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Cessna TR182 1979, Pilot Operating Handbook

The Cessna TR182 1979 Pilot Operating Handbook is an essential manual for pilots flying this aircraft model. Available for free download at manualshive.com, this comprehensive guide provides detailed instructions and information on operating procedures, safety guidelines, and aircraft specifications. Get your manual today to enhance your flying experience.

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Summary of Contents for TR182 1979

Page 1: ...RIED IN THE AIRPLANE AT ALLTIMES 5 I N J If 0 ena Q n i c i if 1 tll 1 f Registration No J j Y A THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED to BE FURNISHED TO THE PILOT BY CAR PART 3 AND CONSTIJUTES THE FAA APPROVED AIRPLANE FLIGHT MAN l AL COPYRIGHT 1978 CESSNA AIRCRAFT COMP A Y WICHITA KANSAS USA Dl143 13RH RPC 425 10 78 1 OCTOBER 1978 ...

Page 2: ...THIS MANUAL WAS PROVIDED FORTHE AIRPLANE IDENTIFIED ON THE TITLE PAGE ON 3 7f SUBSEQUENT REVISIONS SUPPLIED BY CESSNA AIRCRAFT COMPANY MUST BE PROPERLY IN SERTED CESSNA AIRCRAFT COMPANY PAWNEE DIVISION ...

Page 3: ... 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 PERSONNEL to provide you wi...

Page 4: ...bstacle LANDING PERFORMANCE Ground Roll Total Distance Over 50 Ft Obstacle STALL SPEED CAS Flaps Up Power Off Flaps Down Power Off MAXIMUM WEIGHT Ramp Takeoff or Landing STANDARD EMPTY WEIGHT Turbo Skylane fiG Turbo Sky lane RG II MAXIMUM USEFUL LOAD Turbo Skylane RG Turbo Skylane RG II BAGGAGE ALLOWANCE WING LOADING Pounds Sq Ft POWER LOADING Pounds HP FUEL CAPACITY Total OIL CAPACITY ENGINE Turb...

Page 5: ...ea 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 asterisk preceding the pages listed LOG OF EFFECTIVE PAGES Dates of issue for original...

Page 6: ...ENERAL 1 LlMITATIONS 2 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT BALANCE EQUIPMENT LlST 6 AIRPLANE SYSTEMS DESCRIPTIONS 7 AIRPLANE HANDLING SERVICE MAINTENANCE 8 SUPPLEMENTS Optional Systems Description Operating Procedures 9 iv 1 October 1978 ...

Page 7: ...eights 1 5 Standard Airplane Weights 1 5 Cabin And Entry Dimensions 1 5 Baggage Space And Entry Dimensions 1 5 Specific Loadings 1 5 Symbols Abbreviations And Terminology 1 6 General Airspeed Terminology And Symbols 1 6 Meteorological Terminology 1 7 Engine Power Terminology 1 7 Airplane Performance And Flight Planning I errnIno log y 1 7 Weight And Balance Terminology 1 8 1 October 1978 1 1 ...

Page 8: ...span shown with strobe lights installed Maximum height shown with nose gear depressed as far as possible and flashing beacon installed Wheel base length is 65 5 Propeller ground clearance is 11 1 2 6 Wing area is 174 square feet 7 Minimum turning radius pivot point to outboard wing tip is 27 0 PIVOT POINT 1 36 0 1 Figure 1 1 Three View 1 2 1 October 1978 ...

Page 9: ...del Number 0 540 L3C5D Engine Type Turbocharged direct drive air cooled horizontally opposed carburetor equipped six cylinder engine with 541 5cu in displacemen t Horsepower Rating and Engine Speed 235rated BHP at 31inches Hg and 2400 RPM PROPELLER Propeller Manufacturer McCauley Accessory Division Propeller Model Number B2D34C217 90DHB 8 Number of Blades 2 Propeller Diameter Maximum 82 inches Min...

Page 10: ... stabilized NOTE The airplane was delivered from the factory with a corro sion preventive aircraft engine oil This oil should be drained after the first 25 hours of operation MIL L 22851 Ashless Dispersant Oil This oil must be used after first 50 hours or oil consumption has stabilized Recommended Viscosity For Temperature Range MIL L 6082 Aviation Grade Straight Mineral Oil SAE 50 above 16 C 60 F...

Page 11: ...eas A and B is 200lbs STANDARD AIRPLANE WEIGHTS Standard Empty Weight Turbo Skylane RG 1764lbs Turbo Skylane RG II 1815lbs Maximum Useful Load Turbo Skylane RG 1348lbs Turbo Skylane RG II 1297lbs CABIN AND ENTRY DIMENSIONS Detailed dimensions of the cabin interior and entry door openings are illustrated in Section 6 BAGGAGE SPACE AND ENTRY DIMENSIONS Dimensions of the baggage area and baggage door...

Page 12: ... travel Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position Maximum Landing Gear Extended Speed is the maximum speed at which an airplane can be safely flown with the landing gear extended Maximum Landing Gear Operating Speed is the maximum speed at which the landing gear can be safely extended or retracted Maximum Structural Cruising Spee...

Page 13: ...n set to 29 92 inches of mercury 1013 mb BRP ENGINE POWER TERMINOLOGY Brake Horsepower is the power developed by the engine RPM MP Revolutions Per Minute is engine speed Manifold Pressure is a pressure measured in the engine s induction system and is expressed in inches of mercury Rg AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Demon strated Crosswind Velocity Usable Fuel Unusable Fuel GPH...

Page 14: ... product of the weight of an item multiplied by its arm Moment divided by the constant 1000is used in this handbook to simplify balance calculations by reduc ing the number of digits Center of Gravity is the point at which an airplane or equipment would balance if suspended Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane Center of Gra...

Page 15: ...ight of start taxi and run up fuel Maximum Takeoff Weight is the maximum weight approved for the start of the takeoff run Maximum Landing Weight is the maximum weight approved for the landing touchdown Tare is the weight of chocks blocks stands etc used when weighing an airplane and is included in the scale read ings Tare is deducted from the scale reading to obtain the actual net airplane weight ...

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Page 17: ...ower Plant Instrument Markings Weight Limits Center Of Gravity Limits Maneuver Limits Flight Load Factor Limits Kinds Of Operation Limits Fuel Limitations Maximum Operating Altitude Limit Other Limitations Flap Limitations Placards 1 October 1978 SECTION 2 LIMIT ATIONS Page 2 3 2 4 2 4 2 5 2 6 2 6 2 7 2 7 2 7 2 7 2 8 2 8 2 8 2 8 2 9 2 1 2 2blank ...

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Page 19: ... performance data and other necessary information for airplanes equipped with specific options NOTE The airspeeds listed in the Airspeed Limitations chart figure 2 1 and the Airspeed Indicator Markings chart figure 2 2 are based on Airspeed Calibration data shown in Section 5 with the normal static source with the exception of the bottom of the green and white arcs on the airspeed indicator These ...

Page 20: ...s 101 102 control movements above 2100 Pounds 91 91 this speed VFE Maximum Flap Extended Speed To 100 Flaps 138 140 Do not exceed these speeds 100 400 Flaps 97 95 with the given flap settings VLO Maximum Landing Gear 139 140 Do not extend or retract landing Operating Speed gear above this speed VLE Maximum Landing Gear 139 140 Do not exceed th is speed with Extended Speed landing gear extended Max...

Page 21: ...aximum speed for all operations Figure 2 2 Airspeed Indicator Markings POWER PLANT LIMITATIONS Engine Manufacturer Avco Lycoming Engine Model Number 0 540 L3C5D Engine Operating Limits for Takeoff and Continuous Operations Maximum Power 235 BHP Maximum Engine Speed 2400RPM Maximum Manifold Pressure 31 in Hg Maximum Cylinder Head Temperature 500 F 260 C Maximum Oil Temperature 245 F 118 C Oil Press...

Page 22: ... F 245 F Cylinder Head 200 500 F 500 F Temperature Fuel Flow Pressure 0 5 psi 0 5 30 0 psi 30 0 psi Oil Pressure 25 psi 60 90 psi 100 psi Fuel Quantity E 2 Gal Unusable Each Tank Suction 4 5 5 4 in Hg Figure 2 3 Power Plant Instrument Markings WEIGHT LIMITS Maximum Ramp Weight 3112lbs Maximum Takeoff Weight 3100lbs Maximum Landing Weight 31001bs Maximum Weight in Baggage Compartment Baggage Area A...

Page 23: ...e include any maneuvers incidental to normal flying stalls except whip stalls lazy eights chandelles and steep turns in which the angle of bank is not more than 60 Aerobatic maneuvers including spins are not approved FLIGHT LOAD FACTOR LIMITS Flight Load Factors Flaps Up 3 8g 1 52g Flaps Down t2 0g The design load factors are 150 of the above and in all cases the structure meets or exceeds design ...

Page 24: ... Takeoff and land with the fuel selector valve handle in the BOTHposition Operation on either left or right tank is limited to level flight only With 1 4 tank or less prolonged uncoordinated flight is prohibited when operating on either left or right tank in level flight Approved Fuel Grades and Colors 100LLGrade Aviation Fuel Blue 100 Formerly 100 130 Grade Aviation Fuel Green MAXIMUM OPERATING A...

Page 25: ...ane in the Normal Category Other operat ing limitations which must be complied with when operating this airplane in this category are contained in the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual No acrobatic maneuvers including spins approved Flight into known icing conditions prohibited This airplane is certified for the following flight operations as of date of original ai...

Page 26: ...OR AUXILIARY PASSENGER FORWARD OF BAGGAGE DOOR LATCH AND 80 POUNDS MAXIMUM BAGGAGE AFT OF BAGGAGE DOOR LATCH MAXIMUM 200 POUNDS COMBINED FOR ADDITIONAL LOADING INSTRUCTIONS SEE WEIGHT AND BALANCE DATA 6 On flap position indicator Partial flap range with blue color code and 140 kt callout also me chanical detent at 10 Indices at these positions with white color code and 95 kt callout also mechanica...

Page 27: ...5 U S GAL TO BOTTOM OF FILLER NECK 8 Near landing gear hand pump MANUAL GEAR EXTENSION 1 SELECT GEAR DOWN 2 PULL HANDLE FWD 3 PUMP VERTICALLY CAUTION DO NOT PUMP WITH GEAR UP SELECTED 9 A calibration card is provided to indicate the accuracy of the magnetic compass in 30 increments 10 On oil filler cap OIL 8 QTS 1 October 1978 2 11 2 12 blank ...

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Page 29: ...gine Fire In Flight 3 6 Electrical Fire In Flight 3 6 Cabin Fire 3 7 Wing Fire 3 7 Icing 3 7 Inadvertent Icing Encounter 3 7 Static Source Blockage Erroneous Instrument Reading Suspected 3 8 Landing Gear Malfunction Procedures 3 8 Landing Gear Fails To Retract 3 8 Landing Gear Fails To Extend 3 8 Gear Up Landing 3 9 Landing Without Positive Indication Of Gear Locking 3 9 Landing With A Defective N...

Page 30: ...s Static Source Blocked Spins Rough Engine Operation Or Loss Of Power Carburetor Icing Spark Plug Fouling Magneto Malfunction Engine Driven Fuel Pump Failure Low Oil Pressure Landing Gear Malfunction Procedures Retraction Malfunctions Extension Malfunctions Gear Up Landing Electrical Power Supply System Malfunctions Excessive Rate Of Charge Insufficient Rate Of Charge 3 2 CESSNA MODEL TR182 Page 3...

Page 31: ... 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 Wing Flaps Up Wing Flaps Down Maneuvering Speed 3100Lbs 2600Lbs 2100Lbs Maximum Glide 3100Lbs 2600Lbs 2100Lbs Precautionary Landing With Engine Power Landing Without Engine Power W...

Page 32: ... ENGINE POWER 1 Airspeed 70 KIAS flaps UP 65 KIAS flaps DOWN 2 Mixture IDLE CUT OFF 3 Fuel Selector Valve OFF 4 Ignition Switch OFF 5 Landing Gear DOWN UP if terrain is rough or soft 6 Wing Flaps AS REQUIRED 400 recommended 7 Doors UNLATCH PRIOR TO TOUCHDOWN 9 Master Switch OFF when landing is assured 10 Touchdown SLIGHTLY TAIL LOW 12 Brakes APPLY HEAVILY PRECAUTIONARY LANDING WITH ENGINE POWER 1 ...

Page 33: ...ds Heavy Swells PARALLEL TO SWELLS NOTE If no power is available approach at 70KIAS with flaps up or at 65 KIAS with 10 flaps 7 Cabin Doors UNLATCH 8 Touchdown LEVEL ATTITUDE AT ESTABLISHED DESCENT 9 Face CUSHION at touchdown with folded coat 10 Airplane EVACUATE through cabin doors If necessary open windows and flood cabin to equalize pressure so doors can be opened 11 Life Vests and Raft INFLATE...

Page 34: ...s not extinguished increase glide speed to find an airspeed which will provide an incombustible mixture 6 Forced Landing EXECUTE as described in Emergency Landing Without Engine Power ELECTRICAL FIRE IN FLIGHT 1 Master Switch OFF 2 Avionics Power Switch OFF 3 All Other Switches except ignition switch OFF 4 Vents Cabin Air Heat CLOSED 5 Fire Extinguisher ACTIVATE if available I WARNING I After disc...

