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Cessna 152 1978, Pilot Operating Handbook

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Cessna 152 1978 Pilot Operating Handbook Download Page 113

CESSNA AIRCRAFT COMPANY 

 

FOR TRAINING USE ONLY 

MODEL 152 

 

7-17 

 

COOLING SYSTEM 

 

Ram air for engine cooling enters through two intake openings in the front of the engine cowling.  The 

cooling air is directed around the cylinders and other areas of the engine by baffling, and is then 

exhausted through an opening at the bottom aft edge of the cowling.  No manual cooling system control 

is provided. 

 

A winterization kit is available for the airplane.  The kit consists of two cover plates to partially cover the 

cowl nose cap opening, two placards to be installed on the cover plates, insulation for the engine 

crankcase breather line, and a placard to be installed on the map compartment door.  This equipment 

should be installed for operations in temperatures consistently below -7°C (20°F).  Once installed, the 

crankcase breather insulation is approved for permanent use regardless of temperature. 

 

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 vented fuel tanks (one in each wing), a fuel shutoff valve, fuel strainer, 

manual primer, and carburetor.  Refer to figure 7-5 for fuel quantity data for both systems. 

 

FUEL QUANTITY DATA (U.S. GALLONS) 

TANKS 

TOTAL USABLE FUEL 

ALL FLIGHT 

CONDITIONS 

TOTAL 

UNUSABLE FUEL 

TOTAL 

FUEL VOLUME 

STANDARD 

(13 Gal. Each) 

24.5 

1.5 

26.0 

LONG RANGE 

(19.5 Gal. Each) 

37.5 

1.5 

39.0 

 

Figure 7-5. Fuel Quantity Data 

 

Fuel flows by gravity from the two wing tanks to a fuel shutoff valve.  With the valve in the ON position, 

fuel flows through a strainer to the carburetor.  From the carburetor, mixed fuel and air flows to the 

cylinders through intake manifold tubes.  The manual primer draws its fuel from the fuel strainer and 

injects in into the cylinder intake ports. 

 

Fuel system venting is essential to system operation.  Blockage of the venting system will result in a 

decreased fuel flow and eventual engine stoppage.  Venting is accomplished by an interconnecting line 

from the right fuel tank to the left tank.  The left tank is vented overboard through a vent line which is 

Summary of Contents for 152 1978

Page 1: ...DEL 152 SERIAL NO ________________________________________ REGISTRATION NO __________________________________ THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY CAR PART 3 COPYRIGHT 1977 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA ...

Page 2: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 PAGE INTENTIONALLY BLANK ...

Page 3: ...vailable 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 P...

Page 4: ...ice Letters published by Cessna Aircraft Company These are distributed to Cessna Dealers and to those who subscribe through the Owner Follow Up System If you are not receiving subscription service you will want to keep in touch with your Cessna Dealer for information concerning the change status of the handbook Subsequent changes will be made in the form of stickers These should be examined and at...

Page 5: ... 5 OIL 6 MAXIMUM CERTIFICATED WEIGHTS 7 STANDARD AIRPLANE WEIGHTS 7 CABIN AND ENTRY DIMENSIONS 7 BAGGAGE SPACE DIMENSIONS 7 SPECIFIC LOADINGS 7 SYMBOLS ABBREVIATIONS AND TERMINOLOGY 8 GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS 8 METEOROLOGICAL TERMINOLOGY 9 ENGINE POWER TERMINOLOGY 9 AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY 9 WEIGHT AND BALANCE TERMINOLOGY 10 ...

Page 6: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 1 2 PAGE INTENTIONALLY BLANK ...

Page 7: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 1 3 THREE VIEWS Figure 1 1 Three View ...

Page 8: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 1 4 PAGE INTENTIONALLY BLANK ...

Page 9: ...ype Normally aspirated direct drive air cooled horizontally opposed carburetor equipped four cylinder engine with 233 3 cu in displacement Horsepower Rating and Engine Speed 110 rated BHP at 2550 RPM PROPELLER Propeller Manufacturer McCauley Accessory Division Propeller Model Number 1A103 TCM6958 Number of Blades 2 Propeller Diameter Maximum 69 inches Minimum 67 5 inches Propeller Type Fixed Pitch...

Page 10: ... 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 6082 Aviation Grade Straight Mineral Oil SAE 50 above 16 C 60 F SAE 40 between 1 C 30 F and 32 C 90 F SAE 30 between 18 C 0 ...

Page 11: ...low NOTE The maximum combined weight capacity for baggage areas 1 and 2 is 120 lbs STANDARD AIRPLANE WEIGHTS Standard Empty Weight 152 1081 lbs 152 II 1118 lbs Maximum Useful Load 152 589 lbs 152 II 552 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 det...

Page 12: ...ich you may use abrupt control travel VFE Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position VNO Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air then only with caution VNE Never Exceed Speed is the speed limit that may not be exceeded at any time VS Stalling Speed or the minimum steady fligh...

Page 13: ...RPM Static RPM is engine speed attained during a full throttle engine runup when the airplane is on the ground and stationary AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Demonstrated Crosswind Velocity Demonstrated Crosswind Velocity is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing was actually demonstrated during certificati...

Page 14: ...vity Arm is the arm obtained by adding the airplane s individual moments and dividing the sum by the total weight C G Limits Center of Gravity Limits are the extreme center of gravity locations within which the airplane must be operated at a given weight Standard Empty Weight Standard Empty Weight is the weight of a standard airplane including unusable fuel full operating fluids and full engine oi...

Page 15: ...ble of Contents INTRODUCTION 3 AIRSPEED LIMITATIONS 3 AIRSPEED INDICATOR MARKINGS 4 POWER PLANT LIMITATIONS 5 POWER PLANT LIMITATIONS 5 WEIGHT LIMITS 6 CENTER OF GRAVITY LIMITS 6 MANEUVERING LIMITS 6 FLIGHT LOAD FACTOR LIMITS 7 KINDS OF OPERATION LIMITS 7 FUEL LIMITATIONS 7 PLACARDS 8 ...

Page 16: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 2 2 PAGE INTENTIONALLY BLANK ...

Page 17: ...Type Certificate No 3A19 as Cessna Model No 152 AIRSPEED LIMITATIONS Airspeed limitations and their 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 Speed 108 111 Do not exceed this speed except in smooth air and then only with caution VA Maneuvering Speed 1670 Pounds 15...

Page 18: ...nge Lower limit is maximum weight VS0 in landing configuration Upper limit is maximum speed permissible with flaps extended Green Arc 40 111 Normal Operating Range Lower limit is maximum weight VS at most forward C G with flaps retracted Upper limit is maximum structural cruising speed Yellow Arc 111 149 Operations must be conducted with caution and only in smooth air Red Line 149 Maximum speed fo...

Page 19: ...0 RPM Maximum Oil Temperature 118 C 245 F Oil Pressure Minimum 25 psi Maximum 100 psi Propeller Manufacturer McCauley Accessory Division Propeller Model Number 1A103 TCM6958 Propeller Diameter Maximum 69 inches Minimum 67 5 inches POWER PLANT LIMITATIONS Power plant instrument markings and their color code significance are show in figure 2 3 INSTRUMENT RED LINE GREEN ARC RED LINE MINIMUM LIMIT NOR...

Page 20: ... flight In the acquisition of various certificates such as commercial pilot instrument pilot and flight instructor certain maneuvers are required All of these maneuvers are permitted in this airplane No aerobatic maneuvers are approved except those listed below MANEUVER MAXIMUM ENTRY SPEED Chandelles 95 knots Lazy Eights 95 knots Steep Turns 95 knots Spins Use Slow Deceleration Stalls Except Whip ...

Page 21: ...s equipment installed at the time of Airworthiness Certificate issuance Flight into known icing conditions is prohibited FUEL LIMITATIONS 2 Standard Tanks 13 U S gallons each Total Fuel 26 U S gallons Usable Fuel all flight conditions 24 5 U S gallons Unusable Fuel 1 5 U S gallons 2 Long Range Tanks 19 5 U S gallons each Total Fuel 39 U S gallons Usable Fuel all flight conditions 37 5 gallons Unus...

