Cessna 152 Information Manual Download

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For Flight Training Reference Only

Summary of Contents for 152

Page 1: ...For Flight Training Reference Only ...

Page 2: ...VED AIRPLANE FLIGHT MANUAL AND IS TO BE USED FOR GENERAL PURPOSES ONLY IT WILL NOT BE KEPT CURRENT AND THEREFORE CANNOT BE USED AS A SUBSTITUTE FOR THE OFFICIAL PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL INTENDED FOR OPERATION OF THE AIR PLANE CESSNA AIRCRAFT COMPANY 1 JULY 1979 For Flight Training Reference Only ...

Page 3: ...INFORMATION MANUAL CESSNA AIRCRAFT COMPANY 1980 MODEL 152 CESSNA AIRCRAFT COMPANY M mb r of GAMA WICHITA KANSAS USA 1 July 1979 D1170 13 RPC 1OOOO 12 79 iii For Flight Training Reference Only ...

Page 4: ...own Power Off MAXIMUM WEIGHT Ramp Takeoff or Landing STANDARD EMPTY WEIGHT 152 152 II MAXIMUM USEFUL LOAD 152 152 II BAGGAGE ALLOWANCE WING LOADING Pounds Sq Ft POWER LOADING Pounds HP FUEL CAPACITY Total Standard Tanks Long Range Tanks OIL CAPACITY ENGINE Avco Lycoming 110 BHP at 2550 RPM PROPELLER Fixed Pitch Diameter 110 KNOTS 107 KNOTS 320 NM 3 1 HRS 545 NM 5 2 HRS 415 NM 5 2 HRS 690 NM 8 7 HR...

Page 5: ...ONS 2 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT BALANCE EQUIPMENT LIST 6 AIRPLANE SYSTEMS DESCRIPTIONS 7 AIRPLANE HANDLING SERVICE MAINTENANCE 8 SUPPLEMENTS Optional Systems Description Operating Procedures 9 n iv 1 July 1979 For Flight Training Reference Only ...

Page 6: ...5 Standard Airplane Weights 1 5 Cabin And Entry Dimensions 1 5 Baggage Space Dimensions 1 5 Specific Loadings 1 5 Symbols Abbreviations And Terminology 1 5 General Airspeed Terminology And Symbols 1 5 Meteorological Terminology 1 6 Engine Power Terminology 1 7 Airplane Performance And Flight Planning Terminology 1 7 Weight And Balance Terminology 1 7 1 July 1979 1 1 For Flight Training Reference O...

Page 7: ...strobe lights installed If standard wing tips without strobe lights are installed wing span is 32 8 1 2 2 Maximum height shown with nose gear depressed all tires and nose strut prop erly inflated and flashing beacon installed Minimum turning radius sfcpivot point to outboard wing tip is 24 8 Figure 1 1 Three View n n n 1 2 1 July 1979 n n n H n n n For Flight Training Reference Only ...

Page 8: ...izontally opposed carburetor equipped four cylinder engine with 233 3 cu in displacement Horsepower Rating and Engine Speed HO rated BHP at 2550 RPM PROPELLER Propeller Manufacturer McCauley Accessory Division Propeller Model Number 1A103 TCM6958 Number of Biades 2 Propeller Diameter Maximum 69 inches Minimum 67 5 inches Propeller Type Fixed pitch FUEL Approved Fuel Grades and Colors 100LL Grade A...

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

Page 10: ...eful Load 152 566 lbs 152 II 533 lbs CABIN AND ENTRY DIMENSIONS Detailed dimensions of the cabin interior and entry door openings are illustrated in Section 6 BAGGAGE SPACE DIMENSIONS Baggage area dimensions are illustrated in detail in Section 6 SPECIFIC LOADINGS Wing Loading 10 5 lbs sq ft Power Loading 15 2 lbs hp SYMBOLS ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KC...

Page 11: ...VNE Never Exceed Speed is the speed limit that may not be exceeded at any time Vg Stalling Speed or the minimum steady flight speed at which the airplane is controllable V Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the landing configu ration at the most forward center of gravity V Best Angle of Climb Speed is the speed which results in the greatest g...

Page 12: ...ght planning Unusable Unusable Fuel is the quantity of fuel that can not be safely Fuel used in flight GPH Gallons Per Hour is the amount of fuel in gallons consumed per hour NMPG Nautical Miles Per Gallon is the distance in nautical miles which can be expected per gallon of fuel consumed at a specific engine power setting and or flight configura tion g g is acceleration due to gravity WEIGHT AND ...

Page 13: ...of gravity locations within which the airplane must be operated at a given weight Standard Empty Weight is the weight of a standard air plane including unusable i uel full operating fluids and full engine oil Basic Empty Weight is the standard empty weight plus the weight of optional equipment Useful Load is the difference between ramp weight and the basic empty weight Maximum Ramp Weight is the m...

Page 14: ...or Markings 2 4 Power Plant Limitations 2 4 Power Plant Instrument Markings 2 5 Weight Limits 2 5 Center Of Gravity Limits 2 5 Maneuver Limits 2 6 Flight Load Factor Limits 2 6 Kinds Of Operation Limits 2 6 Fuel Limitations 2 7 Other Limitations 2 7 Flap Limitations 2 7 Placards 2 8 1 July 1979 2 1 2 2 blank For Flight Training Reference Only ...

Page 15: ... equipped with specific options Your Cessna is certificated under FAA Type Certificate No 3A19 as Cessna Model No 152 AIRSPEED LIMITATIONS Airspeed limitations and their operational significance are shown in figure 2 1 VNE vN0 vA VFE SPEED Never Exceed Speed Maximum Structural Cruising Speed Maneuvering Speed 1670 Pounds 1500 Pounds 1350 Pounds Maximum Flap Extended Speed Maximum Window Open Speed...

Page 16: ... Operations must be conducted with caution and only in smooth air Maximum speed for all operations Figure 2 2 Airspeed Indicator Markings POWER PLANT LIMITATIONS Engine Manufacturer Avco Lycoming Engine Model Number O 235 L2C Engine Operating Limits for Takeoff and Continuous Operations Maximum Power 110 BHP rating Maximum Engine Speed 2550 RPM NOTE The static RPM range at full throttle carburetor...

Page 17: ... 2550 RPM 245 F 115 psi Figure 2 3 Power Plant Instrument Markings WEIGHT LIMITS Maximum Ramp Weight 1675 lbs Maximum Takeoff Weight 1670 lbs Maximum Landing Weight 1670 lbs Maximum Weight in Baggage Compartment Baggage Area 1 or passenger on child s seat Station 50 to 76 120 lbs See note below Baggage Area 2 Station 76 to 94 40 lbs See note below NOTE The maximum combined weight capacity for bagg...

Page 18: ...95 knots Lazy Eights 95 knots Steep Turns 95 knots Spins Use Slow Deceleration Stalls Except Whip Stalls Use Slow Deceleration Higher speeds can be used if abrupt use of the controls is avoided The baggage compartment and or child s seat must not be occupied during aerobatics Aerobatics that may impose high loads should not be attempted The important thing to bear in mind in flight maneuvers is th...

Page 19: ...Usable Fuel all flight conditions 37 5 U S gallons Unusable Fuel 1 5 U S gallons NOTE Due to cross feeding between fuel tanks the tanks should be re topped after each refueling to assure maximum capacity Takeoffs have not been demonstrated with less than 2 gallons of total fuel 1 gallon per tank Fuel remaining in the tank after the fuel quantity indicator reads empty red line cannot be safely used...

