Cessna 172 P Pilot'S Operating Handbook And Flight Manual Download Page 1

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PILOT'S OPERATING HANDBOOK

and

FAA APPROVED AIRPLANE FLIGHT MANUAL

THIS DOCUMENT MUST BE
CARRIED IN THE AIRPLANE
AT ALL TIMES.

CESSNA AIRCRAFT COMPANY

1981 MODEL 172P

Serial No.

\":t 2.1-2

Registration No.

N7J,s-/)

THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE

FURNISHED TO THE PILOT BY CAR PART 3 AND CONSTITUTES

THE FAA APPROVED AIRPLANE FLIGHT MANUAL.

,) Member of GAMA

CESSNA AIRCRAFT COMPANY

WICHITA, KANSAS, USA

30 May 1980

Summary of Contents for 172 P

Page 1: ...L TIMES ICESSNA AIRCRAFT COMPANY I 1981 MODEL 172P Serial No t 2 1 2 1 Registration No N7J s THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY CAR PART 3 AND CONSTITUTES THE FAA APPROVED AIRPLANE FLIGHT MANUAL Member of GAMA COPYRIGHT 1980 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 30 May 1980 ...

Page 2: ...THIS MANUALWAS PROVIDED FOR THE A RPLANE IDENT FIED ON THE TITTE PAGE ON SUBSEOUENT REVISIONS SUPPLIED BY CESSNA AIRCRAFT COMPANY MUST BE PROPERLY IN SERTED CESSNA AIRCRAFT COMPANY PAWNEE DIVISION ...

Page 3: ...ing services are offe ed by most Cessna Dealers a FACTORY TRAINED PERSONNEL to provide you with courteous expert service TACTORY APPROVED SERVICE ËQUIPMENT to provide you efficient and accurate workmanship a A STOCK Ot CENUINE CESSNA SERVICE PARTS on hand when you need them THE LATEST AUTHORITATIVE INFORMATION FOR SERVICING CESSNA AIR PLANES since Cessna Dealers have all of the Service Manuals and...

Page 4: ...TS CRUISE mixture with fuel allowancefor engine cllmb and 45 minutes reserve 767o Power at 8000 Ft Range 440 NM 40 Clallons Usable Fuel Timõ g B HRg 75õ NM 6 4 HRS õSO NM õ 8 HRÉI 680 NM 7 4 HRS 875 NM 9 4 HRS 7OO FPM 13 000 FT 890 FT 1825 FT 540 FT 1280 FT 51 KNOTS 46 KNOTS Skyhawk II BAGGAGEALLOWAÑCb WÍNG LOADING Pounds Sq Ft PO1üER LOADIÑG Pounds HP FUEL CAPACITY Total Standard Tanks Long Range...

Page 5: ...area on the outer margin ofthe page All revised pages will carry the revieion number and date ou the applicable page The following Log ofEffective Pagea provides the dates ofissue for original and revised pages and a listing of all pages in the handbook Pages affected by the current revision are indicatcd by an asterisk preceding the pagee liated LOG OF EFFECTIVE PAGES Dates ofissue for original a...

Page 6: ...ION GENERAL 1 LIMITATIONS 2 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT BALANCE EOUIPMENT LIST 6 AIRPLANE SYSTEMS DESCRIPTIONS AIRPLANE HANDLING SERVICE MAINTENANCE SUPPLEMENTS Optional Systems Description Operating Procedures I lv 30 May 1980 ...

Page 7: ...ne Propeller Fuel oil Maximum Certifioated Iüeights Standard Airplane lleigbts Cabin And Entry Dimensions Baggage Space And Entry Dimensions Specific Loadings Symbols Abbreviations And Terminology General Airspeed Terminology And Symbols Meteorolo gical Terminolo glr Engine Power Terminology Airplane Performance A nd Flight Planning Terminology lÃleight And Balance Terminology 30 May 1980 1 1 ...

Page 8: ...oporly lnllEtôd ond flðhlng òB n in t lhd 3 hæl bæ lsngth l 6õ 4 Prop llor ground clsEnæ lt 111 5 Wng rro ls 174 qu ro læt 6 Mlnlmum tunlng rldlur plvot polnt to outbmrd wlng tlpl 13 27 5ß 1 1 14 76 1 2 CESSNA MODEL 172P 1 2 1 PIVOT POINT PIVOT POINI o o t 2 Figure 1 1 Three View 80 May 1980 ...

Page 9: ...drive air cooled horizontally opposed oarburetor equipped four cylinder engine with 819 8 cu in displacement Horsepower Rating and Engine Speedl 160 rated BHP at 2700 RPM PROPELLER Propeller Manufacturer McOauley Aocessory Division Propeller Model Number 1C160 DTM7557 Number of Blade 2 Propeller Diametor Maximum B inches Minimumi 74 inches Propeller Type Fixed pitch FUEL Approved Fugl Grades and C...

Page 10: ...ight Minoral OiL Use to replenish supply duríng first 25 hours and at the first 2õ hour oil change Continue to uso until a total of õ0 hou s has aooumulated or oiÌ consumption has stabilized MIL L 22851 Ashless DÍsporsant Oil This oil muat be used after first õO hours or oil consumption has stabilized Recommendod Viscosity for Temperature Range MIL L 6082 Aviation Grade Straight Mineral Oil AII te...

Page 11: ...20 lbs See note below Baggage Area 2 Station 108 to L42 õO lbs See note below NOTE The maximum combined weight capacity for baggage areas 1 and 2 is 120 lbs Weight in Baggage Compartment Utility Category In this category the baggage compartment and rea r seat must not be occupied STANDARD AIRPLANE WE GHTS Utifi Category 693 lbs 667 lbs CABIN AND ENTRY DIMENSIONS Detailed dimensions of the cabin in...

Page 12: ... Speed is the Íghest speed permissiblo with wing flaps in a prescribed extended position V o Maximum Structural Gruising Speed is the speed that shouldnot be oxceededexcept in smooth air then onlywith caution VNp Never Exceed Speed is the speed limit that may not be exceeded at any time VS Stalling Speed or trhe mi lmun steady f ight speed at which the airplane is controllable VS Stalltng Speed or...

Page 13: ...ind oomponent for which adequate control of the airplane during takeoff and landing was actually demon strated during certification tests The value shown is not considered to be limiting Usable Fuel is the fuel available for flight planning Unusable Fuel is the quantifV of fuet that can not be safely used in flight Gallone Per Hour is the amount of fuel in gallons consumed per hour Nautical Miles ...

Page 14: ...vity is tho point at which an airplane or equipment would balance if suspended Its distance from the refergnce datum is found by dividing the total moment by the total weight of the airplane Center of Gravlty A rn is the arm obtained by adding the airplane s individual moments and dividing the sum by the total weight Center of Gravlty Limits are the extreme conter of gravity losations within which...

Page 15: ...etght is the maximum weight ap proved for the landing touchdown Tare is the weight of chooks blooks stands etc usedwhen weighing an airplane and is included in the scale read ings Tare is deducted from the sca le reeding to obtain tho actual net airplane weight 30 May 1980 1 9l 1 10 blank ...

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Page 17: ... Gravity Limits Norrnal Ca tegory Utility Category Maneuver Limits Normal Category UtÍlity Category Flight Load Factor Limits Norrnal Category Utility Category Kinds Of Operation Limits FueI Limitations Other Linitations Flap Limitations Placards SECTION 2 LIMITATIONS SECTION 2 LIMITATIONS Page 2 3 2 4 2 4 2 6 6 2 6 2 6 2 7 z 7 2 7 z 7 2 7 2 7 2 7 2 8 2 8 2 8 2 S z g u 10 2 10 2 10 30 May 198O P 1...

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

Page 20: ...ficance are shown in figure 2 2 SPEED KCAS KtAS REMARKS VNe Never Exceed Speed 152 158 Do not exceed this speed in any operat on Vruo Maximum Structural Cruising Speed 123 127 Do not exceed this speed except in smooth air and then only with caution V Maneuvering Speed 2400 Pounds 20ü Pounds 16ü Pounds 97 91 81 99 92 82 Do not make full or abrupt control movements above this speed Vre Maximum Flap ...

Page 21: ...TATIONS Engine Manufacturer Avco Lycoming Engine Model Number O 320 D2J Maximum Power 160 BHP rating Engine Operating Limite for Takeoffand Continuous Operations Maximum Engine Speed 2700 RPM NOTE The static RPM range at full throttle carburetor heat offand mixture leaned to maximum RPM is 2300 to 2420 RPM Maxinum Oil Temperature 245oF 118 C Oil Preesure Minimum t25 psi Maximum 115 psi Fuel Grade ...

Page 22: ...ggage Area 2 Station 108 to 142 60 lbs See following note l Zo psi red line and 60 90 psi green arc on airplanes modified by Sorvice Kit ISKU2 8r SKI 2 82 or SKr72 1234 30 MaY 1980 2 6 Revision2 1October1994 INSTRUMENT RED LINE GREEN ARC REO LINE MINIMUM LIMIT NORMAL OPERATING MAXIMUM LIMIT Tachometer Sea Level 5000 Feet 10000 Feet Oil Temperature Oil Pressure Fuel Quantity Standard Tanks Fuel Qua...

Page 23: ...LITY CATEGORY Center of Gravit5r Range Forward 35 0 inohos aft of datum at tgõO lbs or less with straight line variation to 36 õ inches aft of datum at 2100 lbs Aft 40 õ inches aft of datum at all weights Reference Datum Lower portion of front face of firewall MANEUVER LIMITS NORMAL CATEGORY This airplane is oertificated in both the normal and utility category The normal category is applicable to ...

Page 24: ...oeleration Abrupt use of the controle ie prohibited above gg knots a ny ma neuver and care should always be exercised to avoid excessive speed which in turn can impose exceseive loads In the execution of all m neuvers avoid abrupt use of controls Intentional spins with flaps extended are prohibited FLIGHT LOAD FACTOR LIMITS NOBMAL CATEGORY Flight Load Faotors Maximum Takeoff Weight 2400lbs iFlaps ...

Page 25: ...sable Fuel all fiight conditions õ0 U S gallons Unusable F uel 4 U S gallons 2Integral Tanks 34 U S gallons eaoh Total Fuel 68 U S gallons Usable Fuel all fiight conditions 62 U S Eallons Unusable Fuel 6 U S gallons NOTE To ensure maximum fuel oapaoity when refueling and minimize cross feeding when parked on a sloping surface place the fuel selectorvalve in either LEFT or RIGHT position Takeoff an...

Page 26: ...ormal Category Other operating limitations which must be complied with when operating this airptane in this category or in the Utility Category are oontained in the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual Normal Category No acrobatic maneuvers including spins approved Utility Category No acrobatic maneuvers approved except th ose listed in the Pilot s Operating Handbook ...

Page 27: ...TITUDES TAKEOFF LANDTNG LEFT 2õ GAL LEVEI FLIGHT ONLY R IGHT 25 GAL LEVEL FLIGHT ONLY OFF On the fuel selector valve integral tanks BOTH 62 GAI AIJL FLIGHT ATTITUDES TAKEOFF LANDING LEFT 31 GAL LEVEL FLIGHT ONLY R IGHT 31GAL I EVEL FLIGHT ONLY OF F 3 Near fuel tank filler cap standard tanks FUEL IOOLL 1OO MIN GRADE AVIATION GASOLINE CAP 21 5 U S GAL Near fuel tank filler cap long range tanks FUEL ...

Page 28: ...K oallout aleo mechanical detent at 10o Indioes at tJrese positione withwhite color aode and 85 kt callout also mechanical detent at 10o and 20o 6 In baggage compartment 7 A calibraiion card ie provided to indicate the accuracy of the magnetio compa ss in 30o increments 8 On oil filler cap OIL 7 QTS 120 POUNDS MAXIMUM BAGGAGE AND OTI AUXILIARY PASSENGEN FOËWAR D OF BAGGAGE DOOR LATCH õO POUNDS MAX...

Page 29: ...CEgSNA MODEI 172P SECTION S I IMITATION 9 On control lock CONTR OL LOCK REMOVE BEF ORE STAR TING ENGINE 10 Near airspeed indicator MANEIryER SPE ED 99 KIAS 30 May 1980 2 I3l t4 blank ...

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Page 31: ...Engine Power Precautionary Landing With Engine Power Ditching Fires During 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 A Flat Main Tire Electrical Power Supply System Malfunctions Ammeter Shows Excessive Rate of Charge Full Scale Deflection Low Volta...

Page 32: ...l Dive Inadvertent Flight Into Icing Conditions Static Source Blocked Spins Rough Engine Oporation Or Loss Of Power Carburetor Icing Spark Plug Fouling Magneto Malfunction Low Oil Pressure Electrical Power Suppty Systom Malfunctions Excessive Rate Of Cbarge Insufficient Rate Of Charge CESSNA MODEL 17gP Page 3 13 3 13 3 13 3 14 3 14 3 14 3 15 3 16 3 16 3 16 3 16 3 16 3 t7 3 t7 3 17 3 P B0 May 1980 ...

Page 33: ...cessa ry to correct the problem Emergency procedures associated with ELT and other optional systems can be found in Section 9 AIRSPEEDS FOR EMERGENCY OPERATION CESSNA MODEL 172P Engine Failure After Takeoffr Wing Flaps Up ïtling Flaps Down Maneuvering Speed 2400 Lbs 2000 Lbs 1600 Lbs Maximum Glide Precautionary lranding With Engine Power Landing Without Engine Power Wing Flaps Up ring Flaps Down O...

Page 34: ...LANDING WITHOUT ENGINE POWER 1 Airspeed 6õ KIAS fiaps UP 60 KIAS flaps DO ryN 2 Mixture IDLE CUT OFF 3 FueI Selector Valvo OFF 4 Ignition Switch OFF 5 Wing Flaps AS RESUIRED t0 recommended 6 Master Switch OFF 7 Doors UNLATCH PRIOR TO TOUCHDOWN 8 Touchdown SLIGHTLY TAIL LOW 9 Brakes APPLY HEAVILY PRECAUTIONARY LANDING WITH ENGINE POWER 1 ïtling Flaps 20o 2 Airspeed 60 KIÀS 3 Selected Field FLY OVER...

Page 35: ...vailable approach at 65 KIAS with flaps up or at 60 KIAS with 10o flaps 6 Cabin Doors UNLATCH 7 Touchdown LEVEL ATTITUDE AT ESTABLISHED RATE OF DESCENT 8 Face CUSHION at touchdown with folded coat 9 Airplane EVACUATE through cabin doors If necessary open window and flood cabin to equalize pressure so doors can be opened 10 Life Vests and Raft INFLATE FIRES DURING START ON GROUND 1 Cranking CONTINU...

Page 36: ... 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 F RE IN FLIGHT 1 Master Switch OFF 2 Avionics Power Switch OFF 3 AII Other Switches except ignition switch OFF 4 Vents Cabin Air Heat CLOSED 5 Fire Extinguisher ACTMTE if available After discharging an extingui...

Page 37: ...installed OFF NOTE Perform a sideslip to keep the flames away from the fuel tank and cabin and land as soon as possible using flaps only as required for final approach and touchdown ICING INADVERTENT ICING ENCOUNTER Turn pitot heat switch ON if installed Turn back or change altitude to obtain an outside air temperature that is less conducive to icing Pull cabin heat control full out and open defro...

Page 38: ...l sorape ice from a portion of the windsbield for visibility in the landing approach 10 Perform a landing approach using a forward slip if necessa ry for improved visibility 11 Approaoh at 65 to 7õ KIAS depending upon the emount of ttre accumulation 12 Perform a landing in level attitude STATIC SOURCE BLOCKAGE Erroneous lnstrument Reading Suspected 1 Alternate Static Source Valve PULL ON 2 Airspee...

Page 39: ... conditions with an electrical load on the system such as during a low RPM taxi Under theee conditions the lightwill go out at higherRPM Themastor switchneednot be rocycled since an over voltage condition has not occurred to de activate the alterna tor system 1 Avionics Power Switch OFF 2 Alternator Circuit Breaker CHECK IN 3 Master Switch OFF both sides 4 Master Switch ON ã Low Voltage Light CHEC...

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Page 41: ...The checklist procedures assume that adequate time exists to secure the fuel and ignition systems prior to touchdown After an engine failure in flight the best glide speed as shown in figure 3 1 should be established as quickly as possible While gliding toward a suitable landing area an effort should be made to identify the cause of the failure If time permits an engine restart should be attempted...

Page 42: ... height over a wa ter surface LANDING WITHOUT ELEVATOR CONTROL Trim for horizontal flight with an airspeed of approximately 6õ KIAS and flaps set to 20o by using throttle and elevator trim controls Then do not change the elevator trim control setting control the glide angle by adjusting power exclusively At flareout the nose down moment resulting from power reduction is an adverse factor and the a...

Page 43: ...eveling the miniature airplane 4 Check a ccuracy of the turn by observing the compass heading whioh should be the reciprocal of the original heading 5 If necessary adjust heading primarily with skidding motions rather than rolling motions so that the compass will read more accurately 6 Maintain altitude and airspeed by cautious applioation of elevator control Avoid overcontrolling by keeping the h...

Page 44: ...ator back pressure to slowly reduce the airspeed to 8O KIAS 4 Adjust the elevator trim control to maintain an 80 KIAS glide õ Keep hands off the control wheel using rudder control to hold a straight heading Adjust rudder trim if installed to relieve unbalanced rudder force 6 Apply carburetor hea t 7 Clear engine occasionally but avoid using enough power to disturb the trimmed glide 8 Upon breaking...

Page 45: ...s within 50 feet of normal SPINS Should an inadvertent spin occur the following recovery procedure should be used 1 RETAR D THROTTLE TO IDLE POSITION 2 PLACE AILERONS IN NEUTRAL POSITION 3 APPLY A ND HOLD FULL R UDDER OPPOSITE TO THE DIREC TION OF N OTATION 4 JUST AI TER THE IIUDDER REACHES THE STOP MOVE THE CONTR OIJ WHEEL BN ISKLY FORWAR D FAR ENOUGH TO BREAI THE STALL FuIl down elevator may be ...

