Cessna 152 1979 Pilot Operating Handbook Download | Manualshive

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CESSNA

SECTION

7

MODEL 152

AIRPLANE & SYSTEMS

DESCRIPTIONS

1 July 1978

7-35

SPEAKER SIDETONE VOLUME CONTROL

A speaker sidetone volume control is a feature of audio control panels used on airplanes not
equipped with marker beacon receivers. The control is used to adjust the level of sidetone
volume heard on the airplane speaker only. Sidetone volume heard on a headset is not
externally adjustable. Rotate the knob, labeled SIDETONE VOL, clockwise to increase
speaker sidetone volume and counterclockwise to decrease it. Be aware that if the sidetone
level is set too high, it can cause audio feedback (squeal) when transmitting.

MICROPHONE-HEADSET INSTALLATIONS

Three types of microphone-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 combination
which permits the pilot to conduct radio communications without interrupting other control
operations to handle a hand-held microphone. One microphone-headset combination is
offered without a padded headset and the other version has a padded headset. The
microphone-headset combinations utilize a remote keying switch located on the left grip of the
pilot's control wheel. The microphone and headset jacks are located on the pedestal below the
instrument panel. Audio to all three headsets is controlled by the individual audio selector
switches and adjusted for volume level by using the selected receiver volume controls.

NOTE

When transmitting, the pilot should key the microphone, place the microphone as
close as possible to the lips and speak directly into it.

STATIC DISCHARGERS

If frequent IFR flights are planned, installation of wick-type static dischargers is recommended
to improve radio communications during flight through dust or various forms of precipitation
(rain, snow or ice crystals). Under these conditions, the build-up and discharge of static
electricity from the trailing edges of the wings, rudder, elevator, propeller tips, and radio
antennas can result in loss of usable radio signals on all communications and navigation radio
equipment. Usually the ADF is first to be affected and VHF communication equipment is the
last to be affected.

Installation of static dischargers reduces interferences from precipitation 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 sever
precipitation areas to prevent loss of dependable radio signals. If avoidance is impractical,
minimize airspeed and temporary loss of radio signals while in these areas

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Summary of Contents for 152 1979

Page 1: ...MPANY THIS DOCUMENT MUST BE CARRIED IN THE AIRPLANE AT ALL TIMES 1979 MODEL 152 Serial No 152 83496 Registration No N49696 THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY CAR PART 3 AND CONSTITUTES THE FAA APPROVED FLIGHT MANUAL CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA ...

Page 2: ...NSERTED _______________________________________________ CESSNA AIRCRAFT COMPANY PAWNEE DIVISION This is a duplicate manual issued to replace one originally provided for the airplane identified on the cover page on 4 6 79 All revisions if any have been incorporated as of 8 3 89 Subsequent revisions supplied by Cessna Aircraft Company must be properly inserted Cessna Aircraft Co ...

Page 3: ...ilable at Cessna Dealers worldwide Specific benefits and provisions of warranty plus other important benefits for you are contained in your Customer Care Program book supplied with your airplane Warranty service is available to you at authorized Cessna Dealers throughout the world upon presentation of your Customer Care Card which establishes your eligibility under the warranty FACTORY TRAINED PER...

Page 4: ...und Roll 725 ft Total Distance over 50 ft obstacle 1340 ft LANDING PERFORMANCE Ground roll 475 ft Total Distance over 51 ft obstacle 1200 ft STALL SPEED CAS Flaps up power off 48 knots Flaps down power off 43 knots MAXIMUM WEIGHT Ramp 1675 lb Takeoff or landing 1670 lb STANDARD EMPTY WEIGHT 152 1101 lb 152 II 1 1133 lbs MAXIMUM USEFUL LOAD 152 574 lbs 152 II 54 lbs2 BAGGAGE ALLOWANCE 120 lbs WING ...

Page 5: ...presently existing pages This bar will be located adjacent to the applicable revised area on the outer margin of the page All revised pages will carry the revision number and date on the applicable page The following Log of Effective pages provides the dates of issue for original and revised pages and a listing of all pages in the handbook Pages affected by the current revision are indicated by an...

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

Page 7: ...ximum Certificated Weights 1 4 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 ...

Page 8: ...CESSNA GENERAL MODEL 152 1 July 1978 1 2 Figure 1 1 Three View ...

Page 9: ...monly used DESCRIPTIVE DATA ENGINE Number of Engines 1 Engine Manufacturer Avco Lycoming Engine Model Number O 235 2L2C Engine Type Normally aspirated direct drive air cooled horizontally opposed carburetor equipped four cylinder engine with 233 31 cu In displacement Horsepower Rating and Engine Speed 110 rated BHP at 2550 RPM PROPELLER Propeller Manufacturer McCauley Accessory Division Propeller ...

Page 10: ... until a total of 50 hours has accumulated or oil consumption has stabilized NOTE The airplane was delivered from the factory with a corrosion 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...

Page 11: ...m Useful Load 152 574 lbs 152 II 542 lbs CABIN AND ENTRY DIMENSIONS Detailed dimensions of the cabin interior and entry door openings are illustrated in Section 6 BAGGAGE SPACE AND ENTRY DIMENSIONS Detailed dimensions of the cabin interior and entry door openings are illustrated in Section 6 SPECIFIC LOADINGS Wing Loading 10 5 lbs sq ft Power Loading 15 2 lbs hp SYMBOLS ABBREVIATIONS AND TEMINOLOG...

Page 12: ...nimum steady flight speed at which the airplane is controllable VSO Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the landing configuration at the most forward center of gravity VX Best Angle of Climb Speed is the speed which results in the greatest gain of altitude in a given horizontal distance VY Best Rate of Climb Speed is the speed which results in...