Page 22: ...152 2 8 PLACARDS The following information is displayed in the form of composite or individual placards 1 In full view of the pilot The DAY NIGHT VFR IFR entry shown on the example below will vary as the airplane is equipped 2 In the baggage compartment ...

Page 23: ...USE ONLY MODEL 152 2 9 3 Near fuel shutoff valve standard tanks 4 Near fuel shutoff valve long range tanks 5 Near fuel tank filler cap standard tanks 6 Near fuel tank filler cap long range tanks 7 On the instrument panel near the altimeter ...

Page 24: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 2 10 PAGE INTENTIONALLY BLANK ...

Page 25: ...KEOFF 4 ENGINE FAILURE DURING FLIGHT 4 FORCED LANDINGS 4 EMERGENCY LANDING WITHOUT ENGINE POWER 4 PRECAUTIONARY LANDING WITH ENGINE POWER 4 DITCHING 5 FIRES 5 DURING START ON GROUND 5 ENGINE FIRE IN FLIGHT 6 ELECTRICAL FIRE IN FLIGHT 6 CABIN FIRE 6 WING FIRE 7 ICING 7 INADVERTENT ICING ENCOUNTER 7 LANDING WITH A FLAT MAIN TIRE 7 ELECTRICAL POWER SUPPLY SYSTEM MALFUNCTIONS 8 OVER VOLTAGE LIGHT ILLU...

Page 26: ...e 10 EXECUTING A 180 TURN IN CLOUDS 11 EMERGENCY DESCENT THROUGH CLOUDS 11 RECOVERY FROM A SPIRAL DIVE 11 FLIGHT IN ICING CONDITIONS 12 SPINS 12 ROUGH ENGINE OPERATION OR LOSS OF POWER 12 CARBURETOR ICING 12 SPARK PLUG FOULING 13 MAGNETO MALFUNCTION 13 LOW OIL PRESSURE 13 ELECTRICAL POWER SUPPLY SYSTEM MALFUNCTIONS 13 EXCESSIVE RATE OF CHARGE 13 INSUFFICIENT RATE OF CHARGE 14 ...

Page 27: ... the basic guidelines described in this section should be considered and applied 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 Maneuver Speed 1670 Lbs 104 KIAS 1500 Lbs 98 KIAS 1350 Lbs 93 KIAS Maximum Glide 60 KIAS Precautionary Landing With En...

Page 28: ...T ENGINE POWER 1 Airspeed 65 KIAS flaps UP 60 KIAS flaps DOWN 2 Mixture IDLE CUT OFF 3 Fuel 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 ...

Page 29: ... cabin to equalize 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 1 Cranking CONTINUE in an effort to obtain a...

Page 30: ... 4 Fire Extinguisher ACTIVATE if available WARNING After discharging an extinguisher within a closed cabin ventilate the cabin If fire appears out and electrical power is necessary for continuance of flight 5 Master Switch 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...

Page 31: ...ld 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 edges be prepared for significantly higher stall speed 8 Leave wing flaps retracted ...

Page 32: ...OVER VOLTAGE LIGHT ILLUMINATES 1 Master Switch OFF both sides 2 Master Switch ON 3 Over Voltage Light OFF If over voltage light illuminates again 4 Flight TERMINATE as soon as practical AMMETER SHOWS DISCHARGE 1 Alternator OFF 2 Nonessential Electrical Equipment OFF 3 Flight TERMINATE as soon as practical ...

Page 33: ...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 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 fai...

Page 34: ...e angle by adjusting power exclusively At flareout the nose down moment resulting from power reduction is an adverse factor and the airplane may hit on the nose wheel Consequently at flareout the trim control should be set at the full nose up position and the power adjusted so that the airplane will rotate to the horizontal attitude for touchdown Close the throttle at touchdown FIRES Although engi...

Page 35: ...o clearance for an emergency descent through clouds To guard against a spiral dive choose an easterly or westerly heading to minimize compass card swings due to changing bank angles In addition keep hands off the control wheel and steer a straight course with rudder control by monitoring the turn coordinator Occasionally check the compass heading and make minor corrections to hold an approximate c...

Page 36: ...ter of gravity loadings to assure optimum recoveries 5 HOLD THESE CONTROL INPUTS UNTIL ROTATION STOPS Premature relaxation of the control inputs may extend the recovery 6 AS ROTATION STOPS NEUTRALIZE RUDDER AND MAKE A SMOOTH RECOVERY FROM THE RESULTING DIVE NOTE If disorientation precludes a visual determination of the direction of rotation the symbolic airplane in the turn coordinator may be refe...

Page 37: ...y landing because an orifice in this line will prevent a sudden loss of oil from the engine sump However a landing at the nearest airport would be advisable to inspect the source of trouble If 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 fie...

Page 38: ...of the master switch off and then on again If the problem no longer exists normal alternator charging will resume and the warning light will go off If the light illuminates again a malfunction is confirmed In this event the flight should be terminated and or the current drain on the battery minimized because the battery can supply the electrical system for only a limited period of time If the emer...

Page 39: ...NSPECTION 5 CABIN 5 EMPENNAGE 5 RIGHT WING Trailing Edge 5 RIGHT WING 5 NOSE 5 LEFT WING 6 LEFT WING Leading Edge 6 LEFT WING Trailing Edge 6 BEFORE STARTING ENGINE 6 STARTING ENGINE Temperatures Above Freezing 6 BEFORE TAKEOFF 7 TAKEOFF 7 NORMAL TAKEOFF 7 SHORT FIELD TAKEOFF 7 ENROUTE CLIMB 8 CRUISE 8 BEFORE LANDING 8 LANDING 8 NORMAL LANDING 8 SHORT FIELD LANDING 8 BALKED LANDING 9 ...

Page 40: ...Freezing 11 TAXIING 12 BEFORE TAKEOFF 13 WARM UP 13 MAGNETO CHECK 13 ALTERNATOR CHECK 13 TAKEOFF 14 POWER CHECK 14 WING FLAP SETTING 14 ENROUTE CLIMB 15 CRUISE 15 FUEL SAVINGS PROCEDURES FOR FLIGHT TRAINING OPERATIONS 16 STALLS 16 SPINS 16 LANDING 18 SHORT FIELD LANDING 18 CROSSWIND LANDING 18 BALKED LANDING 18 COLD WEATHER OPERATION 19 NOISE ABATEMENT 20 ...

Page 41: ...r weight 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 Balked Lan...

Page 42: ...e even small accumulation of frost ice or snow from wing tail and control surfaces Also make sure that control surfaces contain no internal accumulation 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 ...

Page 43: ...ump quick drain valve to check for water sediment and proper fuel grade 4 Fuel Quantity CHECK VISUALLY for desired level 5 Fuel Filler Cap SECURE NOSE 1 Engine Oil Level CHECK do not operate with less than four quarts Fill to six quarts for extended flight 2 Before first flight of the day and after each refueling pull out strainer drain knob for about four seconds to clear fuel strainer of possibl...

Page 44: ...o check the system place a clean handkerchief over the vent opening and apply suction a sound from the warning horn will confirm system operation 3 Fuel Tank Vent Opening CHECK for stoppage 4 Wing Tie Down DISCONNECT LEFT WING Trailing Edge 1 Aileron CHECK freedom of movement and security BEFORE STARTING ENGINE 1 Preflight Inspection COMPLETE 2 Seats Belts Shoulder Harnesses ADJUST and LOCK 3 Fuel...

Page 45: ...uments and Ammeter CHECK d Suction Gage CHECK 9 Radios SET 10 Flashing Beacon Navigation Lights and or Strobe Lights ON as required 11 Throttle Friction Lock ADJUST 12 Brakes RELEASE TAKEOFF NORMAL TAKEOFF 1 Wing Flaps 0 10 2 Carburetor Heat COLD 3 Throttle FULL OPEN 4 Elevator Control LIFT NOSE WHEEL at 50 KIAS 5 Climb Speed 65 75 KIAS SHORT FIELD TAKEOFF 1 Wing Flaps 10 2 Carburetor Heat COLD 3 ...