Page 20: ...ntained in the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual NO ACROBATIC MANEUVERS APPROVED EXCEPT THOSE LISTED BELOW Maneuver Rec Entry Speed Maneuver Rec Entry Speed Chandelles 95 KIAS Lazy 8 s 95 KIAS Steep Turns 95 KIAS Spins Slow Decel Stalls Ex cept Whip Stalls Slow Decel Intentional spins prohibited with flaps extended Flight into known icing conditions prohibited This...

Page 21: ...ASOLINE CAP 13 U S GAL Near fuel tank filler cap long range tanks FUEL 100LL 100 MIN GRADE AVIATION GASOLINE CAP 19 5 U S GAL CAP 13 0 U S GAL TO BOTTOM OF FILLER COLLAR 5 On the instrument panel near the altimeter SPIN RECOVERY 1 VERIFY AILERONS NEUTRAL AND THROTTLE CLOSED 2 APPLY FULL OPPOSITE RUDDER 3 MOVE CONTROL WHEEL BRISKLY FORWARD TO BREAK STALL 4 NEUTRALIZE RUDDER AND RECOVER FROM DIVE 1 ...

Page 22: ...provided to indicate the accuracy of the magnetic compass in 30 increments 7 On oil filler cap 8 On control lock n p CONTROL LOCK REMOVE BEFORE STARTING ENGINE 9 Near airspeed indicator MANEUVER SPEED 104 KIAS n n 2 10 1 July 1979 For Flight Training Reference Only ...

Page 23: ...y Landing With Engine Power 3 4 Ditching 3 4 Fires 3 5 During Start On Ground 3 5 Engine Fire In Flight 3 5 Electrical Fire In Flight 3 6 Cabin Fire 3 6 Wing Fire 3 7 Icing 3 7 Inadvertent Icing Encounter 3 7 Landing With A Flat Main Tire 3 8 Electrical Power Supply System Malfunctions 3 8 Ammeter Shows Excessive Rate Of Charge Full Scale Deflection 3 8 Low Voltage Light Illuminates During Flight ...

Page 24: ...t Through Clouds 3 11 Recovery From A Spiral Dive 3 12 Inadvertent Flight Into Icing Conditions 3 12 Spins 3 12 _ Rough Engine Operation Or Loss Of Power 3 13 Carburetor Icing 3 13 Spark Plug Fouling 3 13 Magneto Malfunction 3 14 Low Oil Pressure 3 14 Electrical Power Supply System Malfunctions 3 14 Excessive Rate Of Charge 3 14 1 P n n n 3 2 1 July 1979 For Flight Training Reference Only ...

Page 25: ...pplied as necessary to correct the problem Emergency procedures associated with ELT and other optional systems can be found in Section 9 AIRSPEEDS FOR EMERGENCY OPERATION Engine Failure After Takeoff 60 KIAS Maneuvering Speed 1670 Lbs 104 KIAS 1500 Lbs 98 KIAS 1350 Lbs 93 KIAS Maximum Glide 60 KIAS Precautionary Landing With Engine Power 55 KIAS Landing Without Engine Power Wing Flaps Up 65 KIAS W...

Page 26: ...el Shutoff Valve OFF 4 Ignition Switch OFF 5 Wing Flaps AS REQUIRED 30 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 Airspeed 60 KIAS 2 Wing Flaps 20 3 Selected Field FLY OVER noting terrain and obstructions then retract flaps upon reaching a safe altitude and airspeed 4 Radio and El...

Page 27: ...oors can be opened 10 Life Vests and Raft INFLATE FIRES DURING START ON GROUND 1 Cranking CONTINUE to get a start which would suck the flames and accumulated fuel through the carburetor and into the engine If engine starts 2 Power 1700 RPM for a few minutes 3 Engine SHUTDOWN and inspect for damage If engine fails to start 4 Cranking CONTINUE in an effort to obtain a start 5 Fire Extinguisher OBTAI...

Page 28: ...discharging an extinguisher within a closed cabin ventilate the cabin If fire appears out and electrical power is necessary for continuance of flight 5 Master Switch ON 6 Circuit Breakers CHECK for faulty circuit do not reset 7 Radio Electrical Switches ON one at a time with delay after each until short circuit is localized 8 Vents Cabin Air Heat OPEN when it is ascertained that fire is completely...

Page 29: ...t as required An unexpected loss in engine speed could be caused by carburetor ice or air intake filter ice Lean the mixture for maximum RPM if carburetor heai is used continuously 6 Plan a landing at the nearest airport With an extremely rapid ice build up select a suitable off airport landing site 7 With an ice accumulation of 1 4 inch or more on the wing leading edges be prepared for significan...

Page 30: ...NOTE Illumination of the low voltage light may occur during low RPM conditions with an electrical load on the system such as during a low RPM taxi Under these conditions the light will go out at higher RPM The master switch need not be recycled since an over voltage condition has not occurred to de activate the alternator system 1 Radios OFF 2 Alternator Circuit Breaker CHECK IN 3 Master Switch OF...

Page 31: ...ute a 180 gliding turn necessary to return to the runway The checklist procedures assume that adequate time exists to secure the fuel and ignition systems prior to touchdown After an engine failure in flight the 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 fail...

Page 32: ...a water surface LANDING WITHOUT ELEVATOR CONTROL n n Trim for horizontal flight with an airspeed of approximately 55 KIAS and flaps lowered to 20 by using throttle and elevator trim controls Then do not change the elevator trim control setting control the glide angle by adjusting power exclusively At flareout the nose down moment resulting from power reduction is an adverse factor and the airplane...

Page 33: ... Check accuracy of the turn by observing the compass heading which should be the reciprocal of the original heading 5 If necessary adjust heading primarily with skidding motions rather than rolling motions so that the compass will read more accurately 6 Maintain altitude and airspeed by cautious application of elevator control Avoid overcontrolling by keeping the hands off the control wheel as muc...

Page 34: ...back pressure to slowly reduce the airspeed to 70 KIAS 4 Adjust the elevator trim control to maintain a 70 KIAS glide 5 Keep hands off the control wheel using rudder control to hold a straight heading 6 Apply carburetor heat 7 Clear engine occasionally but avoid using enough power to disturb the trimmed glide 8 Upon breaking out of clouds resume normal cruising flight Flight into icing conditions ...

Page 35: ... carburetor ice To clear the ice apply full throttle and pull the carburetor heat knob full out until the engine runs smoothly then remove carburetor heat and readjust the throttle If conditions require the continued use of carburetor heat in cruise flight use the minimum amount of heat necessary to prevent ice from forming and lean the mixture slightly for smoothest engine operation SPARK PLUG FO...

Page 36: ...a total loss of oil pressure is accompanied by a rise in oil temperature there is good reason to suspect an engine failure is imminent Reduce engine power immediately and select a suitable forced landing field Use only the minimum power required to reach the desired touchdown spot ELECTRICAL POWER SUPPLY SYSTEM MALFUNCTIONS Malfunctions in the electrical power supply system can be detected by peri...