Page 13: ...able Fuel is the quantity of fuel that can not be safely 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 power setting and or flight configuration g g is acceleration due to gravity WEIGHT AND BALANCE TERMINOLOGY Reference Datum Ref...

Page 14: ...e including unusable fuel full operating fluids and full engine oil Basic Empty Weight Basic Empty Weight is the standard empty weight plus the weight of optional equipment Useful Load Useful Load is the difference between takeoff weight and the basic empty weight Maximum Ramp Weight Maximum Ramp Weight is the maximum weight approved for ground maneuver It includes the weight of start taxi and run...

Page 15: ...D TO O 235 NCS REFER TO DATA IN SECTION 9 SUPLEMENT TABLE OF CONTENTS page Introduction 2 3 Airspeed Limitations 2 3 Airspeed Indicator Markings 2 3 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 ...

Page 16: ...er necessary information for airplanes equipped with specific options Your Cessna is certificated under FAA Type Certificate No A19 as Cessna Model No 152 AIRSPEED LIMITATIONS Airspeed limitations and operational significance are shown in figure 2 1 SPEED KCAS KIAS REMARKS VNE Never Exceed Speed 145 149 Do not exceed this speed in any operation VNO Maximum Structural Cruising Sped 108 111 Do not e...

Page 17: ...peed Yellow arc 111 149 Operations must be conducted with caution and only in smooth air Red Line 149 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 Maximum Engine speed 2550 RPM NOTE The static RPM rang...

Page 18: ... 100 psi Fuel Quantity E 0 75 Gal Unusable Each Tank Figure 2 3 Power Plant Instrument Markings WEIGHT LIMITS Maximum Ramp Weight 1675 lbs Maximum Takeoff Weight 1670 lbs Maximum Landing Weight 1670 lbs Weight in Baggage Compartment Baggage Area 1 or passenger on Child s seat station 50 76 120 lbs See note below Baggage Area station 76 94 40 lbs See note below NOTE The maximum combined weight capa...

Page 19: ...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 that the airplane is that the airplane is clean in aerodynamic design and will build up speed quickly with the nose down Proper speed control is an essential requirement for execution of any maneuver and care should always be exercised to a...

Page 20: ...nditions 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 fuel quantity indicator reads empty red line cannot be safely used in flight Approved Fuel Grad...

Page 21: ...his airplane in this category are contained 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 Spins Slow Decel Chandelles 95 KIAS Stalls Except Whip Stalls Slow Decel Steep Turns 95 KIAS Intentional spins prohibited with flaps extended Flight into k...

Page 22: ... FUEL 100LL 100 MIN GRADE AVIATION CASLOINE CAP 13 U S GAL Near fuel tank filler cap long range tanks FUEL 100LL 100 MIN GRADE AVIATION CASLOINE CAP 19 5 U S GAL CAP 13 0 U S GAL TO BOTTOM OF FILLER COLLAR 5 On instrument panel near 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 RUD...

Page 23: ...978 2 10 6 A calibration card is provided to indicate the accuracy of the magnetic compass in 30 increments 7 On oil filler cap OIL 6 QTS 8 On control lock CONTROL LOCK REMOVE BEFORE STARTING ENGINE 9 Near airspeed indicator MANEUVER SPEED 104 KIAS ...

Page 24: ...hout Engine Power 3 4 Precautionary 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 5 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 Voltag...

Page 25: ...3 11 Emergency Descent 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 Insufficient Rate of Charge 3 15 ...

Page 26: ...essary 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 Wing Flaps Dow...

Page 27: ...alve 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 Electrical Swi...

Page 28: ...qualize pressure so doors 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 Fi...

Page 29: ...vailable WARNING After discharging an extinguisher within a closed cabin ventilate the cabin 5 If fire appears out and electrical power is necessary for continuance of flight 6 Master Switch ON 7 Circuit Breakers CHECK for faulty circuit do not reset 8 Radio Electrical Switches ON one at a time with delay after each until short circuit is localized 9 Vents Cabin Air Heat OPEN when it is ascertaine...

Page 30: ...lter ice and apply carburetor heat 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 heat 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...

Page 31: ...AGE LIGHT ILLUMINATES DURING FLIGHT Ammeter Indicates Discharge 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 Rad...

Page 32: ...ned straight ahead with only small changes in direction to avoid obstructions Altitude and airspeed are seldom sufficient to execute a 180 gliding turn necessary to 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 establish...

Page 33: ...of difficulty in judging height over a water surface LANDING WITHOUT ELEVATOR CONTROL Trim for horizontal flight with an airspeed of approximately 55 KIAS and flaps lowered to 200 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 ...

Page 34: ...evel flight by leveling the miniature airplane 4 Check accuracy of the turn by observing the compass heading which should be the reciprocal of the original heading 5 If necessary adjust heading primarily with skidding motions rather than rolling motions so that the compass will read more accurately 6 Maintain altitude and airspeed by cautious application of elevator control Avoid overcontrolling b...

Page 35: ...lide 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 INADVERTENT FLIGHT INTO ICING CONDITIONS Flight into icing conditions is prohibited An inadvertent encounter with these conditions can best be...

Page 36: ...ottle 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 FOULING A slight engine roughness in flight may be caused by one or more spark plugs becoming fouled by carbon or lead deposits This may be verified by turning the ignition swit...

Page 37: ... 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 periodic monitoring of the ammeter and low voltage warning light however the cause of these malfunctions is usually difficult to determine A broken alternator drive belt or wiring is most likely the cause of alternator fai...

Page 38: ...ions 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 a discharge rate will be shown on the ammeter followed by illumination of the low voltage warning light Since this may be a nuisance trip out an attempt should be made to reac...

Page 39: ...Right Wing 4 5 Nose 4 6 Left Wing 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 Before Landing 4 9 Landing 4 9 Normal Landing 4 9 Short Field Landing 4 9 Balked Landing 4 9 After Landing 4 9 Securing Airplane 4 10 AMPLIFIED PROCEDURES S...

