exceed this speed in any operation Vruo Maximum Structural Cruising Speed 126 12t Do not exceed this speed except in smooth air and then only with c...

Page 17: ...ng limitations operating procedures performanc e data ind other necessary information for iirplanes equipped with specific options NOTE The airspeeds listed in the Airspeed Limitations chart figure Z...

Page 18: ...Oil Temperature 245oF 118 C Oil Pressure Minimum 25 Psi Maximum 115 Psi Propeller Manufacturer McCauley Accessory Division PropeIIer Model Number 1C160 DTM7557 Propelier D iameter M lf l J f 11 l J 1...

Page 19: ...Station 82 to 108 120 lbs See note below Baggage Area 2 Station 108 to 142 50 lbs See note below NOTE The maximum combined weight capacity for baggage areas 1 and 2 is 120 lbs 1 July 1979 2 6 I NSTRUM...

Page 20: ...ine variation to 35 5 inches aft of datum at 2000 lbs Aft 40 5 inches aft of datum at aII weights Reference Datum Lower portion of front face of firewall MANEUVER LIMITS NORMAL CATEGORY This airplane...

Page 21: ...uild up speedquickrywiththenose down Proper speed control is an essentiar iequirement f execudoa ot any maneuver and care should always be exercised to avoid excessive speed which in turn can impose e...

Page 22: ...s Unusable Fuel 3 U S gallons 2 Long Range Tanks Z7 U S gallons each Total FueL 54 U S gallons Usable FueI all flight conditions 50 U S gallons Unusable Flrel 4 U S gallons NOTE To ensure rnaximum fue...

Page 23: ...ility Category are contained in the pilot s Operaling Handbook and FAA Approved Airplane Flight Manual Normal Category No acrobatic maneuvers including spins approved Utility Category No acrobatic man...

Page 24: ...o 40o Partial flaP range with blue color code and 110 kt callout also mechanical detent at 10o Indices at these positions with white color code and 85 kt callout also mechanical detent at 10o and 20o...

Page 25: ...NDS COMBINED FOR ADDITIONAL LOADING INSTRUCTIONS SEE WEIGHT AND BALANCE DATA a SECTION 2 LIMITATIONS CESSNA MODEL 172N 7 A calibration card is provided to indicate the accuracy of the magnetic compass...

Page 26: ...uring Start 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...

Page 27: ...s _ Recovery From A Spiral Dive Inadvertent Flight Into Icing Conditions Static Source Blocked Spins Rough Engine Operation Or Loss Of power Carburetor Icing S_park Plug Fouling Magneto Malfunction El...

Page 28: ...ry to correct the problem Emergency procedures associated with ELT ind other optionaliystems can be found in Section 9 CESSNA MODEL 172N AIRSPEEDS FOR EMERGENCY Engine Failure After Takeoff Wing FlaPs...

Page 29: ...OUT ENGINE POWER Airspeed 65 KIAS ftaps Up 60 KIAS flaps DOWN Mixture IDLE CUT OFF Fuel Selector Valve OFF Ignition Switch OFF Wing Flaps AS REQUIRED 40 recommended Master Switch OFF Doors UNLATCH PRI...

Page 30: ...at 65 KIAS with flaps up or at 60 KIAS with 10o flaPs 6 Cabin Doors UNLATCH 7 Touchdown Le Vgf ATTITUDE AT ESTABLISHED RATE OF DESCENT 8 Face CUSHION at touchdown with folded coat 9 Airplane EVACUATE...

Page 31: ...extinguished increase glide speed to find an airspeed which will provide an incombustible mixture 6 Forced Landing EXECUTE as described in Emergency Landing Without Engine Power ELECTRICAL FIRE IN FL...

Page 32: ...Switch if installed OFF 1 JuIy 1979 NOTE Perform a sideslip to keep the flames away from the fuel ia rt ra cabin and land as soon as possible using flaps it quired for final approach and touchdown ICI...

Page 33: ...ve 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 impro...

Page 34: ...htwill go out athigher RPM The master switch need 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...

Page 35: ...st cases the landing should be planned straight ahead with only small changes in direction to avoid obstructions Altitude and airspeed are seldom sufficient to execute a 180 gliding turn necessary to...

Page 36: ...height over a water surface LANDING WITHOUT ELEVATOR CONTROL Trim for horizontal flight with an airspeed of approximately 60 KIAS and flaps set to 20o by using throttle and elevator trim controls The...