Page 37: ...ge indications may occur during low RPM conditions with an electrical load on the system such as during a low RPM taxi Under these conditions the light will go out at higher RPM The master switch need not be recycled since an over voltage condition has not occurred to de activate the alternator system If the over voltage sensor should shut down the alternator or if the alternator circuit breaker s...

Page 38: ...ng Edge 4 6 Left Wing Trailing Edge 4 6 Before Starting Engine 4 6 Starting Engine Temperatures Above Freezing 4 7 Before Takeoff 4 7 Takeoff 4 8 Normal Takeoff 4 8 Short Field Takeoff 4 8 Enroute Climb 4 8 Cruise 4 8 Descent 4 9 Before Landing 4 9 Landing 4 9 Normal Landing 4 9 Short Field Landing 4 9 Balked Landing 4 9 After Landing 4 10 Securing Airplane 4 10 AMPLIFIED PROCEDURES Starting Engin...

Page 39: ...p Settings 4 14 Crosswind Takeoff 4 15 Enroute Climb 4 15 Cruise 4 15 Leaning With A Cessna Economy Mixture Indicator EGT 4 16 Fuel Savings Procedures For Flight Training Operations 4 17 Stalls 4 18 Spins 4 18 Landing 4 20 Short Field Landing 4 20 Crosswind Landing 4 20 Balked Landing 4 21 Cold Weather Operation 4 21 Noise Abatement 4 22 n H 4 2 1 July 1979 For Flight Training Reference Only ...

Page 40: ... 65 75 KIAS Short Field Takeoff Flaps 10 Speed at 50 Feet 54 KIAS Climb Flaps Up Normal 70 80 KIAS Best Rate of Climb Sea Level 67 KIAS Best Rate of Climb 10 000 Feet 61 KIAS Best Angle of Climb Sea Level thru 10 000 Feet 55 KIAS Landing Approach Normal Approach Flaps Up 60 70 KIAS Normal Approach Flaps 30 55 65 KIAS Short Field Approach Flaps 30 54 KIAS Balked Landing Maximum Power Flaps 20 55 KI...

Page 41: ...il and control surfaces Also make sure that control surfaces contain no internal accumulations of ice or debris Prior to flight check that pitot heater if installed is warm to touch within 30 seconds with battery and pitot heat switches on If a night flight is planned check operation of all lights and make sure a flashlight is available Figure 4 1 Preflight Inspection 4 4 1 July 1979 For Flight Tr...

Page 42: ...could cause the propeller to rotate 5 Fuel Quantity Indicators CHECK QUANTITY 6 Master Switch OFF 7 Fuel Shutoff Valve ON EMPENNAGE 1 Rudder Gust Lock REMOVE 2 Tail Tie Down DISCONNECT 3 Control Surfaces CHECK freedom of movement and security 3 RIGHT WING Trailing Edge 1 Aileron CHECK freedom of movement and security RIGHT WING 1 Wing Tie Down DISCONNECT 2 Main Wheel Tire CHECK for proper inflatio...

Page 43: ... Tire CHECK for proper inflation 7 Nose Tie Down DISCONNECT 8 Static Source Opening left side of fuselage CHECK for stoppage 1 Main Wheel Tire CHECK for proper inflation 2 Before first flight of day and after each refueling use sampler cup and drain small quantity of fuel from fuel tank sump quick drain valve to check for water sediment and proper fuel grade 3 Fuel Quantity CHECK VISUALLY for desi...

Page 44: ... starts 8 Throttle ADJUST for 1000 RPM or less 9 Oil Pressure CHECK 10 Flashing Beacon and Navigation Lights ON as required 11 Radios ON BEFORE TAKEOFF 1 Parking Brake SET 2 Cabin Doors CLOSED and LATCHED 3 Flight Controls FREE and CORRECT 4 Flight Instruments SET 5 Fuel Shutoff Valve ON 6 Mixture RICH below 3000 feet 7 Elevator Trim TAKEOFF 8 Throttle 1700 RPM a Magnetos CHECK RPM drop should not...

Page 45: ...in maximum RPM 6 Brakes RELEASE 7 Elevator Control SLIGHTLY TAIL LOW 8 Climb Speed 54 KIAS until all obstacles are cleared 9 Wing Flaps RETRACT slowly after reaching 60 KIAS ENROUTE CLIMB 1 Airspeed 70 80 KIAS NOTE If a maximum performance climb is necessary use speeds shown in the Rate Of Climb chart in Section 5 2 Throttle FULL OPEN 3 Mixture RICH below 3000 feet LEAN for maximum RPM above 3000 ...

Page 46: ...ps AS DESIRED below 85 KIAS 3 Airspeed 55 65 KIAS flaps DOWN 4 Touchdown MAIN WHEELS FIRST 5 Landing Roll LOWER NOSE WHEEL GENTLY 6 Braking MINIMUM REQUIRED SHORT FIELD LANDING 1 Airspeed 60 70 KIAS flaps UP 2 Wing Flaps 30 below 85 KIAS 3 Airspeed MAINTAIN 54 KIAS 4 Power REDUCE to idle as obstacle is cleared 5 Touchdown MAIN WHEELS FIRST 6 Brakes APPLY HEAVILY 7 Wing Flaps RETRACT BALKED LANDING...

Page 47: ...Flaps UP 2 Carburetor Heat COLD SECURING AIRPLANE 1 Parking Brake SET 2 Radios Electrical Equipment OFF 3 Mixture IDLE CUT OFF pull full out 4 Ignition Switch OFF 5 Master Switch OFF 6 Control Lock INSTALL 4 10 1 July 1979 n n n n n For Flight Training Reference Only ...

Page 48: ... crank the engine through several revolutions with the starter Repeat the starting procedure without any additional priming If the engine is underprimed most likely in cold weather with a cold engine it will not fire at all and additional priming will be necessary After starting if the oil gage does not begin to show pressure within 30 seconds in the summertime and about twice that long in very co...

Page 49: ...WN ELEVATOR USE DOWN AILERON ON RH WING AND DOWN ELEVATOR CODE WIND DIRECTION NOTE Strong quartering tail winds require caution Avoid sudden bursts of the throttle and sharp braking when the airplane is in this attitude Use the steerable nose wheel and rudder to maintain direction Figure 4 2 Taxiing Diagram 4 12 1 July 1979 n n n n n n n n n For Flight Training Reference Only ...

Page 50: ...t cooling precautions should be taken to avoid overheating on the ground MAGNETO CHECK The magneto check should be made at 1700 RPM as follows Move ignition switch first to R position and note RPM Next move switch back to BOTH to clear the other set of plugs Then move switch to the L position note RPM and return the switch to the BOTH position RPM drop should not exceed 125 RPM on either magneto o...

Page 51: ...own back of the propeller rather than pulled into it When unavoidable small dents appear in the propeller blades they should be immediately corrected as described in Section 8 under Propeller Care Prior to takeoff from fields above 3000 feet elevation the mixture should be leaned to give maximum RPM in a full throttle static runup After full throttle is applied adjust the throttle friction lock cl...

Page 52: ...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 duration to improve engine cooling CRUISE Normal cruising is performed between 55 and 75 power ...

Page 53: ... slightly to obtain smooth operation Carburetor ice as evidenced by an unexplained drop in RPM can be removed by application of full carburetor heat Upon regaining the original RPM with heat off use the minimum amount of heat by trial and error to prevent ice from forming Since the heated air causes a richer mixture readjust the mixture setting when carburetor heat is to be used continuously in cr...