Page 40: ...Alternator Check 4 13 Takeoff 4 14 Power Check 4 14 Wing Flap Settings 4 14 Crosswind Takeoff 4 15 Enroute Climb 4 15 Cruise 4 15 Fuel Savings Procedures For Flight Training Operations 4 16 Stalls 4 17 Spins 4 17 Landing 4 19 Short Field Landing 4 19 Crosswind Landing 4 20 Balked Landing 4 20 Cold Weather Operation 4 20 Noise Abatement 4 22 ...

Page 41: ...All speeds in KIAS Takeoff Normal Climb Out 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 ...

Page 42: ...ions of frost ice or snow from wing tail 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 ...

Page 43: ...dicators CHECK QUANTITY 7 External and Interior lights ON if night flight is contemplated check to ensure that all are working 8 Pitot Heat ON if flight in instrument conditions is contemplated check to ensure that pitot tube is warm to touch within 30 seconds 9 Lights and pitot heat OFF 10 Master Switch OFF 11 Fuel valve ON 2 EMPANNAGE 1 Rudder Gust Lock REMOVE 2 Tail Tie down DISCONNECT 3 Contro...

Page 44: ... CHECK for proper inflation cuts wear 2 Fuel sump CHECK before first flight of day and after each refueling drain fuel sample from sump checking for water and other contaminants 3 Fuel Quantity CHECK VISUALLY 4 Fuel Filler Cap SECURE 7 LEFT WING Leading Edge 1 Pitot tube REMOVE COVER CHECK for obstruction damage 2 Stall warning vane CHECK 3 Fuel Tanks Vent Opening CHECK for stoppage 4 Wing Tie Dow...

Page 45: ... 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 exceed 125 RPM on either magneto or 50 RPM differential between magnetos b Carburetor Heat CHECK for RPM drop c Engine Instruments and Ammeter...

Page 46: ... feet LEAN to obtain 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 refer to section 5 of handbook 67 KIAS at sea level decreasing to 60 KIAS at 12 000 ft MSL 2 Throttle FULL OPEN 3 Mixture R...

Page 47: ...OWN 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 1 Throttle FULL OPEN 2 Carburetor Heat COLD 3 Wing Flaps...

Page 48: ...MODEL 152 NORMAL PROCEDURES 1 July 1978 4 10 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 ...

Page 49: ... the mixture control in the idle cut off position the throttle full open and 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 press...

Page 50: ...CESSNA SECTION 4 MODEL 152 NORMAL PROCEDURES 1 July 1978 4 12 ...

Page 51: ...hould 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 or show greater than 50 ...

Page 52: ...ove 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 clockwise to prevent the throttle from creeping back from a maximum power position Similar friction lock adjustment should be made as required in other flight conditions to maintain a fixed throttle setting WING FLAP SETTINGS Norm...

Page 53: ... obtain maximum RPM For maximum rate of climb use the best rate of climb speeds shown in the Rate Of Climb chart in Section 5 If an 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 pe...

Page 54: ...re should be leaned until engine RPM peaks and drops 25 50 RPM At lower powers it may be necessary to enrich the mixture 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 t...

Page 55: ...ventional for the flap up and flaps down condition The stall warning horn produces a steady signal 5 to 10 knots before the actual stall is reached and remains on until the airplane flight attitude is changed Stall speeds for various combinations of flap setting and bank angle are summarized in Section 5 SPINS Intentional spins are approved in this airplane see Section 2 Before attempting to perfo...

Page 56: ...ull aft elevator A slightly greater rate of deceleration than for normal stall entries or the use of partial power at the entry will assure more consistent and positive entries to the spin Both elevator and rudder controls should be held full with the spin until the spin recovery is initiated An inadvertent relaxation of either of these controls could result in the development of a nose down spira...

Page 57: ...aracteristics and in the recovery lengths for spins of more than 3 turns However the above recovery procedure should always be used and will result in the most expeditious recovery from any spin Intentional spins with flaps extended are prohibited since the high speeds which may occur during recovery are potentially damaging to the flap wing structure LANDING Normal landing approaches can be made ...

Page 58: ...lied Upon reaching a safe airspeed the flaps should be slowly retracted to the full up position COLD WEATHER OPERATION Prior to starting with temperatures below freezing it is advisable to pull the propeller through several times by hand to break loose or limber the oil thus conserving battery energy NOTE When pulling the propeller through by hand treat it as if the ignition switch is turned on A ...

Page 59: ...ed an additional three strokes just prior to pulling the propeller through by hand Carburetor heat should be applied after the engine starts Leave the carburetor heat on until the engine runs smoothly NOTE If the engine fires but does not start or continue running repeat the above starting procedure beginning with step 6 If the engine does not start during the first few attempts or if engine firin...

Page 60: ... sensitive areas should make every effort to fly not less than 2000 feet above the surface weather permitting even though flight at a lower level may be consistent with the provisions of government regulations During departure from or approach to an airport climb after takeoff and descent for landing should be made so as to avoid prolonged flight at low altitude near noise sensitive areas NOTE The...

Page 61: ...monstrated Operating Temperature 5 7 Figure 5 1 Airspeed Calibration 5 8 Figure 5 2 Temperature Conversion Chart 5 9 Figure 5 3 Stall Speeds 5 9 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 5 15 Figure 5 9 Endurance Profile 24 5 Gallons 5 17 Figure 5 10...

Page 62: ...CESSNA SECTION 5 MODEL 152 PERFORMANCE 1 July 1978 5 2 ...

Page 63: ...ne and propeller condition and 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 illustrate the effect of different variables Sufficiently detailed information is p...