Page 37: ...ure airplane 4 check accuracy of the turn by observing the compass heading which should be the reciprocal of the original heading 5 If necessary adjust heading primarily with skidding motions rather t...

Page 38: ...elevator back pressure to slowly reduce the airspeed to 80 KIAS 4 Adjusttheelevatortrimcontroltomaintainan80KIASglide b KeLp hands off the control wheel using rudder control to hold a straight headin...

Page 39: ...S PINS Should an inadvertent sPin occur should be used SECTION 3 EMERGENCY PROCEDURES the following recovery Procedure 1 RETARD THROTTLE TO IDLE POSITION 2 PLACE AILERONS IN NEUTRAL POSITION 3 APPLY A...

Page 40: ...eral 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 rough...

Page 41: ...age 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...

Page 42: ...ctivate the alternator system To do this turn the avionics power switch off check that the alternator circuit breaker is in then turn both sides of the master switch off and then on again If the probl...

Page 43: ...rting 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 Landi...

Page 44: ...oute Climb Cruise _ _I eaning With A Cessna Economy Mixture Indicator EGT StalIs Spins Landing Normal Landing Short Field Landing Crosswind Landing Balked Landing Cold Weather Operation Starting Fligh...

Page 45: ...ut 70 80 KIAS Short Field Takeoff Flaps 10o Speed at 50 Feet 53 KIAS Enroute Climb Flaps Up Ol fiPll Normal Sea Level 75 85 KIAS Normal 10 000 Feet 70 80 KIAS Best Rate of Climb Sea Level fl v et 73 K...

Page 46: ...control surfaces Also make sure that control surfaces contain no internal accumulations of ice or debris Prior to flight check that pitot heater if installed is warm to touch within 30 seconds with b...

Page 47: ...reeruNAGE 1 2 3 nrcHr wlNG Trailins Edse 1 Aileron CHECK freedom of movement and security Wing Tie Down DISCONNECT Maii Wheel Tire CHECK for proper inflation g ilr first flight of the day and after ea...

Page 48: ...ional water and further draining of the system at the strainer fuel tank sumps and fuel selector valve drain plug will be necessary q Propeller and Spinner CHECK for nicks and security 4 Landing Light...

Page 49: ...ne if engine is warm engine starts ON as required 4 7 2 3 4 5 6 Seats Belts Shoulder Harnesses ADJUST and LOCK Fuel Selector Valve BOTH AvionicsPowerSwitch Autopilot ifinstalled ElectricalEquip ment O...

Page 50: ...HEEL at 55 KIAS 5 Climb Speed 70 80 KIAS SHORT FIELD TAKEOFF 1 Wing Flaps 10o 2 Carburetor Heat COLD 3 Brakes APPLY 4 Throttle FULL OPEN 5 Mixture RICH above3000feet LEANtoobtainmaximumRPM 6 Brakes RE...

Page 51: ...Valve BOTH 3 Mixture RICH 4 Carburetor HJ ON ap ply full heat before reducing power autopitot if installed OTF 6 alr ionaitioner if installed OFF LANDING NORMAL LANDING 1 Airspeed 60 0 KIAS flaps UP 2...

Page 52: ...10 until obstacles are cleared RETRACT after reaching a safe altitude and 60 KrAS AFTER LANDING 1 Wing Flaps Up 2 Carburetor Heat COLD SECURING AIRPLANE 1 Parking Brake SET 2 Avionics Power Switch El...

Page 53: ...ely in cold weather with a cold engine it wiII 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 start...

Page 54: ...aking when the airplane is in this attitude Use the steerable nose wheel and rudder to maintain direction Figure 4 2 Taxiing Diagram 1 JuIy 1979 wrND DTRECTTON 4 t2 USE UP AILERON ON LH WING AND NEUTR...

Page 55: ...M gneto o show qreater than 50 RPM differen tial between ugrr illIf inEr is a doubt concerning operation of the ignition system nf fvf cttecXs at higher engine speeds wilI usuallv confirm r ih th t a...

Page 56: ...ld be leaned to give maximum RPM in a full throttle static runup After full throttle is applied adjust the throttle friction lock clockwise to prevent the throttle from creeping back from a maximum po...