Page 46: ...FORE LANDING 1 Seats Belts Harnesses ADJUST and LOCK 2 Mixture RICH 3 Carburetor Heat ON apply full heat before closing throttle LANDING NORMAL LANDING 1 Airspeed 60 70 KIAS flaps UP 2 Wing Flaps 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...

Page 47: ...Heat COLD 3 Wing Flaps RETRACT to 20 4 Airspeed 55 KIAS 5 Wing Flaps RETRACT slowly AFTER LANDING 1 Wing 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 ...

Page 48: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 4 10 PAGE INTENTIONALLY BLANK ...

Page 49: ...r flooding Excess fuel can be cleared from the combustion chambers by the following procedure set 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 under primed most likely in cold weather with a cold engine it will not fire at all an...

Page 50: ...balance Figure 4 2 Taxiing Diagram 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 The carburetor heat control knob should be pushed full in during all ground operations unless heat is absolutely necessary When the knob is pulled out to the hea...

Page 51: ...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 RPM differential between magnetos If there is a doubt concerning operation of the ignition system RP...

Page 52: ... 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 SETTING Normal takeoffs are accomplished with wing flaps 0 10 Using 10 wing flaps reduces the total distance over an obstacle by approximately 10 Flap deflections greater than 10 are not approved for takeoff If 10 wi...

Page 53: ...sure proper seating of the rings and is applicable to new engines and engines in service following cylinder replacement or top overhaul of one or more cylinders The data in Section 5 shows the increased range and improved fuel economy that is obtainable when operating at lower power settings The use of lower power settings and the selection of cruise altitude on the basis of the most favorable win...

Page 54: ...g at 75 or less power the mixture may be further leaned until the RPM peaks and drops 25 50 RPM This is especially applicable to cross country training flights but may also be practiced during transition flights to and from the practice area Using the above recommended procedures can provide fuel savings of up to 13 when compared to typical training operations at a full rich mixture STALLS The sta...

Page 55: ...tial 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 spiral NOTE Careful attention should be taken to assure that the aileron control is neutral during all phases...

Page 56: ...ng 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 FIELD LANDING For a short field landing in smooth air conditions make an approach at 54 KIAS with 30 flaps using enough power to control the glide path After all approach obstacles are cleared progre...

Page 57: ... below 7 20 F Cold weather starting procedures are as follows With Preheat 1 Ignition Switch OFF 2 Throttle CLOSED 3 Mixtures IDLE CUT OFF 4 Parking Brake SET 5 Propeller PULL through by hand several revolutions NOTE Caution should be used to ensure the brakes are set or a qualified person is at the controls 6 Mixture RICH 7 Throttle OPEN 1 2 to 3 4 INCH 8 Prime 2 to 4 STROKES depending on tempera...

Page 58: ...T Increased emphasis on improving the quality of our environment requires renewed effort on the part of all pilots to minimize the effect of airplane noise on the public We as pilots can demonstrate our concern for environmental improvement by application of the following suggested procedures and thereby tend to build public support for aviation 1 Pilots operating aircraft under VFR over outdoor a...

Page 59: ...CALIBRATION 7 TEMPERATURE CONVERSION CHART 8 STALL SPEEDS 9 MOST REARWARD CENTER OF GRAVITY 9 MOST FORWARD CENTER OF GRAVITY 9 TAKEOFF DISTANCE 10 SHORT FIELD 10 RATE OF CLIMB 11 TIME FUEL AND DISTANCE TO CLIMB 12 MAXIMUM RATE OF CLIMB 12 CRUISE PERFORMANCE 13 RANGE PROFILE 14 45 MINUTES RESERVE 14 24 5 GALLONS USABLE FUEL 14 RANGE PROFILE 15 45 MINUTES RESERVE 15 37 5 GALLONS USABLE FUEL 15 ENDUR...

Page 60: ...AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 5 2 45 MINUTES RESERVE 16 24 5 GALLONS USABLE FUEL 16 ENDURANCE PROFILE 17 45 MINUTES RESERVE 17 37 5 GALLONS USABLE FUEL 17 LANDING DISTANCE 18 SHORT FIELD 18 ...

Page 61: ... 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 provided in the tables so that conservative values can be selected and used to determine the particular performance figure ...

Page 62: ... 980 Decrease in ground roll 980 feet 13 127 Corrected ground roll 853 Feet Total distance to clear a 50 foot obstacle zero wind 1820 Decrease in total distance 1820 feet 13 237 Corrected total distance to clear 50 foot obstacle 1583 Feet CRUISE The cruising altitude should be selected based on a consideration of trip length winds aloft and the airplane s performance A typical cruising altitude an...

Page 63: ...tion in figures 5 6 and 5 7 For this sample problem figure 5 6 shows that a climb from 2000 feet to 6000 feet requires 1 gallon of fuel The corresponding distance during the climb is 9 nautical miles These values are for a standard temperature as shown on the climb chart and are sufficiently accurate for most flight planning purposes However a further correction for the effect of temperature may b...

Page 64: ... 5 20 2 4 3 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 LANDING A procedure similar to takeoff should be used for estimating the landing distance at the destination airport Figure 5 10 presents landing distances for various airport altitude and ...

Page 65: ...Power 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 66: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 5 8 TEMPERATURE CONVERSION CHART Figure 5 2 Temperature Conversion Chart ...

Page 67: ...ITY WEIGHT LBS FLAP DEFLECTION ANGLE OF BANK 0 30 45 60 KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS 1670 UP 36 46 39 49 43 55 51 65 10 36 43 39 46 43 51 51 61 30 31 41 33 44 37 49 44 58 MOST FORWARD CENTER OF GRAVITY WEIGHT LBS FLAP DEFLECTION ANGLE OF BANK 0 30 45 60 KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS 1670 UP 40 48 43 52 48 57 57 68 10 40 46 43 49 48 55 57 65 30 35 43 38 46 42 51 49 61 Figure 5 ...

Page 68: ...figure WEIGHT LBS TAKEOFF SPEED KIAS PRESS ALT FT 0 C 10 C 20 C 30 C 40 C LIFT OFF AT 50 FT GROUND ROLL TOTAL TO CLEAR 50 FT OBS GROUND ROLL TOTAL TO CLEAR 50 FT OBS GROUND ROLL TOTAL TO CLEAR 50 FT OBS GROUND ROLL TOTAL TO CLEAR 50 FT OBS GROUND ROLL TOTAL TO CLEAR 50 FT OBS 1670 50 54 S L 640 1190 695 1290 755 1390 810 1495 875 1605 1000 705 1310 765 1420 825 1530 890 1645 960 1770 2000 775 1445...

Page 69: ...leaned above 3000 feet for maximum RPM WEIGHT LBS PRESSURE ALTITUDE FT CLIMB SPEED KIAS RATE OF CLIMB FPM 20 C 0 C 20 C 40 C 1670 S L 67 835 765 700 630 2000 66 735 670 600 535 4000 65 635 570 505 445 6000 63 535 475 415 355 8000 62 440 380 320 265 10 000 61 340 285 230 175 12 000 60 245 190 135 85 Figure 5 5 Rate of Climb ...

Page 70: ...C above standard temperature 4 Distances shown are based on zero wind WEIGHT LBS PRESSURE ALTITUDE FT TEMP C CLIMB SPEED KIAS RATE OF CLIMB FPM FROM SEA LEVEL TIME MIN FUEL USED GALLONS DISTANCE NM 1670 S L 15 67 715 0 0 0 0 1000 13 66 675 1 0 2 2 2000 11 66 630 3 0 4 3 3000 9 65 590 5 0 7 5 4000 7 65 550 6 0 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 1...