Page 64: ...ar sample problem the takeoff distance 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 80 Feet Total distance to clear a 50 foot obstacle 20 Feet These distances are well within the available takeoff field length However a correction for the effect of wind may be made based on Note 3 of the takeoff chart T...

Page 65: ...nder no wind conditions The endurance profile chart figure 5 9 shows a corresponding 3 9 hours The range figure of 375 nautical miles is corrected to account for the expected 10 knot headwind at 5500 feet Range zero wind 375 Decrease in range due to wind 3 9 hours x 10 knot headwind 39 Corrected range 336 Nautical Miles This indicates that the trip can be made without a fuel stop using approximate...

Page 66: ... case assuming a temperature 16 C above standard the correction would be 16 C 10 C 16 Increase With this factor included the fuel estimate would be calculated as follows Fuel to climb standard temperature 1 0 gallon Increase due to non standard temperature 1 0 x 16 0 2 gallon Corrected fuel to climb 1 2 gallon Using a similar procedure for the distance to climb results in 10 nautical miles The res...

Page 67: ... distance at the destination airport Figure 5 10 presents landing distances for various airport altitude and temperature combinations using the short field technique The distances corresponding to 2000 feet and 30 C are as follows 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 ...

Page 68: ...wer required for level flight or maximum rated RPM dive Flaps Up KIAS 40 50 60 70 80 90 100 110 120 130 140 KCAS 46 53 60 69 78 88 97 107 117 127 136 Flaps 10 KIAS 40 50 60 70 80 85 KCAS 44 52 61 70 80 84 Flaps 30 KIAS 40 50 60 70 80 85 KCAS 43 51 61 71 82 87 Figure 5 1 Airspeed Calibration ...

Page 69: ...CESSNA SECTION 5 MODEL 152 PERFORMANCE 1 July 1978 5 9 TEMPERATURE CONVERSION CHART Figure 5 2 Temperature Conversion Chart ...

Page 70: ...ST REARWARD CENETER OF GRAVITY ANGLE OF BANK 0º 30º 45º 60º WEIGHT LBS FLAP DEFLECTION KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 36 46 39 49 43 55 51 65 10 36 43 39 46 43 51 51 61 1670 30 31 41 33 44 37 49 44 58 MOST FORWARD CENETER OF GRAVITY ANGLE OF BANK 0º 30º 45º 60º WEIGHT LBS FLAP DEFLECTION KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 40 48 43 52 48 57 57 68 10 40 46 43 49 48 55 57 65 1670 ...

Page 71: ...ances by 15 of the ground roll figure 0 C 10 C 20 C 30 C 40 C Takeoff Speed KIAS WT LBS Lift off at 50 Press Alt Ft GRND RUN TO CLEAR 50 OBS GRND RUN TO CLEAR 50 OBS GRND RUN TO CLEAR 50 OBS GRND RUN TO CLEAR 50 OBS GRND RUN TO CLEAR 50 OBS 1670 50 64 S L 1000 2000 3000 4000 5000 6000 7000 8000 640 705 775 885 940 1040 1145 1270 1405 1190 1310 1445 1600 1775 1970 2200 2470 2800 695 765 840 925 102...

Page 72: ...Mixture Leaned above 3000 for maximum RPM WEIGHT L BS PRESS ALT FT CLIMB SPEED KIAS RATE OF CLIMB FPM 20 C 0 C 20 C 40 C S L 67 835 765 700 630 2 000 66 735 670 600 535 4 000 65 635 570 505 445 6 000 63 535 475 415 355 8 000 62 440 380 320 265 10 000 61 340 285 230 175 1670 12 000 60 245 190 135 85 Figure 5 5 Rate of Climb ...

Page 73: ... standard temperature 4 Distances shown are based on zero wind FROM SEA LEVEL WT LBS PRESSURE ALTITUDE FT TEMP ºC CLIMB SPEED KIAS RATE OF CLIMB FPM TIME MIN FUEL USED GALLONS DISTANCE NM S L 15 67 715 0 0 0 1000 13 66 675 1 2 2 2000 11 66 630 3 4 3 3000 9 65 590 5 7 5 4000 7 65 550 6 9 7 5000 5 64 505 8 1 2 9 6000 3 63 465 10 1 4 12 7000 1 63 425 13 1 7 14 8000 1 62 380 15 2 0 17 9000 3 62 340 18...

Page 74: ... 4 8 56 90 4 6 54 89 4 4 2100 53 86 4 4 51 85 4 2 49 84 4 0 2000 48 81 3 9 46 80 3 8 45 79 3 7 6000 2500 75 105 6 1 71 104 5 7 2400 72 101 5 8 67 100 5 4 64 99 5 2 2300 64 96 5 2 60 95 4 9 57 94 4 7 2200 57 90 4 6 54 89 4 4 52 88 4 3 2100 51 85 4 2 49 84 4 0 48 83 3 9 2000 46 80 3 8 45 79 3 7 44 77 3 6 8000 2550 75 107 6 1 71 106 5 7 2500 76 105 6 2 71 104 5 8 67 103 5 4 2400 68 100 5 5 64 99 5 2 ...

Page 75: ... Temperature Zero Wind NOTES This chart allows for the fuel used for engine start taxi takeoff and climb and distance during climb as shown in figure 5 6 Reserve fuel is based on 45 minutes at 45 BHP and is 2 8 gallons Performance is shown for an airplane equipped with speed fairings which increases the cruise speeds by approximately two knots Figure 5 8 Range Profile Sheet 1 of 2 ...

Page 76: ... Temperature Zero Wind NOTES This chart allows for the fuel used for engine start taxi takeoff and climb and distance during climb as shown in figure 5 6 Reserve fuel is based on 45 minutes at 45 BHP and is 2 8 gallons Performance is shown for an airplane equipped with speed fairings which increases the cruise speeds by approximately two knots Figure 5 8 Range Profile Sheet 2 of 2 ...