Page 35: ...the flames away from the fuel tank and cabin and land as soon as possible using flaps only as required for final approach and touchdown ICING INADVERTENT ICING ENCOUNTER 1 Turn pitot heat switch ON if installed 2 Turn back or change altitude to obtain an outside air temperature that is less conducive to icing 3 Pull cabin heat control full out and rotate defroster control clock wise to obtain maxi...

Page 36: ...sary for improved visibility 11 Approach at 85 to 95 KIAS depending upon the amount of ice accumulation 12 Perform a landing in level attitude STATiC SOURCE BLOCKAGE Erroneous Instrument Reading Suspected 1 Alternate Static Source Valve PULL ON 2 Airspeed Consult appropriate table in Section 5 3 Altitude Cruise 50 feet higher and approach 30 feet higher than normal LANDING GEAR MALFUNCTION PROCEDU...

Page 37: ...Check COMPLETE 2 Approach NORMAL full flap 3 Landing Gear and Gear Pump Circuit Breakers IN 4 Landing TAIL LOW as smoothly as possible 5 Braking MINIMUM necessary 6 Taxi SLOWLY 7 Engine SHUTDOWNbefore inspecting gear LANDING WITH A DEFECTIVE NOSE GEAR Or Flat Nose Tire 1 Moveable Load TRANSFER to baggage area 2 Passenger MOVE to rear seat 3 Before Landing Checklist COMPLETE 4 Runway HARD SURFACE o...

Page 38: ...IGHT 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 RPMtaxi 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 Avionics ...

Page 39: ...ute a 1800 gliding turn necessary to return to the runway The checklist procedures assume that adequate time exists to secure the fuel and ignition systems prior to touchdown After an engine failure in flight the best glide speed as shown in figure 3 1 should be established as quickly as possible While gliding toward a suitable landing area an effort should be made to identify the cause ofthe fail...

Page 40: ... surface In a forced landing situation do not turn off the avionics power and master switches until a landing is assured Premature deactivation of the switches will di a blethe encoding altimeter and airplane electrical sys tems LANDING WITHOUT ELEVATOR CONTROL Trim for horizontal flight with an airspeed of approximately 80 KIAS by using throttle and elevator trim control Then do not change the el...

Page 41: ...rd rate left turn holding the turn coordinator symbolic airplane wing opposite the lower left index mark for 60 seconds Then roll back to level 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...

Page 42: ...al is encountered proceed as follows 1 Close the throttle 2 Stop the turn by using coordinated aileron and rudder control to align the symbolic airplane in the turn coordinator with the horizon reference line 3 Cautiously apply elevator back pressure to slowly reduce the indicated airspeed to 80 KIAS 4 Adjust the elevator trim control to maintain an 80 KIAS glide 5 Keep hands off the control wheel...

Page 43: ...feet higher in cruise With the vents open the speed variation reduces to 1 knot or less If the alternate static source must be used for landing the normal indicated approach speed may be used since the indicated airspeed variations in this configuration are 3knots or less SPINS Intentional spins IU8 prohibited in this airplane Should an inadvert ent spin occur the following recovery procedure shou...

Page 44: ...r R position An obvious power loss in single ignition operation is evidence of spark plug or magneto trouble Assuming that spark plugs are the more likely cause lean the mixture to the recommended lean setting for cruising flight If the problem does not clear up in several minutes determine if a richer mixture setting will produce smoother operation If not proceed to the nearest airport for repair...

Page 45: ...d the LDG GEAR and GEAR PUMP circuit breakers are in reset if necessary Also check both landing gear position indicator lights for operation by pressing to test the light units and rotating them at the same time to check for open dimming shutters A burned out bulb can be replaced in flight by using the bulb from the remaining gear position indicator light RETRACTION MALFUNCTIONS If the landing gea...

Page 46: ...GEAR UP LANDINGS If the landing gear remains retracted or is only partially extended and all efforts to fully extend it including manual extension have failed plan a wheels up landing In preparation for landing reposition the landing gear lever to GEAR UP and push the LDG GEAR and GEAR PUMPcircuit breakers in to allow the landing gear to swing into the gear wells at touchdown Then proceed in accor...

Page 47: ... and ammeter dis charge indications may occur during low RPM conditions with an electrical load on the system such as during a low RPM taxi Under these conditions the light will go out at higher RPM The master switch need not be recycled since an over voltage condition has not occurred to de activate the alternator system If the over voltage sensor should shut downthe alternator a discharge rate w...

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Page 49: ... Left Wing Leading Edge Left Wing Trailing Edge Before Starting Engine Starting Engine Before Takeoff Takeoff Normal Takeoff Short Field Takeoff Enroute Climb Normal Climb Maximum Performance Climb Cruise Descent Before Landing Landing Normal Landing Short Field Landing Balked Landing After Landing Securing Airplane 4 5 4 5 4 5 4 5 4 5 4 6 4 6 4 6 4 7 4 7 4 7 4 8 4 9 4 9 4 9 4 10 4 10 4 10 4 10 4 ...

Page 50: ...ind Takeoff Landing Gear Retraction Enroute Climb Cruise Stalls Before Landing Landing Normal Landing Short Field Landing Crosswind Landing Balked Landing Cold Weather Operation Starting Operation Hot Weather Operation Noise Abatement 4 2 CESSNA MODELTR182 Page 4 13 4 13 4 15 4 15 4 15 4 15 4 15 4 15 4 16 4 16 4 16 4 17 4 17 4 19 4 20 4 20 4 20 4 20 4 20 4 21 4 21 4 21 4 22 4 23 4 23 1 October 197...

Page 51: ...o the particular weight must be used Takeoff Normal Climb Out Short Field Takeoff Flaps 20 Speed at 50 Feet Enroute Climb Flaps and Gear Up Normal Best Rate of Climb Sea Level Best Rate of Climb 20 000Feet Best Angle of Climb Sea Level Best Angle of Climb 10 000Feet Landing Approach Normal Approach Flaps Up Normal Approach Flaps 40 Short Field Approach Flaps 40 Balked Landing Maximum Power Flaps 2...

Page 52: ...rom 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 Preflight Inspection 4 4 1 October 1978...

Page 53: ...thin the arc of the propeller since a loose or broken wire or a component malfunction could cause the propeller to rotate 7 Fuel Quantity Indicators CHECK QUANTITY 8 Landing Gear Position Indicator Light green ILLUMINATED 9 Master Switch OFF 10 Static Pressure Alternate Source Valve OFF 11 Fuel Selector Valve BOTH 12 Baggage Door CHECK for security lock with key if child s seat is to be occupied E...

Page 54: ...n and re insert Wait 5 seconds and then check oil level for an accurate reading 8 Before first flight of the day and after each refueling pull out strainer drain knob for about four seconds to clear fuel strainer of possible water and sediment Check strainer drain closed If water is observed the fuel system may contain additional water and further draining of the system at the strainer fuel tank s...

Page 55: ... during engine start to prevent possible damage to avionics 5 Brakes TEST and SET 6 Cowl Flaps OPEN move lever out of locking hole to reposition 7 Landing Gellr Lever DOWN 8 Circuit Breakers CHECK IN STARTING ENGINE 1 Mixture RICH 2 Propeller HIGH RPM 3 Carburetor Heat COLD 4 Throttle CLOSED NOTE The carburetor does not have an accelerator pump there fore pumping of the throttle must be avoided du...

Page 56: ...engine driven fuel pump should fail However if a fuel pump failure causes the fuel pressure to drop below 0 5 PSI use the auxiliary fuel pump to assure proper engine operation 8 Elevator and Rudder Trim TAKEOFF 9 Throttle i700 RPM a Magnetos CHECK RPM drop should not exceed 175RPM on either magneto or 50 RPM differential between magnetos b Propeller CYCLEfrom high to low RPM return to high RPM ful...

Page 57: ...mb Speed 70 KIAS flaps 20 80 KIAS flaps UP 7 Brakes APPLY momentarily when airborne 8 Landing Gear RETRACT in climb out 9 Wing Flaps RETRACT SHORT FIELD TAKEOFF 1 Wing Flaps 20 2 Carburetor Heat COLD 3 Brakes APPLY 4 Power 31 INCHES Hg Maximum and 2400RPM NOTE To avoid overboosting the engine do not use full throttle for takeoff 5 Mixture FULL RICH 6 Brakes RELEASE 7 Elevator Control MAINTAIN SLIG...

Page 58: ... FULL RICH 5 Cowl Flaps FULL OPEN CRUISE 1 Power 17 25INCHES Hg 2100 2400RPM 2 Elevator and Rudder Trim ADJUST 3 Mixture LEAN 4 Cowl Flaps CLOSED DESCENT 1 Fuel Selector Valve BOTH 2 Power AS DESIRED 3 Carburetor Heat AS REQUIRED to prevent carburetor icing 4 Mixture LEAN for smoothness 5 Cowl Flaps CLOSED 6 Wing Flaps AS DESIRED 0 10 below 140KIAS 10 40 below 95 KIAS NOTE The landing gear may be ...

Page 59: ...IN WHEELS FIRST 6 Landing Roll LOWER NOSE WHEEL GENTLY 7 Braking MINIMUM REQUIRED SHORT FIELD LANDING 1 Airspeed 70 80KIAS flaps UP 2 Wing Flaps 40 below 95 KIAS 3 Airspeed MAINTAIN 64 KIAS 4 Trim ADJUST 5 Power REDUCE to idle as obstacle is cleared 6 Touchdown MAIN WHEELS FIRST 7 Brakes APPLY HEAVILY 8 Wing Flaps RETRACT for maximum brake effectiveness BALKED LANDING 1 Power 31 INCHES Hg and 2400...

Page 60: ... Cowl Flaps OPEN SECURING AIRPLANE 1 Parking Brake SET 2 Throttle IDLE 3 Avionics Power Switch Electrical Equipment OFF 4 Mixture IDLE CUT OFF pulled full out 5 Ignition Switch OFF 6 Master Switch OFF 7 Control Lock INSTALL 8 Fuel Selector Valve RIGHT or LEFT to prevent crossfeeding 4 12 1 October 1978 ...

Page 61: ... NOTE The carburetor used on this airplane does not have an accelerator pump therefore pumping of the throttle must be avoided during starting because doing so will only cause excessive leaning In cold weather 2 strokes of the primer may be necessary prior to starting During extremely cold temperatures up to 4strokes of the primer may be necessary NOTE Additional details concerning cold weather st...

Page 62: ...IND DIRECTION Strong quartering tail winds require caution Avoid sudden bursts of the throttle and sharp braking when the airplane is in this attitude Use the steerable nose wheel and rudder to maintain direction Figure 4 2 Taxiing Diagram 4 14 1 October 1978 ...

Page 63: ...ning operation of the ignition system RPM checks at higher engine speeds will usually confirm whether a deficiency exists An absence of RPM drop may be an indication of faulty grounding of one side of the ignition system or should be cause for suspicion that the magneto timing is set in advance of the setting specified ALTERNATOR CHECK Prior to flights where verification of proper alternator and a...

Page 64: ...n 20 are not approved for takeoff If 20 wing flaps are used for takeoff they should be left down until all obstacles are cleared and a safe flap retraction speed of 70 KIAS is reached To clear an obstacle with wing flaps 20 an obstacle clearance speed of 59 KIAS should be used Soft field takeoffs are performed with 20 flaps by lifting the airplane off the ground as soon as practical in a slightly ...

Page 65: ...t is necessary to climb rapidly to clear mountains or reach favorable winds at high altitudes the best rate of climb speed should be used with maximum power of 31 inches Hg 2400RPM and full rich mixture This speed is 88 KIAS at sea level decreasing to 85 KIAS at 20 000feet If an obstruction ahead requires a steep climb angle a best angle of climb speed should be used with landing gear and flaps up...

Page 66: ...n percent power that will provide smooth engine operation The cowl flaps should be opened if necessary to maintain the cylinder head temperature at approximately two thirds of the normal operating range green arc Cruise performance data in this handbook and on the power computer is based on a recommended lean mixture setting which is established by reference to exhaust gas temperature EGT as shown...

Page 67: ...t by trial and error to prevent ice from forming Whenoperating above approximately 5000 feet at maximum recommended cruise power the heat available from turbocharging increases with altitude and carburetor icing becomes less likely Carburetor heat may be used an an alternate air source in the event the induction air filter becomes blocked However since application of full carburetor heat at high a...

Page 68: ...ing gear up amber indicator light LANDING NORMAL LANDING Landings should be made on the main wheels first to reduce the landing speed and the subsequent need for braking in the landing roll The nose wheel is lowered gently to the runway after the spaad hag diminished to avoid unnecessary nose gear load This procedure is especially impor tant in rough field landings SHORT FIELD LANDING For a short ...

Page 69: ... wire on either magneto could cause the engine to fire In extremely cold 18 C and lower weather the use of an external pre heater and an external power source are recommended whenever possible to obtain positive starting and to reduce wear and abuse to the engine and the electrical system Pre heat will thaw the oil trapped in the oil cooler which probably will be congealed prior to starting in ext...

Page 70: ...pted NOTE Pumping of the throttle will make starting more difficult due to a rapidly varying mixture The carburetor is not equipped w it h an accelerator pump OPERATION During cold weather operations no indication will be apparent on the oil temperature gage prior to takeoff if outside air temperatures are very cold After a suitable warm up period 2 to 5 minutes at 1000 RPM smoothly accelerate the...

Page 71: ...on in this section is appropriate Avoid prolonged engine operation on the ground NOISE ABATEMENT 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...