Page 46: ...everal minutes determine if a richor mixture setting will produce smoother operation If not proceed to the nearest airport for repairs using the BOTH position of the ignition switch unless extreme roughness dictates the use of a single ignition position MAGNETO MALFUNCTION A sudden engine roughness or misfiring is usually evidence of magneto problems Switching from BOTH to either L or R ignition s...

Page 47: ...hough other factors could ca use the problem A defective alternator control unit can also cause malfunctions Probtems of this nature oonstitute an electrical emergency and should be dealt with EXCESSIVE RATE OF CHARGE After engine sta rting and heavy electrical usage at low erigine speeds such as extended taxiing the battery condition will be low enough to accept above normal chargin after thirty ...

Page 48: ... 1o do this tu n the avionios power switoh off oheok that tho alternator oir uit breaker is ln tben turn both sides of the master switch off and then on again If the problem no longer exists no rnal alternator charging will resume and the low voltage lightwill go off The avionios power switch may then be turned back on If the light illuminates again a malfunction is oonfirrned In this event the fl...

Page 49: ...Edge Left ïViñg Trailing Edge Before Starting Engine Starting Engine Beforeiaxeõtt Takeoff Normal Takeoff Short Field Takeoff Enroute Climb Cruise Descent Before Landing Landing Normal Landing Short Field Landing Balked Landing After Landing Securing Airplane CHECKLIST PROCEDURES 4 õ 4 5 4 6 4 5 4 5 4 6 4 6 4 6 4 6 4 7 4 7 4 7 4 8 4 8 4 8 4 8 4 9 4 9 4 9 4 9 4 9 4 9 4 10 4 to 4 to 4 tr 4 tI Starti...

Page 50: ...se CESSNA MODEL 172P Page Leaninp With A Cessna Economy Mixture Indicator EGT 4 L3 4 LS 4 13 4 t3 4 13 4 L3 4 L4 4 15 4 1õ 4 Lá 4 17 4 t7 4 L7 4 t9 4 19 4 ZO 4 20 4 20 4 21 4 2L 4 25 4 23 4 29 Stalls Spins Landing Normal Landing Short Field Landing Crosswind Landing Balked Landing Cold ÃIeather Operation Starting Flight Operations Hot Weather Operation Noise Characteristics 4 2 30 May 1980 ...

Page 51: ... lesser weight However to achieve the perforrnance speoified in Section 5 for takeoff distanoe the speed appropriate to the particular weight must be used Takeoff Flaps Up Normal Climb Out Short Field Takeoff Flaps 10o Speed at 50 Feet Enroute Climb Flaps Up Normal Sea Level Normal 10 000 Feet Best Rate of Climb Sea Level Best Rate of Climb 10 000 Feet Best Angle of Climb Sea Level Best Angle of C...

Page 52: ...and control surfaces Also make sure that control gurfaces contain no internal aocumulations of ice or debris Prior to flight check that pitot heater if installed is warm to touch within 30 seconds with battery and pitot heat switches on If a night flight is planned check operation of all lights and make sure flashlight is available CESSNA MODEL 172P 4 4 Figure 4 1 Preflight Inspection 30 May 1980 ...

Page 53: ...t maÌfunction could cause the propeller to rotate 6 Fuel Quantity Indicators CHECK QUANTITY 7 Avionics Cooling Fan CHECK AUDIBLY FOR OPERATION 8 Master Switch OFF L Static Pressure Alternate Souroe Valve if installed OFF 10 Baggage Door CHECK lock with key if child s seat is to be occupied EMPENNAGE 1 Rudder Gust Lock REMOVE 2 TaiI Tie Down DISCONNECT 3 Control Surfaces CHECK freedom of movement a...

Page 54: ... Carburetor Air Filter CHECK for restrictions by dust or other foreign matter 6 Nose Wheel Strut and Tire CHECK for proper inflation 7 Nose Tie Down DISCONNECT 8 Static Source Opening left side of fusetage CHECK for stop page LEFT WING L Main ïVheel Tire CHECK for proper inflation 2 Before first flight of the day and after each refueling use sempler cup and drain small quantity of fuel from fuel t...

Page 55: ... engine is warm 5 Throttle OPEN UB INCH 6 Propeller Area CLEAR 7 Ignition Switch START release when engine starts 8 Oil Pressure CHECK L Flashing Beacon and Navigation Lights ON as required 10 Avionics Power Switch ON 11 Radios ON BEFORE TAKEOFF 1 Parking Brake SET 2 Cabin Doors and Vtlindow s CLOSED and LOCKED 3 Flight Controls FREE and CORRECT 4 Flight Instruments SET 5 Fuel Selector Valve BOTH ...

Page 56: ...FT NOSE WHEEL at 55 KIAS 5 Climb Speed 70 80 KIAS SHORT FIELD TAKEOFF 1 Wing Flaps 10o 2 Carburetor f eat COLD 3 Brakes APPLY 4 Throttle FULL OPEN 5 Mixture RICH above 3000 feet LEAN to obtain maximum RPM 6 Brakes A ELEASE 7 Elevator Coritrol SLIGHTLY TAIL LOW L Climb Speed õ6 KIAS until all obstacles are cleared ENROUTE CLIMB 1 Airspeed 70 85 KIAS NOTE If a maximum performance climb is necessary ...

Page 57: ...e BOTH 3 Mixture RICH 4 Caiburetor Hoat ON appfy fult heat before reducing power 5 Autopilot if installed OF F 6 Air Conditioner if installed OFF LANDING NORMAL LANDING 1 Airspeed 65 75 KIAS flaps UP 2 Wing Flaps AS DESIRED 0 10o bolow 110 KIAS 10o 30o below 85 KrAS 3 Airspeed 60 70 KIAS flaps DOWN 4 Touchdown MAIN WHEELS FIF ST 5 Landing Roll LOïVER NOSE WHEEL GENTLY 6 BrakÍng MINIMUM REQUIRED SH...

Page 58: ...s 1Oo until obstacles are cleared RETRACT after reaohing 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 Electrical Equipment Autopilot if installed OFF 8 Mixture IDLE CUT OFF pulled full out 4 Ignition Switcb OF F 5 Mastor Switoh OFF 6 Control Lock INSTALL 4 10 30 May 1980 ...

Page 59: ...ssure within 30 seconds in the summertime and about twice that long in very cold weather stop engine and investigate Lack of oil pressure can cause serious engine damage After starting avoid the use of carburetor heat unless icing conditions prevail NOTE Additional detaits concerning cold weather starting and operation may be found under COLD WEATHER OPERA TION paragraphs in this section TAXIING W...

Page 60: ... and sharp bralring when the airplane ls ln thls attitude Use the steerable nose wheel a rd rudder to malntaln directlon USE UP ÀTLERON ON RH WING AND NEUTRAL ELEVATOR USE UP NLERON ON LIT WING AND NEUTRAL ELEVATOR USE IþWN AILERON ON RH WING AND DOWN ELEVATOR USE DOTI N AILERON ON LII II ING AND DO N ELEVATOR 4 12 Figure 4 2 Taxiing Diagram 3O May 1980 ...

Page 61: ...faulty grounding of one side of the ignition system or should be cause for suspicion that the magneto timing is set in advance of the setting specified ALTERNATOR CHECK Prior to flights where verification of proper alternator and alternator control unit operation is essential such as night or instrument flights a positive verification can be made by loading ttre electrical system momentarily 3 to ...

Page 62: ...eeping back from a maximum power position Similar friction lock adjustments should be made as required in other flight conditions to maintain a fixed throttle setting WING FLAP SETTINGS Normal takeoffs a re accomplished with wing flaps 0o 10o Using l0o wing flaps reduces the ground roll and total distance over an obstacle by approximately 10 percent Flap deflections greater than 10o are not approv...

Page 63: ...ay be leaned above 8000 feet for smoother operation or to obtain maximum F PM For maximum rate of climb use the best rate of climb speeds shown in the Rate of Climb chart in Section 5 If an obstruction dictates the use of a steep climb angle the best angle of climb speed should be used with flaps up and maximum power Climbs at speeds lower than the best rate of climb speed should be of short durat...

Page 64: ...ruise at higher thanTíVo 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 full carburetor heat Upon regaining the original RPIIf with heat off use the minimum amount of heat by trial and error to prevent ice from formÍng Since the heated air causes a richer mixture readjust th...

Page 65: ... 4 4 As noted in this table operation at peak EGT provides the best fuel economy This results in approximately 4qo grea tet range than shown in this handbook accompanied by approximately a 3 knot decrease in speed Under some conditions engine roughness may occur while operating at peak EGT In ühis c se operate at the Recommended Lean mixture Any change in altitude or throttle position will require...

Page 66: ...r seat s are not approved The normal entry is made from a power off stall rA s the stall is approached the elevator control should be smoothly pulled to the full aft position Just prior to reaching the statl break rudder control in the desired direction of the spin rotation should be applied so thatfuil rudder deflection is reached almost simultaneousty with reaching full aft eleva tor A slightly ...

Page 67: ... FROM THE RESULTING 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 in basic airplane rigging or in weight and balance due to installed eguipment or right seat occupancy can cause differences in behavior particularly in extended spins These differences are norm...

Page 68: ...of the airplane Touchdown should be made with power off and on the main wheels first Immediately aftertouchdown Iowerthe nose wheel and apply heavy braking as required For maximum bra ke effectivenees retract the flaps hold the control wheel full back and apply maximum brake pressure without sliding tho tires CROSSWIND LANDING When landing in a strong crosswind use the minimum flap setting require...

Page 69: ...se of an externa l preheater and an external power source are recommended wheneve possible to obtain positive starting and to educe wear and abuse to the engine and electrical system Pre heat will thaw the oil trapped in the oil cooler which probably will be congealed prior to starting in extremely cold temperatures When using an external power source the position of the master switch is important...

Page 70: ... Leave on until engine is running smoothty Primer LOCK 2 3 4 Ð 6 7 L o 10 11 L2 NOTE If the engine does not start during the first few attempts or if engine firing diminishes in strength it is probable that the spark plugs have been frosted over Preheat must be used bofore another start is attempted CAUTION Pumping the throttle may cause raw fuel to accumulate in the intake air duct creating a fir...

Page 71: ...ise ou the public We as pilots can demonstrate our concern for environmental im provement by application of the following suggested procedures and thereby tend to build public support for aviation 1 Pilots operating aircraft under VFF over outdoor assemblies of persons recreational and park areas and other noise sensitive a rea s should make every effort to fly not less than 2000 feet above the su...

Page 72: ...ee and avoid other aircraft The certificated noise level for the Model L72P ut 2400 pounds ma xi mum weight is 73 8 dB A No determination has been made by the Federal AviationAdministrationthatthe noisolevels of tbis airplane a re or should be acceptable or unacceptable for operation at into orãut of any airport 4 24 30 May 1980 ...

Page 73: ... Speeds Figure 5 4 Takooff Distance 2400 Lbs Takeoff Distance 22OO Lbs and 2000 Lbs Figure 5 õ Maximum Rate Of Climb Figure 5 6 Time Fuel And Distance To Ctimb Figure õ 7 Cruise Performance Figure 5 8 Range Profile 40 Gallons Fuel Range Profile õ0 GaIIons Fuel Range Profile Q2 Gallons Fuel Figure 5 9 Enduranoo Profile 40 Gallons FueI Endurance Profile ã0 Gallons Fuet Endurance Profile 62 GaIIons F...

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Page 75: ...inutes reserve fuel at the specified power setting Fuel flow data for cruise is based on the recommended lean mixture selting Some indeterminate variables such as mixture leaning techniquo fuel metering characteristics engine end propeller condition and air turbulence ma y a ccount for variations of 107o or more in range and endurance Therefore it is important to utilize all available information ...

Page 76: ...400 pounds pressure altitude of 2000 feet and atempereture of 30oC sbould be used and results in the following Ground roll 1200 Feet Total distance to cloar a õO foot obstacle pp20 Feet These distances are well within the available takeoff field length How ever a correction for the effect of wind may be made based on Note B of the takeoff ohart The correction for a 12 knot headwind is 12 Knots I K...

Page 77: ... nea rly corres pond to the planned altitude end expected temperature conditions The engine speed chosen is 2500 RPM which results in the following Power 667o True airspeed 112 Knots Cruise fuel flow 7 4 GPH The power computer may be used to doterrnine poÌver and fuel conaump tion more accurately during the flight ruel REoUtRED The total fuel requirement for the flight may be estimated using the p...

Page 78: ... Total fuel required 1 6 0 3 1 9 Gallons 320 12 808 Nautioal Miles 1 1 1 9 22 2 ã 6 30 8 Gallons ïtlith an expooted 10 knot headwind the ground speod for cruiso is predicted to be 112 10 iõãKnots Therefore the tisre required for the cruise portion of the trip is 308 Nautical Miles _ i5 Ail 3 0 Hours The fuel required for cruise is 3 0 hours 7 4 gallons hour 22 2 GaIIons A 45 minute reserve require...

Page 79: ...istance to clear a õ0 foot obstacle 1390 Feet A correction for the effect of wind may be made basod on Note 2 of the Ianding chart using the same procedure as outlined for takeoff DEMONSTRATED OPERATI N G TEM PERATUR E Satisfactory engine cooling has boen demonstra ted for this airplane with an outside air temperature 23oC above standard ThÍs is not be to considered a s a n operating limitation Re...

Page 80: ...light or maximum rated RPM d ve Figure 5 1 Airspeed Calibration Sheet 1 of 2 FLAPS UP KIAS KCAS 50 60 70 80 90 56 62 70 79 89 100 98 110 107 120 117 130 126 140 135 150 145 160 154 FLAPS 1OO KIAS KCAS 40 50 60 70 80 90 49 55 62 70 79 89 100 98 110 108 FLAPS 3OO KIAS KCAS 40 50 60 70 80 85 47 53 61 70 80 84 5 8 80 May 1980 ...

Page 81: ... 50 60 70 79 83 FLAPS UP NORMAL KIAS ALTERNATE KIAS 40 50 60 70 80 90 36 48 59 70 80 89 120 118 130 140 128 139 100 110 99 108 FLAPS 1OO NORMAL KIAS ALTERNATE KIAS 40 50 60 70 80 90 38 49 59 69 79 88 100 97 110 106 FLAPS 3OO NORMAL KIAS ALTERNATE KIAS 40 50 60 70 80 85 34 47 57 67 77 81 FLAPS UP NORMAL KIAS ALTERNATE KIAS 40 50 60 70 80 90 26 43 57 70 82 93 100 103 110 113 120 123 130 133 140 143 ...

Page 82: ... õ PER FOR MANCE F u I z U E I u U U U lr 9 r J o TEMPERATURE CONVERSION CHART 120 100 80 40 20 020 DEGREES CELSIUS 40 60 40 20 CESSNA MODEL 172P 20 õ 10 40 Figure 5 2 Temperature Conversion Chart 80 May 1980 ...

Page 83: ...õ PEN FORMANCE I è WEIGHT LBS FLAP DEFLECTION ANGLE OF BANK Oo 300 450 6oo KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS 2400 UP 100 300 44 35 33 51 48 46 47 38 35 55 52 49 52 42 39 61 57 55 62 49 47 72 68 65 WEIGHT LBS FLAP DEFLECTION ANGLE OF BANK Oo 300 450 60o KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS 2400 UP 100 300 44 37 33 52 49 46 47 40 35 56 53 49 52 44 39 62 58 55 62 52 47 74 69 65 30 May 1980 F...

Page 84: ...by 15 of the ground roll f gure 4ooc TOTAL TO CLEAR 50 FT OBS 1945 2155 2355 2685 3030 3455 3990 GRND ROLL r065 1170 1290 1425 1575 t745 1940 3ooc TOTAL TO CLEAR 50 FT OBS t810 20 x 2220 2480 2790 3160 3620 4220 GRND ROLL 995 1090 t200 1325 1465 1 620 1800 2000 200c TOTAL TO CLEAR 50 FT OBS 1685 1860 2060 2295 2570 2895 3300 3805 44AO GRND ROLL 925 1015 1115 123o 1355 1 500 1665 I 850 2060 100c TO...

Page 85: ...0 FT OBS 1375 r 510 1 660 1835 20Æ 2275 2555 2890 3305 1110 1215 1330 1465 161 5 1790 1990 2225 2500 GRND ROLL 750 825 905 995 1100 1210 1340 1485 1650 605 665 725 800 880 970 t070 1 180 1310 looc TOTAL TO CLEAR 50 FT OBS 1 280 1 405 1 545 1705 1890 2105 2355 2655 301 5 1035 1 135 1240 1 365 1500 1660 1845 2055 2305 GRND ROLL 700 765 Srto 925 1020 1125 124o 1375 1 525 565 615 675 7N 8 t 5 900 990 ...

Page 86: ... Maximum Rate of Climb MAX MUM RATE OF CLIMB CESSNA MODEL 172P WEIGHT LBS PR ESS ALT FT CLIMB SPEED KIAS RATE OF CLIMB FPM 20 c ooc 20 c 4ooc 2400 S L 2000 4000 6000 8000 10 000 12 000 76 75 74 73 72 71 70 805 695 590 485 380 275 115 745 640 535 430 330 225 125 685 580 480 375 275 175 625 525 420 320 220 5 t4 30 May 1980 ...

Page 87: ...erature 4 Distances shown are based on zero wind WEIGHT LBS PRESSURE ALTITUDE FT TEMP oç CLIMB SPEED KIAS RATE OF CLIMB FPM FROM SEA LEVEL TIME MIN FUEL USED GALLONS DISTANCE NM 2400 S L 1 000 2000 3000 4000 5000 6000 7000 8000 9000 10 000 11 000 12 OOO 15 13 11 I 7 5 3 1 3 5 7 9 76 76 75 75 74 74 73 72 72 7 71 70 70 700 655 610 560 515 470 425 375 330 285 240 190 145 0 1 3 5 7 I 11 14 17 20 24 29...

Page 88: ... 52 74 67 61 55 50 67 64 59 53 110 104 99 92 115 109 104 98 91 114 108 103 96 90 119 113 108 101 95 118 112 106 100 93 1 1 4 1 05 98 8 1 7 3 6 6 6 0 8 6 7 8 7 O 6 3 5 8 8 2 7 4 6 7 6 1 5 7 8 7 7 8 1 1 6 4 6 0 8 3 7 5 6 8 6 3 5 8 7 5 7 2 6 6 6 l 76 69 62 55 50 76 73 65 59 54 48 77 69 63 57 52 47 77 73 66 60 55 50 70 64 58 53 49 64 6 l 56 51 114 109 103 97 91 117 114 108 102 96 89 119 113 107 101 95...