Page 54: ...le position will require a recheck of EGT indication FUEL SAVINGS PROCEDURES FOR FLIGHT TRAINING OPERATIONS For best fuel economy during flight training operations the following procedures are recommended 1 Use 55 to 60 power while transitioning to and from the practice area approximately 2200 2250 RPM 2 Lean the mixture for maximum RPM during climbs above 3000 feet The mixture may be left leaned ...

Page 55: ...lowed for a 1 turn spin and recovery while a 6 turn spin and recovery may require somewhat more than twice that amount For example the recommended entry altitude for a 6 turn spin would be 6000 feet above ground level In any case entries should be planned so that recoveries are completed well above the minimum 1500 feet above ground level required by FAR 91 71 Another reason for using high altitud...

Page 56: ...tude For the purpose of training in spins and spin recoveries a 1 to 2 turn spin is adequate and should be used Up to 2 turns the spin will progress to a fairly rapid rate of rotation and a steep attitude Application of recovery controls will produce prompt recoveries of from 1 4 to 1 2 of a turn If the spin is continued beyond the 2 to 3 turn range some change in character of the spin may be note...

Page 57: ...70 KIAS with flaps up and 55 to 65 KIAS with flaps down Surface winds and air turbulence are usually the primary factors in determining the most comfortable approach speeds Actual touchdown should be made with power off and on the main wheels first The nose wheel should be lowered smoothly to the runway as speed is diminished SHORT HELD LANDING For a short field landing in smooth air conditions ma...

Page 58: ... battery energy NOTE When pulling the propeller through by hand treat it as if the ignition switch is turned on A loose or broken ground wire on either magneto could cause the engine to fire Preheat is generally required with outside air temperatures below 18 C 0 F and is recommended when temperatures are below 7 C 20 F Cold weather starting procedures are as follows With Preheat 1 Ignition Switch...

Page 59: ...rength it is possible that the spark plugs have been frosted over in which case preheat must be used before another start is attempted During cold weather operations no indication will be apparent on the oil temperature gage prior to takeoff if outside air temperatures are very cold After a suitable warm up period 2 to 5 minutes at 1000 RPM accelerate the engine several times to higher engine RPM ...

Page 60: ...id prolonged flight at low altitude near noise sensitive areas NOTE The above recommended procedures do not apply where they would conflict with Air Traffic Control clearances or instructions or where in the pilot s judgment an altitude of less than 2000 feet is necessary for him to adequately exercise his duty to see and avoid other aircraft The certificated noise level for the Model 152 at 1670 ...

Page 61: ...Temperature Conversion Chart 5 9 Figure 5 3 Stall Speeds 5 10 Figure 5 4 Takeoff Distance 5 11 Figure 5 5 Rate Of Climb Maximum 5 12 Figure 5 6 Time Fuel And Distance To Climb 5 13 Figure 5 7 Cruise Performance 5 14 Figure 5 8 Range Profile 24 5 Gallons Fuel 5 15 Range Profile 37 5 Gallons Fuel 5 16 Figure 5 9 Endurance Profile 24 5 Gallons Fuel 5 17 Endurance Profile 37 5 Gallons Fuel 5 18 Figure...

Page 62: ...nd air turbulence may account for variations of 10 or more in range and endurance Therefore it is important to utilize all available information to estimate the fuel required for the particular flight USE OF PERFORMANCE CHARTS Performance data is presented in tabular or graphical form to illus trate the effect of different variables Sufficiently detailed information is provided in the tables so th...

Page 63: ...e information presented for a pressure altitude of 2000 feet and a temperature of 30 C should be used and results in the following Ground roll 980 Feet Total distance to clear a 50 foot obstacle 1820 Feet These distances are well within the available takeoff field length Howev er a correction for the effect of wind may be made based on Note 3 of the takeoff chart The correction for a 12 knot headw...

Page 64: ... planned altitude and expected temperature conditions The engine speed chosen is 2400 RPM which results in the following Power 64 True airspeed 99 Knots Cruise fuel flow 5 2 GPH The power computer may be used to determine power and fuel consump tion more accurately during the flight FUEL REQUIRED The total fuel requirement for the flight may be estimated using the performance information in figure...

Page 65: ...ired for cruise is 2 9 hours 5 2 gallons hour 15 1 Gallons The total estimated fuel required is as follows Engine start taxi and takeoff Climb Cruise Total fuel required 0 8 1 2 15 1 17 1 Gallons Once the flight is underway ground speed checks will provide a more accurate basis for estimating the time enroute and the corresponding fuel required to complete the trip with ample reserve 1 Using a sim...

Page 66: ...llows Ground roll 535 Feet Total distance to clear a 50 foot obstacle 1300 Feet A correction for the effect of wind may be made based on Note 2 of the landing chart using the same procedure as outlined for takeoff DEMONSTRATED OPERATING TEMPERATURE Satisfactory engine cooling has been demonstrated for this airplane with an outside air temperature 23 C above standard This is not to be considered as...

Page 67: ...imum rated RPM dive FLAPS UP KIAS KCAS FLAPS 10 KIAS KCAS FLAPS 30 KIAS KCAS 40 46 40 44 40 43 50 53 50 52 50 51 60 60 60 61 60 61 70 69 70 70 70 71 80 78 80 80 80 82 90 100 110 120 130 140 88 97 107 117 127 136 CM PR 07 Figure 5 1 Airspeed Calibration 5 8 1 July 1979 n n n n For Flight Training Reference Only ...

Page 68: ... MODEL 152 SECTION 5 PERFORMANCE TEMPERATURE CONVERSION CHART 120 100 80 30 X 40 20 20 40 e 40 20 0 20 DEGREES CELSIUS 40 Figure 5 2 Temperature Conversion Chart 1 July 1979 For Flight Training Reference Only ...

Page 69: ...Y WEIGHT LBS 1670 FLAP DEFLECTION UP 10 30 ANGLE OF BANK 0 KIAS 36 36 31 KCAS 46 43 41 30 KIAS 39 39 33 KCAS 49 46 44 45 KIAS 43 43 37 KCAS 55 51 49 60 KIAS 51 51 44 KCAS 65 61 58 MOST FORWARD CENTER OF GRAVITY WEIGHT LBS 1670 FLAP DEFLECTION UP 10 30 ANGLE OF BANK 0 KIAS 40 40 35 KCAS 48 46 43 30 KIAS 43 43 38 KCAS 52 49 46 45 KIAS 48 48 42 KCAS 57 55 51 60 KIAS 57 57 49 KCAS 68 65 61 Figure 5 3 ...

Page 70: ...D COMPONENTS NOTE Maximum demonstrated crosswind velocity is 12 knots not a limitation o z 2 LJJ c u Q Z i 5 10 15 20 25 CROSSWIND COMPONENT KNOTS 30 Figure 5 4 Wind Components 20 April 1982 5 10A 5 10B BLANK For Flight Training Reference Only ...

Page 71: ... OFF 50 AT SOFT 54 PRESS ALT FT S L 1000 2000 3000 4000 5000 6000 7000 8000 GRND ROLL 640 705 775 855 940 1040 1145 1270 1405 0 C TOTAL TO CLEAR 50 FT OBS 1190 1310 1445 1600 1775 1970 2200 2470 2800 50 F io c GRND ROLL 695 765 840 925 1020 1125 1245 1375 1525 TOTAL TO CLEAR 50 FT OBS 1290 1420 1565 1730 1920 2140 2395 2705 3080 GRND ROLL 755 825 910 1000 1100 1215 1345 1490 1655 0 C TOTAL TO CLEA...