Page 57: ...d 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 Climb chart in Section 5 If an obstruct...

Page 58: ...a n757o power the mixture 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 fuII carburetor heat...

Page 59: ...EGT provides the best fuel economy This results in approximately 47o greater range than shorvn in this handbook accompanied by approximately a 3 knot decrease in speed Under some conditions engine ro...

Page 60: ...be 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 usin...

Page 61: ...E R ESULTING DIVE NOTE If disorientation precludes a visual determination of the direction of rotation the symbolic airplane in the turn coordinator may be referred to for this information Variations...

Page 62: ...y lowering it e rose of thL airplani Touchdown should be made with power off and on the main wheels first Immediately after touchdown Iower the nose wheel and apply heavy braking as required For maxim...

Page 63: ...preheater and an external power source are recommended whenever I possible to obtain positive starting and to reduce wear and abuse to the engine and electrical system Pre heat will thaw the oil trap...

Page 64: ...r engine has started Leave on until engine is running smoothly 12 Primer LOCK NOTE If the engine does not start during the first few attempts or if engine firing diminishes in strength it is probable...

Page 65: ...all 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 there...

Page 66: ...adequately other aircra ft 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 theFederal Aviation Administrationthatthe noise...

Page 67: ...Calibration Normal Static Source Airspeed Calibration Alternate Static Source Figure 5 2 Temperature Conversion Chart Figure 5 3 Stall Speeds Figure 5 4 Takeoff Distance 2300 Lbs Takeoff Distance 2100...

Page 68: ...account for variations of 107o 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...

Page 69: ...the takeoff distance information presentedfor a weight of 2300 pounds pressure altitude of 2000 feet and atemperature of 30oC should be used and results in the following Ground roll 1045 Feet Total di...

Page 70: ...early corres pond to the planned altitude and expected temperature conditions The Lngine peed chosen is 2500 RPM which results in the following Power True airspeed Cruise fuel flow 64qo 114 Knots 7 1...

Page 71: ...or cruise is IS 1 5 2t 3 23 9 Gallons A procedure landing distance 5 6 similar to takeoff should be used for estimating the at the destination airport Figure 5 10 presents landing 1 July 1979 Knots Th...

Page 72: ...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 OPERATI N G TEM PERATUR E satisfactory engine cooling h...

Page 73: ...M dive CESSNA MODEL 172N 1 JuIy 1979 Figure 5 1 Airspeed Calibration Sheet 1 of 2 FLAPS UP KIAS KCAS 40 50 60 70 80 90 100 110 120 130 140 150 160 50 56 63 71 80 89 99 109 119 129 139 149 160 FLAPS lO...

Page 74: ...50 60 70 80 85 38 50 60 70 79 83 40 50 60 70 80 90 1oo 1 10 120 130 140 36 48 59 70 BO 89 99 108 118 128 139 FLAPS UP NORMAL KIAS ALTEBNATE KIAS 40 50 60 70 80 90 100 1 10 38 49 59 69 79 88 97 106 FL...

Page 75: ...SECTION 5 PERFORMANCE TEM PERATU R E 9Efi CONVERSION CHART 120 20 0 20 40 DEGREES CELSIUS Figure 5 2 Temperature Conversion Chart 5 10 1 July 1979...

Page 76: ...REARWARD CENTER OF GRAVITY WEIGHT LBS F LAP DEFLECTION ANGLE OF BANK Oo 300 450 6oo KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS 2300 UP 100 400 39 38 31 50 47 44 42 40 33 54 51 47 47 45 37 59 56 52 56 54...

Page 77: ...OrO C NC9 O c o La J uJO F J oo Foo Fb QOOOOOc OTO BFrFNtOOeex NCtro l ocr oo rNC NN O J ZJ EO 9aE lr c r oororooo O O t NFecDNN ON O OFN Y If tf att j UJI E l CL OOOOOOOO JOOOOOOOO TiOOOOOOOO FC 0Osi...

Page 78: ...o 6o NNN 6 o oo o F F cO orc e N 9 ro tl g o F o o N J o N Ea J co r O F r o l Foo Fto orooroororooo F lr Ne Y ON N llr ror F F FFNNN orooorf rrroroo NC rlr o tosl o O OFNCT t o O FFF OJ ZJ cEO E oo60...