Page 77: ...onditions 1670 Pounds Recommended Lean Mixture for Cruise Standard Temperature NOTES 1 This chart allows for the fuel used for engine start taxi takeoff and climb and distance during climb as shown in figure 5 6 2 Reserve fuel is based on 45 minutes at 45 BHP and is 2 8 gallons Figure 5 9 Endurance Profile Sheet 1 or 2 ...

Page 78: ...onditions 1670 Pounds Recommended Lean Mixture for Cruise Standard Temperature NOTES 3 This chart allows for the fuel used for engine start taxi takeoff and climb and distance during climb as shown in figure 5 6 4 Reserve fuel is based on 45 minutes at 45 BHP and is 2 8 gallons Figure 5 9 Endurance Profile Sheet 2 or 2 ...

Page 79: ...0 C WT LBS Speed at 50 KIAS Press Alt Ft Grnd roll To Clear 50 obs Grnd roll To Clear 50 obs Grnd roll To Clear 50 obs Grnd roll To Clear 50 obs Grnd roll To Clear 50 obs 1670 54 S L 1000 2000 3000 4000 5000 6000 7000 8000 450 465 486 500 520 540 560 585 605 1160 1185 1215 1240 1275 1305 1340 1375 1410 465 486 500 520 540 560 580 605 630 1187 1215 1240 1275 1305 1335 1370 1410 1450 485 500 520 540...

Page 80: ...F Sea Level 15 59 1 000 13 55 5 2 000 11 52 3 000 9 48 5 4 000 7 45 5 000 5 41 5 6 000 3 38 7 000 1 34 5 8 000 1 31 9 000 3 27 5 10 000 5 24 11 000 7 20 5 12 000 9 17 13 000 11 13 5 14 000 13 10 15 000 15 6 5 16 000 17 3 17 000 19 0 5 18 000 21 4 19 000 23 7 5 20 000 25 11 Figure 5 11 Standard Temperature ...

Page 81: ...N 6 MODEL 152 WEIGHT BALANCE EQUIPMENT LIST 1 July 1978 6 1 SECTION 6 WEIGHT BALANCE EQUIPMENT LIST TABLE OF CONTENTS Page Introduction 6 2 Airplane Weighing Procedures 6 2 Weight and Balance 6 4 Equipment List 6 13 ...

Page 82: ...CESSNA SECTION 6 MODEL 152 WEIGHT BALANCE EQUIPMENT LIST 1 July 1978 6 2 ...

Page 83: ...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 record the weight shown on ...

Page 84: ...Weights as weighted W N X B X X ARM A w IN Item Weight Lbs X C G Arm in Moment 1000 Lb in Airplsne Weight From Iem 5 Page 6 3 14 7 Add Oil No Oil Fliter 6 Qts 7 5 lb gal W Oil Fliter 7 qts 7 5 lb gal 14 7 40 0 Add Unusable Fuel Std Tanks 1 5 Gal at 6 lb gal L R Tanks 1 5 Gal at 6 lb gal 40 0 Equipment Changes Airplane Basic Empty Weight Figure 6 1 Sample Ariplane Weighing ...

Page 85: ... 1978 6 5 Airplane Model SERIAL NUMBER PAGE NUMBER Item Nr Description of Article or Modification ADDED REMOVED RUNNING BASIC EMPTY WEIGHT Date IN OUT WT LB AR M IN MOMENT 1000 WT LB ARM IN MOMEN T 1000 WT LB MOMENT 1000 Figure 6 2 Sample Weight and Balance Record ...

Page 86: ...oment 1000 on the loading problem Use the Loading Graph to determine the moment 1000 for each additional item to be carried then list these on the loading problem NOTE Loading Graph information for the pilot passengers and baggage is based on seats positioned for average occupants and baggage loaded in the center of the baggage areas as shown on the Loading Arrangements diagram For loadings which ...

Page 87: ...CESSNA SECTION 6 MODEL 152 WEIGHT BALANCE EQUIPMENT LIST 1 July 1978 6 7 ...

Page 88: ...CESSNA SECTION 6 MODEL 152 WEIGHT BALANCE EQUIPMENT LIST 1 July 1978 6 8 ...

Page 89: ...ong Range tanks 37 5 Gal maximum Reduce Fuel As limited by maximum weight Pilot and Passenger station 33 to 41 340 13 3 Baggage Area 1 station 50 76 120 max 52 3 3 Baggage Area 2 station 76 94 40 max RAMP WEIGHT AND MOMENT 1675 56 8 Fuel allowance for engine start and runup 5 0 2 TAKEOFF WEIGHT AND MOMENT 1670 56 6 Locate this point 1670 at 56 6 on the Center of Gravity envelope chart and since th...

Page 90: ...978 6 10 Figure 6 7 Loading Graph 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 ...

Page 91: ...CESSNA SECTION 6 MODEL 152 WEIGHT BALANCE EQUIPMENT LIST 1 July 1978 6 11 Figure 6 8 Center of Gravity Moment Envelope ...

Page 92: ...CESSNA SECTION 6 MODEL 152 WEIGHT BALANCE EQUIPMENT LIST 1 July 1978 6 12 Figure 6 9 Center of Gravity Limits ...

Page 93: ...A certification S standard equipment 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 instructions or a separate ...

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Page 101: ... 11 Seats 7 11 Seat Belts And Shoulder Harnesses Seat Belts 7 13 Seat belts 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 Engine Oil System 7 17 Air Induction System 7 18 Exhaust System 7 18 Carburetor And Priming System 7 18 Cooling Syste...

Page 102: ...ng System 7 27 Pitot Static System And Instruments 7 27 Airspeed Indicator 7 29 Rate Of Climb 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 Automatic Audio Selector Sw...