Page 72: ...m RPM WEIGHT LBS 1670 PRESS ALT FT S L 2000 4000 6000 8000 10 000 12 000 CLIMB SPEED KIAS 67 66 65 63 62 61 60 RATE OF CLIMB FPM 20 C 835 735 635 535 440 340 245 0 C 765 670 570 475 380 285 190 20 C 700 600 505 415 320 230 135 40 C 630 535 445 355 265 175 85 n n n n Figure 5 5 Rate of Climb 5 12 1 July 1979 For Flight Training Reference Only ...

Page 73: ...d on zero wind WEIGHT LBS 1670 PRESSURE ALTITUDE FT S L 1000 2000 3000 3Si Id 4000 5000 55OC 6000 7000 8000 9000 10 000 11 000 12 000 TEMP C 15 13 11 9 7 5 3 5 1 1 3 5 7 9 CLIMB SPEED KIAS 67 66 66 65 65 65 64 63 63 62 62 61 61 60 RATE OF CLIMB FPM 715 675 630 590 550 505 4 5 465 425 380 340 300 255 215 FROM SEA LEVEL TIME MIN 0 1 3 5 6 8 1 10 5 13 15 18 21 25 29 FUEL USED GALLONS 0 0 2 0 4 0 7 0 ...

Page 74: ...1 6 1 5 4 4 8 4 4 3 9 5 8 5 2 4 6 4 2 3 8 6 2 5 5 5 0 4 5 4 1 5 8 5 3 4 7 4 3 4 0 5 3 5 0 4 6 4 2 3 9 STANDARD TEMPERATURE BHP 75 66 59 53 47 75 71 63 56 51 46 75 67 60 54 49 45 75 71 64 58 52 48 68 61 56 51 46 62 59 54 49 45 KTAS 101 96 91 86 80 103 101 95 90 85 80 105 100 95 89 84 79 107 104 99 94 89 83 103 98 93 88 82 100 97 92 87 81 GPH 6 1 5 4 4 8 4 3 3 9 6 1 5 7 5 1 4 6 4 2 3 8 6 1 5 4 4 9 4...

Page 75: ...e during climb as shown in figure 5 6 2 Performance is shown for an airplane equipped with speed fairings which increase the cruise speeds by approximately two knots 12 000 10 000 8000 6000 4000 2000 S L i_ LL O Q_ i A s f M K c i Sj y 07 TAS M05 KTAS 100 KTA o S i s T 102 _J S 98 KTAS 34 KTAS 8 K 9 K 1 i 30 TAS1 61 a c I A C u i _ TAQ in TAS L79 KTAS II 300 350 400 450 500 RANGE NAUTICAL MILES Fi...

Page 76: ...as shown in figure 5 6 2 Performance is shown for an airplane equipped with speed fairings which increase the cruise speeds by approximately two knots 12 000 10 000 1X1 8000 LJJ g 6000 4000 2000 S L _ C a 1 I r 1 5 M07 KTAS 105 KTAS KTAS 1 c a _ nV i If cc I 02 ta 1 1 98 KTAS TA S i u lL I 1 r 8 94 p80 KTAS KTAS 11 _KTAS 7 TAS u 5 s n 179 KTAS 77 ktas 500 550 600 650 700 RANGE NAUTICAL MILES Figur...

Page 77: ...e for Cruise Standard Temperature NOTE This chart allows for the fuel used for engine start taxi takeoff and climb and the time during climb as shown in figure 5 6 LU Q 3 12 000 10 000 8000 6000 4000 2000 S L k cc 11 i I L I k f I II 3 4 5 ENDURANCE HOURS Figure 5 9 Endurance Profile Sheet 1 of 2 1 July 1979 5 17 For Flight Training Reference Only ...

Page 78: ...emperature NOTE This chart allows for the fuel used for engine start taxi takeoff and climb and the time during climb as shown in figure 5 6 12 000 10 000 I LU U 8000 6000 a 4000 2000 S L k y i j f c 1 l SI II D L i ccl_ u r Jj nl 1 7 8 9 ENDURANCE HOURS 10 Figure 5 9 Endurance Profile Sheet 2 of 2 5 18 1 July 1979 n n n n n n n n n n For Flight Training Reference Only ...

Page 79: ...ESS ALT FT S L 1000 2000 3000 4000 5000 6000 7000 8000 3 t GRND ROLL FT 450 465 485 500 520 540 560 585 605 0 C TOTAL FT TO CLEAR 50 FTOBS 1160 1185 1215 1240 1275 1305 1340 1375 1410 t GRND ROLL FT 465 485 500 520 540 560 580 605 630 10 C TOTAL FT TO CLEAR 50 FT OBS 1185 1215 1240 1275 1305 1335 1370 1410 1450 GRND ROLL FT 485 500 520 540 560 580 605 625 650 20 C TOTAL FT TO CLEAR 50 FT OBS 1215 ...

Page 80: ...LANCE EQUIPMENT LIST SECTION 6 WEIGHT BALANCE EQUIPMENT LIST TABLE OF CONTENTS Page Introduction 6 3 Airplane Weighing Procedures 6 3 Weight And Balance 6 6 Equipment List 6 13 1 July 1979 6 1 6 2 blank For Flight Training Reference Only ...

Page 81: ...ug to drain all oil d Move sliding seats to the most forward position e Raise flaps to the fully retracted position f Place all control surfaces in neutral position 2 Leveling a Place scales under each wheel 500 minimum capacity for scales b Deflate nose tire and or lower or raise the nose strut to center bubble on level see figure 6 1 3 Weighing a With the airplane level and brakes released recor...

Page 82: ...bol L R N W Net Weight X ARM A N x B X W x IN Item Airplane Weight From Item 5 page 6 3 Add Oil No Oil Filter 6 Qts at 7 5 Lbs Gal With Oil Filter 7 Qts at 7 5 Lbs Gal Add Unusable Fuel Std Tanks 1 5 Gal at 6 Lbs Gal L R Tanks 1 5 Gal at 6 Lbs Gal Equipment Changes Airplane Basic Empty Weight Moment 1000 Weight Lbs X C G Arm In Lbs ln 14 7 14 7 40 0 40 0 6 4 Figure 6 1 Sample Airplane Weighing 1 J...

Page 83: ...TICLE OR MODIFICATION Equipment Affecting Weight and Balance SERIAL NUMBER PAGE NUMBER WEIGHT CHANGE ADDED Wt Ib Arm In Moment 1000 REMOVED Wt Ib Arm In Moment 1000 RUNNIN EMPTY V Wt Ib G BASIC HEIGHT Moment 1000 an to a Figure 6 2 Sample Weight and Balance Record M 0 i i S M z r 0 a 8 W Cfi n en For Flight Training Reference Only ...

Page 84: ...the Loading Graph to determine the moment 1000 for each additional item to be carried then list these on the loading problem NOTE Loading Graph information for the pilot passengers and baggage is based on seats positioned for average occu pants and baggage loaded in the center of the baggage areas as shown on the Loading Arrangements diagram For loadings which may differ from these the Sample Load...