Page 72: ...de of less than 2000 feet is necessary for him to adequately exercise his duty to see and avoid other aircraft The certificated noise level for the Model TR182 at 3100 pounds maximum weight is 72 5 dB A No determination has been made by the Federal Aviation Administration that the noise levels of this airplane are or should be acceptable or unacceptable for operation at into or out of any airport ...

Page 73: ...aximum Figure 5 6 Time Fuel And Distance To Clim b Maximum Rate Of Climb Time Fuel And Distance To Climb Norrnal Climb Figure 5 7 Cruise Performance 2000Feet Cruise Performance 4000Feet Cruise Performance 6000Feet Cruise Performance 8000Feet Cruise Perform ance 10 000Feet Cruise Performance 12 000Feet Cruise Performance 14 000Feet Cruise Performance 16 000Feet Cruise Performance 18 000Feet Cruise ...

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Page 75: ...er 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 illus trate the effect of different variables Sufficiently detailed information is provided in th...

Page 76: ...ce information presented for a weight of 3100pounds pressure altitude of 4000feet and a temperature of 30 C should be used and results in the following Ground roll Total distance to clear a 50 foot obstacle 1215Feet 2310Feet These distances are well within the available takeoff field length How ever a correction for the effect of wind may be made based on Note 2 of the takeoff chart The correction...

Page 77: ...ws a corresponding 6 2hours Using this information the estimated distance can be determined for the expected 10knot headwind at 11 500feet as follows Range zero wind Decrease in range due to wind 6 2hours x 10knot headwind Corrected range 914 62 852 Nautical Miles This indicates that the trip can be made without a fuel stop using approximately 65 power The cruise performance chart for 12 000feet p...

Page 78: ...ection would be 16 C 80C x 10 20 Increase With this factor included the fuel estimate would be calculated as follows Fuel to climb standard temperature Increase due to non standard temperature 4 8 x 20 Corrected fuel to climb 4 8 1 0 5 8 Gallons Using a similar procedure for time and distance during a climb the following results are obtained Time to climb Distance to climb 16Minutes 29 Nautical Mi...

Page 79: ...ING A procedure similar to takeoff should be used for estimating the landing distance at the destination airport Figure 5 10presents landing distance information for the short field technique The distances corres ponding to 3000feet pressure altitude and a temperature of 30 C are as follows Ground roll Total distance to clear a 50 foot obstacle 705Feet 1490Feet A correction for the effect of wind ...

Page 80: ... level flight FLAPS UP KIAS 50 60 70 80 90 100 110 120 130 140 150 160 170 KCAS 59 65 72 81 90 99 109 119 129 139 149 158 167 FLAPS 200 KIAS 40 50 60 70 80 90 95 KCAS 51 57 64 72 81 91 96 FLAPS 400 KIAS 40 50 60 70 80 90 95 KCAS 51 57 64 72 82 92 97 Figure 5 1 Airspeed Calibration Sheet 1 o 2 5 8 1 October 1978 ...

Page 81: ...LTERNATE KIAS 50 62 73 83 93 98 FLAPS 40 NORMAL KIAS 40 50 60 70 80 90 95 ALTERNATE KIAS 37 50 62 73 83 93 98 HEATER VENTS OPEN AND WINDOWS CLOSED FLAPS UP NORMAL KIAS 60 70 80 90 100 110 120 130 140 150 160 ALTERNATE KIAS 61 71 81 91 101 111 121 131 140 150 159 FLAPS 20 NORMAL KIAS 50 60 70 80 90 95 ALTERNATE KIAS 49 61 71 81 91 95 FLAPS 40 NORMAL KIAS 40 50 60 70 80 90 95 ALTERNATE KIAS 37 50 60...

Page 82: ...5 PERFORMANCE 60 t w r z LU a r 40 u Vl LU W a J w 0 20 5 10 CESSNA MODELTR182 TEMPERATURE CONVERSION CHART 100 80 o 20 40 40 o 20 20 40 60 DEGREES CELSIUS Figure 5 2 Temperature Conversion Chart 1 October 1978 ...

Page 83: ... OF BANK WEIGHT FLAP 00 30 45 60 LBS DEFLECTION KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 41 54 44 58 49 64 58 76 3100 20 39 51 42 55 46 61 55 72 40 40 50 43 54 48 59 57 71 MOST FORWARD CENTER OF GRAVITY ANGLEOF BANK WEIGHT FLAP 0 30 45 60 LBS DEFLECTION KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 43 55 46 59 51 65 61 78 3100 20 41 52 44 56 49 62 58 74 40 43 52 46 56 51 62 61 74 Figure 5 3 Stall S...

Page 84: ... FT GRND TO CLEAR GRND TO CL EAR GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR OFF 50 FT ROLL 50 FTOBS ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS 3100 52 59 S L 725 1390 790 1505 855 1635 925 1780 1000 1935 1000 775 1475 840 1600 915 1740 990 1895 1070 2065 2000 830 1570 900 1705 975 1855 1060 2020 1145 2205 3000 890 1670 965 1815 1045 1980 1135 2160 1230 2360 4000 955 1780 1035 1940 ...

Page 85: ...05 815 1520 885 1650 955 1790 1035 1950 5000 810 1495 875 1625 950 1765 1025 1915 1110 2085 6000 870 1600 940 1735 1020 1885 1105 2055 1195 2235 7000 935 1710 1015 1860 1100 2020 1190 2205 1285 2405 8000 1005 1830 1090 1990 1180 2170 1280 2365 1385 2585 2500 47 53 S L 445 860 48 925 520 995 560 1075 605 1160 1000 475 910 515 980 555 1055 600 1140 645 1230 2000 510 965 55 1040 595 1120 640 1210 695...

Page 86: ...ches Hg Mixture Full Rich Cowl Flaps Open WEIGHT PRESS CLIMB RATE OF CLIMB FPM LBS ALT SPEED FT KIAS 20 C OOC 20 C 40 C 3100 S L 88 1245 1130 1010 890 4000 87 1160 1040 915 790 8000 87 1050 925 800 675 12 000 86 915 790 675 16 000 86 775 660 545 20 000 85 635 530 Figure 5 5 Rate of Climb 5 14 1 October 1978 ...

Page 87: ...tandard temperature 3 Distances shown are based on zero wind PRESSURE CLIMB RATE OF FROM SEA LEVEL WEIGHT TEMP LBS ALTITUDE c SPEED CLIMB TIME FUEL USED DISTANCE FT KIAS FPM MIN GALLONS NM 3100 S L 15 88 1040 0 0 0 2000 11 88 1020 2 0 8 3 4000 7 87 995 4 1 6 6 6000 3 87 965 6 2 4 9 8000 1 87 930 8 3 3 13 10 000 5 87 890 10 4 2 16 12 000 9 86 845 13 5 1 20 14 000 13 86 800 15 6 1 25 16 000 17 86 75...

Page 88: ...0 for each 80C above standard temperature 3 Distances shown are based on zero wind PRESSURE RATE OF FROM SEA LEVEL WEIGHT TEMP LBS ALTITUDE c CLIMB FT FPM TIME FUEL USED DISTANCE MIN GALLONS NM 3100 S L 15 610 0 0 0 2000 11 610 3 1 1 5 4000 7 610 7 2 3 11 6000 3 600 10 3 5 16 8000 1 590 13 4 6 22 10 000 5 575 17 5 8 28 12 000 9 555 20 7 1 35 14 000 13 525 24 8 4 42 16 000 17 495 2B 9 B 50 18 000 2...

Page 89: ... 143 12 6 21 65 136 12 4 62 136 11 8 59 135 11 3 19 57 128 10 9 54 128 10 5 51 127 10 0 2300 25 78 147 14 9 74 147 14 1 71 147 13 4 23 70 141 13 3 67 140 12 7 63 140 12 1 21 62 133 11 8 59 133 11 3 56 132 10 8 19 54 125 10 4 51 125 10 0 49 123 9 6 2200 25 75 144 14 2 71 144 13 5 67 144 12 8 23 67 138 12 1 64 131 12 1 60 131 11 5 21 59 130 11 3 56 130 10 8 53 129 10 3 19 51 122 9 9 49 121 9 5 46 12...

Page 90: ...146 12 8 21 67 140 12 7 63 139 12 1 60 139 11 5 19 59 132 11 2 56 131 10 7 53 130 10 2 2300 25 79 151 15 0 75 150 14 3 71 150 13 6 23 71 144 13 6 68 144 12 9 64 143 12 3 21 64 137 12 1 60 136 11 5 57 136 11 0 19 56 129 10 7 53 128 10 3 50 127 9 8 2200 25 76 148 14 4 72 147 13 7 68 147 13 0 23 68 141 12 9 65 141 12 3 61 140 11 7 21 60 134 11 5 57 133 11 0 54 132 10 5 19 53 12G 10 2 50 125 9 8 48 12...

Page 91: ...9 12 9 21 67 143 12 8 64 142 12 2 61 142 11 6 19 60 135 11 4 57 135 10 9 54 134 10 4 2300 25 80 153 15 1 76 153 14 4 72 153 13 6 23 72 147 13 7 68 147 13 0 65 146 12 4 21 64 140 12 2 61 140 11 7 58 139 11 1 19 57 132 10 9 54 131 10 4 51 130 10 0 2200 25 76 151 14 5 72 150 13 7 69 150 13 0 23 69 144 13 1 65 144 12 4 62 143 11 8 21 61 137 11 7 58 136 11 2 55 135 10 7 19 54 129 10 4 51 128 10 0 49 12...

Page 92: ...12 4 62 145 11 8 19 61 138 11 6 58 138 11 1 55 137 10 6 2300 25 80 157 15 2 76 156 14 5 72 156 13 7 23 73 150 13 8 69 150 13 1 66 149 12 5 21 65 143 12 4 62 143 11 9 59 142 11 3 19 58 136 11 1 55 135 10 6 52 134 10 1 I 2200 25 77 154 14 6 73 153 13 9 I 69 153 13 1 23 70 147 13 2 66 147 12 6 63 146 12 0 21 62 140 I 11 9 I 59 140 11 3 56 139 I 10 8 19 55 133 10 6 53 I 132 10 2 50 130 9 7 I I 2100 25...

Page 93: ...5 13 1 21 69 149 13 1 66 149 12 5 62 148 11 9 19 62 142 11 7 59 141 11 2 56 140 10 7 2300 25 80 159 15 2 76 159 14 5 72 159 13 7 23 73 153 13 9 70 153 13 2 66 152 12 5 21 66 146 12 5 63 146 12 0 60 145 11 4 19 59 139 11 3 56 138 10 8 53 137 10 2 2200 25 77 156 14 6 73 156 13 9 69 156 13 2 23 70 150 13 3 67 150 12 7 63 149 12 0 21 63 143 12 0 60 143 11 5 57 142 10 9 19 56 136 10 8 53 135 10 3 51 13...

Page 94: ... 13 1 21 69 152 13 2 66 152 12 5 62 151 11 9 19 62 145 11 9 59 144 11 3 56 143 10 8 2300 25 80 162 15 2 76 162 14 5 72 161 13 7 23 73 156 13 9 70 156 13 2 66 155 12 6 21 66 149 12 6 63 149 12 0 60 148 11 5 19 60 142 11 4 57 141 10 9 54 140 10 4 2200 25 77 159 14 6 73 159 13 9 69 159 13 2 23 70 153 13 3 67 153 12 7 63 152 12 1 21 64 146 12 1 61 148 11 S 57 145 11 0 19 57 139 11 0 54 138 10 5 51 136...

Page 95: ...5 13 2 66 155 12 5 63 154 11 9 19 63 148 11 9 60 147 11 4 57 146 10 9 2300 25 80 165 15 1 76 165 14 4 7 2 164 13 6 23 73 158 13 9 70 158 13 2 66 158 12 6 21 67 152 12 7 63 152 12 1 60 151 11 5 19 60 145 11 5 57 144 11 0 54 142 10 5 2200 25 77 162 14 6 73 162 13 8 69 161 13 1 I 23 70 156 13 4 67 156 12 7 63 155 12 1 21 64 149 12 2 61 149 11 6 58 147 11 1 19 58 142 11 1 55 141 10 6 52 139 10 1 2100 ...

Page 96: ...3 13 0 21 70 158 13 2 66 157 12 6 63 156 12 0 19 63 151 12 0 60 150 11 5 57 148 10 9 2300 25 79 167 15 1 75 167 14 3 72 167 13 6 23 73 161 13 9 70 161 13 2 66 160 12 6 21 67 155 12 7 64 155 12 1 60 153 11 5 19 61 148 11 6 58 147 11 1 55 145 10 6 2200 25 76 164 14 5 73 164 13 8 69 164 lJ l 23 70 159 13 4 67 158 12 7 64 157 12 1 21 64 152 12 3 61 152 11 7 58 150 11 1 19 58 145 11 2 56 144 10 7 53 14...

Page 97: ...2 9 21 69 160 13 1 66 160 12 5 62 158 11 9 19 63 153 12 0 60 152 11 5 57 150 10 9 2300 25 78 169 14 9 74 169 14 1 71 169 13 4 23 73 164 13 8 69 163 13 1 65 162 12 4 21 67 157 12 7 63 157 12 1 60 155 11 5 19 61 151 11 6 58 149 11 1 55 147 10 6 2200 25 76 167 14 4 72 167 13 7 68 166 12 9 23 70 161 13 3 67 161 12 6 63 159 12 0 21 64 155 12 2 61 154 11 7 58 152 11 1 19 59 146 11 2 56 146 10 7 5J 143 1...