Page 79: ...ve 3000 Ieet for maximum RPM Figure 5 5 Maximum Rate of Climb 1 July 1979 5 14 WEIGHT LBS PR ESS ALT FT CLIMB SPEED KIAS RATE OF CLIMB FPM 200c 00c 200C 400C 2300 S L 2000 4000 6000 8000 10 ooo 12 OOO...

Page 80: ...perature 4 Distances shown are based on zero wind Figure 5 6 Time FueI and Distance to Climb I July 1979 WEIGHT LBS PR ESSU R E ALTITUDE FT TEMP oc CLIMB SPEE D KIAS RATE OF CLI MB FPM FROM SEA LEVEL...

Page 81: ...9 103 97 119 114 108 102 96 8 0 7 1 6 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 b 1 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 5Z 51 46 75 67 60 54 s 44 75...

Page 82: ...fuel used for engine start distance during climb r 2 000 10 000 8000 6000 4000 2000 S L RANGE PROFILE 45 MINUTES RESERVE 40 GALLONS USABLE FUEL taxi takeoff and climb and the 500 550 RANGE NAUTICAL MI...

Page 83: ...This chart allows for the fuel used for engine start taxi takeoff and climb and the distance during climb 12 000 10 000 F 8000 UJ UJ u H 6000 l F F J 2000 S L RANGE NAUTICAL MILES Figure 5 8 Range Pr...

Page 84: ...nds Recommended Lean Mixture for Cruise Standard Temperature NOTE This chart allows for the fuel used for engine start taxi takeoff and climb and the time during climb 12 000 10 000 8000 F IJJ tJJ L H...

Page 85: ...BLE FUEL CONDITIONS 2300 Pounds Becommended Lean Mixture for Cruise Standard Temperature NOTE This chart allows for the fuel used for engine start taxi takeoff and climb and the time during climb 12 0...

Page 86: ...onroroo OOO NTIOOSI NN f Cr l fIo OJ ZJ cco E oooooroooo TCDIr NOT f oO rorolororo o o o o o Ea J CN urO LJ boI FOo Fro LOtf tf OTOOTf IOO Oo OOCONTlr O Nc NcDrrcr f tto OJ ZJ rO 9CC roooooolr 0ro 6 C...

Page 87: ...ANCE EQUIPMENT LIST TABLE OF CONTENTS Introduction Airplane Weighing Procedures Weight And Balance Equipment List 1 July 1979 6 rl 6 2 blank CESSNA MODEL 172N SECTION 6 WEIGHT BALANCE EQUIPMENT LIST P...

Page 88: ...plug to drain aII oil d Move sliding seats to the most forward position e Raise flaps to the fully retracted position f Place aII control surfaces in neutral position 2 Leveling a Place scales under...

Page 89: ...eighing 6 4 Scale Position Scale Reading Tare Symbol Net Weiqht Left Wheel L Right Wheel R Nose Wheel N Sum of Net Weights As Weighed Item Moment 1000 Weight Lbs X C G Arm ln Lbs ln Airplane Weight Fr...

Page 90: ...b0 o B o g a ai o q tr h0 fr o E og Ui hJ E E E lrJ g Ug ZE k JE mE ots z5 fs 3 o es UJE 3 lrJ J 0 E U 6 5 a U o l z U L E U o l z J s E u J U o o U z J L E F at Se 2y ZL zi f EU c FO oO U z f t F I U...

Page 91: ...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...

Page 92: ...nge Arm measured to the center of the areas shown 1 The usable fuel C G arm for stanchrd and long range tanks is located at station 48 0 2 The rear cabin wall approximate station 108 or aft baggage wa...

Page 93: ...H twR wrNoow tINE CABIN FIOOR DOOR OPENING DIMENSIONS CABIN WIDTH INSTRU VIENT PANEI MEASUREME NTS caBtN I STATIONS O c G aR MS REAR DOORPOST BUI KHEAD I 40 rl 80 90 Figure 6 4 Internal Cabin Dimensio...

Page 94: ...m U ld z J o v UJ J L n c i C U U o q N _ ro u q N Y N q o o o o q _ i lO d o d N f r o N c o N o N r o o N UJ J m uJo Jtr LtL is a3 o o J o l O O x oc S P 1 00 EC E e E 3 Oj 6 lPo t tr Y o x 3 E Sd...