Page 85: ...N C G ARM 39 33 TO 41 64 84 94 JL _ AREA AREA JL 1 2 STATION C G ARM 39 33 TO 41 64 84 94 hild seat AREA 2 STANDARD SEATING OPTIONAL SEATING Figure 6 3 Loading Arrangements BAGGAGE LOADING and TIE DOWN BAGGAGE AREA MAXIMUM ALLOWABLE LOADS AREA 120 POUNDS AREA 40 POUNDS AREAS Q 120 POUNDS TIE DOWN NET ATTACH POINTS A cargo tie down net is provided to secure baggage in the baggage area The net attac...

Page 86: ...DIMENSIONS REAR WALL OF CABIN 1 n n n WIDTH TOP 31 WIDTH BOTTOM 33 4 HEIGHT FRONT 31 2 HEIGHT REAR 31 WIDTH LWR WINDOW LINE CABIN FLOOR CABIN WIDTH MEASUREMENTS CABIN STATIONS 0 0 10 20 30 40 50 C G ARMS 560 TIE DOWN RINGS 6 27 2 24 2 60 70 80 9094 Figure 6 5 Internal Cabin Dimensions 6 8 1 July 1979 For Flight Training Reference Only ...

Page 87: ...40 Lbs Max 6 RAMP WEIGHT AND MOMENT 7 Fuel allowance for engine start taxi and runup 8 TAKEOFF WEIGHT AND MOMENT Subtract Step 7 from Step 6 SAMPLE AIRPLANE Weight lbs 1136 147 340 52 1675 5 1670 Moment Ib ins 1000 34 0 6 2 13 3 3 3 56 8 2 56 6 YOUR AIRPLANE Weight lbs Moment Ib ins 1000 9 Locate this point 1670 at 56 6 on the Center of Gravity Moment Envelope and since this point falls within the...

Page 88: ...CU MAX 118 1 KG MAXI 37 5 GAL 141 liters max 92 7 LITERS MAX LOADING GRAPH 100 75 50 25 12 I 3 14 I 5 LOAD MOMENT 1000 POUND INCHES NOTES Line representing adjustable seats shows the pilot or passenger center of gravity on adjustable seats positioned for an average occupant Refer to the Loading Arrangements Diagram for forward and aft limits of occupant C G range Figure 6 7 Loading Graph cr ID 1 X...

Page 89: ...CENTER OF GRAVITY MOMENT ENVELOPE 1500 1400 Q UJ Q O 1300 1200 1100 1000 650 i 700 I 30 35 40 45 50 55 LOADED AIRPLANE MOMENT 1000 POUND INCHES 60 r800 r775 SQ r 750 725 700 675 r 650 lu E 625 600 575 550 r 525 500 65 I Figure 6 8 Center of Gravity Moment Envelope For Flight Training Reference Only ...

Page 90: ... o 1 2 D i d CJ LU LD C C c 1 D 5 o f LT i i D n 11 s r 2b v s _ c_ c p 1 s s IS r u I i _ L C c s c M C 3 t d ir D LT C L L 1 v 3 i 1 11 r475 f 1 o o CO o o 1HDI3M 3NV1dUIV o o CM o o n n 6 12 LO CO ro CO CM CO a n 1 a LL o LL Ln LU X o IN H d O 1 d d LU _J 0 July mit a a o h 5 o 09 CD 1979 _ H n For Flight Training Reference Only ...

Page 91: ...items O optional equipment items replacing required or standard items A optional equipment items which are in addition to required or standard items A reference drawing column provides the drawing number for the item NOTE If additional equipment is to be installed it must be done in accordance with the reference drawing accessory kit instruc tions or a separate FAA approval Columns showing weight ...

Page 92: ...MBLY MCCAULEY FACH 3RAKE ASSEMBLY CCAJLEY LEFT BRAKE ASSEMBLY MCCAULtY RIGHT TIRE PLY BLACKWALL EACH TUflP EACH IHEELi 3R4KE i Tint ASSY 6 00X6 MAIN 2 WHEEL ASSY CLEVELAND M 1I3 EACH BRAKE ASSY CLEVELAND 30 75A LEFT BRAKE ASSY CLEVELAND 30 75A RIGHT TIRE 4 PLY BLACKWALL EACH TUBE EACH REF DRAWING 0450371 C294510 02Cl 3 611503 0102 0453 71 3406J OR 8406M C450412 0450077 C 161001 3501 0450 377 C4500...

Page 93: ...NJ tPsJrO mino rvoocOHOoociON cc a OOOO 1 0000 1 1 1 1 cooo Uj 0 r t _IO CDUJ X k LU XO h w O 3 T li LJ ccn o_ 5Oa 1 uj _JUJ UOX 1 O C1QLU J_ji OOZ LU I fvjr ifi i an CUUJ t UJl J lulu ctiac I Wh C t _J cC dJCO O o Oc til 1 j 1 r ore 0 CNJf J f f l C C5 OO r J 1 tf 1 i rsj r r or n r i i CO S M J XLU O f X _1 CC 1 iO X Z LU 2l Jfl 0 O 2 LL _ I5 LUX O 1 c z _ a_c ono 3 c i CC JC l LUt l J h i X 1 U...

Page 94: ...GYRO INSTALLATION REQUIRES ITEM A61 A DIRECTIONAL INDICATOR ATTITUDE INDICATOR RECORDER ENGINE HOUR METER OUTSIOE AH TEMPERATURE INDICATOR TACHOMETER INSTALLATION ENGINE RECORDING TACH INDICATOR INDICATOR TURN COORDINATOR 24 VOLT ONLY INDICATOR TURN COORDINATOR 10 30 V3LT INDICATOR VERTICAL SPEED E CABIN ACCOMMODATIONS SEAT PILOT INDIVIDUAL SLIDING SEAT VERTICALLY ADJUSTABLE PILOT REF DRAWING C661...

Page 95: ...CLUDES ENGINE EXHAUST SYSTEM F PLACARDS WARNINGS 6 MANUALS OPERATIONAL LIMITATIONS PLACARD VFR UAY OPERATIONAL LIMITATIONS PLACARD VF DAY NIGHT OPERATIONAL LIMITATIONS PLACARD IFR DAY k I 1 f IT I in 1 STALL WARNING HORN PNFJMATIC AUDIBLE PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL G AUXILIARY EQUIPMENT HOISTING RINGS AIRCRAFT CAbIN TOP NOT FACTORY INSTALLED CORROSION PROOFI...

Page 96: ...NGE FUEL TANKS NET CHANGE H AVIONICS AUTOPILOTS CESSNA 300 ADF RECEIVER WITH BFO K 546E INDICATOR UN 346A1 ANTENNA INSTALLATION LOOP ANTENNA INSTALLATION CABLE INSTALLATION MISC INSTALLATION COMPONENTS CESSNA 400 GLIDESLOPE WITH ILS INDICATOR EXCHANGED FOR LOC INDICATOR RECEIVER R 443B MOUNTING RIGID ANTENNA AUTO RAOIAI CENTERING INDICATOR ARC LOC EXCHANGE FOR VOR LOCIN ITE S H22 A AND H 5 A REF D...