Page 71: ...0 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 78 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 61 98 4 9...

Page 72: ...emperature Zero Wind NOTES 1 This chart allows for the fuel used for engine start taxi takeoff and climb and the 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 3 Performance is shown for an airplane equipped with speed fairings which increase the cruise speeds by approximately two knots Figure 5 8 Range Profile Sheet 1 of 2 ...

Page 73: ...emperature Zero Wind NOTES 1 This chart allows for the fuel used for engine start taxi takeoff and climb and the 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 3 Performance is shown for an airplane equipped with speed fairings which increase the cruise speeds by approximately two knots Figure 5 8 Range Profile Sheet 2 of 2 ...

Page 74: ...CONDITIONS 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 the 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 of 2 ...

Page 75: ...CONDITIONS 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 the 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 2 of 2 ...

Page 76: ... 0 C 10 C 20 C 30 C 40 C GROUND ROLL TOTAL TO CLEAR 50 FT OBS GROUND ROLL TOTAL TO CLEAR 50 FT OBS GROUND ROLL TOTAL TO CLEAR 50 FT OBS GROUND ROLL TOTAL TO CLEAR 50 FT OBS GROUND ROLL TOTAL TO CLEAR 50 FT OBS 1670 54 S L 450 1160 465 1185 485 1215 500 1240 515 1265 1000 465 1185 485 1215 500 1240 520 1270 535 1295 2000 485 1215 500 1240 520 1270 535 1300 555 1330 3000 500 1240 520 1275 540 1305 5...

Page 77: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 6 1 SECTION 6 WEIGHT BALANCE EQUIPMENT LIST Table of Contents INTRODUCTION 3 AIRPLANE WEIGHING PROCEDURES 3 WEIGHT AND BALANCE 6 EQUIPMENT LIST 13 ...

Page 78: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 6 2 PAGE INTENTIONALLY BLANK ...

Page 79: ... 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 record the weight sh...

Page 80: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 6 4 Figure 6 1 Sample Airplane Weighing ...

Page 81: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 6 5 Figure 6 2 Sample Weight and Balance Record ...

Page 82: ...000 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 may dif...

Page 83: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 6 7 Figure 6 3 Loading Arrangements Figure 6 4 Baggage Loading and Tie Down ...

Page 84: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 6 8 Figure 6 5 Internal Cabin Dimensions ...

Page 85: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 6 9 Figure 6 6 Sample Loading Problem ...

Page 86: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 6 10 Figure 6 7 Loading Graph ...

Page 87: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 6 11 Figure 6 8 Center of Gravity Moment Envelope ...

Page 88: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 6 12 Figure 6 9 Center of Gravity Limits ...

Page 89: ...ication 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 FAA appr...

Page 90: ...0 3 2 0 VACUUM GAUGE C668509 0101 0 1 18 0 VACUUM RELIEF VALVE C482001 0401 0 5 1 9 A70 S ENGINE PRIMING SYSTEM 0 5 3 1 A73 A VALVE ENGINE OIL QUICK DRAIN NET CHANGE 1701015 1 0 0 B LANDING GEAR ACCESSORIES B01 R 1 WHEEL BRAKE TIRE ASSY 6 00 6 MAIN 2 C163018 0201 40 3 46 8 WHEEL ASSEMBLY MCCAULEY EACH C163005 0101 7 4 47 1 BRAKE ASSEMBLY MCCAULEY LEFT C163032 0111 1 7 43 7 BRAKE ASSEMBLY MCCAULEY ...

Page 91: ... SUPPLIES IN TIPS SET OF 2 C622008 0102 2 3 39 5 C49 A 1 LANDING LIGHT INSTALLATION SINGLE BULB 0401022 1 0 28 3 C49 A 2 LANDING TAXI LIGHT INSTL DUAL BULB 0101022 1 8 28 3 D INSTRUMENTS D01 R INDICATOR AIRSPEED C661064 0107 0 6 17 2 D01 O INDICATOR TRUE AIRSPEED 0513279 1 0 18 0 D07 R ALTIMETER SENSITIVE C661071 0101 1 0 17 6 D07 0 1 ALTIMETER SENSITIVE 20 FT MARKINGS FEET AND MILLIBARS C661025 0...

Page 92: ...T LAP S 2275 104 1 0 39 0 E15 S SHOULDER HARNESS ASSY PILOT S 2275 202 1 0 39 0 E19 O SHOULDER HARNESS INERTIA INSTL PILOT CO PILOT NET CHANGE 0401012 1 1 3 71 1 E23 S BELT SHOULDER HARNESS ASSY CO PILOT S 2275 4 2 0 39 0 E39 A WINDOWS OVERHEAD CABIN TOP NET INCREASE 0413492 0 5 49 0 E53 A MIRROR REAR VIEW 0400338 0 3 17 0 E55 A SUN VISORS SET OF 2 0413473 1 1 0 27 0 E57 A WINDOWS TINTED SET OF 4 ...

Page 93: ...ABLE INSTALLED ARM SHOWN 0701048 2 3 8 0 G88 A WINTERIZATION KIT INSTALLATION ENGINE COVER PLATES FWD COWL SET OF 2 INSTALLED COVER PLATES FORWARD COWL STOWED CRANKCASE BREATHER TUBE INSULATION 1 2 0 3 0 3 0 3 24 2 37 0 84 0 24 0 G92 A WINGS WITH 39 GALLON CAPACITY EXTENDED RANGE FUEL TANKS SET OF 2 NET CHANGE 0401018 5 9 37 3 H AVIONICS AUTOPILOTS H01 A CESSNA 300 ADF RECEIVER WITH BFO R 546E IND...

Page 94: ...LLATION COMPONENTS ARE SIMILAR TO H22 A 1 3910184 43340 1124 45010 2000 15 4 6 9 0 7 7 8 28 6 13 6 17 8 42 9 H22 A 4 CESSNA 300 NAV COM 720 CHANNEL 1ST UNIT WITH VOR ILS RECEIVER TRANSCEIVER RT 385A VOR ILS INDICATOR 1ST UNIT INSTL COMPONENTS ARE SIMILAR TO H22 A 2 3910184 3 46660 000 46660 2000 13 6 5 4 2 3 6 1 32 1 13 6 15 5 53 9 H22 A 5 CESSNA 300 NAV COM 720 CHANNEL 1ST UNIT RECEIVER TRANSCEIV...

Page 95: ...46660 0000 46860 1200 3910186 3970118 3 9 8 5 4 2 2 1 0 0 2 1 9 15 8 13 6 15 5 30 6 17 0 13 3 H25 A 4 CESSNA 300 NAV COM 720 CH COM 2ND UNIT RECEIVER TRANSCEIVER RT 328T VOR LOC INDICATOR IN 514B H37 A ANTENNA COUPLER KIT VOLTAGE REGULATOR 41010 2ND UNIT SWITCHING INSTL MOUNT WIRING MISC HARDWARE 3910182 43340 1124 45010 1000 3910186 3940224 3970118 3 11 4 6 9 0 6 1 0 1 4 0 2 1 3 13 9 13 6 17 8 30...

Page 96: ...IGHT SINGLE BULB D64 A GYRO INSTALLATION D82 A OUTSIDE AIR TEMPERATURE IND D88 A TURN COORDINATOR D91 A RATE OF CLIMB IND E55 A SUN VISORS E85 A DUAL CONTROLS G34 A CIGARETTE LIGHTER H22 A 1 CESSNA 300 NAV COM RT 308C H22 A 2 CESSNA 300 NAV COM RT 385A 0413466 1 0406003 1 0401022 0413466 C668507 0101 C661003 0505 C661080 0101 0413473 1 0460118 2 9910220 1 3900140 36 7 35 6 4 8 1 4 1 0 7 1 0 1 1 3 ...