Page 98: ...12 8 21 69 163 13 1 65 162 12 4 62 160 11 8 19 63 156 12 0 60 155 11 5 57 152 10 9 2300 25 77 172 14 7 74 172 14 0 70 171 13 3 23 72 166 13 7 69 166 13 0 65 165 12 4 21 67 160 12 7 63 159 12 1 60 157 11 5 19 61 153 11 7 58 152 11 1 55 149 10 6 2200 25 75 169 14 2 71 169 13 5 68 168 12 8 23 70 163 13 2 66 163 12 6 63 161 12 0 21 64 157 12 2 61 156 11 7 58 154 11 1 19 59 150 11 3 55 148 10 8 53 145 ...

Page 99: ...allons 20 000 16 000 I w w 12 000 l L LU 0 l I 8000 i I 4000 If 1 3nAS 1 2IKTAS J Il 127 KTAS t t t N 1 4 Tj S J I r t t II I 1 J 1 I v lf6 KTAS r t 125 KTAS J 16 Tt II 14 KTAS r t II I I I I Ii J I I t t J I I I I I 16 1 rtS if 1r11KT s t P1 1 3 l TtS P1 12 1 3 iYf t II J I 11 JJJ 1 1 J IL I II I J 1 I I I f 155 KT St7 J4fTTA1 y5 TASf5 2 TIA _r I I I 3 L 1 J s f p11 I I l I J pL J J 2 JJ I 1 I J ...

Page 100: ...gine start taxi takeoff and climb and the time during a normal climb as shown in figure 5 6 2 Reserve fuel is based on 45 minutes at 45 BHP and is 6 7 gallons 20 000 4000 1 1 I 1 1 1 1 I I 1 1 t t o f f 0 0 I t 1 UJ UJ UJ I 3 t t 3 61 i t O t t O I 0 j Q f Q Q I 0 cJ rJ rJ t t It t l l t l I to It I I I I 1 i 11 16 000 I UJ UJ u 12 000 UJ c l I 5 8000 S L 4 5 6 7 8 9 ENDURANCE HOURS Figure 5 9 End...

Page 101: ...OTAL TOTAL TOTAL KIAS FT GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS 3100 64 S L 570 1270 590 1305 610 1335 630 1370 650 1400 1000 590 1305 610 1335 635 1375 655 1410 675 1440 2000 610 1335 635 1375 655 1410 680 1450 700 1480 3000 635 1375 660 1415 680 1450 705 1490 730 1530 4000 660 1415 685 1455 ...

Page 102: ......

Page 103: ...IGHT BALANCE EQUIPMENT LIST SECTION 6 WEIGHT BALANCE EQUIPMENT LIST TABLE OF CONTENTS Introduction Airplane Weighing Procedures Weight And Balance Baggage Tie Down Equipment List 1 October 1978 Page 6 3 6 3 6 6 6 6 6 15 6 1 6 2 blank ...

Page 104: ......

Page 105: ...drain plug to drain all oil d Move sliding seats to the most forward position e Raise flaps to the fully retracted position f Place all control surfaces in neutral position 2 Leveling a Place scales under each wheel minimum scale capacity 1000 pounds b Deflate the nose tire and or lower or raise the nose strut to properly center the bubble in the level see figure 5 1 3 Weighing a With the airplane...

Page 106: ... Tare Symbol Net Weight Left Wheel L Right Wheel R Nose Wheel N Sum of Net Weights As Weighed W x ARM A N x B X x IN W Item Moment 1000 Weight Lbs X C G Arm In Lbs In Airplane Weight From Item 5 Page 6 3 Add Oil 9 Ots at 7 5 Lbs Gal 17 15 7 3 Add Unusable Fuel 4 Gal at 6 Lbs Gal 24 48 0 1 2 Equipment Changes Airplane Basic Empty Weight Figure 6 1 Sample Airplane Weighing 6 4 1 October 1978 ...

Page 107: ...AL NUMBER I PAGE NUMBER WEIGHT CHANGE ITEM NO RUNNI NG BASIC ADDED REMOVED EMPTY WEIGHT DATE DESCRIPTION OF ARTICLE OR MODIFICATION Wt I Arm I Moment Wt I Arm I Moment Wt I Moment In Out lb l n 1000 lb In 1000 lb 1000 O l c n Figure 6 2 Sample Weight and Balance Record Q Ot l urn t lrn t Z 3 d i s t l H trlO o r c 3 tdrn trl trl Zt O 3 3 t Z5 HOe rntrl 3 0 l ...

Page 108: ...n list these on the loading problem NOTE Loading Graph information for the pilot passengers and baggage is based on seats positioned for average occu pants and baggage items loaded in the center of these areas as shown on the Loading Arrangements diagram For loadings which may differ from these the Sample Loading Problem lists fuselage stations for these items to indicate their forward and aft C G...

Page 109: ... wheel well and slightly inboard of each sidewall approximately at station 124 When the cabin floor Baggage A only is utilized for baggage the four eyebolts located on the cabin floor may be used or the two forward eyebolts on the cabin floor and the two eyebolts on the upper forward surface of the wheel well may be used When the upper surface of the wheel well Baggage B only contains baggage the ...

Page 110: ...e aft baggage wall approximate station 134 can be used as a convenient interior reference point for determining the location of baggage area fuselage stations c c ARM 37 32 50 74 II _ 97 11 0 BAGGAGE 121 134 OPTIONAL SEATING Figure 6 3 Loading Arrangements C G ARM ttj sm ottjttj C HO Q j 1 I r H jO ttj Z Z m jtJj L HL m jZ o ttj 37 W 32 50 74 II _ 97 BAGGAGE A 0 0 o tj 0 ttjO 0 L ttj CD jm um co Z...

Page 111: ...TH I HEIGHT I BOTTOM FRONT HEIGHT REAR CABIN DOOR I 32 BAGGAGE DOOR 15 I 36 I 41 I 1514 22 38 1 20 1 WIDTH LWR WINDOW L1NE CABIN FLOOR CABIN WIDTH MEASUREMENTS r REAR DOORPOST BULKHEAD r __ i EJ 1 TIE DO W N RIN G 5 8 r 42 36 I I CABIN STATIONS 0 C G ARMS I I I 10 20 30 40 50 60 I 70 80 90 100 110 120 130 65 3 Figure 6 4 Internal Cabin Dimensions 1 October 1978 6 9 ...

Page 112: ...0 25 2 5 8aggage Area A or Passengeron Child s Seat Station 82 to 110 120 l bs Maximum 120 11 6 6 Baggage Aft Area 8 Station 110 to 134 80 Lbs Max imum 72 8 7 7 RAMP WEIGHT AND MOMENT 3112 138 2 2 PB I t Ii j 8 Fuel allowance for engine start ta xi and runup 12 6 2 cb 9 TAKEOFF WEIGHT AND MOMENT f 3l S qq 7J Subtract step 8 from step 7 3100 137 6 10 Locate this point 3100 at 137 6 on the Center of...

Page 113: ... ON CHILD S SEAT 75 7j V 120 LBS MAX AFT BAGGAGE AREA B 80 LBS MAX I 5 15 i I 10 20 25 30 LOAD MOMENT l000 POUND INCHES 0 NOTES Line repnsenting adjustable seats shows pi lot and front seat passenger center of gravity on adjustable seats positioned for an average occupant Refer to the Loading Arrangements diagram for forward and aft limits of occupant C G range Figure 6 6 Loading Graph 400 250 225...

Page 114: ... I I I II I I 1111i l I I I I 1I II I I I II I I III 1I I I 1I I I II I Il l I I II II I I I I I I I I II I I II I 1I I II I I I II I I 11 1100 2400 fil 230011 II 1II 111II 1 11II 1HII i 1III 11II 11II 11111111111 111I11 II 11111111111 11I1 1II III 1III ill tt II U i 1lii l0oo 0 J 220011 I I 1II II III II 1111I1 II II III I I III I 1III I I III II III IlCIlll I III I I III I 1111 I II II II 1II II...

Page 115: ...0 _ U 2800 c iii a 0 1250 5 2700 J 0 iji 1200 I 2600 C o W W 1150 3 2500 w z z 1100 i 0 J 2400 a Q il 2300 1050 l 0 c c 9 0 CENTER OF GRAVITY J 2200 1000 LIMITS 2100 950 c 1111111111111111111111111111111111 1111111111111111111111111111111111111111 i c r 01 8 8 0 AIRPLANE C G LOCATION INCHES AFT OF DATUM STA O O t Z a p I o Qz s Ultrl lJ Figure 6 8 Center of Gravity Limits 8 c ...

Page 116: ......

Page 117: ...ndard equipment items 0 optional equipment items replacing required or standard items A optional equipment items which are in addition to required or standard items A reference drawing column provides the drawing number for the item NOTE If additional equipment is to be installed it must be done in accordance with the reference drawing accessory kit instruc tions or a separate FAA approval Columns...

Page 118: ...R ASSY JuME A SSY BULKHEAD ASSY TURBOCHAR ER ASSEMBLY TUR80CHAR ER WASTEGATE ASSEMBLY TURBUCHAR ER OVERBOOST RELIEF VALVE VACUUM SYSTEM ENGI NE DR IVEN VACUUM PUMP FILTER ASSEMBLY PRHH NG SYS 4 CYL Oil QUICK DRAIN VALVE B LANDI NG GEAR ACCESSOR IES REF DRAWING 2250065 D6LN 2031 TYPE HA 6 MHB 4010 C294510 0901 C611503 0102 10614A C294506 0102 C161 008 0 108 C161031 0111 2250003 1750050 1 0752637 16...

Page 119: ... 6 5 3 1 1 1 9 22 8 23 2 24 8 0 4 3 1 4 1 3 3 0 3 EG 0 5 0 4 7 2 7 2 7 2 7 2 7 2 7 2 7 2 7 2 7 2 58 0 4 5 4 5 4 5 0 4 2 5 217 7 221 0 216 0 26 5 17 5 16 5 22 5 61 7 1 2 208 6 253 0 253 0 212 0 44 4 44 4 42 0 BATTERY 24 VOLT STANDARD DUTY BATTERY 24 VOLT MANIFOLD STANDAD DUTY BATTERY 24 VOLT HEAVY DUTY ALTERNATOR CONTROL UNIT WITH HIGH AND LO Vl lTAGE SENSING GROUND SERVICE PLUG RECEPTACLE HEC TRIC...

Page 120: ... 2 17 1 20 5 0 3 17 0 13 1 14 0 14 6 11 5 13 4 13 4 14 6 13 4 1 8 1 4 INDICATOR AIRSPEED INDICATOR f TRUE A RSPEED NET CHANGEI STATIC AL ERNATE AIR SOURCE ALTIMETER SENSI TIVE ALTlNETER SENSITIVE FEET f MILLIBARS ALTIMETER SENSITIVE 20 FT MARKINGS ALTIMETER INSTL SECOND UNIT ENCUDING ALTU1ETER INCHES HG REQUIRES RELOCATING STD ALTIMETERl ENCODING ALTIMETER FEET AND MILLIBARS REQUIRES RELOCATING ST...

Page 121: ...0 0 2 0 9 0 1 0 9 0 7 1 3 1 3 1 3 1 0 1 0 15 l J 28 5 13 8 16 9 15 0 15 0 15 0 15 4 44 0 41 5 44 0 41 5 80 5 103 5 104 4 101 1 37 0 37 0 92 0 37 0 74 5 74 5 62 3 62 3 47 0 45 5 62 3 98 0 140 7 143 6 143 6 S r AuJUSTAdLE FORE AFT PILOT St Tt ARTICULATING VERT ADJ PILOT SI T ADJUSTAt3LE FORE AFT CO PILOT SE I ARTICULATING VERT ADJ CO PILOT SL T 2NJ ROW BE NCH SE T INSTALLATION CHILDS StAT ASSY FOLDA...

Page 122: ...TIE DOWN NET CONTROLS INSTALLATION DUAL lCD PILOT CONTROL WiEEL ALL PURPOSE PILOT ONLY INCLUDES MIC SWITCH AND PANEL MOUNTED AUXIlLARY MIC JACK HEATING SYSTEM CABIN CARBURETOR AIR F PLACARD S WARtH NGS s MANUALS C166005 1 1 1201124 2 3 0 1 1215073 1 0 9 1215073 1 0 9 0701024 1 1 0 1515151 0 1 1215042 1 0 5 0760101 4 6 1 1260243 13 5 NEGL NEGL NEGL 0 3 EGL 1 3 1 0 1 5 0 1 7 1 0 4 2 7 1 6 13 0 12 1 ...

Page 123: ...608 0 3 96 2 H01 A 2 CESSNA 400 ADF WITH 8FO 3910160 19 8 5 22 0 ADF RECEI VER WI Tli BFO R 446At 43090 1128 3 5 13 0 GUNI OMETER INOI CATOR 1N 346AI 40980 1001 0 9 15 0 ADF lOOP ANTENNA 41000 1000 1 4 40 9 ADF SENSE ANTENNA 0170150 0 3 96 2 MOUNT SOX INSTL ITEMS 2 6 17 0 H04 A l DME INSTl NARCO DME 190 3910166 11 7 2 21 0 TRANSCE IVER OUNT EL Cl3312 403 6 3 11 0 ANTENNA INSTL 3960133 1 0 1 188 0 ...

Page 124: ...t LV PAIOlJA PUWER SUPPLY MOUNT ANTENNA COUPLER CU II0 i I TtNNA COUPLER SUPPORTS ANTEI NA It lS TL i lIKi J CL SNA 400 1ARK E R BE ACON E CEIVER 1 STL REC IVER R 412AI 11 N TENW NSTL CONTROL PANEL I NSTL THESE PARTS INSTALLED IN AUDra PNL 3930182 8 3950136 3910203 3910157 11 42100 0000 36450 0000 46860 2000 3960119 4 3950136 3910195 5 0701107 1 44690 2000 41038 0000 394J252 1 47240 0000 43270 000...