Page 89: ...d Lean Mixture for Cruise Standard Temperature Zero Wind NOTE This chart allows for the fuel used for engine start taxi takeoff and climb and the distance during climb 12 000 10 000 8000 6000 4000 2000 s L 400 450 500 550 RANGE NAUTICAL MILES t r J tu u I t J ô f t tr J 30 May 1980 F igure 5 8 Range Profile Sheet 1 of 3 600 õ lV ...

Page 90: ...d Lean Mixture for Cruise Standard Temperature Zero Wind NOTE This chart allowi for the fuel used for engine start taxi takeoff and climb and the distance during climb 12 000 10 000 8000 6000 4000 2000 S L 550 600 650 700 750 RANGE NAUTICAL MILES F IJJ I JJ tl r o f F F J 1 112 5 18 Figure 5 8 Range Profile Sheet 2 of 3 30 May 1980 ...

Page 91: ... for Cruise Standard Temperature Zero Wind NOTE This chart allows for the fuel used for eng ne start taxi takeoff and climb and the distance during climb 12 000 10 000 8000 6000 4000 2000 S L 700 750 800 850 900 950 RANGE NAUTICAL MILES F uJ t t t rJ o l t tr J 01 14 20 11 AS 112 AS 105 KT KT 80 May 1980 Figure 5 8 Range Profile Sheet 3 of 3 õ 19 ...

Page 92: ...unds 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 6000 4000 2000 s L 3 6 F ul t J lJ I uJ o l t tr J 4 7 ENDURANCE _ HOURS õ 20 Figure õ 9 Endurance profilo Sheet 1 of B 30 May 1980 ...

Page 93: ...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 OOO 10 000 8000 6000 4000 2000 s L 4 6 7 ENDURANCE _ HOURS t I JJ rlJ t L I uJ o f F F J F 30 May 1980 Figure 5 9 Endufance Profile Sheet 2 of 3 I 6 2r ...

Page 94: ...45 MINUTES RESERVE 62 GALLONS USABLE FUEL CESSNA MODEL 172P NOTE This chart allows for the fuel used for engine start taxi takeoff and clímb and the time during climb t trJ lrl tL I IJJ o l t t J 12 000 10 000 8000 6000 4000 2000 S L 6 8 I ENDURANCE _ HOURS 7 É 5 22 Figure õ 9 Endurance profile Sheet B of B 10 80 May 1980 ...

Page 95: ...1350 1390 1425 1460 15ü 1540 1580 1630 1675 GRND ROLL 585 610 630 655 680 705 730 760 790 300c TOTAL TO CLEAR 50 FT OBS 1325 1360 1390 1430 1470 1510 1 550 1 590 1635 GRND ROLL 570 590 610 635 660 685 710 735 765 2ooc TOTAL TO CLEAR 50 FT OBS 1 295 1325 1360 1395 1430 1470 1510 1550 1595 GRND ROLL 550 570 590 615 635 660 685 710 740 looc TOTAL TO CLEAR 50 FT OBS 1265 1295 1330 1360 1400 1435 1470 ...

Page 96: ......

Page 97: ...BLE OF CONTENTS Introduction Airplane Weighing Procedures Weight And Balance Equipment List SECTION 6 I EIGHT BALANCE ESUIPMENT LIST 6 3 6 3 6 6 6 13 SECTION 6 WEIGHT BALANCE EQUIPMENT LIST Page 30 May 1980 6 tl 6 2 blank ...

Page 98: ......

Page 99: ...rain 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 2 Leveling a Place scales undor each wheel minimum scale capacity 500 pounds nose 1000 pounds each main b Deflate the nose tire and or lower or raise the nose strut to properly center the bubble in the level see figure 6 1 3 Wei...

Page 100: ...bol Net We ght Left Wheel L Right Wheel R Nose Wheel N Sum of Net Weights As Weighedl w Item Moment 1000 Weight Lbs l a O Orr n l Lbs ln l Airplane Weight From ltem 5 page 6 31 Add Oil 8 Ots at 7 5 Lbs Gall 15 0 14 0 o 2 Add Unusable Fuel Std Tanks 3 Gal at 6 Lbs Gall L R Tanks 4 Gal at 6 Lbs Gall lntegral Tanks 6 Gal at 6 Lbs Gall 46 0 46 0 46 0 Equipment Changes Airplane Basic Empty Weight 6 4 F...

Page 101: ...ht and Balance g Ëo öE cd ËR 3Fo EÞTd zla iÞ l 5ãÞ nEt4 ts CD olI r PAGE NUMSER BUNNING BASIC EMPTY WEIGHT Moment 1 000 W flb WEIGHT CHANGE REMOVED I Moment r000 SEBIAL NUMBER Arm ln wt 0b ADDED Moment r000 Arm ln wt rb AIRPLANE MODEL DESCRIPTION OF ARTICLE OR MODIFICATION ITEM NO Out ln DATE Figure 6 2 Sample Weight and Balance Record ...

Page 102: ... 1000 for each additional item to be carried then list these on the loading problem NOTE Loading Graph information for the pilot passengers and baggage is based on seats positioned for average occu pants and baggage loaded in the center of the baggage areas as shown on the Loading Arrangements diagram For loadings which may differ from these the Sample Loading Problem lists fuselage stations for t...

Page 103: ...ntegral tanks is located at stot on 48 0 2 The rear æbin wall approximate station 108 or aft baggage wall lapproximate station 1421 can be us d as convsnienl interlor reference points for dotermining the location of baggEge ârea fuselage stâtions 142 STANDAED SEATING Figure 6 3 Loading Arrangements SECTION 6 WEIGHT BALANCE ESUIPMENT LIST OPTIONAL SEATING STATION C G ABM 34 to 46 STATION C G ARMI 3...

Page 104: ...R OPENING DIMENSIONS HEICHI IREARI 39 21 CABIN WIDTH MEASUREMENTS f INSTRU YIENI PANET EAR DOORPOsI BUI KHEAO IflIDIH twR w Dow IINE rt CABIN FIOOR 2lYz l I 70 0 I tl I o I 90 2 3 142 ro 20 30 40 50 óo 6 5 3 o ot ot o 140 i 43 l WIDTH lroPl WIDTH BOrroru HEIGHT lf roNrl 32 16V 37 16U OYr 22 t t t t 9 I I 5 29 3 os0h l__ 3 ó 3 2 t 6 8 Figure 6 4 Internal Cabin Dimensions 30 May 1980 ...

Page 105: ...ront Pasençr Station 34 to 46 4 Rear Passengers 5 Baggge Area I or Passenger on Ghild s Seat Station 82 to 108 120 Lbs Max 6 F Baggage Area 2 Stat on lOBto 142 50 Lbs Max 7 RAMP WEIGHT AND MOMENT 8 Fuel allowance for engine start taxí and runup 9 TAKEOFF WEIGHT AND MOMENT Subtract Step 8 from Step 7 10 Locate this point 2 t00 at 107 8 on the Center of Gravity Moment Envelope and since this po nt f...

Page 106: ... pasençr centc of grwity m ad ul ble æat positioned for an avsragE ooci Psnt Refer æ the Loading ArrångemenG diagram for forward 8nd aft l miß of occupcm C G range Figure 6 6 Loading GraPh 350 4æ ãD lq 350 CD 2æ ãx 150 t x 50 175 6 É I o I I 9t ê o J o Ee r ìã Íit 7 À f FdÞ qt o 3 F o l o g z t o g 9 t ê o 1f 125 75 c 25 0 0 MAXIMUM I SA8LE FUEL r STANDARO TANKS rT LONG RANGE TANKS fi INTEGRAL TAN...

Page 107: ... 9 o J g Iu t t z È É ot J o o 2üX 1900 ræ0 r7m t6 n 95 900 850 8 Il 7æ 7û o Þ 60 65 70 75 æ 85 90 95 100 105 110 LOADED AI RPI ANE MOMENT 1 Oü POUND I NCHESI É lã Eff dq ËR 3tro rdÞtd zÈ1 c iÞÊ øez Et cÞ NORtTiAL CATEGORY CENTER OF GRAVITY MOMENT ENVELOPE rrtt ltltlt tat ttlltltlttrrltt lllll lllll llllt r Ittttllttllzt ltrlr It l rt r 50 55 Figure 6 7 Center of Gravity Moment Envelope ...

Page 108: ...tlltt llttt ltrrr lllr ltrlt r t lttttltl r rrtt tttttlr a r t tr rlllt tltltlt lllllt trr tltttt ltt t ttr r lrrrrr tltr trrt lr rrIIt ttltt r tltt ltrt rr Iltttltttttt tllttlltrrr ttt t trtt tttl tr r lr t ttltl rr tlr tltltttt lllrltrtrtr ltttttlrtltr tltttt l ttl rl llllltt l rtltt tllttl rrtl rllr r tttrtttttttr Illt llrl ltr rltl lltt tttt tttt tttt tllt rttt tt t t tt Ittt lttlr lttlttlt r ...

Page 109: ...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 equipment is to be installed it must be done in accordance with the reference drawing áccessory kit instruc tions or a separate FAA approval Columns showing welght in pounds and arm in Inches provide the weight and center of gravity l...

Page 110: ...P PAD SPARK ARBURETOR FILTËRT CARBURÊTOR AIR ALTERNATORT 28 VOLI óO AI P OIL COOLER INSTALLAIION IL COOLER OII FILTËR INSTALLATION SPIN_ON ELÉÍ IËNTI NEI CHANGE PROPÊLLER ASSY IFIXED PIÌCH LANDPLANEI PRC PELLER I CCAULEYI fROP SPACER AÚAPTER IICCAULEYI PROPEII ER ASSY FIXED PTTCI I FLBATPLANE PROPÊLLER T CCAULEY ROP SPACER ADAPTER IICCAULEY SPINNEE INSTALLATIONT PROPELLER sPrNNÊR 00llÊ FT O SPINNÉ...

Page 111: ...SE HHEÊL ASSY T HCCAIJLEY TIRÊ 4 PLY bLACKI ÚALL I UBL FAIRING INSIALLATITN lt OSÊ l hrEL FA KING I1A1N HHTEL ÉAIRINú IÉACFII BRAKÉ FAIRINGS 2 C ÊLÊCTRICAL SYSIÉI IS gAIIERYT 2 VOLTr SfANDARD DtrTY tsAITERY 24 V LT hhAVY CUTY 4 I ERryA10t çGNTRGL rJr tTr ZB VeLT t ITFt HIGH AND LO I VGLIAGË SENSING GRúUN0 SERVICc PLTJG kECEPIACLÉ HEATING SYSTEI FIIOT INET CHANGÊI l IQÞIS INSJRU iENI pt sT È ÊQUIRE...

Page 112: ...T NAVIGATION LIGHT SÊT OF 2 LIGHÍ INSTALLATIONT OFINIFLASH BEACON BEACON LIGHT OÑ FIN TIP FLASHËR PO TÊR SUPPLY RESISïoR lr tEüCoRl IISC HARDIIARE LIGI IT INSTALLAf IONT I ING TIP STROBÊ FLASHER POIIÊR SUPPLY ISEÎ OF 2I STROEE LIGHTT IING TTP SET OF 2 IRING A HARD ÚARE LIGHT INSÏALLATION CO IL I OUNIÊD LANOING LAHP 25O htATl G E l L IGHI S T DUAL CO IL I OUNTED LANDING LAÈIPr IOO I ATT G E fÊACH D...

Page 113: ...TON FEEÍ At D nn uBARs ALTII IER zND t Î ff NSrAU T ON ltuAL ENCOOIÎ G ALIIMEIER BEc ulREs Ftr ocAfloN oF BEGUI AR ALÍ MEIER E I IXNGALTIMEIEF FEET MILUBA BS REqJßES RÉOCAT ON OF REGULAR ALrlMErEn ALÎMJDE EI CODEF BUND DOES NOTREGUIRE INS IBI I IENT PA NE IIOJNING AMMEIER GAGE CARBIJRETOR AIR TE IPÉTìAIURE ct oo ELEgfFlc CL rcK DGTÁI BEADOT T COI FASS lrAGNEllC NSífAtl ATtON NSÎFilrIÆNICLuSTER LH ...

Page 114: ... 28 VOLT ONLy INDICATOR TURN COORDTÍ ATORT 10 30 VOLT INDICATÛRI TURN COORDINATOR FOR USE IITH NAV I Í IAÏIC 2OOA AND 3OOAI IND CATOR VERTICAL SPEEO E CABIN ACCOI IIODATIONS SEATr ADJUSTATìLE FORE Â AFT PILoT SEATT INFINIIE ADJUSTABLE PILOT SEAÏ ADJUSTABLÊ FORË 6 AFT CO PILOT SEAT INFTNITÊ ASJUSTABLE CO PILOT SEAT REAR ONE PIECË 8 ACK CUSHIONI SEAT REAR T IO PIECÊ BACK CUSHIONI PILOT LAP EELT ASSY...

Page 115: ...SEAT CI JVÉRING INET CHANGE LÊATHER T VIIYYL ÚR FABRIC COVÉR ÍNET CHG IINOOIÚ IIINGbt Rh E C GR NET CHAN6EI TIINTOIS OVÊKHÊAt CAÊ IN IOP NÊT CFIANËÉ VÉNTILATIDN SYSTEH RÉAR 5EAT INGT COM PATIBLE hIIH bôB A I OR E8S A I BÊVËRAGÈ CUP hOLDIR HEAI RESTT IST ROH 5Éï 0F 2 HEADRESÏ 2ND ROI SET OF 2T SUtt VISÛRS I SET üF 2l HINDOHST TINTEO CA8IN NÉI CHANGËI APPROACH PLATE FIULI JÉR INSTALLATION tsAGGAGÊ N...

Page 116: ...TOR AIR EXHAUST SYSTEI I INCLUOED NOÏE_CARBURETOR IIÊAT IS R SUIRED ITE CABlN HEAT IS SIANOARD ITEI F PLACAROS IIARN INGS T Í ANUALS PLACARO ÚPERATIONAL LII IITATIONS OAY vFR PLACARO OPERATIONAL LI TTIATIONS DAY NIGhT VFR PLACARÐT OPËRAlIBNAL LIli ITAIIONS DAY NIGHI VFR E IFR PLACARO ÜPERATIONAL LIITITATIONS OAY VFR FLOAI PLANË PLÀCARO OPERÀTIONAL LI IIATIONS DAY NTGHT VFR FLOATPLANE PLACARDT ÜPË ...

Page 117: ...NG CABIN TT PI CORRT SIOÑ PRGOF INt INTERNAL STAIIC DISCHARGTRS STABILIZËF AERASION EI JOTS Tol BAR l5ì Ot Ê t PAINT T ÜVERALL ËXTERIÜR OVERALL HHITË 6A5Ê OLCR STRIPE CABLESI COF ROSION RLSISTANT COI IROL NET CHANGE FIRE ÈXfIIIGUIShER 1NS FIRE ËXT INGUIShER FIRÊ ÊXTINGUISHEK IALLAT ION HOUNTING CLAI P FIRE EXÏINGUISrlER INSTL VERTICAL ADJ SÊAI STbPS T HANDLTS RÊFUÉLING ASSISIING RUÚDËR PhËAL EXÏIN...

Page 118: ... EDl eor ourleT covÊR ll sroHED FUÉL SYSTËI1 ËXIENIjED RANGE T ING TANKS fNEl CHANGE 6ó 6ALLON CAPACITYI FUÊL SYSTEI ËXTENUEO RANGE IIET HINGS NET CHANGE I FI ÀVIONICS E AUTOPILOTS CËSSNA 30Ú ADF INSTALLATITJN RÊCEMR hllh EFGr R 54ôE INDICATOR IN 34 ÓA SEÑSt ANTËNNA INSTALLATION LOOP ANTENNA NSIALLAIION trlhEs r MÚUNTING 6 l ISC lrE rs CESSNA 3OC ADF INSTL T IIIO AP CASÉ sAñE AS hol A Ir ËxcEPT IA...

Page 119: ...or r5T t 2Nû uNIl r NÉr cHGl ARC LOC INDICATOR ADOED VOR LOC INþICATOR TJELETED AUTO RADIAL CENTERING INDICATTJR ARC ILS ÊXCHANGE FOR VC IRIILS INOICATOR USED IIÏI t ITÉ HO A SNLY XT NET CI IANGEI ARC ILS INDICATOR ADOED VOR ILS INOICATOR ÛELETED SUNAIR ASE IZ I IF TRANSCËIVER NO UNII ANTET NA LOAI bOX PO IER SUPPLY RÊI OTE TRANSCÉIVER IPANEL I OUNTEDI ANTENNA INSTL 35I IN LONG rlsc s ITcHËs HIRÊS...

Page 120: ... VOR LOC INDICATOR IN 385A tjrnT tIR INc t n ISC ITE S ERGENCY LOCA OR IRANSI4ITTÊR IRANSHIITER U E M DI iELT ó II ANÏtsNNA ìTAF DhIARE ERGENCY LOCATT R TRANSI ITTER SED IN CANAT AI IRANSIIIÌIER fþ E I DI ELT 6 1CI ANTENNA IARDIiARE NAV f ATIC 200A ONTROLLÊR AI PLI F IER ÏURN COORÛINATOR NET CHANGE G 3OOAI ROLL ACTUATTJR IRING 6 HARO TARE RELAY INSIALLATTgN NAV HATIC 300A IAF 3e5Al ONTROLLÉR AT PL...

Page 121: ... KIT REÉUIRED I ITH zND UI IT NAV COH FACTgRY INSTALLATION ONLY ZND N C TRANSCEIVÊR KIT INSTALLATICIN OÈI ANTENNA LAbLE INSTL RH ANTENNA CÛUPLÊR INSTALLAÍ IT N ANfËNNA INSIALLATION AVI0NICS ùPTItrN ú NAV ú ÈIATIC HING PROV iIKE FIËADSb Î LOI BIÑATION I FIÊADSÊT STO JËD IREOUIRÉS ITEM E89 PAODÊI HEAÛPHONES å ICROPHT NE REQUIRES ITEII E89 O ALL PURPCSE CONTROL HhEEL SKYhAHK II Ê 001 o 16 Lr J SPECIA...