Page 97: ...AR SYSTEM 10 BAGGAGE COMPARTMENT 10 SEATS 10 SEAT BELT AND SHOULDER HARNESSES 11 SEAT BELTS 11 SHOULDER HARNESSES 11 INTEGRATED SEAT BELT SHOULDER HARNESSES WITH INERTIA REELS 13 ENTRANCE DOORS AND CABIN WINDOWS 13 CONTROL LOCKS 14 ENGINE 14 ENGINE CONTROLS 14 ENGINE INSTRUMENTS 14 NEW ENGINE BREAK IN AND OPERATION 15 ENGINE OIL SYSTEM 15 IGNITION STARTER SYSTEM 16 AIR INDUCTION SYSTEM 16 EXHAUST ...

Page 98: ... GROUND SERVICE PLUG RECEPTACLE 22 LIGHTING SYSTEM 22 EXTERIOR LIGHTING 22 INTERIOR LIGHTING 23 CABIN HEATING VENTILATING AND DEFROSTING SYSTEM 24 PITOT STATIC SYSTEM AND INSTRUMENTS 25 AIRSPEED INDICATOR 25 RATE OF CLIMB INDICATOR 26 ALTIMETER 26 VACUUM SYSTEM AND INSTRUMENTS 26 ATTITUDE INDICATOR 27 DIRECTIONAL INDICATOR 28 SUCTION GAGE 28 STALL WARNING SYSTEM 28 AVIONICS SUPPORT EQUIPMENT 28 AU...

Page 99: ...l 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 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 addi...

Page 100: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 7 4 Figure 7 1 Flight Control and Trim Systems Sheet 1 of 2 ...

Page 101: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 7 5 Figure 7 1 Flight Control and Trim Systems Sheet 2 of 2 ...

Page 102: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 7 6 Figure 7 2 Instrument Panel Sheet 1 of 2 ...

Page 103: ...Instrument and Radio Space 20 Secondary Altimeter 21 Over Voltage Warning Light 22 Ammeter 23 Map Compartment 24 Cabin Heat Control Knob 25 Cabin Air Control Knob 26 Circuit Breakers 27 Wing Flap Switch and Position Indicator 28 Mixture Control Knob 29 Throttle With Friction Lock 30 Microphone 31 Elevator Trim Control Wheel 32 Carburetor Heat Control Knob 33 Electrical Switches 34 Oil Pressure Gag...

Page 104: ...ht 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 the instrument panel The right side of the panel also contains the tachometer ammeter over voltage light and additional instruments such as a flight hour recorder A subpanel under the primary instrument panel contains the fuel quantity i...

Page 105: ...he airplane may be rotated around either main landing gear by pressing down on the tailcone just forward of the vertical stabilizer to raise the nose wheel off the ground WING FLAP SYSTEM The wing flaps are of the single slot type see figure 7 3 and are extended or retracted by positioning the wing flap switch lever on the instrument panel to the desired flap deflection position The switch lever i...

Page 106: ...t lift the lever under the inboard corner of the seat slide the seat into position release the lever and check that the seat is locked in place To adjust the seat back pull forward on the knob under 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 forw...

Page 107: ... seats To release these 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 fastening a...

Page 108: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 7 12 Figure 7 4 Seat Belts and Shoulder Harnesses ...

Page 109: ... door only a door stop mechanism and an openable 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 close or open the doors from inside the airplane use the recessed door handle and arm rest Both cabin doors should be checked for security prior to flight and should not be opened int...

Page 110: ...also made for a vacuum pump and full flow oil filter ENGINE CONTROLS Engine power is controlled by a throttle located on the lower center portion of the instrument panel The throttle operates in a conventional manner in the full forward position the throttle is open and in the full aft position it is closed A friction lock which is a round knurled disk is located at the base of the throttle and is...

Page 111: ...suction strainer screen into the engine driven oil pump From the pump oil is routed to a bypass valve If the oil is cold the bypass valve allows the oil to bypass the oil cooler and go directly from the pump to the oil pressure screen full flow oil filter if installed If the oil is hot the bypass valve routes the oil out of the accessory housing and into a flexible hose leading to the oil cooler o...

Page 112: ...ake manifold tubes In the event carburetor ice is encountered or the intake filter becomes blocked alternate heated air can be obtained from the muffler shroud through a duct to a valve in the airbox operated by the carburetor heat control on the instrument panel Heated air from the muffler shroud is obtained from an unfiltered outside source Use of full carburetor heat at full throttle will resul...

Page 113: ...rosion 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 vented fuel tanks one in each wing a fuel shutoff valve fuel strainer manual primer and carburetor Refer to figure 7 5 for fuel quantity data for both systems FUEL QUANTITY DATA U S GALLONS TANKS TOTAL USABLE FUEL ...

Page 114: ...t wing near the wing strut attach point The right fuel tank filler cap is also vented Fuel quantity is measured by two float type fuel quantity transmitters one in each tank and indicated by two electrically operated fuel quantity indicators on the lower left portion of the instrument panel Figure 7 6 Fuel System Standard and Long Range ...

Page 115: ...duced fuel capacity to permit heavier cabin loadings This is accomplished by filling each tank to the bottom of the indicator on the fuel filler neck When filled to this level the tank contains 12 gallons 12 25 usable in all flight conditions BRAKE SYSTEM The airplane has a single disc hydraulically actuated brake on each main landing gear wheel Each brake is connected by a hydraulic line to a mas...

Page 116: ...or from the electrical system With this switch in the OFF position the entire electrical load is placed on the battery Continued operation with the alternator switch in the OFF position will reduce battery power low enough to open the battery contactor remove power from the alternator field and prevent alternator restart AMMETER The ammeter indicates the flow of current in amperes from the alterna...

Page 117: ...RAFT COMPANY FOR TRAINING USE ONLY MODEL 152 7 21 The warning light may be tested by momentarily turning off the ALT portion of the master switch and leaving the BAT portion turned on Figure 7 7 Electrical System ...

Page 118: ...bsorb transient voltages which otherwise might damage the transistors in the electronic equipment The battery and external power circuits have been designed to completely eliminate the need to jumper across the battery contactor to close it for charging a complete dead battery A special fused circuit in the external power system supplies the needed jumper across the contacts so that with a dead ba...

Page 119: ...operated by a switch on the lower portion of the instrument panel To turn the light on place the switch in the ON position A control wheel map light is available and is mounted on the bottom of the pilot s control wheel The light illuminates the lower portion of the cabin just forward of the pilot and is helpful when checking maps and other flight data during night operations To operate the light ...

Page 120: ...ING VENTILATING AND DEFROSTING SYSTEM The temperature and volume of airflow into the cabin can be regulated to any degree desired by manipulation of the push pull CABIN HT and CABIN AIR control knobs see figure 7 8 Figure 7 8 Cabin Heating Ventilating and Defrosting System ...

Page 121: ...strument panel and associated wiring When the pitot heat switch is turned on the element in the pitot tube is heated electrically to maintain proper operation in possible icing conditions Pitot heat should be used only as required AIRSPEED INDICATOR The airspeed indicator is calibrated in knots and miles per hour Limitation and range markings include the white arc 35 to 85 knots green arc 40 to 11...

Page 122: ...nob near the lower left portion of the indicator provides adjustment of the instrument s barometric scale to the current altimeter setting VACUUM SYSTEM AND INSTRUMENTS An engine driven vacuum system see figure 7 9 is available and provides the suction necessary to operate the attitude indicator and directional indicator The system consists of a vacuum pump mounted on the engine a vacuum relief va...

Page 123: ...visual indication of flight attitude Bank attitude is presented by a pointer at the top of the indicator relative to the bank scale which has index marks at 10 20 30 60 and 90 either side of the center mark Pitch and roll attitudes are presented by a miniature airplane in relation to the horizontal bar A knob at the bottom of the instrument is provided ...

Page 124: ...should not be considered reliable STALL WARNING SYSTEM The airplane is equipped with a pneumatic type stall warning system consisting of an inlet in the leading edge of the left wing an air operated horn near the upper left corner of the windshield and associated plumbing As the airplane approaches a stall the low pressure on the upper surface of the wings moves forward around the leading edge of ...