Page 125: ...NDICATOR IN 385M 10UNT WIRI N 1 s MISC ITEMS EMERGENCY LOC ATOR TRANSMITTER TRANSMITTER ASSY O M DMELT 6 l ANTENNA EMERGENCY LOCATOR TRANSMITTER USED IN CANADA Tk ANSMITTER ASSY 0 M OMELT 6 1CI ANTENNA NAV O MAfIC 200A INSTALLATION AF 2 t a CONTROLLER AMPLIFIER TURN COORDINATOR D88 0 1HNET CHff4NGEI wING SeRVO INSTALLATION NAV O MAlIC 300A INSTALLATION AF 395 Al CONTROLLER AMPLIFIER IC 395A JYRO I...

Page 126: ... C 01 1 INSTL KIT lh VHF ANTENNA I NSTL AIHEhiNA COUPLER INSTL CABLE INSTL ANTENNA AIH ADAPTOR I NSTl REMOVED AUF ANTI PREC SENSE ANTENNA FLUSH HOUNTEO CON ANTENNA I LUSH MTD IN LEADING EDGE VERTICAL FIN rlEAJSET MICRUP lONE LIGHT WEIGHT STOWED HEADSET MICRLJP IONE PADDED STOWED CAdI I SPEAKER REQUIRED AS PART OF STALL WARNING SYSI REMOTE TRANSPONDER IDENT SWITCH WIRING 42320 0J28 0700215 4 42660 ...

Page 127: ...ED IND NET CHANGE 1201008 15 0 2 16 5 E d5 A DUAL CONTROLS 0160101 4 6 1 14 1 H01 A l CESSNA 300 ADF R 546E 3910159 20 8 5 22 0 rl16 A 1 CESSNA 300 TRANSPONDER RT359AJ 3910121 28 1 7 p 1 H22 A l fIRST 300 NAY COM RT 385AI 3910183 20 3 0 H28 A l EMERGENC r LOCATOR TRANSMITTER 0410419 23 3 5 134 6 rl31 A l CESSNA ZOOA AUTO PILOT 3910162 24 8 2 58 9 H34 A BASIC AVIONICS KIT 6 2 65 1 J04 A INAV PAC IS...

Page 128: ......

Page 129: ...Pump 7 12 Landing Gear Warning System 7 13 Baggage Compartment 7 13 Seats 7 13 Seat Belts And Shoulder Harnesses 7 14 Seat Belts 7 15 Shoulder Harnesses 7 15 Integrated Seat Belt Shoulder Harnesses With Inertia Reels 7 15 Entrance Doors And Cabin Windows 7 17 Control Locks 7 18 Engine 7 18 Engine Controls 7 19 Engine Instruments 7 19 New Engine Break In And Operation 7 21 Engine Oil System 7 21 Ig...

Page 130: ... 37 Exterior Lighting 7 37 Interior Lighting 7 37 Cabin Heating Ventilating And Defrosting System 7 39 Pitot Static System And Instruments 7 41 Airspeed Indicator 7 42 Rate Of Climb Indicator 7 42 Altimeter 7 42 Vacuum System And Instruments 7 42 Attitude Indicator 7 44 Directional Indicator 7 44 Suction Gage 7 44 Stall Warning System 7 44 Avionics Support Equipment 7 45 Audio Control Panel 7 45 T...

Page 131: ...e wheel The externally braced wings containing the fuel tanks are con structed of a front and rear spar with formed sheet metal ribs doublers and stringers The entire structure is covered with aluminum skin The front spars are equipped with wing to fuselage and wing to strut attach fit tings The aft spars are equipped with wing to fuselage attach fittings and are partial span spars Conventional hi...

Page 132: ...SECTION 7 AIRPLANE SYSTEMS DESCRIPTIONS CESSNA MODELTR182 AILERON CONTROL SYSTEM RUDDER AND RUDDER TRIM CONTROL SYSTEMS Figure 7 1 Flight Control and Trim Systems Sheet 1 of 2 7 4 1 October 1978 ...

Page 133: ...CESSNA MODELTR182 SECTION 7 AIRPLANE SYSTEMS DESCRIPTIONS ELEVATOR CONTROL SYSTEM ELEVATOR TRIM CONTROL SYSTEM Figure 7 1 Flight Control and Trim Systems Sheet 2 of 2 1 October 1978 7 i1 ...

Page 134: ...SECTION 7 AIRPLANE SYSTEMS DESCRIPTIONS CESSNA MODEL TR182 Ftgtrre 7 2 Instrument Panel Sheet 1 of 2 7 6 1 October 1978 ...

Page 135: ...ophone e Lights and Switches 43 Fuel Selector Light S 15 Autopilot Control Unit 44 Fuel Selector Valve Handle d d D 16 Transponder 45 Elevator Trim Control Wheel and t J e 17 Audio Control Panel Position Indicator d 18 Radios 46 Carburetor Heat Control Knob Z i trl J 19 Area Navigation Radio 47 Landing Gear Lever D 20 Manifold Pressu re Gage 48 Landing Gear Position rr J m 21 Fuel Quantity Indicat...

Page 136: ...ble for the rudder Ibrake pedals They consist of a rudder pedal face two spacers and two spring clips To install an exten sion place the clip on the bottom of the extension under the bottom of the rudder pedal and snap the top clip over the top of the rudder pedal Check that the extension is firmly in place To remove the extensions reverse the above procedures TRIM SYSTEMS Manually operated rudder...

Page 137: ...rol throttle propeller control and mixture control The right side of the panel contains the wing flap switch and position indicator cabin heat cabin air and defroster control knobs and the cigar lighter A pedestal extending from the switch and control panel to the floorboard contains the elevator and rudder trim control wheels cowl flap control lever and microphone lJmc l et The tuel selector valv...

Page 138: ...o obtain a minimum radius turn during ground handling the airplane may be rotated around either main landing gear by pressing down on a tail cone bulkhead just forward of the horizontal stabilizer to raise the nose wheel off the ground WING FLAP SYSTEM The single slot type wing flaps see figure 7 3 are extended or retracted by positioning the wing flap switch lever on the right side of the switch ...

Page 139: ...em fluid level may be checked by utilizing the dip stick filler cap located on the top right side of the power pack adjacent to the motor mountirig flange The syatem should be checked at 25 hour intervals and anytime a hydraulic failure in the system requires the use of the emergency hand pump to extend the landing gear If the fluid level is at or below the ADD line on the dipstick hydraulic fluid...

Page 140: ... normal cycle the gear stops full up or locks down limit switches close and the indicator light comes on amber for up and green for down indicating completion of the cycle After indicator light illumination the power pack will continue to run until the fluid pressure reaches 1500PSI opens the pressure switch and turns the power pack off Whenever fluid pressure in the system drops below 1000PSI the...

Page 141: ...acted BAGGAGE COMPARTMENT The baggage compartment consists of the area from the back of the rear passenger seats to the aft cabin bulkhead A baggage shelf above the wheel well extends aft from the aft cabin bulkhead Access to the baggage compartment and the shelf is gained through a lockable baggage door on the left side of the airplane or from within the airplane cabin A baggage net with six tie ...

Page 142: ...y adjustable seat backs The seat backs are adjusted by raising levers below the respective seat backs at the outboard ends of the seat cushion After adjusting the seat back to the desired position it is spring loaded to the vertical position release the lever and check that the seat back is locked in place The seat backs will also fold full forward A child s seat may be installed aft of the rear p...

Page 143: ... behind the sheath When rear seat shoulder harnesses are furnished they are attached adjacent to the lower corners of the aft side windows Each rear seat harness is stowed behind a stowage sheath above an aft side window No harness is available for the child s seat To use a front or rear seat shoulder harness fasten and adjust the seat belt first Lengthen the harness as required by pulling on the ...

Page 144: ...ESS l Pull down to tighten f fN AN SS Snap onto retaining stud on seat belt link to attach harness SEAT BELT LINK HALF AND SHOULDER HARNESS RETAlN1NG STUD FREE END OF SEAT BELT Pull to tighten CESSNA MODEL TR182 PilOT S SEAT SHOWN l SEAT BElT SHOULDER HARNESS WITH INERTIA REEL Figure 7 4 Seat Belts and Shoulder Harnesses 7 16 1 October 1978 ...

Page 145: ...s The doors incorporate a recessed exterior door handle a conventional interior door handle a key operated door lock left door only a door stop mechanism and an openable window in the left door An openable right door window is also available To open the doors from outside the airplane utilize the recessed door handle near the aft edge of each door Depress the forward end of the handle to rotate it...

Page 146: ... a red metal flag attached to it The flag is labeled CONTROL LOCK REMOVE BEFORE STARTING ENGINE To install the control lock align the hole in the top of the pilot s control wheel shaft with the hole in the top of the shaft collar on the instrument panel and insert the rod into the aligned holes Installation of the lock will secure the ailerons in a neutral position and the elevators in a slightly ...

Page 147: ...ly 12inches of manifold pressure The turbocharger has the capability of producing manifold pressures in excess of 31 inches Hg red line Therefore in most cases full waste gate closed full throttle will not be necessary to maintain maximum allowable manifold pressure Close attention must be paid to manifold pressures during high power operations especially during cold day conditions at low altitude...

Page 148: ...es both engine and propeller speed An hour meter below the center of the tachometer dial records elapsed engine time in hours and tenths Instrument markings include a normal operating range green arc of 2100 to 2400 RPM and a maximum red line of 2400 RPM The manifold pressure gage is located on the right side of the instru ment panel above the tachometer The gage is direct reading and indicates in...

Page 149: ...ing to Specification No MIL 1 00082 ENGINE Oil SYSTEM Oil for engine lubrication propeller governor operation and turbo charger bearing lubrication is supplied from a sump on the bottom of the engine The capacity of the sump is 8 quarts one additional quart is contained in the engine oil filter Oil is drawn from the sump through a filter screen on the end of a pickup tube to the engine driven oil ...

Page 150: ...ch is labeled clock wise OFF R L BOTH and START The engine should be operated on both magnetos BOTH position except for magneto checks The Rand L positions are for checking purposes and emergency use only When the switch is rotated to the spring loaded START position with the master switch in the ON position the starter contactor is energized and the starter will crank the engine When the switch i...

Page 151: ...ne driven fuel pump and or auxiliary fuel pump In the carburetor fuel is atomized proportionally mixed with compressed air and delivered to the cylinders through intake manifold tubes The proportion of atomized fuel to air may be controlled within limits by the mixture control located on the lower center portion of the instrument panel For easy starting in cold weather the engine is equipped with ...

Page 152: ...low the induction air as it enters the air filter and passes through the engine until it is expelled as exhaust gasses 1 Air from the slipstream enters the induction system through a recessed opening in the left engine cowl passes through a filter enters a carburetor heat airbox and is then ducted into the compressor side of the turbocharger 2 The compressed air is then forced through the carburet...

Page 153: ...URETOR HEAT CONTROL OFF POSITION ON POSITION CAUTION FULL WASTE GATE CLOSED CONTROL POSITON WILL NOT BE NECESSARY TO MAINTAIN MAXIMUM ALLOWABLE MANIFOLD PRESSURE 31 IN HG l WITH A POSSIBLE EXCEPTION DURING HOT DAY CONDITIONS AT HIGH ALTITUDE THROTTLE I THROTTLE CONTROL FINAL 1 2 CONTROL TRAVEL WASTE GATE PORTION OF CONTROL INITIAL 1 2 CONTROL TRAVEL THROTTLE PORTION OF CONTROL Figure 7 5 Turbochar...

Page 154: ...d pressure of 31 in Hg Since the waste gate is manually controlled the throttle control will have to be advanced as necessary to maintain the maximum 31in Hg or cruise 25 in Hg manifold pressure during climb MANIFOLD PRESSURE VARIATION WITH AIRSPEED Whenthe compressor side ofthe turbocharger is provided with a larger quantity of air at the intake as with an increase in airspeed the manifold pressu...

Page 155: ...piston twists the blades toward high pitch low RPM When oil pressure to the piston in the propeller hub is relieved centrifugal force assisted by an internal spring twists the blades toward low pitch high RPM A control knob on the center area of the switch and control panel is used to set the propeller and control engine RPM as desired for various flight conditions The knob is labeled PROPELLER PU...

Page 156: ...UXILIARY FUEL PUMP AUXILIARY D FUEL PUMP SWITCH ENGINE DRIVEN FUEL PUMP FUEL PRESSURE GAGE THROTTLE CONTROL 0_ MIXTURE CONTROL CARBURETOR CODE TO ENSURE MAXIMUM FUEL CAPACITY WHEN REFUELING AND MINIMIZE CROSS FEEDING WHEN PARKEDONA SLOPING SURFACE PLACE THE FUEL SELECTOR VALVE IN EITHER LEFT OR RIGHT POSITION TO ENGINE VENT I i FUEL SUPPLY MECHANICAL LINKAGE ELECTRICAL CONNECTION Figure 7 6 Fuel S...

Page 157: ...ons usable in all flight conditions Fuel system venting is essential to system operation Complete blockage of the venting sy stern will result in a decreasing fuel flow and eventual engine stoppage Venting consists of an interconnecting vent line between the tanks and check valve equipped overboard vents in each tank The overboard vents protrude from the bottom surfaces of the wings behind the win...