Page 95: ...T LIST Y 6 69 38 vJ c boE PI Elo o ci g E E coo fr H 3 I q JE 2 E E sai f g EEE O p e X 6o E E E oLsl E 9 3tE e E o iE e 3 EgF t g o6x 9 t6 E tr oGc r6 i F o z G9 cE U F U f Jo R IE o o o ZN o o F zo...

Page 96: ...H9r3M 3NVldU lV OIOVO l EEBSBsB 9oo 0oN CESSNA MODEL 172N 1 July 1979 ro I o o tDg LlJ ir b 2ts Td O r l oZ o 1 0 BA roaO Sx oZ a IJJ cB o i rn F U i z IE R g o l i LlJ L op oJI 6 i tr 8 6 E UJ F IJJ...

Page 97: ...r3 1 lNVtdU rV OTOVO SECTION 6 WEIGHT BALANCE EQUIPMENT LIST 6 t2 F t o o S tf N o ci 8 F g N F o ra F I aDo cc tJJ F LlJ E J J o 8 z Oo o FO O O91 N O O ue zo J Lh rN ao o o ro N o a loO t I 2a KE CD...

Page 98: ...ing 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 lf additional equ...

Page 99: ...FFIA u 1 A F Yv u4 r g C O 6X A u J a u J utJJ J 13 U JU j O U J J HU J F r uv a0 d n a yacn I sq 1 CF CJUU Ll vu u cu b t q f U ira dtsl rI cactsF 3 ur u fa FUI UUJ 7 JtJ J r uru Z Z ul ui e f J clX...

Page 100: ...JI dLl J rX stz Z c J Jc tJu 6 o Fo r a F llJJ ZZ F HuvO Ju F O N FF JJ J JC tsq Z d dr u o Lt H vd 5 u C F LruFxTl Z Z Z l 3uF f u Z d tgi O 3 rZ Z Z HJ Q rz u d u ZZetA U dZOH td L F r F fH OdUJtrIT...

Page 101: ...HFLUC CJCCJC d Ci J d Z O dr C J FFFFmC 3 C Al ts ts C Jr J6 F e Of O r u n V 62 Cf ucj F FFIJZHXU F F aCjHiHHZo e dH H iI JF oJJC OHd d cZ HOCCC r UUU u F ZeZ d CZ jCCf Jc OuFZcad F 6 COF vul H C H...

Page 102: ...ZtJ J uU J H a j C Z L uL vF C r J urz JFtr Zr lr cfcara dd U l ddz d vC A ts ts I t I 9t EOBU I F NZ L C s u ouFu u s I L ZZA f ccd 33 Zd Z z v1c 3 l OOr qu Ca ZU C l I l m Ll H rFUZa C l UrU r Z tsO...

Page 103: ...t ztz J JJ 6 dU 4 4 _JJO jIZ zzzzzuzdot uz CLI c c CZTJFJH jJ H H L ozz c Fts F F FJFC ZFgia 4 d O JClFa F F d A oU rytso l ilC u u u uzu u ro1 caao dLCl6 cuucl CC CECJCJCO LL dU u d u LrILjd c F FF C...

Page 104: ...c J a 4 J J ti d zl u zz tsJ 4f ClFurv rA 0 c ddTv c za zv u UupUO I Z FZL C TT rxzra Z AV d ULTF F F U UI FHU FJc UU BUILj l ff x yc Y x6 9 rUu a7 uul zz U ZFF Z hU e F f JCJC 2 t OZ o l Hd F F xxz...

Page 105: ...A FU auut iU Uil eU I r E ul I r U I ue a utJF s Fr 4 u d Foru oFqiuFF ZFOFTZ CFqZ Uj 6H Z Z O IUArI JLdTFFJ HUuu fHU UZ u J tH J vtHHU ZC z zC 7Q Cq U Z C u Z u Z j cuHr ue r uzq u z oc c crcdtsLj _q...

Page 106: ...C F Z HUIU U v d Fuu r g OJ o I 6 ZZZa 3 J t uJ o6US d O LlH F d e 4Vz ul 7az FJZJ l Huro CJ F IC C eO U o c t rF E IC F J HC g z ooz d d i u 4 utstsd aE Z t ZZY L CJF 6 C cyu aot cl ZUC G r CH OCJdL...