Page 103: ...lerons 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 and V type corrugated aluminum skin joined together at the trailing edge The flaps are constructed basically the same as the ailerons with the exception of the balance weights and the addition of a formed sheet metal leadin...

Page 104: ...CESSNA SECTION 7 MODEL 152 AIRPLANE SYSTEMS DESCRIPTIONS 1 July 1978 7 4 ...

Page 105: ...CESSNA SECTION 7 MODEL 152 AIRPLANE SYSTEMS DESCRIPTIONS 1 July 1978 7 5 ...

Page 106: ...CESSNA SECTION 7 MODEL 152 AIRPLANE SYSTEMS DESCRIPTIONS 1 July 1978 7 6 ...

Page 107: ...2 Nav Com 31 Elevator Trim Control Wheel and Position Indicator 11 Course Deviation and ILS Glide Slope Number 1 Nav Com 32 Carburetor Heat Control Knob 12 Marker Beacon Indicator Lights and Switches 33 Electrical Switches 13 Transponder 34 Oil Pressure Gage 14 Number 1 Nav Com Radio 35 Oil Temperature Gage 15 Audio Control Pane 36 Cigar Lighter 16 Number 2 Nav Com Radio 37 Instrument Panel and Ra...

Page 108: ...r slightly to the left of the control column To the left of these instruments is the airspeed indicator turn coordinator and suction gage The clock altimeter rate of climb indicator and navigation instruments are above and or to the right of the control column Avionics equipment is stacked approximately on the centerline of the panel with space for additional equipment on the lower right side of t...

Page 109: ...er pedals left rudder pedal to steer left and right rudder pedal to steer right When a rudder pedal is depressed a spring loaded steering bungee which is connected to the nose gear and to the rudder bars will turn the nose wheel through an arc of approximately 8 51 each side of center By applying either left or right brake the degree of turn may be increased up to 301 each side of center ...

Page 110: ...0º move the switch lever to the right to clear 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 15 ampere circuit breaker labeled FLAP on the right side of the instrument panel LANDING GEAR SYSTEM The landing gear is of the tricycle type with a steerable nose wheel and two ma...

Page 111: ...ay 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 bottom and slide the seat to the desired position Release the lever and check that the seat is locked in place To raise or lower the seat rotate the crank located under the outboard comer of each seat Seat back angle ...

Page 112: ...CESSNA SECTION 7 MODEL 152 AIRPLANE SYSTEMS DESCRIPTIONS 1 July 1978 7 12 ...

Page 113: ...senger s seats To release the seat 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 faste...

Page 114: ...s one on each side of the cabin refer to Section 6 for cabin and cabin door dimensions The doors incorporate a recessed exterior and interior door handle a key operated door lock left door only a door stop mechanism and an operable window To open the doors from outside the airplane utilize the recessed door handle near the aft edge of each door Grasp the forward edge of the handle and pull out To ...

Page 115: ... is powered by a horizontally opposed four cylinder overhead valve air cooled carbureted engine with a wet sump oil system The engine is a Lycoming Model 0 235 L2C and is rated at 110 horsepower at 2550 RPM Major engine accessories mounted on the front of the engine include a starter a belt driven alternator and an oil cooler Dual magnetos are mounted on an accessory drive pad on the rear of the e...

Page 116: ...s are the normal operating range green arc which is IOO 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 increments of 100 RPM and indicates both engine and propeller speed An hour meter below the center of the tachometer dial records elapsed e...

Page 117: ... the pressure oil is circulated to various engine parts for lubrication Residual oil returns to the sump by gravity flow An oil filler cap oil dipstick is located at the rear of the engine on the right side The filler cap dipstick is accessible through an access door in the engine cowling The engine should not be operated on less than four quarts of oil To minimize loss of oil through the breather...

Page 118: ...ted air from the muffler shroud is obtained from an unfiltered outside source Use of full carburetor heat at full throttle will result in a loss of approximately 150 to 200 RPM EXHAUST SYSTEM Exhaust gas from each cylinder passes through riser assemblies to a muffler and tailpipe on the underside of the engine The muffler is constructed with a shroud around the outside which forms a heating chambe...

Page 119: ...uipped 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 is equipped with either a standard fuel system see figure 7 6 The system consists of two vented fuel tanks one in each wing a fuel shutoff valve fuel strainer manual primer and carburetor Refer to figure 7 5 for fuel qu...

Page 120: ...CESSNA SECTION 7 MODEL 152 AIRPLANE SYSTEMS DESCRIPTIONS 1 July 1978 7 20 ...

Page 121: ...allon remains in either a standard or long range tank as unusable fuel The indicators cannot be relied upon for accurate readings during skids slips or unusual attitudes The amount of unusable fuel is relatively small due to the dual outlets at each tank The maximum unusable fuel quantity as determined from the most critical flight condition is about 1 5 gallons total This quantity was not exceede...

Page 122: ...re If the brakes become spongy or 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 off set 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 f...

Page 123: ...CESSNA SECTION 7 MODEL 152 AIRPLANE SYSTEMS DESCRIPTIONS 1 July 1978 7 23 ...

Page 124: ...e rate ALTERNATOR CONTROL UNIT AND LOW VOLTAGE WARNING LIGHT The airplane is equipped with a combination alternator regulator high low voltage control unit mounted on the engine side of the firewall and a red warning light labeled LOW VOLTAGE under the ammeter on the instrument panel In the event an over voltage condition occurs the alternator control unit automatically removes alternator field cu...

Page 125: ...its are protected by fuses mounted adjacent to the battery GROUND SERVICE PLUG RECEPTACLE A ground service plug receptacle may be installed to permit the use of an external power source for cold weather starting and during lengthy maintenance work on the electrical and electronic equipment LIGHTING SYSTEMS EXTERIOR LIGHTING Conventional navigation lights are located on the wing tips and top of the...