Page 125: ...nd transmitter operation Since headset audio is not affected by audio amplifier operation the pilot should be aware that while utilizing a headset the only indication of audio amplifier failure is loss of the selected transmitter This can be verified by switching to the speaker function The speaker phone switches determine whether the output of the receiver in use is fed to the headphones or throu...

Page 126: ...nnas can result in loss of usable radio signals on all communications and navigation radio equipment Usually the ADF is first to be affected and VFH communication equipment is the last to be affected Installation of static dischargers reduces interference from precipitation static but it is possible to encounter severe precipitation static conditions which might cause the loss of radio signals eve...

Page 127: ... AIRPLANE FILE 4 AIRPLANE INSPECTION PERIODS 5 FAA REQUIRED INSPECTIONS 5 CESSNA PROGRESSIVE CARE 5 CESSNA CUSTOMER CARE PROGRAM 6 PILOT CONDUCTED PREVENTIVE MAINTENANCE 6 ALTERATIONS OR REPAIRS 6 GROUND HANDLING 7 TOWING 7 PARKING 7 TIE DOWN 7 JACKING 7 LEVELING 8 FLYABLE STORAGE 8 SERVICING 9 ENGINE OIL 9 FUEL 11 LANDING GEAR 11 CLEANING AND CARE 12 WINDSHIELD WINDOWS 12 PAINTED SURFACES 13 ...

Page 128: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 8 2 PROPELLER CARE 13 ENGINE CARE 13 INTERIOR CARE 14 ...

Page 129: ...The plate is accessible by sliding the seat forward and lifting the carpet in this area Located adjacent to the Identification Plate 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 Y...

Page 130: ...e met A To be displayed in the airplane at all times 1 Aircraft Airworthiness Certificate FAA Form 8100 2 2 Aircraft Registration Certificate FAA Form 8050 3 3 Aircraft Radio Station License if transmitter installed FCC Form 556 B To be carried in the airplane at all times 1 Weight and Balance and associated papers latest copy of the Repair and Alteration Form FAA Form 337 if applicable 2 Equipmen...

Page 131: ...ty to comply with all FAA inspection requirements while ensuring timely replacement of life limited parts and adherence to factory recommended inspection intervals and maintenance procedures CESSNA PROGRESSIVE CARE The Cessna Progressive Care Program has been designed to help you realize maximum utilization of your airplane at a minimum cost and downtime Under this program the inspection and maint...

Page 132: ...ection depending on which program you choose to establish for your airplane While these important inspections will be performed for you by any Cessna Dealer in most cases you will prefer to have the Dealer from whom you purchased the airplane accomplish this work PILOT CONDUCTED PREVENTIVE MAINTENANCE A certified pilot who owns or operates an airplane not used as an air carrier is authorized by FA...

Page 133: ...the best precaution against damage to the parked airplane by gusty or strong wings To tie down the airplane securely proceed as follows 1 Set the parking brake and install the control wheel lock 2 Install a surface control lock between each aileron and flap 3 Tie sufficiently strong ropes or chains 700 pounds tensile strength to the wing and tail tie down fittings and secure each rope to a ramp ti...

Page 134: ...ng points on both upper door sills may be 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 operational use for the first 25 hours are considered in flyable storage status Every seventh day during these periods the propeller should be rotated by hand through five revolutions This action...

Page 135: ...tions or tests For these regulatory requirements owners should check with local aviation officials where the airplane is being operated For quick and ready reference quantities materials and specifications for frequently used service items are as follows ENGINE OIL GRADE AND VISCOSITY FOR TEMPERATURE RANGE The airplane was delivered from the factory with a corrosion preventive aircraft engine oil ...

Page 136: ...nge to dispersant oil and change the filter Repeat every 100 hours thereafter Change engine oil at least every 6 months even though less than the recommended hours have accumulated Reduce intervals for prolonged operation in dusty areas cold climates or when short flights and long idle periods result in sludging conditions NOTE During the first 25 hour oil and filter change a general inspection of...

Page 137: ... CAPACITY EACH LONG RANGE TANK 19 5 Gallons NOTE Due to cross feeding between fuel tanks the tanks should be re topped after each refueling to assure maximum capacity LANDING GEAR NOSE WHEEL TIRE PRESSURE 30 PSI on 5 00 5 4 Ply Rated Tire MAIN WHEEL TIRE PRESSURE 21 PSI on 6 00 6 4 Ply Rated Tires NOSE GEAR SHOCK STRUT Keep filled with MIL H 5606 hydraulic fluid and inflated with air to 20 PSI Do ...

Page 138: ...cohol acetone carbon tetrachloride fire extinguisher or anti ice fluid lacquer thinner or glass cleaner to clean the plastic These materials will attack the plastic and may cause it to craze Follow by carefully washing with a mild detergent and plenty of water Rinse thoroughly then dry with a clean moist chamois Do not rub the plastic with a dry cloth since this builds up an electrostatic charge w...

Page 139: ...remove ice before flight care should be taken to protect the painted surfaces during ice removal with chemical liquids A 50 50 solution of isopropyl alcohol and water will satisfactorily remove ice accumulations without damaging the paint A solution with more than 50 alcohol is harmful and should be avoided While applying the de icing solution keep it away from the windshield and cabin windows sin...

Page 140: ...the instructions 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 used according to the manufacturer s instructions To minimize wetting the fabric keep the foam as dry as possible and remove it with a vacu...

Page 141: ... PROCEDURES 8 SECTION 4 NORMAL PROCEDURES 9 SECTION 5 PERFORMANCE 9 SUPPLEMENT 11 CESSNA 300 NAV COM COM VOR No LOC Type RT 308C 11 SECTION 1 GENERAL 11 SECTION 2 LIMITATIONS 13 SECTION 3 EMERGENCY PROCEDURES 13 SECTION 4 NORMAL PROCEDURES 13 SECTION 5 PERFORMANCE 13 SUPPLEMENT 15 CESSNA 300 NAV COM 720 Channel Type RT 328T 15 SECTION 1 GENERAL 15 SECTION 2 LIMITATIONS 17 SECTION 3 EMERGENCY PROCE...

Page 142: ...300 TRANSPONDER Type RT 359A AND OPTIONAL ENCODING ALTIMETER Type EA 401A 29 SECTION 1 GENERAL 29 SECTION 2 LIMITATIONS 31 SECTION 3 EMERGENCY PROCEDURES 31 SECTION 4 NORMAL PROCEDURES 31 SECTION 5 PERFORMANCE 32 SUPPLEMENT 33 CESSNA 300 TRANSPONDER Type RT 359A AND OPTIONAL ALTITUDE ENCODER BLIND 33 SECTION 1 GENERAL 33 SECTION 2 LIMITATIONS 35 SECTION 3 EMERGENCY PROCEDURES 35 SECTION 4 NORMAL P...

Page 143: ...CEDURES 43 SECTION 4 NORMAL PROCEDURES 43 SECTION 5 PERFORMANCE 44 SUPPLEMENT 45 CESSNA 400 MARKER BEACON Type R 402A 45 SECTION 1 GENERAL 45 SECTION 2 LIMITATIONS 47 SECTION 3 EMERGENCY PROCEDURES 47 SECTION 4 NORMAL PROCEDURES 47 SECTION 5 PERFORMANCE 47 SUPPLEMENT 49 CESSNA 400 GLIDE SLOPE Type R 443B 49 SECTION 1 GENERAL 49 SECTION 2 LIMITATIONS 50 SECTION 3 EMERGENCY PROCEDURES 50 SECTION 4 N...

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Page 145: ...ptional system which may be installed in the airplane Each supplement contains a brief description and when applicable operating limitations emergency and normal procedures and performance Other routinely installed items of optional equipment whose function and operational procedures do not require detailed instructions are discussed in Section 7 ...