Page 107: ...Cf ICjOF Z u u gt zdA otsHF L x s H l 3 Z UacO UjCalFc OUeFUT oa ac7 a 7_ FJ dF urrF s C ZiQ s f iZF l l r Q6 nFZ I JG Y 6rZ JUc aA f OFIPUCJU J I CC U dr aats aa 1 7q o Flr Z FJ I I I I tr C q C U Ul...

Page 108: ...JZZ u C gjclrl dzl vuldHtiJetsJzZ BCl t ZZ9V tl l ZOA Ul oJcful ZL nZ 6uQ ZZO abA Z F H Z Z uJd HuH t Z u Hl E Z xl E QtlF UJX Z 3O u JICfJZClllF uJ lH OtlF uJ ru uJFdF ZZIIL UFd JA rIU L FdFtL IU urF...

Page 109: ...ance Doors And Cabin Windows Control Locks Engine Engine Controls Engine Instruments New Engine Break In And Operation Engine Oil System 7 18 Ignition Starter System 7 19 Air Induction System 7 19 Exh...

Page 110: ...ting Ventilating And Defrosting System Pitot Static System And Instruments Airspeed Indicator Vertical Speed Indicator Altimeter Vacuum System And Attitude Indicator Directional Indicator Suction Gage...

Page 111: ...s The entire structure is covered with aluminum skin The front pur are equipped with wing to fuselage and wing to strut attach fit tings The at spars are equipped with wing to fuselage attach fittings...

Page 112: ...N 7 AIRPLANE SYSTEMS DESCRIPTIONS CESSNA MODEL 172N 1 July 1979 l l r AILERON CONfROL SYSTEM RUDDER AND RUDDER TRIM CONTROL SYSTEMS i __ rl r Figure 7 1 Flight Control and Trim Systems Sheet 1 of 2 J...

Page 113: ...CESSNA MODEL 172N 1 Control and Trim Systems Sheet 2 of 2 I t t ji SECTION 7 AIR PLANE SYSTEMS DESCRIPTIONS ELEVATOR CONTROL SYSTEM j T a t ELEVATOR TR IM CONTROL SYSTEM r i 7 5...

Page 114: ...o o 6 o SECTION 7 AIRPLANE SYSTEMS DESCRIPTIONS 7 6 CESSNA MODEL 172N 1 July 1979 o o o o e F igure 7 2 Instrument Panel Sheet I of 2...

Page 115: ...l l eI l eg galg g EE A t s r sg zZ E gg E I r Fr 6 st HtsE gcE iE i E 8 EEEE 3 Efi8 EE EEi ps E E flEgnAEi IEEi ai E E gE E gE PFs A s E gg e s s g A ggs rj rjF qi oj cj ic icj rjdD cdae iaic ji n dr...

Page 116: ...st of a 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 to...

Page 117: ...witch and control panel in front of the pilot For details concerning the instruments switches circuit breakers and controls on this panel refer in this section to the description of the systems to whi...

Page 118: ...the stop and position it as desired A scale and pointer on the Ieft side of the switch lever indicates flap travel in degrees The wing flap system circuit is protected by a 15 ampere circuit breaker l...

Page 119: ...ide 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 loahed to the Iocked positi...

Page 120: ...headrest apply enough pressure to it to raise or lower it to the desired level The headrest may be iemoved at any time by raising it until it disengages from the top of the seat back SEAT BELTS AND SH...

Page 121: ...NESS RETAINING ST JD FREE END OF SEAA BELT Pull to tighten CESSNA MODEL 172N 1 July 1979 SECTION 7 AIRPLANE SYSTEMS DESCRIPTIONS STANDARD SHOULDER HARNESS PtroT s sEAr sHowN SEAI BEIT SHOUtDER HARNESS...

Page 122: ...ud on the seat belt link In an 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 s...

Page 123: ...handle is spring Ioaded to the CLOSE up position when the door has been pulled shut and Iatched lock it by rotating the door handle forward to the LocK position flush with the arm rest when the handle...

Page 124: ...d over the vertical stabilizer and rudder The control lock and any other type of locking device should be removed prior to starting the engine EN GIN E The airplane is powered by a horizontally oppose...

Page 125: ...ange green arc which is 1000F 38oC to 245oF 1180C and themaximum redline which is 245 F 118 C The engine driven mechanical tachometer is 1ocated on the instrument panel to the left of the pilot s cont...

Page 126: ...sory housing and into a flexible 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 strai...