Page 126: ...olled by the RADIO LT rheostat control knob The integral compass and engine instrument cluster light intensity is controlled by the PANEL LT rheostat control knob A cabin dome light in the overhead console is operated by a switch on the left switch and control panel To turn the light on move the switch to the ON position A control wheel map light is available and is mounted on the bottom of the pi...

Page 127: ...nob out approximately 1 4 to 1 2 inch for a small amount of cabin heat Additional heat is available by pulling the knob out farther maximum heat is available with the CABIN HT knob pulled out and the CABIN AIR knob pushed full in When no heat is desired in the cabin the CABIN HT knob is pushed full in Additional ventilation air may be obtained by opening the adjustable ventilators near the upper l...

Page 128: ...CESSNA SECTION 7 MODEL 152 AIRPLANE SYSTEMS DESCRIPTIONS 1 July 1978 7 28 ...

Page 129: ...hrenheit Pressure altitude 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 barometric scale to the original barometric setting after pressure altitude has been obtained Having set the ring to correct for altitude and temperature read ...

Page 130: ...IPTIONS 1 July 1978 7 30 vacuum pump mounted on the engine a vacuum relief valve and vacuum system air filter on the aft side of the firewall below the instrument panel and instruments including a suction gage on the left side of the instrument panel ...

Page 131: ...ecession SUCTION GAGE A suction gage is located on the left side of the instrument panel when the airplane is equipped with a vacuum system Suction available for operation of the attitude indicator and directional indicator is shown by this gage which is calibrated in inches of mercury The desired suction range is 4 5 to 5 4 inches of mercury A suction reading below this range may indicate a syste...

Page 132: ...udio control panel The switch is either a two position toggle type or a three position rotary type depending on which audio control panel is installed Both switches are labeled with numbers which correspond to the top number 1 or the bottom number 2 NAV COM radio Position 3 is not used in this airplane The audio amplifier in the NAV COM radio is required for speaker and transmitter operation The a...

Page 133: ...CESSNA SECTION 7 MODEL 152 AIRPLANE SYSTEMS DESCRIPTIONS 1 July 1978 7 33 ...

Page 134: ...h the appropriate NAV COM receiver audio to the transmitter being selected To utilize this automatic feature leave all NAV COM receiver switches in the OFF center position and place the AUTO selector switch in either the SPEAKER or PHONE position as desired Once the AUTO selector switch is positioned the pilot may then select any transmitter and its associated NAV COM receiver audio simultaneously...

Page 135: ... a remote keying switch located on the left grip of the pilot s control wheel The microphone and headset jacks are located on the pedestal below the instrument panel Audio to all three headsets is controlled by the individual audio selector switches and adjusted for volume level by using the selected receiver volume controls NOTE When transmitting the pilot should key the microphone place the micr...

Page 136: ...pection Periods 8 5 FAA Required Inspections 8 5 Cessna Progressive Care 8 6 Cessna Customer Care Program 8 6 Pilot Conducted Preventive Maintenance 8 7 Alterations or Repairs 8 7 Ground Handling 8 7 Towing 8 7 Parking 8 8 Tie Down 8 8 Jacking 8 8 Leveling 8 9 Flyable Storage 8 9 Servicing 8 10 Engine Oil 8 10 Fuel 8 12 Landing Gear 8 12 Cleaning and Care 8 12 Windshield Windows 8 12 Painted Surfa...

Page 137: ...CESSNA SECTION 8 MODEL 152 HANDLING SERVICE MAINTENANCE 1 July 1978 8 2 ...

Page 138: ...ocated on the upper part of the left forward doorpost Located on the lower forward edge of the left cabin door is a Finish and Trim Plate which contains a code describing the interior color scheme and exterior paint combination of the airplane The code may be used in conjunction with an applicable Parts Catalog if finish and trim information is needed OWNER FOLLOW UP SYSTEM Your Cessna Dealer has ...

Page 139: ...ost 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 containing the owner s name airplane serial number and registration number must be included in replacement requests since the Pilot s Operation Handbook and FAA Approved Airplane Flight Manual is identified for specific airpla...

Page 140: ...Registry must undergo a complete inspection annual each twelve calendar months In addition to the required ANNUAL inspection aircraft operated commercially for hire must have a complete inspection every 100 hours of operation The FAA may require other inspections by the issuance of airworthiness directives applicable to the airplane engine propeller and components It is the responsibility of the o...

Page 141: ...ers Regardless of the inspection method selected by the owner he should keep in mind that FAR Part 43 and FAR Part 91 establishes the requirement hat properly certified agencies or personnel accomplish all required FAA inspections and most of the manufacturer recommended inspections CESSNA CUSTOMER CARE PROGRAM Specific benefits and provisions of the CESSNA WARRANTY plus other important benefits f...

Page 142: ...rocedures are followed Your Cessna Dealer should be contacted for further information or for required maintenance which must be accomplished by appropriately licensed personnel ALTERATIONS OR REPAIRS It is essential that the FAA be contacted prior to any alteration on the airplane to ensure that airworthiness of the airplane is not violated Alterations or repairs to the airplane must be accomplish...

Page 143: ...o the wings and tail tie down fittings and secure each rope to a ramp tie down 4 Tie a rope no chains or cables to the nose gear strut and secure to a ramp tie down 5 Install a pitot tube cover JACKING When a requirement exists to jack the 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 need...

Page 144: ...ly center the bubble in the level A level placed across the front seat rails at corresponding points is used to level the airplane laterally FLYABLE STORAGE Airplanes placed in non operational storage for a maximum of 30 days or those which receive only intermittent operations use for the first 25 hours are considered in flyable storage status Every seventh day during these periods the propeller s...