Page 158: ...ncoor dinated flight such as slips or skids can uncover the fuel tank outlets causing fuel starvation and engine stoppage Therefore with low fuel reserves do not allow the airplane to remain in uncoordinated flight for periods in excess of one minute NOTE When the fuel selector valve handle is in the BOTH position in cruising flight unequal fuel flow from each tank may occur if the wings are not m...

Page 159: ...etract the gear The hydraulic system normally operates at 1000 PSI to i500 P8I and is protected by relief valves which prevent high pressure damage to the pump and other components in the system The electrical portion of the power pack is protected by a 30 amp push pull type circuit breaker switch labeled GEAR PUMP on the left switch and control panel The hydraulic pOTJVer is turned on by a pressu...

Page 160: ...SE GEAR UP SWITCH DOWN SWITCH t EXTEND HANDLE IJ PUMP VERTICALLY Q PRESSURE SWITCH SUMP VENT HYDRAULIC POWER PACK EMERGENCY HAND PUMP CODE PRESSURE c J VENT c z J RETURN g u g K I J MAIN GEAR CONDITION AIR PLANE ON GROUND ENGINE AND ELECTRICAL POWER OFF Figure 7 8 Hydraulic System Pressure Switch 1000 PSI ON 1500 PSI OFF t w t r l do 0 3 t t O z Z t r l l c W 3 t r l s u tJ t r l W o d 0 3 o z u s...

Page 161: ... in need of immediate attention If during taxi or landing roll braking action decreases let up on the pedals and then re apply the brakes with heavy pressure 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 offset the good brake ELECTRICA...

Page 162: ...82 TO ALT REG CIRCUIT BR AKER GROUND SERVICE PLUG RECEPTACLE j INST LIGHTS CIRCUIT BREAKER MAGNETOS CO _ 0 CIRCUlTBREAKERIPUSHTO RfSETi FUSE DIOOEt t RESiSTOR it CAPACITQR N01SE FIU R 2 CIRCUIT BREAKtR f TCH I Figure 7 9 Electrical System 7 34 1 October 1978 ...

Page 163: ...avionics circuit breaker panel and is ON in the up position and OFF in the down position With the switch in the OFF position no electrical power will be applied to the avionics equipment regardless of the position ofthe master switch or the individual equipment switches The avionics power switch also functions as a circuit breaker If an electrical malfunction should occur and cause the circuit bre...

Page 164: ...ctrical 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 The warning light may be tested by turning on the landing lights and momentarily turning of the ALT portion of the master switch while leaving the BAT portion ...

Page 165: ... left rear door post All exterior lights except the courtesy lights are operated by rocker type switches on the left switch and control panel The switches are ON in the up position and off in the down position The flashing beacon should not be used when flying through clouds or overcast the flashing light reflected from water droplets or particles in the atmosphere particularly at night can produc...

Page 166: ...ghts and electroluminescent lights are turned off for day light operation by rotating the FLOOD POST and EL PANEL knobs full counterclockwise The control pedestal has two post lights and if the airplane is equipped with oxygen the overhead console is illuminated by post lights Pedestal and console light intensity is controlled by the knob labeled ENG RADIO on the right dimming rheostat Map lightin...

Page 167: ...ocks to permit intermediate settings NOTE For improved partial heating on mild days pull out the CABIN AIR knob slightly when the CABINHEAT knob is out This action increases the airflow through the systenl increasing efficiency and blends cool outside air with the exhaust manifold heated air thus eliminating the possibil ity of overheating the system ducting Front cabin heat and ventilating air is...

Page 168: ...NTROL CABIN HEAT _ I CONTROL ff t ff DEFROSTER CONTROL VENTILATORS AlRFLO N ADJUSTMENT L WHEELS CP 7 ADJUSTABLE AIR OUTLETS CODE o RAM AIR FLOW 7 VENTILATING AIR HEATEDAIR BLENDED AIR MECHANICAL CONNECTION Figure 7 10 Cabin Heating Ventilating and Defrosting System 7 40 1 October 19 78 ...

Page 169: ...on the lower surface of the left wing two external static ports Onthe left and right sides of the forward fuselage and the associated plumbing necessary to connect the instruments to the sources The heated pitot system if installed consists of a heating element in the pitot tube a rocker switch labeled PITOT HEAT and a lO amp push to reset circuit breaker on the left side of the ewitoh and control...

Page 170: ... read the true airspeed shown on the rotatable ring by the indicator pointer For best accuracy the indicated airspeed should be corrected to calibrated airspeed by referring to the Airspeed Calibration chart in Section 5 Knowing the calibrated airspeed read true airspeed on the ring opposite the calibrated airspeed RATE OF CLIMB INDICATOR The rate of climb indicator depicts airplane rate of climb ...

Page 171: ...N 7 AIRPLANE SYSTEMS DESCRIPTIONS CODE c J INLET AIR CI J VACUUM DISCHARGE AI R OVERBOARD VENT LINE I VACUUM PUMP VACUUM RELIEF VALVE ATTITUDE SUCTION GAGE VACUUM SYSTEM AIR FILTER Figure 7 11 Vacuum System 1 October 1978 7 43 ...

Page 172: ...ssion SUCTION GAGE The suction gage located below the flight instruments is calibrated in inches of mercury and indicates suction available for operation of the attitude and directional indicators The desired suction range is 4 6to 5 4 inches of mercury A suction reading below this range may indicate a system malfunction or improper adjustment and in this case the indica tors should not be conside...

Page 173: ...es to use To select a transmitter rotate the switch to the number corresponding to that transmitter The numbers 1 2 and 3 above the switch correspond to the top second and third transceivers in the avionics stack The audio amplifier in the NAV COMradio is required for speaker and transmitter operation The amplifier is automatically selected along with the transmitter by the transmitter selector sw...

Page 174: ...CTION AUTOMATIC AUDIO SELECTOR SWITCH AUDIO SELECTOR SWITCH TYPICAL As illustrated the number 1 transmitter is selected the AUTO selector switch is in the OFF position the number 1 NAV COM receiver is in the PHONE position and the number 1 ADF is in the SPEAKE R position With the switches set as shown the pilot will transmit on the number 1 transmitter and hear the number 1 NAV COM receiver on a h...

Page 175: ...smitting Head phone sidetone level adjustment to accommodate the use of the different type headsets is accomplished by adjusting potentiometers in the NAV COMradios AUDIO SELECTOR SWITCHES The audio selector switches labeled NAV COM1 2 and 3 and ADF 1 and 2 allow the pilot to initially pre tune all NAV COM and ADF receivers and then individually select and listen to any receiver or combination of ...

Page 176: ...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 left side of the instrument panel Audio to all three headsets is controlled by the individual audio selector switches and adjusted for volume level b y using the selected receiver volume contr...

Page 177: ...ter severe precipitation static conditions which might cause the loss of radio signals even with static dischargers installed Whenever possible avoid known severe precipita tion areas to prevent loss of dependable radio signals If avoidance is impractical minimize airspeed and anticipate temporary loss of radio signals while in these areas 1 October 1978 7 49 7 50blank ...

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Page 179: ...ve Care Cessna Customer Care Program Pilot Conducted Preventive Maintenance Alterations or Repairs Ground Handling Towing Parking Tie Down Jacking Leveling Flyable Storage Servicing Engine Oil Fuel Landing Gear Cleaning and Care Windshield Windows Painted Surfaces Propeller Care I I Landing Gear Care Engine Care Interior Care 8 3 8 3 8 3 8 3 8 4 8 5 8 5 8 6 8 6 8 7 8 7 8 8 8 8 8 8 8 8 8 8 8 9 8 9 ...

Page 180: ......

Page 181: ...mber PC and Type Certificate Number TC can be found on the Identification Plate located on the left forward doorpost Located adjacent to the Identification Plate is a Finish and Trim Plate which contains a code describing the interior color scheme and exterior paint combination ofthe airplane The code may be used in conjunction with an applicable Parts Catalog if finish and trim information is nee...

Page 182: ...atalog covering all available items many of which he keeps on hand He will be happy to place an order for any item which is not in stock NOTE A Pilot s Operating Handbook and FAA Approved Air plane Flight Manual which is lost or destroyed may be replaced by contacting your Cessna Dealer or writing directly to the Customer Services Department Cessna Aircraft Company Wichita Kansas An affidavit cont...

Page 183: ...ations of other nations may require other documents and data owners of airplanes not registered in the United States should check with their own aviation officials to determine their individual requirements Cessna recommends that these items plus the Pilot s Checklists Power Computer Customer Care Program book and Customer Care Card be carried in the airplane at all times AIRPLANE INSPECTION PERIO...

Page 184: ...time Under this program your airplane is inspected and maintained in four operations at 50 hour intervals during a 200 hour period The operations are recycled each 200 hours and are recorded in a specially provided Aircraft Inspection Log as each operation is conducted The Cessna Aircraft Company recommends Progressive Care for airplanes that are being flown 200hours ormore per year and the 100 ho...

Page 185: ...e 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 FAR Part 43 to perform limited maintenance on his airplane Refer to FAR Part 43 fo...

Page 186: ...n accumu lated moisture may freeze the brakes or when the brakes are overheated Close the cowl flaps install the control wheel lock and chock the wheels In severe weather and high wind conditions tie the airplane down as outlined in the following paragraph TIE DOWN Proper tie down procedure is the best precaution against damage to the parked airplane by gusty or strong winds To tie down the airpla...

Page 187: ... ofthe airplane LEVELING Longitudinal leveling of the airplane is accomplished by placing a level on the leveling screws located on the left side of the tailcone Deflate the nose tire and or lower or raise the nose strut to properly center the bubble in the level Corresponding points on both upper door sills may be used to level the airplane laterally FLYABLE STORAGE Airplanes placed in non operat...

Page 188: ...r testing at special intervals Sinmr Ge5 ma Dealers oonduct all service tnspectlon and test proce dures in accordance with applicable Service Manuals it is recommended that you contact your Cessna Dealer concerning these requirements and begin scheduling your airplane for service at the recommended intervals Cessna Progressive Care ensures that these requirements are accomp lished at the required ...

Page 189: ... sump with straight mineral oil and use until a total of 50 hours has accumulated or oil consumption has stabilized then change to dispersant oil Drain the engine oil sump and change the filter each 50 hours thereafter The oil change interval may be extended to iOO hour intervals providing the oil filter is changed at 50 hour intervals Change engine oil at least every 6 months even though less tha...

Page 190: ...dle in either LEFT or RIGHT position LANDING GEAR NOSE WHEEL TIRE PRESSURE 50 PSI on 5 00 5 6 Ply Rated Tire MAIN WHEEL TIRE PRESSURE 68 PSI on 15 x 6 00 6 6 Ply Rated Tires NOSE GEAR SHOCK STRUT Keep filled with MIL H 5606 hydraulic fluid and inflated with air to 55 PSI with no load on strut HYDRAULIC FLUID RESERVOIR Check every 25 hours and service with MIL H 5606 hydraulic fluid CLEANING AND CA...

Page 191: ... to delivery of the airplane In the event that polishing or buffing is required within the curing period it is recommended that the work be done by someone experienced in handling uncured paint Any Cessna Dealer can accomplish this work Generally the painted surfaces can be kept bright by washing with water and mild soap followed by a rinse with water and drying with cloths or a oh a mois Harsh or...

Page 192: ...ng gear ENGINE CARE The engine may be cleaned with Stoddard solvent or equivalent then dried thoroughly CAUTION Particular care should be given to electrical equipment before cleaning Cleaning fluids should not be allowed to enter magnetos starter alternator and the like Protect these components before saturating the engine with sol vents All other openings should also be covered before cleaning t...

Page 193: ... your airplane is equipped with leather seating cleaning of the seats is accomplished using a soft cloth or sponge dipped in mild soap suds The soap suds used sparingly will remove traces of dirt and grease The soap should be removed with a clean damp cloth The plastic trim headliner instrument panel and control knobs need only be wiped offwith a damp cloth Oil and grease onthe control wheel and c...

Page 194: ......

Page 195: ...pe AF 295B 300 ADF Type R 546E 300 Nav Oom Type RT 385A I I I I I 300 Nav Com Type RT 385A With 400 Area Navigation System Type RN 478A 300A Navomatic Autopilot Type AF 395A 400 ADF Type R 446A 400 Area Navigation System Type RN 478A 400 DME Type R 476A 400 Glide Slope Type R 443B 400 Marker Beacon Type R 402A 400 Na v Com Type RT 485A 400 Nav Com Type RT 485A With 400 Area Navigation System Type ...

Page 196: ... the Table of Contents the supplements are classified under the headings of general and avionics and are arranged alphabetically and numerically to make it easier to locate 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 Limitations contained in the following supp...

Page 197: ...n type switches directly below the display control all time keeping functions These control functions are summarized in figures 2 and 3 The digital display features an internal light back light to ensure good visibility under low cabin lighting conditions or at night The intensity ofthe back light is controlled by the ENG RADIOlights rheostat In addition the display incorporates a test function se...

Page 198: ...h shown to the right of the colon The display automatically returns to the clock mode after approximately 1 5 seconds However if the RH button is pressed continuously longer than approximately two seconds the display will return from the date to the clock mode with the activity indicator colon blinking altered to show continuously or be blanked completely from the display Should this occur simply ...

Page 199: ... 2 Clock Mode Figure 3 Timer Mode SETTING CORRECT DATE AND TIME The correct date and time are set while in the clock mode using the LH and RH push buttons as follows press the LH button once to cause the date to appear with the month flashing Press the RH button to cause the month to advance at one per second holding button or one per push until the correct month appears Push the LH button again t...