Page 122: ... l 3O0 TRANSPONDER RT 35941 FLOATPLANE I UsEL GE STRUCTURAL I OOIFICA rICNS AND FIITIIYG IOPTION CI FLCAJPLANL CrlhLDÉCK V 8RACE IINSIALLEDI I LPATPLANE CUíÍJÉCK V 6RACE ST0HED FLOATPLANÊ AILÉRON RUÛDER INTERCONNÊCT FLTATPLANÊ ONLY INSTALLEOI FLÛATPLANË ONLY ISTOWEDI NOTE ITE Is JIO A AND J13 A ARE ALSO APPRDVEO FÛR LANDPLANE OPERATTONS ltoË NET tT NOS Kll oAls 6 5CZ AÎTACH EN STANOARO LANOT IIEN ...

Page 123: ... t tCK V tRACE STO Êtr lNì tsRCUNNËCT SYSTEÌ SïOl úEIJI CU L ASSY FLC ATPLANE NET çHG lFlt ENl Kll I tTl r PRIIP CHANGh SION PRUOFlNG CONSISTS OF PKUPLLLTR FLTATPLANE ËXCùiË PLACARD ÊLOAIPLANE OPERATIONS RINGS AIRPLANE hOISTING SITP L ËANC LET RÉFUÉLING FUSbLAGE iIODIF ICATION S COITL LECK V 6RACE TNSTALLTLI NIERCûI NËCT SYSïËH lNSTL COÍL ASSYr I LOATPLANËr NET CHG FLOATPLANT h ANÜ NO CCRRü A3 F0 ...

Page 124: ......

Page 125: ...eIt Shoulder Harnesses With Inertia Reels Entrance Doors And Cabin Windows Control Locks Engine Engine Controls Engine Instruments New Engine Break In And Operation Engine OiI System Ignition Starter System Air Induction System Exhaust System Carburetor And Priming System Cooling System Propeller Fuel System Brake System Electrical System Master Switch Avionics Power Switch 7 3 7 3 7 8 7 8 7 8 7 9...

Page 126: ...ing And Defrosting System Pitot Static System And Instrgments Airspoed Indicator Vertícal Speed Indicator Altimeter Vacuum System And Instruments Attitude Indicator Directional Indicator Suction Gage Stall üarning System Avionics Support Equipment Avionics Cooling Fan Microphone Headset Installations Static Dischargers CESSNA MODEL 172P Page 7 P 6 7 26 7 27 7 28 7 28 7 28 7 28 7 80 7 30 7 32 7 54 ...

Page 127: ...ribs doublers and stringers The entire structure is covered with aluminum skin The front spars are equipped with wing to fuselage and wing to strut ettach fit tings The aft spars are equipped with wing to fuselage attech fittings and are partial span spars Conventional hinged ailerons and single slot type flaps are attached to the trailing edge of the wings The ailerons are constructed of a forwar...

Page 128: ...SECTION 7 AIRPLANE SYSTEMS DESCRIPTIONS AII ER ON CONTROL SYSTEM CESSNA MODEL 172P ii RUDDER AÀID AI DDEN TR IM co ma ol sYslEMS Figure 7 1 Flight Control and Trim Systems Sheet 1 of p 7 4 30 May 1980 ...

Page 129: ...CESSNA MODEL 172P SECTION 7 AIRPLANE SYSTEMS DESCRIPTIONS ELEVAÎOR CONTROL SYSTTM EI EVATOR TRIM CO üTROL SYSTEM Figure 7 1 Flight Control and Trim Systems Sheet 2 of Z 30 May 1980 7 õ ...

Page 130: ...N o N o N Þ o SECTION 7 AIRPLANE SYSTEMS DESCIIIPTIONS CESSNA MODEL 172P NO oao ooo b N æ ø o N Instrument Panel Sheet 1 of 2 7 6 l igure 7 2 3O May 1980 ...

Page 131: ...ke Jacks Front Passenger 23 Map Compartment 24 Cabin Heat and Air Control Knobs P õ Cigar Lighter 26 Wing Flap Switch and Position Indicator 27 Mixture Control 28 Throttle With Friction Lock 29 Static Pressure Alternate Sou ce Valve 30 Instrumeut and Radio Light Dimming FJreostats 31 Hand HeldMicrophone 32 Air Conditioning Controls 33 Fuel Selector Valve Handle 34 Rudder Tri n Control Lever 35 Ele...

Page 132: ... the above procedures TRIM SYSTEM A manually operated elevator trim system is provided a rudder trim system may also be installed see figure 7 1 Elevator trimming is accomplished through the elevator trim tab by utitizing the vertically mounted trim control whoel Forward rotetion of the trim wheel wiII trim nose down conversely aft rotation will trím no6e up Ruddertrimming is accomplished through ...

Page 133: ...switch 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 which these items are related GROUND CONTROL Effective ground control while taxiing is accomplished through nose wheel steering by using the rudder pedals left rudder pedal to steer left and right rudde...

Page 134: ... the stop and position it as desired A scale and pointer on the left side of the switch lever indicates flap travel in degrees The wing flap system circuit is protected by a lO ampero circuit breaker Iabeled FLAP on the left side of the switch and control panel LANDING GEAR SYSTEM The landing gear is of the tricycle type with a steerable nose wheel two main wheels and wheel fairings Shock absorpti...

Page 135: ...he center of the seat frarne slide the seat into position relea se the handle and check that the seat is looked in place The seat back angle is controlled by a cylinder lock releese button which is spring Ioaded to the locked position The release button is located on the right side below the forward corner of the seatcushion To adjust the angle ofthe seat back push up on the release button positio...

Page 136: ...sure to it to raise or lower it to the desired level The headrest may be removed at a ny time by raising it until it disengages from the top of tho seat back SEAT BELTS AND SHOULDER HARNESSES AII seat positions are equipped with seat belts see figure 7 4 The pilot s and front passenger s seats ere also equipped with separate shoulder harnesses shoulder harnesses are available for the rear seat pos...

Page 137: ...LINK HALF AND SHOULDEN HARNESS RETAIMNO STUD FREE END OF SEÀT Pull to tlghten STANDARD SHOUTDER H AR NESS SECTION 7 AIR PLANE SYSTEMS DESCRIPTIONS SEAT AELT SHOULDER HARNESS ADJUSTAALE LINK P rsltir l llilk iust ltel t shuu der levcli Dull link irìd hilntess do tilrd kr cr n c l Ir sctt bc l buckle PrroT s SEAT SHOWN SÊAT BETI SHOULDER HARNESS WITH INERTIA REEI SEAT BELT DUCKLE lN nr rdrusltrble 3...

Page 138: ... sses extend from inertia reels located in the cabin ceiling to attach points inboard of the two front seats A separate seat belt half and buckle is located outboard of the seats Inertia reels allow comflete freedom ofbody movement Flowever in the event of a sudden deceleration they will lock automatically to protect the occupants NOTE The inertia reels are located for maximum shoulder harness com...

Page 139: ...e handle is spring loaded to the CLOSE up position When the door has been pulled shut and latched lock it by rotating the door handle forward to the LOCK positÍon flush with the arm rest When the handle is rotated to the LOCK position a n over center action will hold it in that position Both cabin doprs should be locked prior to flight and should not be opened intentionally during flight NOTE Acci...

Page 140: ... a control surface lock should be installed over the vertical stabilizer and rudder The control lock and any other type of locking device should be removed prior to starting the engine ENGINE The airplane is powered by a horizontally opposed four cylinder overhead valve air sooled carbureted engine with a wet sump oil system The engine is a Lycoming Model O 320 D2J and is rated at 160 horsepower a...

Page 141: ...emperature is indicated by a gage adjacent to the oil pressure gage The gage is operated by an electrical eeistance type temperature senaor which receives porver from the airplane electrical system Gage markings indicate the normal operating range green arc which is 100 F 38 C to 245 F 118 C and the maximum red line which is 245 F 118 C The engine driven mechanical tachometer is located on the ins...

Page 142: ...r on the rÍght rear engine baffle Pressure oil from the cooler returns to the accessory housing whero it passes through the full flow oil filter The filter oÍl then enters e pressure relief valve which regulates engine oil pressure by allowing excessive oil to return to the sump while the balance of the oil is circulated to various engine parts for lubrication Residual oil is returned to tbe sump ...

Page 143: ...a duct to a valve in tho airbox operated by the carburetor heat control on the instrument panel Heated air from the shroud is obtained from an unfil tered outside source Use offull carburetor heat at futt throttle will result in a loss of approximately 7õ to 1õ0 RPM EXHAUST SYSTEM Exhaust gas from each cylinder pa sses through riser assemblies to a muffler and tailpipe The muffler is constructed w...

Page 144: ...ion The propeller is 75 inches in diameter FUEL SYSTEM The airplane may be equipped with a standard fuel system or either of two long range systems see figure 7 6 Each system consists of two valve åäi r each system Fuel flows by gravity from the two wing tanks to a four position selector valve labeled BOTH RIGHT LEFT and OFF With the selector valve in either the BOTH LEFT or RIGHT position fuel fÌ...

Page 145: ...arthe wing strut The right fuel tank fitler cap is also vented When long ra nge integral tanks are installed the airplane may be serviced to a reduced capacity to permit heavier oa bin loadings This is accomplished by filling each tank to the bottom edge of the fuel filler collar thus giving a reduced fuel load of 24 gallons in each tank 21 gallons usa ble in all flight conditions Fuel quantity is...

Page 146: ...EIMER FUE L STRAINER FUE L STRAINER DRAIN CONTROL CONDITION SYSIEM SHOWN WITH FUEL SELECTOR VALVE IN EOTH POSITION TO ENGINE ______o THROTTLE CONTROL MIXTURE CONTROL TO ENSURE MAXIMUM FUEL CAPACITY WHEN REFUELING AND IVìNIMIZE CROSS FEEDING WHEN PARKED ON A SLOPING SURFACE PLACE THE FUEL SELECTOR VALVE IN EITHER LEFT OR RI6HT POSIIION Figure 7 6 Fuel System Standard and Long Range SE LECTOF VALVE ...

Page 147: ...witchÍng to the opposite tank expect an equal duration from the remain ing fuel The airspace in both fuel tanks is interconnected by a vent line and therefore some sloshing of fuel between tanks can be expected when the tanks are nearly full and the wings are not level The fuel system is equipped with drain valves to provide a means for the examination of fuel in the eystem for contamination and g...

Page 148: ...on or off starting the engine or applying an external power source the avionios power switch labeled AVIONICS POWER should be turned off to prevent any harmful transient voltage from damaging the avionics equipment MASTER SWITCH The master switch is a split rocker type switch rabered MASTER and is oN in the up position and off in the doïn position The right harf of the 7 24 30 May 1980 ...

Page 149: ... WANNIßG LIGHI LI INSTNUMENT RADIO MAGilETIC COMPAS AilO POST LIGHTING AUDIO MUÍIXG NÊUY FLASHING EEACON CIGAN LIOHTEN lwFH crscull 8ñEAKEf ANO FUSEI ÍAXI ANO LANOING LIGHTS ALT MASTER SWITCH TO WING FTAP SYSÎEM TO PITOT H AT SYSTEM TO tGNtftoN swlc IO OIL T MPENAIURE GAGE STñO8E LIGHTS AVIONIG COOLING FAN to tNl CIRCUIT ENEAREF IGNITION SWITCH fo nAoto fO RADIO avtot tcs PowER swtTcH CIRCUII SfiE...

Page 150: ...idual equipment swit also functions as a circuit breaker If an electrical malfunction should occur and cause the be If es should u prr o iui or off starting the be utilized in place AMMETER rhe ammeter located on the lower left side of the instrument panel indicates the amount of current in amperes from the alternator to the battery or from the battery to the airplane electrical system when the en...

Page 151: ...t will go out at higher RPM The master switch need not be recycled since an over voltage condition has not occurred to de activate the alternator system The warning light may be tested by turning on the landing lights and momentarily turning off the ALT portion of the master switch while leaving the BAT portion turned on CIRCUIT BREAKERS AND FUSES Most of the electrical circuits in the airplane ar...

Page 152: ...nstalled Lighting intensity is controlled by a dual light dimming rheostat equippod with an outer knob labeled PANEL LT and an inner knob labeled RADIO LT located below the throttle A slidã type switch if installed on the overhead console labeled PANEL LIGHTS is used to select ftood Iighting in the FLOOD position post lighting in the POST position or a combination of post and flood lighting in the...

Page 153: ...ob full counterclockwise A cabin dome light in the aft part of the overhead console is operated by a switch near the light To turn the light on move the switch to the right A control wheel map light is available and is mounted on the bottom of the pilot s control wheel The light illuminates the lower portion of the cabin just forward of the pilot and is helpful when checking maps and other flight ...

Page 154: ...m the manifold one extending down each side of the cabin to an outlet at the front doorpost at floor level Windshield defrost air is also supptied by two ducts leading froln the cabin manifold to defroster outlets near the lower edge of the windshield Two knobs control sliding valves in either defroster ouilet to perrnit regulation of defroster airflow Separate adjustable ventilators supply additi...

Page 155: ...ET ADJUSTABLE DEFRGTER oUTLET 2 CABIN HEAT CONTROL 2 z I SECTION 7 AIR PLANE SYSTEMS DESCTìIPTIONS HEATER VALVE VENTILATING AIR DOOR CABIN AIR CONTROL 79 a r CODE RAM AIR FLOW VENTILATING AIR HEATED AIR BLENDED AIR MECHAMCAL CONNECTION G ë Figure 7 8 Cabin Heating Ventilating and Defrosting System 30 May 1980 7 31 ...

Page 156: ...thin the cabin wilt vary with open heater vents and windows Refer to section 5 for the effect of varyiñg cabin pressures on airspeed readings AIRSPEED INDICATOR dicator is calibrated in knots and miles per hour e markings in KIAS include the white arc BB to 85 to 127 knots yellow arc IZ7 to 159 knots and a red If a true airspeed indicator is installed it is equipped with a rotatable ring which wor...

Page 157: ...YSTEMS DESCR IPTIONS OVERBOARD VENT LINE VACUUM RELIEF VALVE CODE lffil vAcuuM VACUUM SYSTEM AIR FILTER VACUUM PUMP ATTITUDE INDrcATOR I o o 0 o o 00 00 oo 00 40 o SUCTION GAGE DI RECTIONAL INDICATOR 30 May 1980 Figure 7 9 Vacuum System 7 33 ...

Page 158: ...esented by a pointer at the top of the indicator relative to the bank scale which has index marks at 10o ZO B0o 60o and g0o either side of the center mark Pitch and roll attitudes are presented by a miniature airplane superimposed over a symbolic horizon area divided into two sections by a white horizon bar The upper blue sky area and the lower ground area have arbitrary pitch reference lines usef...

Page 159: ...on A sound will confirm that the system is operative AVIONICS SUPPORT EOUIPMENT If the airplane is equipped with avionics various avionics support equipment may also be installed Equipment awailable includes an avio nics cooling fan microphone headset installations and control surfa ce static dischargers The followi rg pa ra gra phs disouss these items Des cription and operation of radio equipment...

Page 160: ...eak directty into it STATIC DISCHARGERS If freguent IFR flights are planned i dischargers is recommended to improve flight through dust or various forms of p crystals Under these conditions the build static electricity from the trailing edges of the wings peller tips and radio antenna s can result in loss of on aII communications and navigation radio equipment usually the ADF is first to be affect...

Page 161: ...ditions which might c use the loss of radio signals even with static dischargers installed Whenever possible avoid known õevere precipita tion areas to prevent loss of dependable radio signals If avoidance is impractical minimize airspeed and anticipate temporary loss of radio signals while in these areas 30 May 1980 7 37l 7 38 blank ...

Page 162: ......

Page 163: ...rogram Pilot Conducted Preventive Maintonance Alterations Or RepaÍrs Ground Handling Towing Parking Tie Down Jacking Leveling Flyable Storage Servicing Engine Oil FueI Landing Gear Cleaning And Care Windshield Windows Painted Surfaces Propeller Care Engine Care Interior Care SECTION 8 HANDLING SERVICE MAINTENANCE 8 3 8 3 8 3 8 3 8 4 8 5 8 5 8 6 8 6 8 7 8 7 8 7 8 7 8 8 8 8 8 8 8 9 8 9 8 10 8 10 8 t...

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Page 165: ...C and Type Cortificate Number TC can be found on the Identification Plate located on the lower part of the left forward doorpost Located adjacent to the Identification Plate is a Finish and Trim Plate which contains a code describing the interior color scheme and exterior paint combina tion of the airplane The code may be used in conjunction with an applicable Parts Catalog if finish and trim info...

Page 166: ...ble items many of which he keeps on hand He will be happy to place an order for any item which is not in stock NOTE A Pilot s Operating Handbook and FAA Approved Air plane Flight Manual which is lost or destroyed may be replaced by contacting your Cessna Dealer or writing directly to the Customer Services Department Cessna Aircraft Company Wichita Kansas An affidavit con taining the owner s nam ai...

Page 167: ...red by the United States Federal Aviation Regulations Sinoe the Regulations of other nations may reqgire other documents and data owners of airplanes not registored in the United States should check with their own aviation officials to determine their individual requirements Cessna recommends that these items plus the Pilot s Checklists Power Computer Customer Care Program book and Customer Care C...

Page 168: ...y worked out by the factory a nd re followed by the CessnaDealer Organization Your Cessna Dealer oan assist you in selecting the inspection program most suitable for your type of aircraft and operation The oomplete familiarity of Cessna Dealers with Cessna equipment and factory approved prooedures pro vides the highest level of sorvice possible at lower cost to Cessna owners Regardless of the insp...

Page 169: ...ould refer to the regulatlons of the country of certifiaa tion for inforznation on preventivê maintena nce thçt may bo perforrred by pilots A Service Manual should be obtained prior to performÍng any preven tive maintenance to ensure that proper procedures are followed Your Cessna Dealer should be contacted for further infornration or for required ma intenance which must be accomplished by appropr...

Page 170: ... 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 the Service Manual for specific procedures and equipment required Individual main gear may be jacked by using the jack pad which is incorporated in the main landing geer strut step bracket When usin...