Page 145: ... scheduling your airplane for service at the recommended intervals Cessna Progressive Care ensures that these requirements are accomplished at the required intervals to comply with the 100 hour or ANNUAL inspection as previously covered Depending on various flight operations your local Government Aviation Agency may require additional service inspections or tests For these regulatory requirements ...

Page 146: ...d with an oil filter drain the engine oil sump and clean the oil pressure screen each 50 hours thereafter On airplanes which have an oil filter drain the engine oil sump and clean the oil pressure screen each 50 hours thereafter Change engine oil at least every 6 months even though less than the recommended hours have accumulated Reduce the intervals for prolonged operation in dusty areas cold cli...

Page 147: ... WHEEL TIRE PRESSURE 21 psi on 6 00 6 6 Ply Rated Tire NOSE GEAR SHOCK STRUT Keep filled with MIL H 5506 hydraulic fluid and inflated with air to 20 psi Do not over inflate CLEANING AND CARE WINDSHIELD WINDOWS The plastic windshield and windows should by cleaned with an aircraft windshield cleaner Apply the cleaner sparingly with soft cloths and rub with moderate pressure until all dirt oil scum a...

Page 148: ...ois Harsh or abrasive soaps or detergents which cause corrosion or scratches should never be used Remove stubborn oil grease with a cloth moistened with Stoddard solvent Waxing is unnecessary to keep the painted surfaces bright However if desired the airplane may be waxed with a good automotive wax A heavier coating on the leading edges of the wings and tail and on the engine nose cap and propelle...

Page 149: ...a dull knife then spot clean the area Oily spots may be cleaned with household spot removers used sparingly Before using any solvent read the instruction on the container and test it on an obscure place on the fabric to be cleaned Never saturate the fabric with a volatile solvent it may damage the padding and backing materials Soiled upholstery and carpet may be cleaned with foam type detergent us...

Page 150: ...erization Kit 2 pages Avionics Emergency Locater Transmitter ELT 4 pages 300 ADF Type R 546E 6 pages 300 Nav Com Type RT 385A 8 pages 300 Transponder Type RT 359A and optional Altitude Encoder Blind 6 pages 300 Transponder Type RT 359A and optional Altitude Encoder type EA 401A 6 pages 400 Glide Slope Type R 443B 4 pages 400 Marker Beacon Type R 402A 4 pages 400 Transponder Type RT 459A and option...

Page 151: ...nce As listed in the Table Contents the supplements are classified under the headings of Major Configuration Variations General and Avionics and are arranged alphabetically and numerically to make it easer to located a particular supplement Other routinely installed items of optional equipment whose function and operational procedures do not require detailed instructions are discussed in Section 7...

Page 152: ... circuits have been designed to completely eliminate the need to jumper across the battery contactor to close it for charging a completely dead battery A special fused circuit in the external power system supplies the needed jumper across the contacts so that with a dead battery and an external power source applied turning the master switch ON will close the battery contactor SECTION 2 LIMITATIONS...

Page 153: ...ng on the master switch using an external power source or pulling the propeller through by hand treat the propeller as if the ignition switch were ON Do not stand nor allow anyone else to stand within the arc of the propeller since a loose or broken wire or a component malfunction could cause the propeller to rotate Turning on the master switch is especially important since it will enable the batt...

Page 154: ...ed strobe lights with integral power supplies a two position rocker switch labeled STROBE LTS on the left switch and control panel and a 5 ampere push to reset circuit breaker located on the right switch and control panel SECTION 2 LIMITATIONS Strobe lights must be turned off when taxiing in the vicinity of other airplanes or during night flight through clouds fog or haze SECTION 3 EMERGENCY PROCE...

Page 155: ...y 1978 2 of 2 Revision 1 31 March 1983 SECTION 4 NORMAL PROCEDURES To operate the strobe light system proceed as follows 1 Master Switch ON 2 Strobe Light Switch ON SECTION 5 PERFORMANCE The installation of strobe lights will result in a minor reduction in cruise performance ...

Page 156: ...card to be installed on the map compartment door This equipment should be installed for operations in temperatures consistently below 20 F 7 C Once installed the crankcase breather insulation is approved for permanent use regardless of temperature SECTION 2 LIMITATIONS The following information must be presented in the form of placards when the airplane is equipped with a winterization kit 1 On ea...

Page 157: ...PROCEDURES There is no change to the airplane emergency procedures when winterization kit is installed SECTION 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 ...

Page 158: ...cordance with STC SA2613CE and SE2606CE The information contained herein supplements or supersedes the basic manual only in those areas listed herein For limitations procedures and performance information not contained in this supplement consult the basic Airplane Flight Manual LIMITATIONS Fuel The use of unleaded and leaded automotive gasoline 91 minimum antiknock index RON MON 2 per ASTM Specifi...

Page 159: ...dels that incorporate any other previously approved modification unless it is determined that the interrelationship between this change and any other previously approved modifications will introduce no adverse effect upon the airworthiness of the engines Specific approval must be obtained for each model aircraft t insure compatibility with its fuel system This certificate and the supporting data w...

Page 160: ... 6 Conformity Statement A Agency s Name and Address B Kind of Agency C Certificate No X U S Certificated Mechanic Foreign Certificated Mechanic Certificate Repair Station JON R McNAY 11409 BRISTOL TERR KANSAS CITY MO 64134 Manufacturer 1823528 A P D I certify that the repair and or alteration made to the unit s identified in item 4 above and described on the reverse or attachments hereto have been...

Page 161: ...ality and registration mark and date work completed 28 MAY 96 CESSNA 152 S N 15283496 N49696 AIRFRAME ALTERATION Operation of airplane on unleaded and leaded automotive Gasoline 91 minimum antiknock index RON MON 2 per ASTM Specification D 439 I A W STC SA2613CE ENGINE ALTERATION Add the following approved fuel unleaded and leaded automotive Gasoline 91 minimum antiknock index RON MON 2 per ASTM S...

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