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Page 147: ...s monitored by the military Following a crash landing the ELT will provide line of sight transmission up to 100 miles at 10 000 feet The ELT supplied in domestic aircraft transmits on both distress frequencies simultaneously at 75 mw rated power output for 48 continuous hours in the temperature range of 40 F to 131 F 40 C to 55 C The ELT unit in export aircraft transmits on 121 5 MHz at 25 mw rate...

Page 148: ...o battery pack 3 ANTENNA RECEPTACLE Connects to antenna mounted on top of tailcone SECTION 2 LIMITATIONS There is no change to the airplane limitations when this equipment is installed SECTION 3 EMERGENCY PROCEDURES Immediately after a forced landing where emergency assistance is required the ELT should be utilized as follows 1 ENSURE ELT ACTIVATION Turn a radio transceiver ON and select 121 5 MHz...

Page 149: ...CTION 4 NORMAL PROCEDURES As long as the function selector switch remain in the AUTO position the ELT automatically activates following an impact of 5G or more over a short period of time Following a lightning strike or an exceptionally hard landing the ELT may activate although no emergency exists To check your ELT for inadvertent activation select 121 5 MHz on your radio transceiver and listen f...

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Page 151: ...h frequencies between 108 1 and 111 9 MHz can also be received the navigation receiver does not include the necessary circuits to interpret the signals for localizer indications However the audio portion of the localizer is audible so that flight information such as that broadcast in certain areas on select localizer frequencies by the Automatic Terminal Information Service ATIS may be heard All c...

Page 152: ...F ON VOLUME CONTROL Turns complete set on and controls volume of audio from communication receiver Clockwise rotation increases audio level 6 COMMUNICATION RECEIVER TRANSMITTER FRACTIONAL MEGAHERTZ SELECTOR Selects communication receiver transmitter fractional frequency in 0 05 MHz steps between 0 00 and 0 95 MHz 7 NAVIGATION RECEIVER MEGAHERTZ SELECTOR Selects navigation receiver frequency in 1 M...

Page 153: ...gency procedures when this avionics equipment is installed SECTION 4 NORMAL PROCEDURES COMMUNICATIONS TRANSCEIVER OPERATION 1 OFF VOL Control TURN ON and adjust to desired listening level 2 XMTR SEL Switch SET to desired transceiver 3 SPEAKER PHONE or AUTO Switch SET to desired mode 4 COM Frequency Selector Knob SELECT desired operating frequency 5 SQ Control ROTATE counterclockwise to decrease ba...

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Page 155: ...DME receiver transmitter or a glide slope receiver or both may be interconnected with the Cessna 300 Nav Com set for automatic selection of the association DME or GS frequency When a VOR frequency is selected on the Nav Com the associated VORTAC or VOR DME station frequency will also be selected automatically likewise if a localizer frequency is selected the associated glide slope frequency will b...

Page 156: ...requency in 1 MHz steps between 118 and 135 MHz 5 OFF ON VOLUME CONTROL Turns set on and controls volume of audio from communications receiver 6 COMMUNICATION RECEIVER TRANSMITTER FRACTIONAL MEGAHERTZ SELECTOR Selects communication receiver transmitter fractional frequency in 05 MHz steps between 000 and 950 MHz or between 025 and 975 MHz depending on position of 50 25 MHz selector switch 7 7 50 2...

Page 157: ...alizer signal OFF position flag indicates unreliable signal When OFF position disappears indicator shows whether selected VOR course is TO or FROM the station if LOC frequency is selected indicator will only show TO 14 RECIPROCAL COURSE INDEX Indicates reciprocal of selected VOR course 15 OMNI BEARING SELECTOR OBS Selects desired course to or from a VOR station 16 BC During LOC operation when opti...

Page 158: ...dentifier More Code signal b To Filter Out Station Identifier Signal SET to CENTER unmarked position to include filter in audio circuit 6 OBS Knob SELECT desired course TO SELF TEST VOR NAVIGATION CIRCUITS 1 COM OFF VOL Control TURN ON 2 NAV Frequency Selector Switches SELECT usable VOR station signal 3 OBS Knob SET for 0 course at index CDI pointer centers or deflects left or right depending on b...

Page 159: ... with the Nav Com set for automatic selection of the associated DME or glide slope frequency When a VOR frequency is selected on the Nav Com the associated VORTAC or VOR DME station frequency will also be selected automatically likewise if a localizer frequency is selected the associated glide slope frequency will be selected automatically The course deviation indicator includes either a single po...

Page 160: ...Hz Selector to select frequency in 05 MHz steps between 025 and 975 MHz In 0 position enables COM frequency readout to display and Com Fractional MHz Selector to select frequency in 05 MHz steps between 000 and 950 MHz NOTE The 5 or 0 may be read as the third decimal digit which is not displayed in the Com fractional frequency display 3 NAVIGATION OPERATING FREQUENCY READOUT 4 ID VOX T SWITCH With...

Page 161: ... DEVIATION POINTER Indicates course deviation from selected omni course or localizer centerline 15 GLIDE SLOPE GS FLAG When visible red GS flag indicates unreliable glide slope signal or improperly operating equipment Flag disappears when a reliable glide slope signal is being received 16 GLIDE SLOPE DEVIATION POINTER Indicates deviation from ILS glide slope 17 NAV TO FROM INDICATOR Operates only ...

Page 162: ...OM Frequency Selector Switches SELECT desired operating frequency 6 SQ Control ROTATE counterclockwise to decrease background noise as required 7 Mike Button a To Transmit DEPRESS and SPEAK into microphone NOTE Sidetone may be selected on all models except 152 models by placing the AUTO selector switch in either the SPEAKER or PHONE positions On 152 models sidetone is constant in both the SPEAKER ...

Page 163: ...able VOR station signal 3 OBS Knob SET for 0 course at course index course deviation pointer centers or deflects left or right depending on bearing of signal NAV TO FROM indicator shows TO or FROM 4 ID VOX T Switch PRESS to T and HOLD at T course deviation pointer centers and NAV TO FROM indicator shows FROM 5 OBS Knob TURN to displace course approximately 10 to either side of 0 while holding ID V...

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Page 165: ...scribed in Figure 1 The Cessna 300 ADF can be used for position plotting and homing procedures and for aural reception of amplitude modulated AM signals With the function selector knob at ADF the Cessna 300 ADF provides a visual indication on the bearing indicator of the bearing to the transmitting station relative to the nose of the airplane This is done by combining signals from the sense antenn...

Page 166: ...ations transmitting keyed CW signals Morse Code to be heard REC Selects operation as standard communication receiver using only sense antenna ADF Set operates as automatic direction finder using loop and sense antenna TEST Momentary on position used during ADF operation to test bearing reliability When held in TEST position slews indicator pointer clockwise when released if bearing is reliable poi...

Page 167: ...ECT operating frequency 3 ADF SPEAKER PHONE Switch SELECT speaker or phone position 4 Function Selector Knob ADF position and note relative bearing on indicator 5 VOL Control ADJUST to desired listening level TO TEST RELIABILITY OF AUTOMATIC DIRECTION FINDER 1 Function Selector Knob ADF position and note relative bearing on indicator 2 Function Selector Knob TEST position and observe that pointer ...

Page 168: ...8 SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounted antenna or several related external antennas will result in a minor reduction in cruise performance ...

Page 169: ...se signals on 1030 MHz and transmits coded pulse train reply signals on 1090 MHz It is capable of replying to Mode A aircraft identification and Mode C altitude reporting interrogations on a selective reply basis on any of 4 096 information code selections When an optional panel mounted EA 401A Encoding Altimeter not part of a standard 300 Transponder system is included in the avionic configuratio...

Page 170: ... pulses glows steadily to indicate transmission of IDENT pulse or satisfactory self test operation Reply Lamp will also glow steadily during initial warm up period 3 IDENT ID SWITCH When depressed selects special pulse identifier to be transmitted with transponder reply to effect immediate identification of aircraft on ground controller s display Reply Lamp will glow steadily during duration of ID...