Page 171: ...idered in flyable storage status Every seventh day during these periods the propeller should be rotated by hand through five revolutions This aotion limbers the oil and prevents any a ccumulation of corrosion 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 andthe airplaneis secured ...

Page 172: ... inspeotions ortests For these regulatory requiromente 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 usod serrrice items a re s follows ENG NE OIL GRADE AND VISCOSITY F OR TEMPER ATTTRE N ANGE The airplane w a delivered lrom the factory with aviation grade straight mineral...

Page 173: ...ccumulated Reduce inten als for pro longed operation in dusty a rea s aold climates or wben short flights and long idle periods result in sludging conditions NOTE During the first Zã hour oil and lilter change a general inspection of the overall engine compartment is required Items which are not normtlly cheaked during a preflight inspection ehould be given special attention floses metal lines and...

Page 174: ...ks full to minimizo condensation in the tanks FUEL ADDITIVES Strict adherence to recommended preflight draining instructions as called for in Soction 4 will eliminate any free water accumulations from the tank sumps While small amounts of water may still remain Ín solution in the gasolìne it will normally be consumed and go unno ticed in the operation of the engine One exception to this can be enc...

Page 175: ...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 capacity and then transferring this mixture to the tank prior to the fuel operation Any high quality isopropyl alcohol may be used such as Anti Icing Fluid MIL F õ566 or lsopropyl Alcohol Federal Specificat...

Page 176: ... GEAR NOSE WHEEL TIRE PRESSURE 34 PSI on 5 00 õ 6 Ply Rated Tire MAIN ITHEEL TIRE PRESSURE 28 PSI on 6 00 6 4 Ply Rated Ti es NOSE CIEAR SHOCK STR UT Keep filled with MIL H õ606 hydraulic fluid per filling instructions placard and with no load on tJ e strut inflate with air to 4õ PSI Do not over lnflate 0 Figure 8 1 Additive Mixing Ratio l II lttl ttttl rlrtt attt t ll ltt t ttt Itttl t2 tl r Illt...

Page 177: ...ob A thln even coat of wax poliehed out by h nd wlth olean soft fla nnel cloths will fill ln minor eoratcbes end help prevent furtJrer soratobing Do not uao ca rva s cover on the windshield unless freezing rain or sleet is antioipated since tbe oover may scratch the plastic eurface PAINTED SURFACES The painted exterior surfaces of your new Ceesna have a durable long lasting flnieh and under nomal ...

Page 178: ... and if ignored may resuit in cracks Never use n alkaline cloaner on the blades remove grease and dirt with Stoddard solvent ENGINE CARE The engine may be cleaned with Stoddard solvent or equivalent then drieil thoroughly CAUTION Particular care should be before cleaning Cleaning to electrical equipment should not be allowed to given fluids enter magnetos starter alternator and the like Protect th...

Page 179: ...o tþo manufasturer s inetructions 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 oleaning of the seats is accomplished using a soft cloth or sponge dippedinmildsoap suds The soap suds used sparingly will removetraces of dirt and grease The soap should be removed with a clean damp cloth The plasti...

Page 180: ......

Page 181: ... Autopilot Type AF 29õB 15 300 ADF Type R õ468 16 800 Nav Com Type RT 38õA 17 300 Traneponder Type R T 3õ9A And Optional Altitude Enooder Bfind 18 300 Transponder Type RT 3õ94 And OPtional Encoding Altimeter Type EA 4014 19 3004 Navomatic Autopilot Type AF 39õA 20 4OO Glide Slope Type R 4438 21 40O Marker Beaoon Type R 4O24 22 4OO Transponder Type RT 4õ94 And Optional Altitude Encoder Bfind SECTIO...

Page 182: ...TABLE OF CONTENTS Continued 23 4OO Transponder Type RT 4õ94 And Optlonal Encoding Altimeter lype EA 4014 SECTION 9 SUPPLEMENTS CESSNA MODEL 172P 6 pages l 9 2 30 May 1980 ...

Page 183: ... under the headings of Major Configuration VarÍatiotrs Genoral and AvionÍcs and have been provided with reference numbers AIso tJre supplements are arranged alphabetically and numerically to make it easier to locate a particular supplemeut Otùrer routinoly installed items of optional oquipment whose function and operational procedures do not require detailed instnrctions are discussed in Section 7...

Page 184: ......

Page 185: ...e Cessna Sþhawk floatplane provides infomation not found in tbe basic hand book It contains proc dures and data required for safe and efficient operatlon of the alrplane equipped with Edo Model 89 2000 floats Infomration contained in the basic handbook for the Skyhawk which is tho same s that for t he floatplane is generally not repeated in this supplement 30 May 1980 Iof4P ...

Page 186: ...15 000 FT 1 FLOATPLANE MODEL 172P Wator Run Total Distance Over õO Ft Obstacle LANDING PER FORMANCE Water Run Total Distanoe Over 50 Ft Obstacle STALL SPEED KCAS Flaps Up Power Off Flaps Down Power Off MAXIMUM WEIGHT Ramp Dock Takeoff or Landing STANDARD EMPTY WEIGHT Skyhawk Floatplane Skyhawk II Floatplane MAXIMUM USEFUL LOAD Skyhawk Floatplane Skyhawk II Floatplane BAGGAGE ALI OWANCE WING LOADIN...

Page 187: ...20 lbs Landing 2220 lbs Weight in Baggage Compartment Éaggag Áreã r or iassenger on child s seat station 82 to 108 120 lbs See note below Baggage Area 2 Station 108 to 1421 50 lbs See note below NOTE The maximum combined weight capacity for baggage areas 1 and 2 is 120 lbs STANDARD AIN PLANE WEIGHTS Standard Empty Weight Skybawk Floatplane 1593 lbs Skyhawk II FloatPlane 1619 lbs Maximum Useful Loa...

Page 188: ...OPER ATING I IANDBOOK ST PPLEMENT 11 11 1 1 NOTESI t lrll hÊldìtfid ffi ll hrttñ E oòtrlnd rlû thr flo ÞltÈ lill d 2 lüq rn ôua wlü tlroö llght lÈÈlhd 3 M lmm lxl hl ûom wlth tldrlno hoñlnËllcd 4 l 0 o Figure 1 Three View 30 Mey 1980 ...

Page 189: ...i ritations is required by Federal Aviation Regulations AIF SPEED LIMITATIONS Airspoed limitations and their operational significance are shown in figure 2 5 SPEED KCAS KIAS REMARKS Vrue Never Exceed Speed 157 158 Do not exceed this speed in any operation vruo Maxímum Structural Cruising Speed 126 12t Do not exceed this speed except in smooth air and then only with caution VA Maneuvering Speed 222...

Page 190: ...5 inches WEIGHT LIMITS Maximum Ramp Dock Weight 2227Lbs Maximum lakeoff Weight 2220 lbs Maximum Landlng Weight 2220 lbs Maximum Weight in Baggage Compartment Baggage Area 1 or passenger on child s seat Station 82 to 108 120 lbs See note below Baggage Area 2 Station 108 to 142 õO lbs See note below NOTE The maximum combined weight capacity for baggage areas I and 2 is 120 lbs NOTE When floats are i...

Page 191: ... Factors Maximum Ta 5eoff Weight 2220 lbs FlapsUp 3 89 I õ2g Flaþs Dówn 3 09 The design load factors arc L6070 0f the above and in all cases the structure meets or exceeds design loads OTHER LIMITATIONS FLAP LIMITATIONS Approved Takeoff Range 0o to 10o Approved Landing F ange 0 to 30o WATER RUDDER LIMITATIONS Water rudders must be retracted for all flight operations 7 30 May 1980 ...

Page 192: ...when operating this airplane in the Normal Category Other operating limitations wtrictr must be oomplied with when operating this airplane in this category are contained in the Pilot s Operatlng Handbook and FAA Appro red Airplane Ftight Manual No acrobatio ma neuvers including spins approved Flight into known icing conditions prohibited This airplane is certified for the following flight operatio...

Page 193: ...PILOT S OPEIR ATING HANDBOOK SUPPLEMENT 4 Near the airspeed indioator 1 FT OATPI ANE MODEL 172P MANEUVER SPEED 96 KIAS 30 May 1980 9 10 blank ...

Page 194: ......

Page 195: ... GENCY OPEF ATION The speeds listed below should be substituted as appropriate for the speeds contained in Section 3 of the basic handbook PILOT S OPER ATING HANDBOOK SUPPLEMENT Engine Failure After Takeoff Wing Flaps Up Wing Flaps Down 10o Maneuvering Speed 222OLbs 2020 Lbs 1820 Lbs Maximum Glide Precautionary Landing With Engine Power Flaps Down Landing Without Engine Power Wing Flaps Up Wing Fl...

Page 196: ...elector Valve OFF 4 Ignition Switch OFF 5 Water Rudders UP 6 Wing Flaps AS REQUIRED 7 Master Switch OFF L Doors UNLATCH PRIOR TO APPROACH 9 Touchdown SLIGHTLY TAIL LOW 10 Control Wheel HOLD FULL AFT as floatplane decelerates EMEN GENOY LANDING ON I AND WITHOUT ENGINE POWER 1 Airspeed 70 KIAS flaps UP 60 KIAS flaps DO rtrN 2 Mixture IDLE CUT OFF 3 Fuel Selector Va lve OFF 4 Ignition Switch OFF 5 Wa...

Page 197: ...S MAXIMUM GLIDE After an engine failure in flight the best glide speed as shown in figure 3 sbould be established as quickly as possible In the likely event the propeller should stop maintain the speed shown 0 000 t l I z É É u l F t J o ó F T 9 t J Í 0 0 46810121416 GROUND DISTANCE NAUTICAL MILES Figure 3 Maximum Glide t p I t I tt d_ J fl di fr 30 May 1980 13 14 blank ...

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Page 199: ...te of Climb Sea Level Best Rate of Climb 10 000 Feet Best Angle of Climb Sea Level thiu 10 000 F eet Landing Approach Normal Approach Flaps Up Normal Approach Flaps 30o Maximum Perforrnance Approach Flaps 30o Balked Landing Maximum Power Flaps 20 Maximi m F eoommended Turbulent Air Penetration Speed 2220 Lbs 2020 Lbs 1820 Lbs Maximum Demonstrated Crosswind VelocÍty Takeoff or Landing I FLOAÎPLANE ...

Page 200: ...ecurity BEFORE STAR TING ENGINE 1 Water H udder Operation CHECK VISUALLY 2 Water Rudders DOWN for taxiing retraction handle removed from stowage hook TAKEOFF 1 Water F udders UP retraction handle secured on stowage hook 2 Wing Flaps O tOo 10o preferred 3 Carburetor Hoat COLD 4 Control Wheel HOLD FULL AFT 5 Throttle FULL advance slowly 6 Mixture RICH or LEAN to obtain maximum RPM above 300O feet 7 ...

Page 201: ...t BEFOR E LANDING 1 Water Rudders UP 2 Wing Ftaps AS DESIRED 3 Airspeed 65 75 KIAS flaps UP 55 65 KIAS ftaps DOWN LANDING 1 Touchdown SLIGHTLY TAIL LOW 2 Control Wheel HOLD FULL AFT as floatplane decelerates to taxi speed NOTE With forward loading a slight nose down pitch may occur if the elevator is not held full up as floatplane comes down off step AFTER LANDING 1 Water Rudders DOWN SECURING AIR...

Page 202: ...ed during sailing To taxi great distances it may be advisable to taxi on the step with the wa ter rudders retracted Turns on the step from an upwindheadingmay be made with safety providing they a re not too sharp and if ailerons are used to counteract any overturning tendency TAKEOFF Start the takeoff by applying full throtüle smoothly while holding the control wheel full aft When the nose stops r...

Page 203: ... With one float out of the water the floatplane accelerates to takeoff speed almost instantaneously CROSSWIND TAKEOFF For a crosswind takeoff start the takeoff run with wing flaps up ailerons deflected partially into the wind and water rudders extended for better directional control Flaps should be extended to 10o and the water rudders retracted when the floatplane is on the step the remainder of ...

Page 204: ...ld bo flown onto the water at this sink rate with no flare attempted sinco height above glassy water is nearly impossible to judge Power should be reduced to idle and control wheel back pressure inoreased upon contacting the surface As the floatplane decelerates off the step apply full back Pressure on the control wheel If this gtassy water technÍque is used in conjunction with an obstacle clearan...

Page 205: ...y engine cooling has been demonstrated fo this floatplane with an outside air temperature 23oC above standard This is not to be considered a s a n operating limitation Reference should be made to Section 2 for engine operating limitations AIRSPEED CATIBRATION NORftlAt STATIC SOURCE CONDITION Power required for level flight or maximum rated RPM dive FLAPS UP KIAS KCAS 40 50 60 47 54 62 70 71 80 90 ...

Page 206: ...OST FORWARD CENTER OF GRAVITY WEIGHT LBS FLAP DEFLECTION ANGLE OF BANK go 300 45 6oo KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS 2220 UP 100 300 38 35 36 48 46 44 41 38 39 52 49 47 46 42 44 57 55 52 55 50 53 68 65 62 WEIGHT LBS FLAP DEFLECTION ANGLE OF BANK Oo 300 450 600 KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS 2220 UP 100 300 41 37 36 50 47 44 44 40 39 54 51 47 49 45 44 59 56 52 58 5 4 53 71 66 62 22...

Page 207: ... 2245 27æ 3460 45æ 3ooc TOTAL rO CLEAR 50 FT OBS 2505 2920 3455 4165 5150 rvrt I Er Rr m 1660 1975 2395 æ60 3775 20 c TOTAL TO CLEAR 50 FT OBS 2270 2625 3075 3665 4460 UY ì I EIl RI JN 14æ 1 750 2095 2555 3195 looc TOTAL TO CLEAR 50 FT OBS 2060 2365 27æ 3245 39ü VYAI EN RUN 1325 1550 18 rc 2225 2735 ooc TOTAL TO CLEAR 50 FT OBS 1870 214p 2470 2æ0 3430 BUN 1 185 1380 1625 1945 2365 PRESS ALT FT s L...

Page 208: ...aned above 3000 feet for maximum RPM Figure 7 Maximum Rate of Climb MAXIMUM RATE OF CLIMB SI PPLEMENT WEIGHT LBS PR ESS ALT FT CLIMB SPEED KIAS RATE OF CLIMB FPM 00c 200c 40 c 2220 s L 20 x 4000 6000 8000 10 000 64 62 61 60 59 57 790 690 590 495 395 300 725 625 530 435 340 245 655 560 465 375 24 30 May 1980 ...

Page 209: ...by 10 for each 1ooC above standard temperature 4 Distances shown are based on zero wind Figure 8 Time Fuel and Distance to Climb WEIGHT LBS PRESSURE ALTITUDE FT TEMP oC CLIMB SPEED KIAS RATE OF CLIMB FPM FROM SEA LEVEL TIME MIN FUEL USED GALLONS DISTANCE NM 2220 s L 1000 2000 3000 4000 5000 6000 7000 8000 9000 10 000 15 13 11 I 7 5 3 1 1 3 5 64 63 62 62 61 61 60 59 59 58 57 740 695 655 610 570 525...

Page 210: ... 69 62 56 72 65 59 53 69 62 56 92 88 84 79 92 88 83 77 95 91 87 81 95 90 85 79 94 89 83 8 6 7 6 ô 8 6 2 8 1 7 3 6 5 6 0 8 6 7 7 6 9 6 3 8 1 7 3 6 6 6 0 7 7 6 9 6 3 75 71 64 5l 51 75 68 61 55 49 71 64 58 52 68 61 55 50 64 58 53 94 92 87 82 77 95 91 86 81 75 95 90 85 79 94 89 83 77 s2 87 81 8 5 8 0 7 2 6 5 5 9 8 4 7 6 6 8 6 2 5 7 8 0 7 2 6 5 6 0 7 6 6 9 6 2 5 8 7 2 6 5 6 0 71 67 61 54 49 71 64 58 52...

Page 211: ...Standard Temperature Zero Wind NOTE This chart allows for the fuel used for engine start taxi takeoff and climb and the distance during climb 10 000 8000 6000 4000 2000 S L 300 350 400 450 RANGE NAUTICAL MILES 500 F IJJ uJ u u o f t tr J 1 FLOATPLANE MODEI 172P 83 KT KTAS AS É rlJ o ô n ro 1 87 KTAS AS 30 May 1980 Figure 10 Range Profile Sheet 1 of 2 27 ...

Page 212: ...RATING HANDBOOK gI PPLEMENT RANGE PROFILE 45 MINUTES RESERVE 50 GALLONS USABLE FUEL NOTE This chart allows for the fuel used for engine start taxi takeoff and climb and the distance during climb Þ uJ t J II I u o f F F J 4000 2000 s 450 500 550 RANGE NAUTICAL MILES 600 L KT KT KT KTAS KT 87 2a Figure 10 Range Profile Sheet 2 of Z 30 May 1980 ...

Page 213: ... CONDITIONS 2220 Pounds Recommended Lean Mixture for Cruise Standard Temperature NOTE This chart allows for the fuel Lsed for engine start taxi takeoff and climb and the time during climb 10 000 8000 6000 2000 S L 45 ENDURANCE HOURS 3 F t IJJ u I uJ o f F Þ J 6 a lo 0 30 May 1980 Figure 11 Endurance Profile Sheet I of 2 29 ...

Page 214: ...ONDITIONS 2220 Pounds 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 10 000 8000 2000 S L 4 567 ENDURANCE HOURS 6000 t uJ t I tJ I t l o l t tr J I àe lt r 30 Figure 11 Endurance Profile Sheet 2 of 2 3O May 1980 ...

Page 215: ... CLEAR 50 FT OBS 1420 1455 1495 1530 1570 IA ATER RUN r0 6ô5 690 715 740 300c TOTAL TO CLEAR 50 FT OBS 13fX 1425 1465 15 n 1ilo I ATER Rt ht 620 645 670 695 720 200c TOTAL TO CLEAR 50 FT OBS 1360 1390 1430 1465 1500 WATER RUN ô00 620 æ5 670 695 10 c TOTAL TO CLEAR 50 FT OBS 1330 1360 1395 1430 1465 WATER RU 580 600 625 ar5 670 00c TOTAL TO CLEAR 50 FT OBS 13 x 1330 1360 1395 1435 VIIATER RIJN s60 ...