Page 127: ...the switch is released it will automati 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 engi...

Page 128: ...ngs in the front ofthe 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 cow...

Page 129: ...uel quantity transmitters 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...

Page 130: ...SLOPING SURFACE PLACE THE FUEL SELECTORVALVE N ElTHER LEFT ON RIGHT POSITION Figure 7 6 Fuel System Standard and Long Range 7 22 1 JuIy 1979 FUEL OUANTITY INDICATORS VE NT lWITH CHECK LEFT FI EL TANK...

Page 131: ...wheel Each brake is connected by a hydrauric rine to a master cylinder attached to each of the pilot s rudder peaut The brakes are operated by applying pressure to the top of either the left pilot s o...

Page 132: ...BREAKER IDIGITAL CLOCK ONLY TO DOOR POST MAP LIGHT TO DOME AND COURTESY LIGHIS IO NSTRUMENT BAOIO MAGNETIC COMPASS AND POST LIGHTING TO AUDIO MUTING RELAY TO NAVIGATION LIGHTS ANO CONTFOL WHEEL MAP LI...

Page 133: ...d simultane ously however the BAT side of the switch could be turned on separately to check equipment while on the ground To check or use avionics equipment or radios while on the ground the avionics...

Page 134: ...ne is equipped with a combination alternator regulator high Iow voltage control unit mounted on the engine side of the firewall and a red warning light Iabeled LOW VOLTAGE on the left side of the inst...

Page 135: ...rcuits are protected by fuses mounted adjacent to the battery GROUND SERVICE PLUG RECEPTACLE A ground service plug receptacle may be installed to permit the use of an external power source for cold we...

Page 136: ...ide direct lighting To use post lighting move the slide switch in the overhead console Iabeled PANEL LIGHTS to the POST position and rotate the outer knob on the light dimming rheostat labeled PANEL L...

Page 137: ...dor turn off the Iight switch of the affected 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 tempe...

Page 138: ...TLET 2 CABIN HEAT CONTROL 9 R CESSNA MODEL 172N HEATER VALVE VENTILATING AIR DOOR CABIN AIR CONTROL CODE J RAM AIR FLOW VENTILATING AIR HEATED AIR BLENDED AM MECHANICAL CONNECTION I tn v 7 30 Figure 7...

Page 139: ...e pitot heat switch is turned on the element in the pitot tube is heated electrically to maintain proper operation in possible lcing conditions Pitot heat should be used only as required A static pres...

Page 140: ...e 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 iltimeter seiti rg VAC...

Page 141: ...NS OVERBOARD VENT LINE VACUUM RELIEF VALVE CODE INLET AIR VACUUM DISCHARGE Figure 7 9 Vacuum SYstem VACUUM PUMP VACUUM SYSTEM AIR FILTER 1 July 1979 ATTITUDE INDICATOR AIR r_ j ffi lrya 7 33 000 0000...

Page 142: ...is equipped with a pneumatic type stall warning system consisting of an inlet in the Ieading edge of the left wing an air operated horn nearthe upper left corner of the windshield and associated plum...

Page 143: ...amplif ier associated with that transmitter to provide spLaker audio For example if the number one transmitter is setected ttr raio amplifier in the number one NAV COM is also selected and is used for...

Page 144: ...ITCH AUDIO SELECTOR SWITCHES 1 July 1979 USED WITH ONE OR TWO TRANSMITTERS HEADSETSIDETONE T_SPEAKER SIDETONE TNTERNAL ADJUSTMENTI rrurenrunl ADJUSTMENT ccESS I nccess COM AUTO AUDIO SELECTOR SWITCHES...

Page 145: ...he other transmitter auto matically switches the other communications receiver audio to the speaker This automatic audio switching feature may also be utilized when listening on a headset by placing t...

Page 146: ...nter 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...

Page 147: ...ches Adjust ment of speaker and headset sidetone volume can only be accomplished by adjusting the sidetone potentiometers located inside the audio control panel NOTE Sidetone is not available on HF Tr...

Page 148: ...of the wings rudder elevator propeller tips and radio antennas can result in loss of usable radio signals on all communications and navigation radio equipment Usually the ADF is first to be affected a...

Page 149: ...Cessna Progressive Care Cessna Customer Care Program Pilot Conducted Preventive Maintenance Alterations Or Repairs Ground Handling Towing Parking Tie Down Jacking Leveling 3 3 Flyable Storage Servicin...