Page 171: ...G KNOB Dials in desired altimeter setting in the range of 27 9 to 31 0 inches of mercury on the standard altimeter or 950 to 1050 millibars on the optional altimeter SECTION 2 LIMITATIONS There is no change to the airplane limitations when this avionic equipment is installed SECTION 3 EMERGENCY PROCEDURES TO TRANSMIT AN EMERGENCY SIGNAL 1 Function Switch ON 2 Reply Code Selector Knobs SELECT 7700 ...

Page 172: ...d controller to stop altitude squawk turn Function Switch to ON for Mode A operation only NOTE Pressure altitude is transmitted by the transponder for altitude squawk and conversion to indicated altitude is done in ATC computers Altitude squawked will only agree with indicated altitude when the local altimeter setting is used by the ground controller is set in the encoding altimeter 5 DIM Control ...

Page 173: ...f replying to Mode A aircraft identification and also Mode C altitude reporting when coupled to an optional altitude encoder system The transponder is capable of replying on both modes of interrogation on a selective reply basis on any of 4 096 information code selections The optional altitude encoder system not part of a standard 300 Transponder system required for Mode C altitude reporting opera...

Page 174: ...ENT pulse or satisfactory self test operation Reply lamp will also glow steadily during initial warm up period 3 IDENT ID SWITCH When depressed selects special pulse identifier to be transmitted with transponder reply to effect immediate identification of aircraft on ground controller s display Reply lamp will glow steadily during duration of IDENT pulse transmission 4 DIMMER DIM CONTROL Allows pi...

Page 175: ...te then SELECT 7600 operating code for 15 minutes and then REPEAT this procedure at same intervals for remainder of flight 3 ID Switch DEPRESS then RELEASE at intervals to effect immediate identification of aircraft on ground controller s display SECTION 4 NORMAL PROCEDURES BEFORE TAKEOFF 1 Function Switch SBY TO TRANSMIT MODE A AIRCRAFT IDENTIFICATION CODES IN FLIGHT 1 Reply Code Selector Knobs S...

Page 176: ... ground controller is set in the aircraft altimeter 3 DIM Control ADJUST light brilliance of reply lamp TO SELF TEST TRANSPONDER OPERATION 1 Function Switch SBY and wait 30 seconds for equipment to warm up 2 Function Switch ON or ALT 3 TST Button DEPRESS reply lamp should light brightly regardless of DIM control setting 4 TST Button Release for normal operation SECTION 5 PERFORMANCE There is no ch...

Page 177: ...se signals on 1030 MHz and transmits coded pulse train reply signals on 1090 MHz It is capable of replying to Mode A aircraft identification and Mode C altitude reporting interrogations on a selective reply basis on any of 4 096 information code selections When an optional panel mounted EA 401A Encoding Altimeter not part of 400 Transponder System is included in the avionic configuration the trans...

Page 178: ... interrogating signal 2 REPLY LAMP Lamp flashes to indicate transmission of reply pulses glows steadily to indicate transmission of IDENT pulse or satisfactory self test operation Reply Lamp will also glow steadily during initial warm up period 3 IDENT ID SWITCH When depressed selects special pulse identifier to be transmitted with transponder reply to effect immediate identification of aircraft o...

Page 179: ...dard altimeter or 946 to 1049 millibars on the optional altimeter 13 ALTIMETER SETTING KNOB Dials in desired altimeter setting in the range of 27 9 to 31 0 inches of mercury on standard altimeter or 950 to 1050 millibars on the optional altimeter SECTION 2 LIMITATIONS There is no change to the airplane limitations when this avionic equipment is installed SECTION 3 EMERGENCY PROCEDURES TO TRANSMIT ...

Page 180: ... ALT NOTE When directed by ground controller to stop altitude squawk turn Function Switch to ON for Mode A operation only NOTE Pressure altitude is transmitted by the transponder for altitude squawk and conversion to indicated altitude is done in ATC computers Altitude squawked will only agree with indicated altitude when the local altimeter setting in use by the ground controller is set in the en...

Page 181: ...ode A aircraft identification and also to Mode C altitude reporting when coupled to an optional altitude encoder system The transponder is capable of replying on both modes of interrogation on a selective reply basis on any of 4 096 information code selections The optional altitude encoder system not part of a standard 400 Transponder system required for Mode C altitude reporting operation consist...

Page 182: ...NT pulse or satisfactory self test operation Reply lamp will also glow steadily during initial warm up period 3 IDENT ID SWITCH When depressed selects special pulse identifier to be transmitted with transponder reply to effect immediate identification of aircraft on ground controller s display Reply lamp will glow steadily during duration of IDENT pulse transmission 4 DIMMER DIM CONTROL Allows pil...

Page 183: ...te then SELECT 7600 operating code for 15 minutes and then REPEAT this procedure at same intervals for remainder of flight 3 ID Switch DEPRESS then RELEASE at intervals to effect immediate identification of aircraft on ground controller s display SECTION 4 NORMAL PROCEDURES BEFORE TAKEOFF 1 Function Switch ON TO TRANSMIT MODE A AIRCRAFT IDENTIFICATION CODES IN FLIGHT 1 Reply Code Selector Switches...

Page 184: ...the ground controller is set in the aircraft altimeter 3 DIM Control ADJUST light brilliance of reply lamp TO SELF TEST TRANSPONDER OPERATION 1 Function Switch SBY and wait 30 seconds for equipment to warm up 2 Function Switch ON 3 TST Button DEPRESS reply lamp should light brightly regardless of DIM control setting 4 TST Button RELEASE for normal operation SECTION 5 PERFORMANCE There is no change...

Page 185: ...ction On 152 series airplanes a HI LO sensitivity selector switch is provided with a separate press to test button This system provides visual and aural indications of 75 MHz ILS marker beacon signals as the marker is passed The following table lists the three most currently used marker facilities and their characteristics MARKER FACILITIES MARKER IDENTIFYING TONE LIGHT Inner Continuous 6 dots sec...

Page 186: ...ition is a lamp test function only 4 LO HI SWITCH 152 Model Series Only In the LO position Up receiver sensitivity is positioned for ILS approaches In the HI position Down receiver sensitivity is positioned for airway flying 5 SPEAKER PHONE SWITCH Selects speaker or phone for aural reception 6 MARKER BEACON INDICATOR LIGHTS Indicates passage of outer middle and inner marker beacons The OUTER light...

Page 187: ...ired listening level 2 LO HI SENS Switch SELECT HI position for airway flying or LO position for ILS approaches 3 SPKR PHONE Switch SELECT speaker or phone audio 4 TEST Switch PRESS and ensure that marker beacon indicator lights are operative 5 BRT Control SELECT BRT full clockwise ADJUST as desired when illuminated over marker beacon SECTION 5 PERFORMANCE There is no change to the airplane perfor...

Page 188: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 9 48 PAGE INTENTIONALLY BLANK ...

Page 189: ...d indicator and an externally mounted antenna The glide slope receiver is designed to receive ILS glide slope signals on any of 40 channels The channels are spaced 150 kHz apart and cover a frequency range of 329 15 MHz through 335 0 MHz When a localizer frequency is selected on the NAV receiver the associated glide slope frequency is selected automatically Operation of the Cessna 400 Glide Slope ...

Page 190: ...ard all glide slope signal indications when making a localizer back course approach unless a glide slope ILS BC is specified on the approach and landing chart SECTION 2 LIMITATIONS There is no change to the airplane limitations when this avionic equipment is installed However the pilot should be aware that on many Cessna airplanes equipped with the windshield mounted glide slope antenna pilots sho...

Page 191: ...uency is automatically selected 2 NAV COM VOX ID T Switch SELECT ID position to disconnect filter from audio circuit 3 NAV VOL Control ADJUST to desired listening level to confirm proper localizer station CAUTION When glide slope OFF or GS flag is visible glide slope indications are unusable SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is install...

Page 192: ...CESSNA AIRCRAFT COMPANY FOR TRAINING USE ONLY MODEL 152 9 52 PAGE INTENTIONALLY BLANK ...

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