Page 216: ......

Page 217: ...nd will enable you to operate the floatplane t and center of gravity limitations The lly required for operation of the Mod el t72P 000 floats is presented in this section NOTE When floats are installed it is possible to exceed the maximum takeoff weight with aII seats occupied and minimum fuel It is the responsibility of the pilot to ensure tha t the floatplane is loaded properly 30 May 1980 33 ...

Page 218: ...o J T tsl o l o Èd H ã Þ Ë z øQ dx ËË trru 58 3R 775 7û 725 7ú 1100 12æ 100 1900 18 þ 1700 t o z l o g t t t 1 t z J o É a ot ô o J 15m 5560657075æ859095 LOADED AI RPLAN E MOMENT I MO IPOUND I NCHES 45 50 cÞ o 3Ee o o FLOATPLANE CENTER OF GRAVITY MOMENT ENVELOPE lltl tt l ttrtl ltrI rt tlrtttt rr lattttt rrrrr Ill Figure 13 Center of Gravit r Moment Envelope ...

Page 219: ...o x z2 21tO 2ñ 1900 1800 1700 16 x an o z o É Å IUJ u z J À CÉ o t o o J 975 950 õ Ê 9 o J Y Á 9 lrJ u z È É o ul o o J 875 850 825 800 775 7n 725 7æ jt F Éô sã FF r Þ t r t El 1 C I C OJ d te FLOATPLANE CENTER OF GRAVITY LIMITS I l tt lt tl ttl tlr rtl tll rl rrl ltrtt Itttt rtllr ltll ttrtr trll trttt llltl rtttt trtl lllrl II II llll t t l llt lt l ltltr ltll ttltt rlt l rllll tl ttrlr r rttlr ...

Page 220: ......

Page 221: ...upport the float installa tion 3 An additional structural V brace is installed between the top of the front door posts and the cowl deck 4 The airplane has additional oorrosion proofing and stainless steel cables 5 Interoonnect springs aro added between the rudder and aileron control systems 6 The fuel strainor installation is modified for floatplane use 7 The standard propeller is replaoed wÍth a...

Page 222: ... CONTROL PEDESTAL STOWAGE HOOK RETRACTION HANOLE CABLE FAIRLEAD BETWEEN PI LOT FRONT PASSENGER SEATS I t rd ri o n o Fd tã F Þ È ti z CDO dtt Fä Itl Ft Ë I i O 20 iX g o 3F F o o Figure 15 Water Rudder Retraction System ...

Page 223: ... retractiori hinge which when the tvater rudders are rotracted make contact of each float looking the rudders in the centere the water rudder steering system permit normal with the water rudders retracted and improve directional stability in flight A water rudder retraction handle located on the cabin floor between the front seats is used to manually raise and lower the water rudders and in ld be ...

Page 224: ...LERON CAB LEFT WATER RUDDER PILOT S OPEF ATING HANDBOOK SUPPLEMENT DER CABLES RUDDER AI LERON INTERCONNECT SPRING AND CABLE INSTALLATION TYPICAL IGHT WATER RUDDER I I l Ì AI RPLAN E RUDDER 40 Figure 16 Water Rudder Steering System 30 May 1980 ...

Page 225: ...r should use the method most a ppropríate for his operation Some of the most common mooring alternatives re as follows 1 The floatplane ca n be moored to a buoy using a yoke tied to the forward float cleats so that it will freely weathervane into the wind 2 The ftoatplane c n be secured to a dook using the fore and aft cleats of one float although this method is generally not recommended unless th...

Page 226: ......

Page 227: ...ITIONING SYSTEM sEcTroN I GENERAL lhounted under the aft baggage area floor Two freon lines connect the receiver drier to the condãnseì and the thermostatic expansion valve A sight glass on the top of the receiver drier is covered by a plug button in the aft ba gga ge area floor 30 May 1980 1of 6 ...

Page 228: ...RESSORI HIGH PRESSUßE FREON ICOMPRESSOR 10 CONOENSERI CONDENSER AIR IBOTTOM OF TAI LCONÊI TO FAN CONÎROL SYSTEM CONTBOLS ION CONIROL PEDESTALI cOLD AIR DUcTs ARE INTEGRAL PAPÍ OF DOOR AND WINDOW MOLOING RECE WITH SIGHT GLASS EVAPORATOR BLOWERS AND EXPANSION VALVE SEALÈD BULKH CONDENSATE DRAIN LI ITHROUGH BOTÍOM OF lAILCONEI CODE LIOUID FREON VAPOR FREON ORAIN LINE CAPILLAßY ÎUSE ELECTRICAL CONNECT...

Page 229: ...ghts above 2300 pounds when the condenser fairing is not installed With the con denser fairing installed or at maximum weights of 2800 pounds or less up to 10o flaps is approved The following information must be presented in the form of a placard located near the engine instrument cluster TURN OFF A IF CONDITIONER FOR TAKEOFF AND LANDING sEcTloN 3 EMERGENCY PROCEDURES There is no change to the air...

Page 230: ...the following proce dures for best utilization of the system prior to flight 1 Cabin Doors and ït indows CLOSED 2 Cabin Air Control Knob PUSHED IN 3 Wing Root Ventilators CLOSED 4 AIR TEMP Control Knob MAX 5 FAN Control Knob HI 6 After Initia l Cooldown REPOSITION AIR TEMP and FAN control knobs as required to maintain desired temperature NOTE A high pressure switch in the air conditioning system d...

Page 231: ...s may frost over The evaporator unit is equipped with an automatic defrost system which will normally prevent this However when the AIR TEMP control is placed in the MA X position the automatic defrost system will not operate This problem can be recognized by a continual rise in the temperature of the airflow from the outlets To correct the problem move the AIR TEMP control knob approximately one ...

Page 232: ...ch handbook for any particular RPM A condenser air scoop fairing provided with the system will change the performance decrements to 2 knots forcruise speed and 2õ FpM for rate of climb The faiiing is intended for use during ofi season operations Do not operate the aÍr conditioning system wtth the fairing inita ed DEMONSTR ATED OPERATING TEMPER ATUN E satisfactory engine cooling has been demonstrat...

Page 233: ...rc betweon 15oc and õoc which indicates the temperature range most conducive to carburetor icing sEcTloN 2 LIMITATIONS There is no change to the airplane limitations when the carburetor air temperature gage is installed sEcTloN 3 EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when the cq buretor air temperature gage is installed sEcTloN 4 NORMAL PROCEDURES applied 30 ...

Page 234: ...FORMANCE There is no change to the airplane performance when the carburetor air temperature gage is installed However if it is necessaty to operate with carburetor heat applied a small performance loss may be expeóted at any given power setting due to the warmer induction air temperature 2 30 May 1980 ...

Page 235: ...an and motor located above the extended baggage compartment system ducting and four futly adjustable outlets above the cabin side windows The circulation fan and motor includes an electric motor equipped with an output shaft on each end attached to squirrel cage type blowers within blower housings which provide airflow through the ducts to the cabin outlets The volume of airflow through the cabin ...

Page 236: ...BOOK SIIPPLEMENT e CflI E COOL AIR RETURN AI R ELECTRICAL CONNECTION F THESE AIR DUCTS ARE INTEGRAL PART OF DOOR ANO WINDOW MOLOING FI REWALL INSTRUMENT PANEL lÉ AIR DUCT DI RECTIONAL OUTLET TYPICALI R DUCT AI R DUCT AIR DUCT AIR DUCT TYPICALI CIRCULATION FAN ANO TO FAN CONTROL SEALED EULKHEAD tç 2 MOTOR ASSEMBLY Figure 1 Circulation Fan System 80 May 1980 ...

Page 237: ...e the following proce dures for best utilization of the system prior to flight 1 Cabin Window s OPEN 2 Cabin A ir Control Knob PULL OUT 3 Wing Root Ventilators OPEN 4 CIRCULATION FAN Control Khob HI BEFORE TAKEOFF 1 Cabin Window s CLOSED AND LOCKED OPER ATION IN FLIGHT The inflight operation of the circulation fan system is basically the same as for ground operation The cabin air control knob wing...

Page 238: ...CI TJATION FAN gYSTEM MODEL 172P PII OT S OPER ATING HAI DBOOK SUPPT E MENT sEcTtoN 5 PERFORMANCE There is no change to t he airplane perfor na nce when the oirculation fan system is installed 4 30 May 1980 ...

Page 239: ...button type switches directly below the display control all time keeping functions These control functions are summarized in figures 2 and 3 The digital displq y features an internal light back light to ensure good visibility under low cabin lighting conditions or at night The intensity of the back light is controlled by the RADIO LT rheostat In addition the display incorporates a test function se...

Page 240: ...momentarily while in the clock mode the calendar dato appears numerically on the display with month of year to the left of the colon and day of the month shown to the right of the colon The display automatically returns to the clock mode after approximately 1 5 seconds However if the RH button is pressed continuously longer than approximately two seconds the display will return from the date to th...

Page 241: ... Figure 3 Timer Mode selected by changing the position of an inte nal slide switch accessible through a small hole on the bottom of the instrument ca se Notice that in the Z4 hour format the clock mode indicator does not appear SETTING CORRECT DATE AND TIME The correct date and time are set while in the clock mode using the LH and RH push buttons as follows press the LH button once to cause the da...

Page 242: ...sh button until the timer mode indicator appears Reset the display to zero by pressing the LH button Begin timing an event by pressing the F H button The timer will begin counting in minutes and seconds and the colon activity indicator will blink off for 1 10 second each second When 59 minutes bg seconds have accumulated the timer changes to count in hours andminutes up to a rnaximum of 23 hours 5...

Page 243: ... door adjacent t NOTE switch turned on a low battery NOTE Use of the ground servioe plug receptacle for starting an airplane with a dead battery or charging a dead battery in the airplane is not recommendod The battery should be removed from the airplane and serviced in accordance with Service Manual procedures Failure to observe tbis precaution could result in loss of electrical power during ftig...

Page 244: ...re is no change to the ai4llane emergency procedures when the ground servioe plug receptacle is installed SECTION 4 NORMAL PROCEDURES Just before connecting an external power source generator type or battery cart the avionics powor switch should be turned off and the master switch on l4 hen turning on tho master switch using an exüernal powor source or pulling the propeller tJrrough by hand treat ...

Page 245: ...to the oonflition of the battery L Master Switch OFF 2 Taxi and Landing Light Switches ON 3 Engine RPM REDUCE to idle 4 Master Switch ON with taxi and landing lights turned on 5 Engine RPM INCREASE to approximately 1ã00 F PM 6 Ammetor and Low Voltage lVarning Light CHECK NOTE If the ammeter does not show a oharge or the low voltage warning light does not go out the battery should be removed from t...

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Page 247: ...SECTION 2 LIMITATIONS Strobe lights must be turned off when taxiing in the vicinity of other airplanes or during night flight through clouds fog or haze sEcTloN 3 EMERGENCY PROCEDURES There is no change to the airplane emergency Procedures when strobe lights are installed sEcfloN 4 NORMAL PROCEDURES To operate the strobe light system proceed as follows 1 Master Switch ON 2 Strobe Light Switch ON 3...

Page 248: ...7 STROBE LIGHT SYBTEM MODEL 172P PILOT g OPERATINC HANDBOOK SUPPLEMENT sEcTroN 5 PERFORIVIANCE The installation of strobe ligbts will result in a minor reduction in cruise performance ì 2 80 May 1980 ...

Page 249: ...nstalled on the instrument panel This equipment ehould be installed for operations in temperatures consistently bolow 20 F oC Once installed the crankcase breather insulation is approved for permanent use regardless of temperature SECTION 2 L MITATIONS The following inforrnation must be presented in the form of placards when the airplane is equipped with a winterization kit 1 On each nose cap cove...

Page 250: ...UTSIDE AIR TEMPERATURE IS ABOVE 20 F sEciloN 3 EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when the winterization kit is installed sEcTloN 4 NORMAL PROCEDURES There is no change to the airplane normal procedures when the winterization kit is installed SECTION 5 PERFORMANCE There is no change to the airplane performance when the winterization kit is installed 2 30 M...

Page 251: ...ation PILOT S OPERATING HANDBOOK SUPPLEMENT 9 AUDIO CONTROL PANELS AUDIO SELECTOR SWITCHES Both audio control panels see figure 1 incorporate three position toggle type audio selector switches for iudividual control of the audio systems installed in the airplane These switches allow receiver audio to be directed to the airplane spea ker or to a headset and heard eingly or in combination with other...

Page 252: ...rporates a three position toggle switch Iabeled AUTO which is provided to automat ically match the audio of the appropriate NAV COM receiver to the selected transmitter ANNUNCTATOII LIGHTS BR IGHTNESS AND TEST S ryITCH The audio control panel used with either one or two transmitters incorporates a three position toggle switch with NITE up and DAY middle positions to control the brightness level of...

Page 253: ...tion and utilizing the indivldual audio solector switchos Adjust ment of speaker and headset sidetone volume can only be acoomplished by adjusting the sidetone potentiometers located inside the audio oontrol panel NOTE Sidetone is not available on HF Transceiver Type ASB 12õ when installed OPTIONAL INTER COM SYSTEM The optional intercom systom is a pilot and copilot intercom phone system which is ...

Page 254: ... intercom system ie not being used the volume control should be turned full countorcloskwise to eliminate auy noise over the headphones NOTE When the interaom volume ts turrred up and an auxiliary mike is plugged in there will be a loud squeal over the speaker if the COM BOTH and COM AUTO switches are inadvertently placed in the opposite positione one in the SPEAKER position and tbe other in the P...

Page 255: ...n toggle switch used to activa te the audlo amplifier and switch the microphone to tho døsired transmittér Tbe number I up posltion end 2 dou n position corresponds to the first and seoond from top to bottom trensmiùters reÊpeotively Figure 1 Audio Control Panol Operating Controls Sheet 1 of 2 b I ll I it llI I 1NN L lj NI lt0tl iJ I t B0l11 1llf 0filt iltl Nil t lliY r Itsl t L t tR ilÂv l 30 May...

Page 256: ...t any one or more audio signals on oither SPEAKER or pHONE at the samo time or to silence audio when placod in the OFF posltlon COMBOTHAUDIO SELECTO hree posiüontoggle switch used to allow both COM e same timo placing the COM BOTH Ewitoh in the I enable the pilot to monitor both the number 1 and the SpEAKEH at the same time Pla cing the switch iu the down PHONE posltion allows the pilot to monitor...

Page 257: ...NS 1 Transmitter Selector XMTR or XMTR SEL Switch SELECT desÍred transmitter for transoeiver operation 2 COM AUTO or AUTO Selector Switch SELECT SPEAKER or PHONE position to automatically select SPEAKER or PHONE audio NOTE If the NAV COM audio selector switah corresponding to the selected transmitter is in the PHONE position ivith the AUTO selector switch in the SPEAKER position all audio selector...

Page 258: ...ne speaker and the headset simultaneously 4 Audio SPEAKE R PHONE Selector Switchos SELECT desired SPEAKER or PHONE audio position only if COM AUTO switch is not used ã INT Control Knob ROTATE as deeired to increase or deorease intercom audio volume 6 ANN LTS Switch a TEST Position SELECT to verlfy operation of marker beacon BC and RN annunciator lights when installed b DAY Position SELECT for typi...

Page 259: ... covered over by a remole REM flag and the DMb will utilize tbe frequency set by the NAV set s channeling knobs When the DME is not coupled with a remote NAV set the DME will reflect the chaunel selected on the DME unit The transmitter operates in the frequency ra nge of 1041 to 1tã0 MHz and is paired with 108 to 117 95 MHz to provide a utoma tic DME channeling The receiver operates in the frequen...

Page 260: ... only give distanoo MILES in R Nav mode 3 REMOTE CHANNELING SELECTOR lwo position aeleator In the flrst posi tion the DME will utiltzo tl o froqu ncy Eot by tho DME chennoling knob8 In the second positlon the MHz dlgite will utillze the frequency s6t by the NAV 1 unlt s channeling knobs 4 WHOLE MEGAHERTZ SEITECTOF KNOB Selects operating frequency ln 1 MHz eteps between 108 and LL7 NlIIz 5 FREQUENC...

Page 261: ... will light in the MIITES mode When th oontrol ig released and had the DME been channeled to a nearby statioD the dietauoe to thet sta tion will epp ar If the station obanneled was not in range a ba r readoutwlll be seon or 10 MODE SELECTOR SWITCH OFF Turns the DME OFF MILES Allows a digital readout to a ppear in the window whlch represents slant range in nautica I miles to or from the channeled s...

Page 262: ...UST 5 DME SPEAKER pHoNE selector Switch on a udio control panel SELECT as desired 6 IDENT CONTROL ADJUST audio output in speaker orheadset 7 Mode Selector Funstions MILES Position Distance to Station is slant range in nauti cal miles MIN Position Time to Station when flying direcfly to sta tion KNOTS Position Ground Speed in knots when flyingdirecily to or from station CAUTION After the DME 190 ha...

Page 263: ...8 MHz and 1213 MHz The IND 450C digitally displays distances to or from the selçcted station up to 200 nautioal miles aircraft ground speed from 30 to 399 knots or time to station with a maximum time o1 120 minutes A Nav mode selector switoh providos selection of ON OFF Nav 1 Nav 2 Hold and RNAV operation A DME display selector switch provides selection of distance to or from station NM aircraft g...

Page 264: ... lock on in the KTS or MIN mode NOTE In all DME modes except nNAV aircraft ground speed and ti ne to station are meaningful only when the aircraft track is directly to or from the ground station The KTS and MIN indications require approximately 1 5 minutes after stâ tion acquisition for finel accu ra cy 3 DME DISPLAY SELECTOR SMTCH Solects desired mode rea douts as follows NM Position Displays dis...

Page 265: ...es without a ffectlng the previously selected DME operatlon CAUTION In the Hold mode thore is no annunci tion of the VOR DME station frequency However an annunciator labeled HLD will illuminate on the DME to flag the pilot tha t the DME is in the Hold mode NAV 2 Selects DME oper tion with No 2 VHF na vigation seti eneblos channel Bel ction by Nav 2 frequency aelector swftches RNAV Selects e roa na...