Page 150: ...nd Type Certificate Number TC can be found on the Identification Plate located on the Iower part of the left forward doorpost Located adjacent to the Identification Plate is a Finish and Trim Plate wh...

Page 151: ...e items many of which he keeps on hand He will Ue frappy 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 o...

Page 152: ...t these items plus the Pilot s Checklists Power Computer Customer Care Program book and Customer Care Card be carried in the airplane at all times AIRPLANE INSPECTION PERIODS FAA REOUIRED INSPECTIONS...

Page 153: ...y worked out by the factory and are followed by the cessna Dealer organization your cessna Dealer can assist you in selecting the inspection program most suitable for your type of aircraft and operati...

Page 154: ...d 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 perf orming any preve...

Page 155: ...or chain to a ramp tie down 4 Install a pitot tube cover JACKING When a requirement exists to jackthe entire airplane off the ground or when wing jack points are used in the jacking operation refer to...

Page 156: ...red 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 corro...

Page 157: ...perations your local Government Aviation Agency may require additional service inspections ortests For these regulatory requirements owners should check with local aviation officials where the airplan...

Page 158: ...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...

Page 159: ...ensation 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 sm...

Page 160: ...e fuel 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 capa...

Page 161: ...e 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 for the differential refractometer b...

Page 162: ...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 freezin...

Page 163: ...ervice Small nicks on the propeller particularly near the tips and on the leading edges should be dressed out as soon as possible since these nicks produce stress concentrations and if ignored may res...

Page 164: ...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...

Page 165: ...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 vo...

Page 166: ...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...

Page 167: ...rnal power source will flow only if the ground service plug is correctly connected to the airplane If the plug is accidentally connected backwards no power will flow to the electrical system thereby p...

Page 168: ...s at 10 000 feet The ELT iupplied 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...

Page 169: ...s to battery pack ANTENNA RECEPTACLE Connects to antenna mounted on top of tailcone Figure 1 ELT Control Panel sEcTloN 3 EMERGENCY PROCEDURES Immediately after a forced landing where emergency assista...

Page 170: ...RMAL 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...

Page 171: ...ok The cessna 300 ADF can be used for position plotting and homing procedures and for aural reception of amplitude moduiated AM signa s with the function selector knob at ADF the cessna 300 ADF provid...

Page 172: ...primary power to receiver further clockwise rotation increases audio level PILOT S OPERATING HANDBOOK SUPPLEMENT ADF Operating Controls and Indicators Sheet 1 of 2 1 July 1979 FREQUENCY SELECTORS Knob...

Page 173: ...using loop and sense anten nas TEST Momentary on position used during ADF operation to test bearing reliability When held in TEST position slews indicator pointer clockwisei when released if bearing...

Page 174: ...uency Selector Knobs SELECT operating frequency 3 ADF SPEAKER PHONE Selector Switch on audio controt panet SELECT AS DESIRED 4 Function Selector Knob ADF position and note relative bearing on indicato...

Page 175: ...in the audio output when a CW signal Morse Code is tuned in properly SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installa...

Page 176: ...apable of replying to Mode A aircraft identification and also Mode C altitude reporting when coupled to an optional altitude encoder system The transponder is capable of replying on both modes of inte...

Page 177: ...A aircraft identification reply pulses ALT Turns set on and enables transponder to transmit either Mode A aircraft identification reply pulses or Mode C altitude reporting pulses selected automaticall...

Page 178: ...pilot to control brilliance of reply 1amp 5 SELF TEST TST SWITCH When depressed causes transponder to generate a self interrogating signal to provide a check of transponder operation Reply lamp wiII g...

Page 179: ...ERGENCY SIGNAL 1 Function Switch ON 2 Reply Code Selector Knobs SELECT 7700 operating code TO TRANSMIT A SIGNAL REPRESENTING LOSS OF ALL COMMUNICATIONS WHEN IN A CONTROLLED ENVIRONMENT 1 Function Swit...

Page 180: ...n S vitch ALT NOTE When directed by ground controller to stop altitude squawk turn Function Switch to ON for Mode A opera tion onIy NOTE Pressure altitude is transmitted by the transponder for altitud...

Page 181: ...UPPLEMENT SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounted antenna or several related ext...

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