Page 200: ...t altering the minutes timing TIMER OPERATION The completely independent 24 hour elapsed timer see figure 3 is operated as follows press the center MODE push button until the timer mode indicator appears Reset the display to zero by pressing the LH button Begin timing an event by pressing the RH button The timer will begin counting in minutes and seconds and the colon activity indicator will blink...

Page 201: ...n the nose up direction When the switch is released it automatically returns to the center off position and elevator trim tab motion stops The disengage switch labeled ELEC TRIM DISENGAGE disables the system when placed in the DISENGAGE aft position A servo unit which includes a motor and chain driven solenoid operated clutch actuates the trim tab to the selected position When the clutch is not en...

Page 202: ...itch ON 2 Elevator Trim Disengage Switch ON 3 Trim Switch ACTUATE as desired 4 Elevator Trim Position Indicator CHECK NOTE To check the operation of the disengage switch actuate the elevator trim switch with the disengage switch in the DISENGAGE aft position Observe that the manual trim wheel and indicator do not rotate when the elevator trim switch is activated SECTION 5 PERFORMANCE There is no c...

Page 203: ...should be turned off If main tenance is required on the avionics equipment it is advisable to utilize a battery cart external power source to prevent damage to the avionics equipment by transient voltage Do not crank or start the engine with the avionics power switch turned on The battery and external power circuits have been designed to com pletely eliminate the need to jumper across the battery ...

Page 204: ... no change to the airplane emergency procedures when the ground service plug receptacle is installed SECTION 4 NORMAL PROCEDURES Just before connecting an external power source generator type or battery cart the avionics power switch should be turned off and the master switch turned on WARNING When turning on the master switch using an external power source or pulling the propeller through by hand...

Page 205: ...rnal power source will flowonly if the ground service plug is correctly connected to the airplane Ifthe plug is accidentally connected backwards no power will flow to the electrical system thereby preventing any damage to electrical equipment SECTION 5 PERFORMANCE There is no change to the airplane performance when the ground service plug receptacle is installed 1 October 1978 3 4 blank ...

Page 206: ......

Page 207: ...e provided for the passengers All masks are the partial rebreathing type equipped with vinyl plastic hoses and flow indicators NOTE The hose provided for the pilot is of a higher flow rate than those for the passengers it is color coded with an orange band adjacent to the plug in fitting The passenger hoses are color coded with a green band If the airplane owner prefers he may provide higher flow ...

Page 208: ...gen cylinder when fully charged contains approximately 48 cubic feet of oxygen under a pressure of 1800 psi at 70DF 21DC Filling pressures will vary however due to the ambient temperature in the filling area and because of the temperature rise resulting from compression of the oxygen Because of this merely filling to 1800 psi will not result in a properly filled cylinder Fill to the pressures indi...

Page 209: ... d oxygen line fitting and passengers with green c o l or c o d e d line fittings Figure 2 Oxygen Duration Chart For FAA requirements concerning supplemental oxygen refer to FAR 91 32 Supplemental oxygen should be used by all occupants when cruising above 12 500 feet As described in the Cessna booklet Man At Altitude it is often advisable to use oxygen at altitudes lower than 12 500 feet under con...

Page 210: ...t only for nearly 6 hours and 15minutes The same pressure will sustain the pilot and three passengers for approximately 2 hours and 30 minutes NOTE The Oxygen Duration Chart is based on a standard config uration oxygen system having one orange color coded hose assembly for the pilot and green color coded hoses for the passengers If orange color coded hoses are provided for pilot and passengers it ...

Page 211: ...Adjust mask to face and adjust metallic nose strap for snug mask fit 2 Delivery Hose PLUG INTO OUTLET nearest to the seat you are occupying NOTE When the oxygen system is turned on oxygen will flow continuously at the proper rate of flow for any altitude without any manual adjustments 3 OXYg n 9upply Control Knob ON 4 Face Mask Hose Flow Indicator CHECK Oxygen is flowing if the indicator is being ...

Page 212: ......

Page 213: ...BE LIGHTS and a 5 amp push to reset circuit breaker on the left side of the switch and control panel and associated wiring 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 PROCEDURES There is no change to the airplane emergency procedures when strobe lights are installed SECT...

Page 214: ...STROBE LIGHT SYSTEM MODELTR182 PILOT S OPERATING HANDBOOK SUPPLEMENT SECTION 5 PERFORMANCE The installation of strobe lights will result in a minor reduction in cruise performance 2 1 October 1978 ...

Page 215: ...y or by a remote NAV set When coupled with a remote NAV set the MHz digits will be covered over by a remote REM flag and the DME will utilize the frequency set by the NAV set s channeling knobs When the DME is not coupled with a remote NAV set the DME will reflect the channel selected on the DME unit The transmitter operates in the frequency range of 1041to 1150MHz and is paired with 108to 117 95M...

Page 216: ... MILES in R Nav mode 3 REMOTE CHANNELING SELECTOR Two position selector In the first posi tion the DME will utilize the frequency set by the DME channeling knobs In the second position the MHz digits will utilize the frequency set by the NAV 1unit s channeling knobs 4 WHOLE MEGAHERTZ SELECTOR KNOB Selects operating frequency in 1 MHz steps between 108 and 117 MHz 5 FREQUENCY INDICATOR Shows operat...

Page 217: ...r KNOTS position The decimal point along with 188 8 will light in the MILES mode When the control is released and had the DME been channeled to a nearby station the distance to that station will appear If the station channeled was not in range a bar readout will be seen or 10 MODE SELECTOR SWITCH OFF Turns the DME OFF MILES Allows a digital readout to appear in the window which represents slant ra...

Page 218: ...88 8 in function window 4 DIM Control ADJUST 5 IDENT CONTROL ADJUST audio output in speaker 6 Mode Selector Functions MILES Position Distance to Station is slant range in nauti cal miles MIN Position Time to Station when flying directly to sta tion KNOTS Position Ground Speed in knots when flying directly to or from station CAUTION After the DME 190has been turned OFF do not turn it on again for 5...

Page 219: ...00feet The ELT supplied in domestic aircraft transmits on both distress frequen cies simultaneously at 75mw rated power output for 50continuous hours in the temperature range of 4 F to 131 F 20 Cto 55 C The ELT unit in export aircraft transmits on 121 5MHz at 25mw rated power output for 50 continuous hours in the temperature range of 4 F to 131 F 20 C to 55 C The ELT is readily identified as a bri...

Page 220: ... Removable for access to battery pack 3 ANTENNA RECEPTACLE Connects to antenna mounted on top of tailcone Figure 1 ELT Control Panel 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 If the ELT can be heard transmitting it was activat...

Page 221: ...NORMAL PROCEDURES As long as the function selector switch remains in the AUTO position the ELT automatically activates following an impact of 5g or more over a short period of time Following a lightning strike or an exceptionally hard landing the ELT may activate although no emergency exists To check your ElLT for inadvertent activation select 121 5 MHz on your radio transceiver and listen for an ...

Page 222: ......

Page 223: ... to the waypoint repeatedly to provide continual informa tion on WHICH WAY and HOW FAR to the waypoint The pilot can rn onf tor BEARING and RANGE on RNA V 511 to fly straight line paths to waypoints up to 200 NM distance from the aircraft position Waypoints can be precisely dialed into the thumbwheels to 0 10 and 0 1 NM resolution The RNAV 511 also provides immediate position orientation relative ...

Page 224: ...idual placards 1 Adjacent to panel unit when used with the DME 190 RNAV FOR VFR FLIGHT ONLY TUNE DME NAV 1 TO SAME VORTAC FOR RNAV OPERATION 2 Adjacent to panel unit when used with the 400 DME RNAV FOR VFR FLIGHT ONLY DME MODE SELECTOR ON NAV 1 OR NAV 2 ONLY SECTION 3 EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when this avionic equipment is installed 2 1 October 1...

Page 225: ... ON VJhen pressed again set will be turned OFF and the RNAV ON light will go out The pushbutton lighting is automatically dimmed by the photocell 4 4 PHOTOCELL Senses ambient cockpit light and controls brightness of push but tons 1 3 5 7 and digital displays 2 6 5 VOR DME PUSHBUTTON Provides PRESENT POSITION information as to VOR RADIAL and DME DISTANCE digitally in positions 2 and 6 respectively ...

Page 226: ...TAC is 199 9 NM 9 TEST PUSHBUTTON Press to check proper calibration of RNAV 511 If the computer is properly calibrated the displays 2 6 read the active WPT RADIAL and DISTANCE as dialed into the thumbwheels Test may be performed anytime during or before flight 10 LOCKING SCREW Secures RNAV 511 in dustcover Turn locking screw counterclockwise several turns to release unit from panel 11 RADIAL AND D...

Page 227: ...e and may become unusable within 1 1 1 2 miles of the waypoint Thus the RANGE readout is the primary means of approximating waypoint passage 4 Tracking from a waypoint is not recommended since the pilot would have to fly a reciprocal bearing and make error corrections in the opposite direction from flying to a waypoint DIAGNOSTIC FUNCTIONS All RNAV systems are rendered inoperative under certain co...

Page 228: ...waypoint s from appropriate VOR DME stations 2 VHF Navigation Receiver ON When installed with DME 190 RNAV 511is connected to the Nav 1Rcvr When installed with the 400DME RNAV 511may be connected to either the Nav 1or Nav 2 Rcvr and channeled to the desired VORTAC 3 DME ON OFF Switch ON 4 DME Remote Channeling Selector on DME 190Selector SET to REM position on DME 190 5 DME Mode Selector on 400DME...

Page 229: ... computer 14 VOR DME Pushbutton PRESS at anytime to observe the radial and DME distance from the VORTAC associated with the way point 15 Upon Waypoint Passage CHECK or SELECT next desired waypomt s VORTAC frequency on the selected Nav receiver and then PRESS next WPTPushbutton in and repeat steps 9through 12 to proceed to next waypoint which was dialed in the right set of thumbwheels NOTE Waypoint...

Page 230: ...itial right hand waypoint is passed This procedure can be followed for as many waypoints as necessary providing that the desired Nav receiver is selected and the VORTACfrequency has been re channeled to each VORTAC station SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed 8 1 October 1978 ...

Page 231: ...l Selector Knob determines the operating frequency of the transmitter and receiver The frequencies of operation are shown on the frequency chart adjacent to the channel selector The VOLUME control incorporates the power switch for the trans ceiver Clockwise rotation of the volume control turns the set on and increases the volume of audio The meter on the face of the transceiver indicates transmitt...

Page 232: ...in the frequency chart 3 CHANNEL READOUT WINDOW Displays channel selected in frequency chart 4 SENSITIVITY CONTROL Controls the receiver sensitivity for audio gain 5 ANTENNA TUNING METER Indicates the energy flowing from the transmit ter into the antenna The optimum power transfer is indicated by the maximum meter reading 6 ON OFF VOLUME CONTROL Turns complete set on and controls volume of audio F...

Page 233: ...Frequency Chart SELECT desired operating frequency 5 Channel Selector DIAL in frequency selected in step 4 6 SENSITIVITY Control ROTATE clockwise to maximum posi tion NOTE If receiver becomes overloaded by very strong signals back off SENSITIVITY control until background noise is barely audible NOTE The antenna tuning meter indicates the energy flowing from the airplane s transmitter into the ante...

Page 234: ...ION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation ofan externally mounted antenna or several related external antennas will result in a minor reduction in cruise performance 4 1 October 1978 ...

Page 235: ...termines the operating frequency of the transceiver which has predetermined crystals installed to provide the desired operating frequencies A mode selector control is provided to supply the type of emission required for the channel either sideband AM or telephone for public correspondence An audio knob clarifier knob and squelch knob are provided to assist in audio operation during receive In addi...

Page 236: ... telephone and ship to shore Optional Selects lower sideband operation not legal in U S Canada and most other countries LSB 4 SQUELCH CONTROL Used to adjust signal threshold necessary to activate receiver audio Clockwise rotation increases background noise decreases squelch action counterclockwise rotation decreases background noise 5 CLARIFIER CONTROL Used to clarify single sideband speech during...

Page 237: ...nd may be used Use of lower sideband is prohibited b Only AM transmissions are permitted on frequen cies 2003kHz 2182kHz and 2638kHz The selection of these channels will automatically select the AM mode of transmission 1 XMTR SEL Switch on audio control panel SELECT trans ceiver 2 SPEAKER PHONE or AUTO Switch on audio control panel SELECT desired mode 3 ON AUDIO Control ON allow equipment to warm ...

Page 238: ...ch in either the SPEAKER or PHONE positions b To Receive RELEASE mike button NOTE Voice communications are not available in the LSB mode NOTE Lower sideband LSB mode is not legal in the U S Canada and most other countries 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...

Page 239: ...ios When dual Nav Com radios are installed the HSI is coupled to the number 1NAV COMand a standard 300 or 400 series VOR LOC course deviation indicator is coupled to the number 2 NAV COM This system consists of a Horizontal Situation Indicator HSI Type IG 832C and a remote mounted VOR LOC Converter Type B 445A The indicator is unslaved and course datum is not available When the HSI is installed wi...

Page 240: ...displays glide slope deviations and gives heading reference with respect to magnetic north when compass card is set to agree with compass 2 OMNI BEARING POINTER Indicates selected VOR course or localizer course on compass card 6 The selected VOR radial or localizer heading remains set on the compass card when the compass card 6 is rotated 3 NAV FLAG When flag is in view indicates that the NAV rece...