Page 266: ...position is selected when the currently controlling Nav receiver 1 or 2 frequency is about to be changed but the pilot wishes the DME to remain operating on the current frequency after the navigation frequency has been changed 1 NAV Mode Selector Switch SELECT HOLD CAUTION Inadvertent switching to any other DME Nav Mode posi tion other than HOLD must be avoided since this could ca use the DME to d...

Page 267: ... at 10 000 feet The ELT supplied in domestic aircraft transmits on both distress frequen cies simultaneously at 5 mw rated power output for 5O continuous hours in the temperature ra nge of 4oF to 131oF 20oC to 55oC The ELT unit in export aircraft transmits on 121 5 MHz at 25 mw rated power output for 50 continuous hours in the temperature ra nge of 4oF to 131oF 20 C to 5õ C The ELT is readily iden...

Page 268: ... COVER Removable for access to battery pack 3 ANTENNA RECEPTACLE Connects to antenna mounted on top of tailcone Figure 1 ELT Control Panel SECT ON 3 EMERGENCY PROCEDURES Immediately aftet a forced landing where emergency assistance is required the ELT should be utilized as follows 1 ENSURE ELT ACTIVATION Turn a radio transceiver ON and select 121 5 MHz If the ELT can be heard transmitting itwas ac...

Page 269: ...otor switch in the OFF position terminating emergency transmissions SECT ON 4 NORMAL PROCEDURES As long a s the function selector switch remains in the AUTo position the ELT autornatioally activates following an impact of õg or more over a short period of time Following a lightning strike ing the ELT may activate although no em ELT for inadverient activation sãlect 121 ver and listen for an ernerg...

Page 270: ......

Page 271: ...craft to the waypoint repeatedly to provide continual informa tion on WHICH t AY aud HO ry FAR to the waypoint The pilot can monitor BEARING and RANGE on RNAV õ11 to fly straight line patbs to waypoints up to 200 NM distance from tJre aircraft position Waypoints can be precisely dialed into the thumbwheels to 0 1o and 0 1 NM resolution The RNAV 511 also provides immediato positiou oriontation rela...

Page 272: ...ividual plq cards 1 Adjacent to panel unit when used with the DME 190 R NAV FOR VFR T LIGHT ONLY TUNE DME NAV 1 TO SAME VORTAC F OR RNAV OPERATION 2 Adjacent to panel unit when used with the 400 DME sEcTroN 3 EMERGENCY PROCEDURES There is no change to the airplane emorgency procedures when this avionic equipment is instailed 2 RNAV FOR VFR FLIGHT ONLY DME MODE SELECTOR ON NAV 1 OR NAV 2 ONLY 30 Ma...

Page 273: ... pressed F NAV ON light witl illuminato and set is turned ON When preesed egtin set will bo turned OFF a nd tho RNAV ON light will go out The pushbutton lighting is automs tica lly dimmed by the photooell 4 4 PHOTOCELL Senses ambient cockpit light a nd controls brightness of pushbut tonÊ 1 3 5 7 and digital displays 2 6 5 VOII DME PUSHBUTTON Provides PRESENT POSITION informa tion as to VOF F ADIAL...

Page 274: ... olllbra ted the dleplaye Z 6 read the aotive ilpT bwbeele CDI left rtght neodle TO when the OBS Betting i6 a t iut thumbwheele Test may be LOCKïNG SCREW Secures RNAV õ11 in dustcover Turn locklng screw counterolockwise several tutng to releaee unlt from panel RADIAL AND DISTANCE THUMBWHEELS Waypoint locarion IT ADIAL AND DISTANCE is dlaled into thumbwheels to 0 1o and 0 1 NM resolution Meximum wa...

Page 275: ...Thus the RANGE readout is the primary means of approximating waypoint passage 4 Tracking from a waypoint is not reoommended since the pilot would have to fty a reciprocal bearing and make error oorrections in the opposite direotion from flying to a waypoint DIAGNOSTIC FUNCTIONS All RNAV systems ars rendered inoporative under certain conditions The RNAV õ11 provides a Flag mode and permits a diagno...

Page 276: ...stalled with DME 190 RNAV 511 is connected to the Nav 1Rcvr When inetalled with the 400 DME RNAV õ11 may be counected to either the Nav 1 or Nav P Rcvr and channeled to the desired VORTAC 3 DME ON OFF Switch ON 4 DME F emote Channeling Seloctor on DME 190 Selector SET to REM position on DME 190 5 DME Mode Selector on 400 DME SET TO desired NAV 1 or N A V 2 position on 400 DME NOTE FNAV and HOLD po...

Page 277: ...CONTROL AIRCRAFT as required to maintain desired track to or from waypoint NOTE Due to wind drift it may be necessary to fly a few degrees plus or minus the calculated BEARING readout in order to malntaln the desired BEARING readout on the oomputer 74 VOR DME Pushbutton PRESS at an rtime to observe the radial and DME distance from the VOF TAC a ssocia ted with the way point 1õ Upon Waypoint Passag...

Page 278: ...DISTANCE Then new waypolnt lf neceseary ca n be eet into the right hand thumbwheels after the initiat right hand wa qpoint ia passed This procedure can be fotlowed for as many waypoints a B Deoessa ry providing the t the desired Nav receiver is seleoted and the VORTAC frequency has been re chauneled to each VORTAC station sEcTroN 5 PERFORMANCE there is no change to the air la De performance when t...

Page 279: ...e installed without Course Datum The ANS 3õ1C Area Navigation computer contains concentric rotary displays and annunciators Primary Power is applied to the ANS 351C by the Number 2 VHF Navigation Receiver to which it is coupled The ANS 3õlC Area Navigation Computer calculates the following parameters when activated Crosstrack deviation of the aÍrcraft from the selected course and to from informati...

Page 280: ...nels between 1041 MHz and 1150 MHz it receives associatod ground to air replies between 978 MHz and lP18 MHz The IND 4õ0C digitally displays distances to or from the selected station up to 200 nautical miles aircraft ground speed from 30 to Bgg knots or time to station with a maximum time of 120 minutes A Nav mode selector switch provides seloction of ON OFF Nav 1 Nav 2 HoId and RNAV operation A D...

Page 281: ...6 t9 26 25 23 IN 442AR STANDARD VOR LOC CDI Figure 1 ANS 3õ1C Computer IND 450C Indicator and Associated CDI Controls Sheet 1 of ã 1 12A R NAV TYPE ANS gõ1C 25 28 2l 24 23 l8 t0 l4 20 2l 22 24 20 2l 22 IN 443AR OPTIONAL VOB LOC LS CDI 3 Collins DME t 1t i l II I 3O May 1980 ...

Page 282: ...the active waypoint 6 RADIAL DISPLAY READOUT RADIAL When DME is eet to RNAV mode the computor will digitally display the VOF RADIAL from the reference station on which the waypoint is loca ted ltlhen the DME ts set to Nav 1 Hold or Nav 2 the computer display will spell out Vor when a VOR frequency is selected on the Nav recoiver or Loc will be spelled out if a localizor frequency is selocted on th...

Page 283: ...nto the active waypoint Brightness of this button is controlled by the radio light dimming rheosts t 12 RETURN PUSHBUTTON RTN Pressing the RTN pushbutton returns the display to the previously selected active waypoint when a non activo waypoint is currenüly being displayed Brightness of this button is controlled by the radio ligtrt dimming rheo6tat 13 AMBIENT LIGHT SENSOR Senses ambient cockpit lig...

Page 284: ...VOR DME station frequency However an nnuncirtor l beled HLD will illuminate on the DME to flag the pilot that the DME Is in the Hold mode NAV 2 Selects DME operation with No 2 VHF navigetlon set nebles channel selection by Nav 2 frequency selector switches RNAV Selects area navigation operation with the No 2 VHF navigation set Brightness of this switch is controlled by the radio light dimming rheo...

Page 285: ...cates whether selôcted course is TO or FROM station or waypolnt With usable localÞer signal white TO flag is in view 26 COUR SE DEVIATION POINTER Indicatos course deviation from selected VOR or RNAV course or localizer centerline 26 COURSE INDEX Indicates select d VOR or FTNAV courso bearing 27 GLIDE SLOPE DEVIATION POINTER Indicates deviation from ILS glide elope 28 GLIDE SLOPE OFF FLAG When visi...

Page 286: ...TION TEST 1 Since the TEST position on the 300 and 400 Nav Com radios is inoperative when the Nav Coms are coupled to this Area Naviga tion System the VOR SELF TEST OPERATION as outlined in the 300 and 400 Nav Com Types F T 3854 and RT 4854 Supple ments cannot be used To check out the complete system follow the GROUND CHECK PROCEDURES as outlined later in this Sup plement VOR LOC NAVIGATION As a c...

Page 287: ...cally eliminates the ANS 351C from the RNAV system making the computor non receptive to all inooming data When operating in these conventional VOF DME modes the ANS 3õlC RADIAL display will spell out Vor or Loc to prevent being misled into believing that an F NAV waypoint is being flown Rotating the waypoint selector knob allows preview and set up of waypoints even though operating in the qonventi...

Page 288: ...rary display changes for ground speed time to waypoint or distance to waypoint Initially ground speed wiII decrease and both time to waypoint and distance to waypoint will increase after the course cha nge is made After the new course has been established for several minutes all functions will again stabilize and display final calculated values Course changes exceeding 120 degrees require stabiliz...

Page 289: ...uld agree with the previous step 10 RNAV DME distance to waypoint readout within 0 õ NM I2 DME NAV MODE Selector Switch SELECT NAV 2 andobserve that the CDI remains within 2 dots of center and check that the DME distance to VOR display remains within 0 õ NM of the distance displayed in step 10 PREV EWING AND MODIFYING WAYPOINTS NOTES Modifications to the active waypoint should not be made while th...

Page 290: ...n any way WAYPOINT PROGRAMMING ON THE GROUND 1 Using a VFF sectional enroute instrument chart inst ument approach plate or enroute RNAV chart DETERMINE distance and radial for desired waypoints from appropriate VOR DME stations NOTE Start engine prior to turning ON avionics equipment 2 VHF NAV 2 Receiver ON to apply power to Nav receiver and RNAV set 3 DME Nav Mode Selector Switch RNAV 4 WPT Selec...

Page 291: ...G WAYPOINTS IN FLIGHT 1 WPT Selector Knob ROTATE until thedesiredwaypointnumber and coordinates are displayed 2 VHF Nav 2 Receiver SELECT the desired reference frequency and identify station by listening to ident tone 3 Nav Indicator OBS Knob SET to desired course 4 USE Pushbutton PRESS a nd observe that the waypoÍnt identÍfi cation number stops blinking 5 DME Display Selector Switch SELECT desire...

Page 292: ...ME Digital Display OBSERVE diEtauoe from VOR DME station displayed 3 DME lIIAYPOINT VPT Annunoiator OBSERVE WPT annun ciator EXTINGUISHED as a signal that raw DME data is being displayed on the DME 4 CHK Pushbuttou RELEASE sEcTloN 5 PERFORMANCE Thore Ís no change to the airplane performance when thÍs avionic equipment is installed However the installation of an externally mounted antenna or severa...

Page 293: ...a A channel seleotor knob detemiuee the operating frequoncy of the transceiver whioh has predetemined orystals inetalled to provlde tJre desired operating frequencies A mode seleator oontrol is provided to supply the type of em either sideband AM or telephone for publi b clarifier knob and squelch knob are provided to asslst in audio operatlon during receive In additiou to tJre aforemeutioned cont...

Page 294: ...ea pond noe telephone and ship to shore LgB Optional Selects lower eideband operation not legal in U S Cauoda etrd moÊt othe countrles 4 SQUELCH CONTROL Used to adjust slgnal threshold necessary to activate reoelver audio Clookwlso rotation lncreases baokground noise deoreases squeloh action oounterclookwise rotation decreasss beckground noise 5 CLARIFIEH CONTROL Usod to clarlfy elngle sideband sp...

Page 295: ...nited States Canada and various other countries only the upper sideband may be used Use of lower sideband is prohibÍted b Only AM tranemissione are permitted on frequencies 2003 kHz 2 82 kIJz and 2638 kHz The selection of these channels will automatÍoally seleot the AM mode of trans mission 1 XMTR SEL Switch on audio control panel SELECT trans ceiver 2 SPE AKER PHONE Selector Switches on audio con...

Page 296: ...SS and SPEAK lnto microphone NOTE Sidetone and interpbone intercom is not avallaÞle on this radio b To Reaeive RELEASE mike buttou NOTE Voice communications are not available ln tbe LSB mode NOlE Lower sideband LSB mode is not legal in the U 8 Canada and most other countries sEciloN 5 PERFORMANCE There is no ohango to the airplane perfor rrance when this avionic equipment is inetalled However the ...

Page 297: ...des a thermostatic switch which monitors the operating temperature of tbe motor If the temperature becomes abnornal the thermostatic switch opens and disengages tùre autopilot to remove power from the actuator After approximately 1O minutes tho switch will automatically olose to reapply power to the actuator a rd autopilot system The 2004 Navomatic will also capture and track a VOR or localizer co...

Page 298: ...B NAV 1 PTLOT S OPERATING HANDBOOK SUPPLEMENT AlLERON ACTUATOR r I l0 COMPUTER AMPLIFIER NAV 2 2 2 CDI INDICATORS TURN COORDINATOR I I 2 Figure 1 Cessna 2004 Autopilot Operating Controls and Indicators Sheet 1 of 2 a PILOT t00 30 May 1980 ...

Page 299: ...ivity position push Ùutton out response to NAV signal is dampened for smoother tracking of enroute VOR radials it also smooths out offeot of course scalloping during NAV opera tion 8 BACK CRS PUSHBUTTON Used with LOC operation only With A P switch OFF or ON and when navigation receiver selected by NAV switch is set to a Iooalizer frequency it reverses normal localizer needle indication CDI a nd ca...

Page 300: ... requiredto override autopi tot NOTE The servo may be overpowered at anytime without da m age TO TUR N OFF AUTOPILOT 1 A P ON OFF Switch OFF sEcTroN 4 NORMAL PROCEDURES BEFORE TAKE OFF AND LANDING 1 A P ON OFF Switch OFF 2 BACK CRS Button OFF see Caution note uuder Nav Capture NOTE Periodically verify operation of a mber warning light s labeledBO on CDI s byengagingBAOK CRS buttonwith a LOC freque...

Page 301: ... and PIILL out 2 Autopilot TRIM Control r ADJUST for zero tum rate 3 Airplane Rudder Trim ADJUST for zero slip Ball oentered 4 DIR HOLD Button PUSH õ PULL TITRN Knob PUSH in detent positiotr whetr airplane ís on desired beading 6 Autopilot TRIM Control READJUST for zero tu a ra te NAV CAPTURE VOR LOC 1 PUIJL TITRN K ob CENTER and PIILL out 2 NAV 1 Z Selector Switch SELE CT desired VOR receiver 3 N...

Page 302: ...tion or more than 3 minutes from intercept use a manual interceptprocedure NAV TRACKTNG VOR LOC 1 NAV TRK Button PUSH when CDI centers and airplane is within t5 of course heading 2 HI SENS BUTTON DISENGAGE for enroute omni tracking Ieave ENGAGED for localizer 3 Autopilot TF IM Control READJUST as required to maintain track NOTE Optional AF C function if installed should not be used for autopilot o...

Page 303: ... Cessna 300 ADF provides a visual indication on the bearing indicator of the bearing to the transmit ting station relative to the nose of the airplane This is done by combining signals from the sense antenna with signals from the loop antenna With the function seloctor knob at REC the Cessna 300 ADF uses only the sense antenna and operates s a conventional low frequency receiver The Cessna 300 DF ...

Page 304: ...k wise rotation from OFF posltion epplies primary power to receiver further clockwise rotation incroases audio level 2 FREQUENCY SEIJECTORS Knob A selects 100 kHz inoroments of recoiver frequsncy knob B selects 10 kHz l crements a nd knob C selocts 1 kHz incrementg Figuro 1 Cessna 800 ADF Operating Controls and Indicators Sheet 1 of 2 2 80 May 1980 ...

Page 305: ...e to be hsard REC Seteots operation aa atandard communiceùlon Ì o lv r ueing only senae antenna ADF 9et operates as eutometlo dirêotioD finder uslng loop and EeDBe enten DA Ê TEIST Momental1 on posltion us d durlng r I f operation to test beartng reliabllity lühen held in TEST position 6lewe lndlo tor polnter olookwisei wben released if beoring ie elioble pointer returtrs to origl el beorlng poslt...

Page 306: ...requency Selector Knobs SELECT operating frequency 3 ADF SPEAKER PHONE Selector Switch on audio control panel SELECT AS DESIRED 4 Function Selector Knob ADF poeition and note relative bearing on indicator 1O TEST RELIABILITY OF AUTOMATIC DIRECTION FINDER 1 Function Selector Knob ADF position andnote relative bearing on indicator 2 Function Selector Knob TEST position and observe that pointer moves...

Page 307: ... in the audio output when a C I signal Morse Code ts tuued in properly sEcTroN 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment ie installed However the installatlon of en externally mounted antenna or related external a ntennas will result Ín a minor reduction irt cruÍse perfonrranoe 30 May 1980 5 6 blank ...

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Page 309: ...ating frequoncies are digitally displayed by iucandescent readoutE on the front panel of the Nav Com A DME receivor transmitter or a glide slope receiver or both may be interconnected with the Nav Com set for automatic seloation of the associated ÐME or glide slope frequency When a VOR frequenoy is selected on the Nav Com associated VORTAC or VOR DME station frequency will also be selected automat...

Page 310: ... 5 poêition enablos Com frequency roadout to display and Com Fractional MHz Seloctor to solect frequoncy in 05 MHz steps between 0p5 and 97õ l Ifz In 0 position enables COM frequency reedout to displa y a nd Com Fractional MHz Selector to solect frequency in 05 MHz steps between 000 and 950 MHz NOTE The 5 or 0 mey be read as the third decimal digit which is not displayed in the Com fractional freq...