Page 97: ...A 3ASIC AVIONICS KII USED rf ITH 1ST UNIT NAV COM FACTORY INSTALLATION RAOIO COOLING NOISE FILTER AU0I0K0N ALTERNATOR LH COM ANTENNA CABLE OMNI ANTENNA CABLE OMMI ANTENNA INSTALLATION VHF L H COM ANTENNA MICROPHONE INSTALLATION AUOIO CONTROL CABIN SPEAKFR INSTL HEADPHONE INSTALLATION COM ANTENNA OMNI COUPLER KIT AVAILABLE REF DRAWING 46860 2200 42410 5128 0770681 1 3910127 1 41420 0028 42943 0030 ...

Page 98: ...8 A TURN COORDINATOR D91 A RATE OF CLIMB IND E55 A SUN VISORS G05 A DUAL CONTROLS G34 A CIGARETTE LIGHTER H22 A CESSNA 300 MAV CQM RT 385A H34 A B4SIC AVIONICS KIT 152 II NAV PAC EQUIPMENT H16 A 1 CESSNA 301 TRANSPONDER 3T 3S9A H25 A RT 385A ND UNIT H 7 A COM ANTENNA E COUPLER KIT REF DRAWING S 2086 1 C 596530 0101 C596531 0101 0413466 2 0406003 1 0401022 0 413 466 C663507 n01 C661003 0505 C661080...

Page 99: ...ts 7 13 Shoulder Harnesses 7 13 Integrated Seat Belt Shoulder Harnesses With Inertia Reels 7 14 Entrance Doors And Cabin Windows 7 14 Control Locks 7 15 Engine 7 15 Engine Controls 7 15 Engine Instruments 7 16 New Engine Break In And Operation 7 17 Engine Oil System 7 17 Ignition Starter System 7 18 Air Induction System 7 18 Exhaust System 7 18 Carburetor And Priming System 7 18 Cooling System 7 1...

Page 100: ...irspeed Indicator 7 29 Vertical Speed Indicator 7 29 Altimeter 7 29 Vacuum System And Instruments 7 29 Attitude Indicator 7 31 Directional Indicator 7 31 Suction Gage 7 31 Stall Warning System 7 31 Avionics Support Equipment 7 32 Audio Control Panel 7 32 Transmitter Selector Switch 7 32 Audio Selector Switches 7 34 Com Auto Audio Selector Switch 7 34 Coin Both Audio Selector Switch 7 35 Annunciato...

Page 101: ...ered with aluminum skin The front spars are equipped with wing to fuselage and wing to strut attach fit tings The aft spars are equipped with wing to fuselage attach fittings and are partial span spars Conventional hinged ailerons and single slotted flaps are attached to the trailing edge of the wings The ailerons are constructed of a forward spar containing balance weights formed sheet metal ribs...

Page 102: ...PLANE SYSTEMS DESCRIPTIONS CESSNA MODEL 152 AILERON CONTROL SYSTEM RUDDER CONTROL SYSTEM Figure 7 1 Flight Control and Trim Systems Sheet 1 of 2 n n n n r n n n 7 4 1 July 1979 n n For Flight Training Reference Only ...

Page 103: ...A MODEL 152 SECTION 7 AIRPLANE SYSTEMS DESCRIPTIONS ELEVATOR CONTROL SYSTEM ELEVATOR TRIM CONTROL SYSTEM Figure 7 1 Flight Control and Trim Systems Sheet 2 of 2 1 July 1979 7 For Flight Training Reference Only ...

Page 104: ...n SECTION 7 AIRPLANE SYSTEMS DESCRIPTIONS CESSNA MODEL 152 Figure 7 2 Instrument Panel Sheet 1 of 2 n n 7 6 1 July 1979 n n n n n n For Flight Training Reference Only ...

Page 105: ...ator Additional Instrument Space Low Voltage Warning Light Ammeter 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 Map Compartment Cabin Heat Control Cabin Air Control Circuit Breakers Wing Flap Switch and Position Indicator Mixture Control Throttle With Friction Lock Microphone Elevator Trim Control Wheel and Position Indicator Carburetor Heat Control Electrical Switches Oil Pressure ...

Page 106: ... extension is firmly in place To remove the extensions reverse the above procedures TRIM SYSTEM _ A manually operated elevator trim tab is provided Elevator trimming is accomplished through the elevator trim tab by utilizing the vertically mounted trim control wheel Forward rotation of the trim wheel will trim nose down conversely aft rotation will trim nose up INSTRUMENT PANEL The instrument pane...

Page 107: ...on the extreme right side of the switch and control panel 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 ...

Page 108: ...ck of the pilot and passenger s seats to the aft cabin bulkhead Access to the baggage n n The minimum turning radius of the airplane using differential braking and nose wheel steering during taxi is approximately 24 feet 8 inches To obtain a minimum radius turn during ground handling the airplane may be rotated around either main landing gear by pressing down on the tailcone just forward of the ve...

Page 109: ...the center of the seat and apply pressure to the back To return the seat back to the upright position pull forward on the exposed portion of the seat back frame Both seat backs will also fold full forward The six way seats may be moved forward or aft adjusted for height and the seat back angle changed Position either seat by lifting the tubular handle under the inboard front corner of the seat bot...

Page 110: ... SHOULDER HARNE DETAINING STUD FREE END OF SEAT BELT Pull to tighten CESSNA MODEL 152 PILOT SSEATSHOWN SEAT BELT SHOULDER HARNESS WITH INERTIA REEL SEAT BELT BUCKLE Non adjustable SEAT BELT SHOULDER HARNESS ADJUSTABLE LINK Position link just below shoulder level pull link and harness down ward to connect to seat belt buckle Figure 7 4 Seat Belts and Shoulder Harnesses 7 12 1 July 1979 n n r r n n ...

Page 111: ... belts grasp the top of the buckle opposite the link and pull upward SHOULDER HARNESSES Each shoulder harness is attached to a rear doorpost above the window line and is stowed behind a stowage sheath above the cabin door To stow the harness fold it and place it behind the sheath No harness is available for the child s seat The shoulder harnesses are used by fastening and adjusting the seat belt f...

Page 112: ...d seat belt shoulder harnesses with inertia reels are availa ble for the pilot and front seat passenger The seat belt shoulder harnesses extend from inertia reels located in the upper cabin sidewall just aft of each cabin door to attach points outboard of the front seats A separate seat belt half and buckle is located inboard of the seats Inertia reels allow complete freedom of body movement Howev...

Page 113: ...ition and the elevators in a slightly trailing edge down position Proper installation of the lock will place the red flag over the ignition switch In areas where high or gusty winds occur 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 power...

Page 114: ...n electrical resistance type temperature sensor which receives power from the airplane electrical system Oil temperature limitations are 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 near the upper center portion of the instrument panel The instrument is calibrated in incremen...

Page 115: ...ilter If the oil is hot the bypass valve routes the oil from the accessory case forward through a flexible hose to the engine oil cooler mounted on the left forward side of the engine Returning to the accessory case the oil passes through the filter The filtered oil then enters a pressure relief valve which regulates engine oil pressure by allowing excessive oil to return to the sump while the bal...

Page 116: ...overed by an air filter which removes dust and other foreign matter from the induction air Airflow passing through the filter enters an airbox After passing through the airbox induction air enters the inlet in the carburetor which is under the engine and is then ducted to the engine cylinders through intake manifold tubes In the event carburetor ice is encountered or the intake filter becomes bloc...