Page 311: ...ld necessery to activate COM receiver audio Clockwise rotation increasos background noise decreases squolch action oountorclockwise rotatiorl docroasos background noise 10 COMMUNICATION IIECEIVER TN ANSMITTER MEGAHERTZ SELECTOR Solects COM frequency in l MHz steps between 118 and 135 MHz 11 COM OFF VOL CONTROL Combination on off swltch and volume control turns on NAV COM set end controls volume of...

Page 312: ...ble localizer signal shows TQ 18 RECIPROCAL COURSE INDEX Indicatos reciprocal of solected VOR course 19 OMNI BEAF ING SELECTOR OBS RotateÊ courae cerd to seleot dosired courae 21 TERINCI ARC LAMP Ambor tight illurninatee tering is ln use Light dirnming is only aveila ble control panel incorporating the annunoiator lights 22 COUBSE CARD Indioates ssl cted VOR course under course index Figuro 1 Cess...

Page 313: ...ld This a Justment should be rechecked periodically during eaoh flight to assure optinum reception All oontrole for the Nav Com exoept the sta ndard omni bearlng selector OBS hob ortJre optlonal automatio radial oentertng AEC knob located on the course devlation i dioator a re mounted on the frontpanel of the eceiver tran mitter Operation and desoription ol the audio control paneli used in ooujuno...

Page 314: ...be selected by placing the AUTO selector switch on audio control panel in either the SPEAKER or PHONE position Sidetone may be eliminated by ptacing the AUTO selector switch in the OFF position Adjustment of sidetone on audio control panels supplied with three transmitters cannot be accomplished externally How ever audio control panels supplied with two or less transmitters ha ve sidetone adjustme...

Page 315: ... As Conventtonal OBS PLACE in center dotent and solect desired oourse b To Obtain Boaring TO VOR Station PUSH ARC PUSH TO knob to inner momentary on position NOTE A RC lamp will illuminate amber while the course card is moving to center with the courso deviation pointer After alignment has been achieved to reflest bearing to VOR automatic radial oentering will automatically shut down causing ths A...

Page 316: ...D VOX T to T Course deviation pointer deflects full scale in dircction corresponding to course displace ment NAV TO FIìOM indicator shows FROM NOTE llhen the 300 NAV COM ie ooupled to the ANS 3õ1C R NAV system the TEST operation ie non fuuctional Refer to the Ground Check Procedures in the Area Navigation System Type ANS 3õlC Supplement in thts section to verify VOR operation of the CDI 6 ID VOX T...

Page 317: ...3OO TRANSPONDER Type RT 3594 AND oPTIoNAL ALTITUDE ENCODER BLIND sEciloN I GENERAL more readily information is availaþle in 100 foot inorements All Cessna 300 Traneponder operating oontrole are located on tJre front panel of the unit Functions of the operating controls are described in Figure 1 30 May 1980 1of6 ...

Page 318: ... alrcraft identification reply pulsee Turne set on a Dd enables tr nsponder to trêDÊmit êlth r Mode A aircralt identification reply pulsea or Mode C altitude reporti g pulãos eelected automotically by the intsrogstlng stgual ALT 2 REPLY LAMP Lamp flashes to indio te tr nemlaeio of reply pul e glowe steedlly to hdlcote trangmlseion of IDENT pulse or gatlsfÈctory self tost opers tion Reply lamp wlll...

Page 319: ...ws pilot to control brillianc of reply lamp 5 SELF TEST TST SWITCH When depressed ceuses transponder to g nerate a self interrogating aignal to provide check of transponder operation Reply lamp will glow steadily to verify self test operation 6 REPLY CODE SELECTOR KNOBS 4 Select assigned Mode A reply code 7 IìEPLY CODE INDICATORS 4 Display selected Mode A reply code 8 REMOTE MOUNTED DIGITIZER Prov...

Page 320: ...R GENCY SIGNAL 1 Function Switch ON Z Reply Code Selector Knobs SELECT 7700 operating code TO TR ANSMIT A SIGNAI REPR ESENTING LOSS OF AI I COMMUNTCATTONS WHEN rN A CONTROLLED ENVIRONMENT 1 Function Switch ON 2 Reply Code Selector Knobs SELECT 7700 operating code for 1 minute then SELECT 7600 operating codo for 1õ minutes and then REPEAT this procedure at same intervals for remainder of flight sEc...

Page 321: ...ion Switch ALT NOTE by ground oontroller to stop altitude Function Switch to ON for Mode A opera NOTE Pressure altitude is transmitted by the transponder for altitude squawk and conversion to indicated altltude is done in ATC computers Altitude squawked will only agree with indioated altitude when the local alti neter setting in use by the ground controlter is set in the aircraft altimeter When di...

Page 322: ...UPPLEMENT sEcTroN 5 PERFORMANCE There is no ohange to the airplane performance when this avionic equipment is installod However the installation of an externally mounted antenna or several related external antennas will result in a minor reduction in cruise performance 6 30 May 1980 ...

Page 323: ...eivos interrogat ing pulse signals on 1030 MHz a nd transmits coded pulse train reply signals on 1090 MHz It is capable of replying to Mode A aircraft identification and Mode C altitude reporting interrogations on selec tive roply basis on any of 4096 information code selections lttthen an optional panel mounted EA 4014 Encoding Altimeter not part of a standard 300 Transpondor system is included i...

Page 324: ...tlon r6ply pulses ALT Turns set on and enables traneponder to transmit either Mode A alrcraft identification reply pulses o Mode C altitude reporting pulses sêleoted eutometlca lly by the interrogating signal 2 F EPLY LAMP Lamp flashes to indicate transmlssion of reply pulses glows steadily to indlcate tra nsmisslon of IDENT pulee or satlsfactory self test opera tion F eply Lamp will olso glow ste...

Page 325: ... from the altimeter to indicate that readout is not reliable 10 100 FOOT DRUM TYPE INDICATOR Provides digitat altitude readout in 100 foot increments between 0 feet and 1000 feet 11 zO FOOT INDICATOR NEEDLE Indica tes a ltitude in 2o foot increments between 0 feot and 1000 feet 12 ALTIMETER SETTING SCALE DR UM TYPE Indicates selocted altimeter setting in the range of 27 9 to 31 0 ihches of mercury...

Page 326: ...tor Knobs SELECT 7700 operating code for 1 minute then SELECT 7600 operating code for 15 minutes and then REPEAT thÍs procodure at same intervals for remainder of flight sEcTloN 4 NORMAL PROCEDURES BEFOF E TAKEOFF t Function Switch SBY TO TRANSMIT MODE A AIRCnAFT TDENTTFTCATION CODES rN FLIGHT 1 tleply Code Selector Knobs SELECT a ssigned code 2 Function Switch ON 3 DIM Control ADJUST light brilli...

Page 327: ... the transponder for altitude squawk and conversion to indicated altitude is accomplished in ATC computers Altitude squawked will only agree with indicated attÍtude when the local altimeter setting in use by the ground controller is set in the encoding altimeter 5 DIM Control ADJUST light brilliance of reply lamp TO SELF TEST TR ANSPONDEII OPERATION 1 Function Switch SBY and wait 30 seconds for eq...

Page 328: ......

Page 329: ... the airplane in the commanded lateral a ttitude or heading The actuator includes a thermoetatic switch which monitors the operating temperature of the motor If the temperature becomes abnormal the thermostatic switch opens and disengages the autopilot to remove power from the actuator After approximately 10 minutes the switch wiII automatically close to reapply power to the actua tor and a utopil...

Page 330: ...LOT S OPER ATING HANDBOOK SUPPLEMENT AILERON ACTUATOR NAV 2 2 I 10 il12 t4 DIRECTIONAL GYRO g t9 t8 l6 COMPUTER AMPLIFIER TURN COORDINATOR Figure 1 Cessna 3004 Autopilot Operating Controls and Indicators Sheet 1 of 3 t5 2 PILOT O l00t tlâI0ililrG o1 I 3O May 1980 ...

Page 331: ...ing indicated by the compass The compass card must be ma nua lly reset perfodically to compensate for precessional errors in the gyro 9 TURN COORDINATOF Senses roll and yaw for wings leveling a nd command turn functions 10 HDG SEL PUSHBUTTON Aircraft will turn to and hold hoading selected by the heading bug on the directional gyro 11 NAV INT PUSHBUTTON When heading bug on DG is sot to selected cou...

Page 332: ...l execut a right sta nderd ra te turni when turned to the left L the alrylane will xecute a left standard rate turn When oentered in detent end pu8hed ln the opora tlng mode selected by e pushbuttoD ls etrga g d 18 TRIM Us dtotrimautopilottocompensat lormltrorvariationelnaircrafttrim or lateral weight distribution For proper oper tion the aircraft s rudder trim if so equipped must be menually trlm...

Page 333: ...red to override autopi lot NOTE The servo may be tiverpowered at any time without dam age TO TUN N OFF AUTOPILOT 1 A P ON OFF Switoh OFF sEcTloN 4 NORMAL PROCEDURES BEFORE TAKE OFF AND LANDING 1 A P ON OFF Switch OFF 2 BACK CRS Button OF F see Caution note under Nav Intercept NOTE Periodically verify operatiou of amber wa rni rg light s labeled BC on CDI s by engaging BACK CRS buttonwith a LOC fre...

Page 334: ...n 180 185 U206 and TU206 Series Models COMMAND TURNS 1 PULL TURN Knob CENTER PULL out and ROTATE HEADING SELECT 1 Directional Gyro SET to airplane magnetic heading 2 Heading Selector Knob ROTATE bug to desired hoading 3 Heading Select Button PUSH 4 PULL TURN Knob CENTER and PUSH NOTE Airplane will turn automatically to selected heading If airplane fails to hold the precise heading readjust autopi ...

Page 335: ...e CDI on selected nav radio will be reversed even when the autopilot switch is OFF L PULL TURN Knob PUSH NOTE Airplane will automatically turn to a 45o intercept angle NAV TR ACKING VOR I OC 1 NAV TRK Button PUSH when CDI centers within one dot and airplane is within t 1Oo of oourse heading 2 HI SENS Button Disengage for enroute omni tracking loave engaged for localizer NOTE PULL TURN knob and rei...

Page 336: ......

Page 337: ...e slope receiver is designed to receive tf S glide slope signals on any of 40 channels Tho channels are spaced 150 kÞtr2 apart and cover a frequency ra nge of 329 15 MHz through 335 0MH2 ïtlhena localizerfrequency is selected ontheNAV receiver the associated glide slope frequoncy is seleated automatically Operation of the Cessna 400 Glide Slope system is controlled by the associated navigation sys...

Page 338: ...The flag disappea rs when a reliable glide slope signal ls being received CAUTION Spurious glide slope signels may exÍst in the area of the looalizer back course approach which can cause the glido slope OFF or GS flag to disappear and present unreliable gtide slope informa tion Disrogard all glide slop signa l indications when making a localizer back course approach unloss a glide 6lope ILS BC is ...

Page 339: ...ilOO RPM on airplanes equipped with a three bladed propeller during ILS approaches to avoid oscillations of the glide slope devÍation pointer caused by propeller interference 1 NAV Frequency Select Knobs SELECT desired localizer fre quenoy glide slope frequency is autornatically selected 2 NAV COM VOX ID T Switch SELECT ID positiontodisconnect filter from audio circuit 3 NA I VOL Control ADJUST to...

Page 340: ......

Page 341: ...es One switch is labeled HIGH LO MUTE and provides the pilot with HIGH LO sensitivity selection and marker beacon audio muting for approximately 30 seconds to enable voice communica tion to be heard without interference of marker beacon signals The marker beacon audible tone is automatically restored at the end of the 30 second muting period to continue marker audio for passage over the next marke...

Page 342: ...th two or less transmitters a marker Beacon audio level adjustment potentiometer and an annunciator lights minimum dimming potentiomster are mounted on the audio control panel circuit board Potentiometer adjustments cannot be accomplished exter nally However if readjustments a re desired adjustments can be made in accordance wittr instructions found in the Avionics Installations Ser vice Parts Man...

Page 343: ...for night flying operations Lightintensityofthe NITE position is controlledby the RADIO LT dimming hoostat DAY POSITION Pla ces the anuunciator lights in the full bright position for daylight flying operations TEST POSITION Illuminates all marker beacon annunciator lights a nd oth r annunciators in the full bright poeition to verify operation of annuncia tor lights 4 HIGH LO MUTE SELECTOR SWITCH H...

Page 344: ...e to indicate pa ssege of inner or fan ma rker beacon 3 SPEAKER PHONE SELECTOR SWITCH SPEAKER POSITION Selects speaker for aural reception PHONE POSITION Seleots headphone for aurel reception 4 HI LO TEST SELECTOR SWITCH HI POSITION Receiver sensitivlty is poeltioned for airway flying LO POSITION Receiver seneitivity is positioned for ILS approaches TEST POSITION Illuminates all a Ânunciator light...

Page 345: ... OFF PHN Seleotor Switch SELECT desired speaker or phone audio Eithe selected position will turn set on 2 NITE DAY TEST Selector Switch PRESS to TEST position and verify that all marker beacon annunciator lights illuminate full bright to indicate lights are operational 3 NITE DAY TEST Solector Switoh SELECT desired position for NITE or DAY lighting 4 HIGH LO MUTE Selector Switch SELECT HI position...

Page 346: ...increases audio level 2 HI LO Sen Switch SELECT HI position for airway fl ying or LO position for ILS approaohes 3 SPKR PHN Switch SELECT speaker or phone audio 4 BRT Control SELECT BRT full clockwisè ADJUST as desired when illuminated over marker beacon 5 TEST Switch PRESS to TEST position and verify that all marker beacon annunciator lights will illuminate fult bright to indicate lights are oper...

Page 347: ...lying to Mode aircraft identification and also to Mode C altitude reporting when coupled to an optional altitude encoder system The transponder is capable of replying on both modes of intorrogation on a selective reply basis on any of 4 096 information code selections The optional altitude encoder system not part of a standard 4OO Transponder system required for Mode C altitude reporting operation...

Page 348: ...A a ircra ft identification reply pulses Turns set on and enablee traasponder to tre nsmit either Mode A eircreft idontification reply pulses or Mode C altitude reporting pulses select d eutome tica lly by the interroga ting signal 2 2 REPLY LAMP Lamp flashes to indicate trensmission bf reply pulses glows steadily to indicate transmission of IDENT pulse or eatisfactory self test opera tion Reply l...

Page 349: ...t to control brilliance of reply lamp õ SELF TEST TEST SWITCH ll hen depressed causes transponder to gen ra te a self interroga ting signal to provido a check of transponder operation F eply lamp wlll glow eteadlly to verify self teet oper tion 6 REPLY CODE SELECTOR SWITCHES 4 Select assigned Mode A reply oode 7 REPLY CODE INDICATORS 4 Display seleoted Mode A reply code 8 REMOTE MOUNTED DIGITIZER ...

Page 350: ...ENCY SIGNAL L Function Switch ON 2 Reply Code Selector Switches SELECT ZZO0 operating code TO TRANSMIT A SIGNAL F EPR ESENTING LOSS OF ALL OOMMUNTCATTONS WHEN IN A CONTROLLED ENVTF ONMENT l Function Switch ON 2 Reply Code Selector Switches SELECTZZ0Ooperatingcodefor 1 minute then SELECT 7600 operating code for 15 minutes and then REPEAT this procedure at same intervals for remainder of flight sEcT...

Page 351: ...tion Switch ALT NOTE When directed by ground controller to stop altitude squawk turn Function SwÍtcb to ON for Mode A opera tion only NOTE Pressure altitude is transmitted by the transponder for altitude squawk and conversion to indicated altitude is done in ATC computers Altitude squawked wiII only agree with indicated altitude when the looal altÍmeter setting in use by the ground controller is s...

Page 352: ...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 externai antennas will result in a minor reduction in cruise performance 6 3O May 1980 ...

Page 353: ...oot increments between 1000 and 3ã 000 feet AII Cossna 400 Transponder operating controls with the exception of the optional altitude encòder s altimeter setting knob are located on the front panel of tbe unit The altimeter setting knob is located on the encoding altimeter Functions of the operating controls are described in Figure 1 PILOT S OPER ATING HANDBOOK SUPPLEMENT 23 CESSNA 4OO TRANSPONDEF...

Page 354: ...23 CESSNA 4OO TR ANSPONDER AND ENCODING ALTIMETER PILOT S OPEN ATING HANDBOOK SUPPLEMENT 45 0 I t0 Figure 1 Cessna 400 Transponder a nd Encoding Altimeter Operating Controls Sheet 1 of 2 2 30 May 1980 ...

Page 355: ...auses transponder to generate a self interrog ting signal to provide a oheck of transponder operation Reply Lamp will glow s adily to verify self t st operation 6 REPLY CODE SELECTOR SWITCHES 4 Select assigned Mode A Reply Code 7 REPLY CODE INDICATOH S 4 Display selected Mode A Reply Code 8 1000 FOOT DRUM TYPE INDICATOR Provides digital altitude readout in 1000 foot increments between 1000 and 3õ ...

Page 356: ...NSMIT AN EMER GENCY SIGNAL 1 Function Switch ON 2 Reply Code Selector Switches SELECT 7700 operating code TO TR ANSMIT A SIGNAL R EPF ESENTING LOSS OF OOMMUNTCATTONS WHEN IN A CONTROLLED ENVTRONMENT 1 Function Switch ON 2 Reply Code Seleotor Switches SELECT 7700 oporating code for 1 minute then SELECT 7600 operating code for 1õ minutes and then BEPEAT this procedure t sa me intervals for remainder...

Page 357: ... setting 3 Itreply Code Selector Switches SELECT assignod code 4 Function Switch ALT NOTE When dirècted by ground controller tò stop altitude squawk turn Function Switch to ON for Mode A opera tion only NOlE Pressure altitude is transmitted by the transponder for altitude squawk and conversion to indicated altitude is done in A TC computers Altitude squawked will only agree with indicated altitude...

Page 358: ...OOK SUPPLEMENT sEcTroN 5 PERFORMANCE Thore is no chonge to the airplano perforrnance when this avionic equipment Ís installed However the iuetallation of an externally mount d antenna or eeveral related extetna l ntennas will resutt in a minor reduction in cruise performance ...

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Summary of Contents for 172 P

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Cessna 172 P, Pilot'S Operating Handbook And Flight Manual, Page: 1 / 358

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Summary of Contents for 172 P

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