Page 117: ...he airplane Details of this kit are presented in Section 9 Supplements PROPELLER The airplane is equipped with a two bladed fixed pitch one piece forged aluminum alloy propeller which is anodized to retard corrosion The propeller is 69 inches in diameter FUEL SYSTEM The airplane may be equipped with either a standard fuel system or long range system see figure 7 6 Both systems consist of two vente...

Page 118: ...uel quantity as determined from the most critical flight condition is about 1 5 gallons total This quantity was not exceeded by any other reasonable flight condition including pro longed 30 second full rudder sideslips in the landing configuration Takeoffs have not been demonstrated with less than 2 gallons total fuel 1 gallon per tank The fuel system is equipped with drain valves to provide a mea...

Page 119: ...ION SYSTEM SHOWN WITH FUELSHUTOFF VALVE IN ON POSITION CODE LZZ LZZD FUEL SUPPLY VENT MECHANICAL LINKAGE ELECTRICAL CONNECTION TO ENGINE Due to crossfeeding between fuel tanks the tanks should be re topped after each refueling to assure maximum capacity Figure 7 6 Fuel System Standard and Long Range 1 July 1979 7 21 For Flight Training Reference Only ...

Page 120: ...pedal travel increases pumping the pedals should build braking pressure If one brake becomes weak or fails use the other brake sparingly while using opposite rudder as required to offset the good brake ELECTRICAL SYSTEM The airplane is equipped with a 28 volt direct current electrical system see figure 7 7 This system uses a 24 volt battery mounted on the right forward side of the firewall as the ...

Page 121: ... FUEL QUANTITY INDICATORS TO FLASHING BEACON TO PITOT HEAT TO DIGITAL CLOCK TO STROBE LIGHTS TO CIGAR LIGHTER WITH FUSE AND CIRCUIT BREAKER TO LANDING AND TAXI LIGHTS TO IGNITION SWITCH TO WING FLAP SYSTEM TO RED DOORPOST MAPLIGHT TO LOW VOLTAGE WARNING LIGHT TO INSTRUMENT RADIO COMPASS AND POST LIGHTS TO OIL TEMPERATURE GAGE TO TURN COORDINATOR TO WHITE DOORPOST MAPLIGHT TO AUDIO MUTING RELAY TO ...

Page 122: ...OL UNIT AND LOW VOLTAGE WARNING LIGHT n The airplane is equipped with a combination alternator regulator high low voltage control unit mounted on the engine side of the firewall and a red warning light labeled LOW VOLTAGE under the ammeter on the instrument panel In the event an over voltage condition occurs the alternator control unit automatically removes alternator field current which shuts dow...

Page 123: ...ounted adjacent to the battery GROUND SERVICE PLUG RECEPTACLE A ground service plug receptacle may be installed to permit the use of an external power source for cold weather starting and during lengthy maintenance work on the electrical and electronic equipment Details of the ground service plug receptacle are presented in Section 9 Supple ments LIGHTING SYSTEMS EXTERIOR LIGHTING Conventional nav...

Page 124: ...e used in combination with the standard flood lighting The engine instrument cluster if post lighting is installed radio equipment and magnetic compass have integral lighting and operate independently of post or flood lighting Light intensity of the radio lighting is controlled by the RADIO LT rheostat control knob The integral compass and engine instrument cluster light intensity is controlled by...

Page 125: ...in from outlets in the cabin manifold near the pilot s and passenger s feet Windshield defrost air is also supplied by a duct leading from the manifold to a pair of outlets below the windshield For cabin ventilation pull the CABIN AIR knob out To raise the air temperature pull the CABIN HT knob out approximately 1 4 to 1 2 inch for a small amount of cabin heat Additional heat is available by pulli...

Page 126: ...CESSNA MODEL 152 DEFROSTER OUTLETS 0 CODE RAM AIR FLOW VENTILATING AIR HEATED AIR BLENDED AIR MECHANICAL CONNECTION P H n 0 n 0 n Figure 7 8 Cabin Heating Ventilating and Defrosting System 7 28 1 July 1979 r For Flight Training Reference Only ...

Page 127: ...e should not be confused with indicated altitude To obtain pressure altitude momentarily set the barometric scale on the altimeter to 29 92 and read pressure altitude on the altimeter Be sure to return the altimeter baromet ric scale to the original barometric setting after pressure altitude has been obtained Having set the ring to correct for altitude and temperature read the true airspeed shown ...

Page 128: ...OVERBOARD VENT LINE VACUUM PUMP VACUUM SYSTEM AIR FILTER aooo o o o 0 O 0 0 o o o o o o o o o o VACUUM RELIEF VALVE DIRECTIONAL INDICATOR n n n n n n Figure 7 9 Vacuum System 7 30 CODE INLET AIR VACUUM DISCHARGE AIR 1 July 1979 For Flight Training Reference Only ...

Page 129: ...e and displays airplane heading on a compass card in relation to a fixed simulated airplane image and index The directional indicator will precess slightly over a period of time Therefore the compass card should be set in accordance with the magnetic compass just prior to takeoff and occasionally re adjusted on extended flights A knob on the lower left edge of the instrument is used to adjust the ...

Page 130: ...s package includes a marker beacon receiver The operational features of both audio control panels are similar and are discussed in the following paragraphs TRANSMITTER SELECTOR SWITCH _ When the avionics package includes two transmitters a two position toggle type switch labeled TRANS SELECT or XMTR depending upon which audio control panel is installed is provided to switch the micro phone to the ...

Page 131: ...H SPEAKER SIDETONE VOLUME CONTROL USED WITH MARKER BEACON COM BOTH AUDIOSELECTOR SWITCH HEADSET SIDETONE INTERNAL ADJUSTMENT ACCESS SPEAKER SIDETONE INTERNAL ADJUSTMENT ACCESS XMTR ANN LTS TRANSMITTER SELECTOR SWITCH COM AUTO 1 AUDIOSELECTOR SWITCH AUDIOSELECTOR SWITCHES ANNUNCIATOR LIGHTS BRIGHTNESS AND TEST SWITCH Figure 7 10 Audio Control Panel 1 July 1979 7 33 For Flight Training Reference Onl...

Page 132: ...he associated receiver n n n A special feature of the audio control panel used with a marker beacon receiver is separate control of NAV and COM audio from the NAV COM radios With this installation the audio selector switches labeled NAV 1 and 2 select audio from the navigation receivers of the NAV COM radios only Communication receiver audio is selected by the switches labeled COM AUTO and BOTH De...

Page 133: ...ation of placing the COM AUTO switch in the SPEAKER position and the COM BOTH switch in the PHONE position or vice versa is not normally recom mended as it will cause audio from both communications receivers and any other navigation receiver with its audio selector switch in the PHONE position to be heard on both the airplane speaker and the headset simultaneously ANNUNCIATOR LIGHTS BRIGHTNESS AND...

Page 134: ...ne headset installations are offered The standard system provided with avionics equipment includes a hand held microphone and separate headset The keying switch for this microphone is on the microphone Two optional microphone headset installations are also available these feature a single unit microphone headset combina tion which permits the pilot to conduct radio communications without interrupt...

Page 135: ...F communication equipment is the last to be affected Installation of static dischargers reduces interference from precipita tion static but it is possible to encounter severe precipitation static conditions which might cause the loss of radio signals even with static dischargers installed Whenever possible avoid known severe precipita tion areas to prevent loss of dependable radio signals If avoid...

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