Page 241: ...6 to agree with magnetic compass The omni bearing pointer 2 heading bug 14 and deviation bar 15 rotate with the GOmptlJBS card 6 NOTE The compass card 6 must be reset periodically to compensate for precessional errors in the gyro 10 COURSE SELECTOR t KNOB When rotated positions omni bearing pointer 2 on the compass card 6 to select desired VOR radial or localizer course 11 GLIDE SLOPE SCALE Indica...

Page 242: ...utopilot to reverse for back course operation 17 BACK COURSE REVERSE SENSE REV SNS LOC 1 OR LOC 2 SELECTOR SWITCH With AP switch ON on 400A or 400B Autopilot control units and either LOC 1 or LOC 2 selected localizer signals to the Cessna 400A or 400B Autopilots will reverse for back course operation With autopilot ON or OFF the course omni deviation bar on the HSI will not reverse but the standar...

Page 243: ...st be set to the inboard front course for both front and back course approaches to retain this pictorial presentation When the HSI system is installed with a Cessna 300A Type AF 395A Cessna 400A Type AF 530A or Cessna 400B Type IF 550A Autopilot a back course indicator light labeled BC is mounted adjacent to the HSI and will illuminate amber when the reverse sense REV SNS switch mounted in the upp...

Page 244: ......

Page 245: ...oordina tor gyro The computer amplifier electronically computes the necessary correction and signals the actuator to move the ailerons to maintain the airplane in the commanded lateral attitude The 200A Navomatic will also capture and track a VOR or localizer course using signals from a VHF navigation receiver The operating controls for the Cessna 200ANavomatic are located on the front panel of th...

Page 246: ...LOT TYPE AF 295B PILOT S OPERATING HANDBOOK SUPPLEMENT NAV 1 NAV 2 PILOT AILERON ACTUATOR COMPUTER AMPLIFIER TURN COORDINATOR Figure 1 Cessna 200A Autopilot Operating Controls and Indicators Sheet 1 of 2 2 1 October 1978 ...

Page 247: ...ty position push button out response to NAV signal is dampened for smoother tracking of enroute VOR radials it also smooths out effect of course scalloping during NAV opera tion 8 BACK CRS PUSHBUTTON Used with LOC operation only With AlP switch OFF or ON and when navigation receiver selected by NAV switch is set to a localizer frequency it reverses normal localizer needle indication CDI and causes...

Page 248: ...irplane Control Wheel ROTATE as required to override autopi lot NOTE The servo may be overpowered at anytime without dam age TO TURN OFF AUTOPILOT 1 AlP ON OFF Switch OFF SECTION 4 NORMAL PROCEDURES BEFORE TAKE OFF AND LANDING 1 AlP ON OFF Switch OFF 2 BACK CRS Button OFF see Caution note under Nav Capture NOTE Periodically verify operation of amber warning light s labeled BC on CDI s by engaging ...

Page 249: ...U206 and TU206 Series Models COMMANDTURNS 1 PULL TURN Knob CENTER PULL out and ROTATE DIRECTION HOLD 1 PULL TURN Knob CENTER and PULL out 2 Autopilot TRIM Control ADJUST for zero turn rate 3 Airplane Rudder Trim ADJUST for zero slip Ball centered 4 DIR HOLD Button PUSH 5 PULL TURN Knob PUSH in detent position when airplane is on desired heading 6 Autopilot TRIM Control READJUST for zero turn rate ...

Page 250: ...tion or more than 3 minutes from intercept use a manual intercept procedure NAV TRACKING VOR LOC 1 NAV TRK Button PUSH when CDlcenters and airplane is within 50 of course heading 2 HI SENS BUTTON DISENGAGE for enroute omni tracking leave ENGAGED for localizer 3 Autopilot TRIM Control READJUST as required to maintain track NOTE Optional ARC function if installed should not be used for autopilot ope...

Page 251: ...essna 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 transmit ting station relative to the nose of the airplane This is done by combining signals from the sense antenna with signals from the ...

Page 252: ...otation from OFF position applies primary power to receiver further clockwise rotation increases audio level 2 FREQUENCY SELECTORS Knob Al selects lOO kHzincrmnents of receiver frequency knob B selects lO kHz increments and knob C selects 1 kHz increments Figure 1 Cessna 300 ADF Operating Controls and Indicators Sheet 1 of 2 2 1 October 1978 ...

Page 253: ...d sense anten nas TEST Momentary on position used during ADF operation to test bearing reliability When held in TEST position slews indicator potnter clockwise when released if bearing is reliable pointer returns to original bearing position 4 INDEX ROTATABLE CARD Indicates relative magnetic or true heading of aircraft as selected by HDG control 5 POINTER Indicates station bearing in degrees of az...

Page 254: ...r Knobs SELECT 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 AUTOMATICDIRECTION FINDER 1 Function Selector Knob ADF position and note relative bearing on indicator 2 Function Selector Knob TEST position and observe tha...

Page 255: ...n the audio output when a CW signal Morse Code is tuned in properly SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounted antenna or related external antennas will result in a minor reduction in cruise performance 1 October 1978 5 6 blank ...

Page 256: ......

Page 257: ...g frequencies are digitally displayed by incandescent readouts on the front panel of the Nav Com A DME receiver transmitter or a glide slope receiver or both may be interconnected 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 associated VORTAC or VOR DlVlE station frequency will also be selected automatic...

Page 258: ...equency readout to display a nd Com Fractional MHz 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 Tile 5 or 0 may be read as the third decimal digit which is not displayed in tile Com fractional frequency display Figure 1 Cess...

Page 259: ...d noise decreases squelch action counterclockwise rotation decreases background noise 10 COMMUNICATION RECEIVER TRANSMITTER MEGAHERTZ SELECTOR Selects COM frequency in 1 MHz steps between 118 and 135MHz 11 COM OFF VOL CONTROL Combination on off switch and volume control turns on NAVICOM set and controls volume of communications receiver audio 12 BC LAMP Amber light illuminates when an autopilot s ...

Page 260: ...rd to center course deviation pointer with a TO flag then returns to conventional OBS selection Pulled to outer detent continuously drives OBS course card to indicate bearing from VOR station keeping course deviation pointer centered with a FROM flag ARC function will not operate on localizer frequencies 21 AUTOMATIC RADIAL CENTERING ARC LAMP Amber light illuminates when Automatic Radial Centering...

Page 261: ...ld This adjustment should be rechecked periodically during each flight to assure optimum reception All controls for the Nav Com except the standard omni bearing selector OBS knob or the optional automatic radial centering ARC knob located on the course deviation indicator are mounted on the front panel of the receiver transmitter Operation and description of the audio control panel used in conjunc...

Page 262: ... Mike Button a To Transmit DEPRESS and SPEAK into microphone NOTE Sidetone may be selected by placing the AUTO selector switch on audio control panel in either the SPEAKER or PHONE position Adjustment of side tone may be accomp lished by adjusting the sidetone pot located inside the audio control panel b To Receive RELEASE mike button NAVIGATION OPERATION NOTE The pilot should be aware that on man...

Page 263: ...esired course b To Obtain Bearing TOVORStation PUSH ARC PUSH TO knob to inner momentary on position NOTE ARC lamp will illuminate amber while the course card is moving to center with the course deviation pointer After alignment has been achieved to reflect bearing to VOR automatic radial centering will autcmatically shut down causing the ARC lamp to go out c To Obtain Continuous Bearing FROM VOR S...

Page 264: ...V TO FROM indicator shows FROM 5 OBS Knob TURN to displace course approximately 10 to either side of 0 while holding ID VOX T to T Course deviation pointer deflects full scale in direction corresponding to course displace rrierrt NAV TO FROM indicator shows FROM 6 ID VOX T Switch RELEASE for normal operation NOTE This test does not fulfill the requirements of FAR 91 25 SECTION 5 PERFORMANCE There ...

Page 265: ...perating informa tion for the communication set and for VOR localizer navigation is presented in this supplement Operating information for area navigation and for DME is presented in separate supplements The RT 385A Receiver Transmitter includes a 720 channel VHF com munication receiver transmitter which receives and transmits signals between 118 000MHz and 135 975MHz in 25 kHz steps It also inclu...

Page 266: ...ion enables COM frequency readout to display and COM Fractional MHz Selector to select frequency in 05MHz steps between 025and 975 MHz In 0 position enables COM frequency readout to display and COM Fractional MHz Selector to select frequency in 05MHz steps between 000and 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 Fi...

Page 267: ...o adjust signal threshold necessary to activate COM receiver audio Clockwise rotation increases background noise decreases squelch action counterclockwise rotation decreases background noise iO COMMUNICATION RECEIVER TRANSMITTER MHz FREQUENCY SELECTOR Selects COM frequency in 1 MHz steps between 118 and 135MHz 11 COM OFF VOL CONTROL Combination on off switch and volume control turns on NAV COM Set...

Page 268: ...ition flag indicates unusable signal With usable VOR signal when OFF position disappears indicates whether selected course is TO or FROM station or waypoint With usable localizer signal shows TO 19 RECIPROCAL COURSE INDEX Indicates reciprocal of selected VOR or RNA V course Figure 1 Cessna 300 Nav Com Set Operating Controls and Indicators Sheet 3 of 3 4 1 October 1978 ...

Page 269: ...are included on the front panel of the RT 385A Receiver Transmitter and the associated Course Deviation Indicator These controls and indicators are shown and described in Figure 1 Operating controls for the RN 478A Area Navigation Computer which are used for area navigation and operating controls for the associated Type R 476A DME are shown in the appropriate supplements in this manual Operating c...

Page 270: ...7 Mike Button a To Transmit DEPRESS and SPEAK into microphone NOTE Sidetone may be selected by placing the AUTO selector switch on audio control panel in either the SPEAKER or PHONE position Adjustment of sidetone may be accomp lished by adjusting the sidetone pot located inside the audio control panel b To Receive RELEASE mike button NAVIGATION OPERATION NOTE The pilot should be aware that on man...

Page 271: ...dex CDI pointer centers or deflects left or right depending on bearing of signal OFF TO FROM indicator shows TO or FROM 4 ID VOX T Switch PRESS to T and HOLDat T CDIpointer should center and OFF TO FROM indicator should show FROM 5 OBS Knob TURNto displace course approximately 10 to either side of0 while holdingID VOX T switch at T CDIpointer should deflect full scale in direction corresponding to...

Page 272: ......

Page 273: ...eading are sensed by the direction al gyro T e computer amplifier electronically computes the necessary correction nd signals the actuator to move the ailerons to maintain the airplane in the commanded lateral attitude or heading The 300A Navomatic will also intercept and track a VOR or localizer course using signals from a VHF navigation receiver The operating controls for the Cessna 300ANavomati...

Page 274: ...AUTOPILOT TYPE AF 395A PILOT S OPERATING HANDBOOK SUPPLEMENT NAV 1 NAV 2 i I I I I COMPUTER AMPLIFIER TURN COORDINATOR Figure 1 Cessna 300A Autopilot Operating Controls and Indicators Sheet 1 of 2 2 1 October 1978 ...

Page 275: ...V signal to provide more precise operation during localizer approach In low sensitivity position push button out response to NAV signal is dampened for smoother tracking of enroute VOR radials it also smooths out effect of course scalloping during NAV opera tion 9 BACK CRS PUSHBUTTON Used with LOC operation only With AlP switch OFF or ON and when navigation receiver selected by NAV switch is get t...

Page 276: ...rplane Control Wheel ROTATE as required to override autopi lot NOTE The servo may be overpowered at any time without dam age TO TURN OFF AUTOPILOT 1 AlP ON OFF Switch OFF SECTION 4 NORMAL PROCEDURES BEFORE TAKE OFF AND LANDING 1 AlP ON OFF Switch OFF 2 BACK CRS Button OFF see Caution note under Nav Intercept NOTE Periodically verify operation of amber warning light s labeled BC on CDI s by engagin...

Page 277: ...180 185 U206 and TU206 Series Models COMMANDTURNS 1 PULL TURN Knob CENTER PULL out and ROTATE HEADING SELECT 1 Directional Gyro SET to airplane magnetic heading 2 Heading Selector Knob ROTATE bug to desired heading 3 Heading Select Button PUSH 4 PULL TURN Knob CENTER and PUSH NOTE Airplane will turn automatically to selected heading If airplane fails to hold the precise heading readjust autopi lot...

Page 278: ... Airplane will automatically turn to a 45 intercept angle NAV TRACKING VOR LOC 1 NAV TRK Button PUSH when cm Mnters within one dot and airplane is within 10 of course heading 2 HI SENS Button Disengage for enroute omni tracking leave engaged for localizer NOTE Optional ARC feature if installed should not be used for autopilot operation If airplane should deviate off course pull out PULL TURN knob ...

Page 279: ...alerts the operator to non ADF operation by slewing the pointer to the 3 00o clock position when the REC mode is selected Operating controls and displays for the Cessna 400ADF are shown and described in Figure 1 The audio system used in conjunction with this radio for speaker phone selection is shown and described in Section 7 of this handbook The frequency range of the Cessna 400ADF is electronic...

Page 280: ...CESSNA 400 ADF TYPE R 446A PILOT S OPERATING HANDBOOK SUPPLEMENT Figure 1 Cessna 400 ADF Operating Controls and Indicator Sheet 1 of 2 2 1 October 1978 ...

Page 281: ...ls Morse Code to be heard 7 REC Pushed in Selects receive mode set operates as a standard communica tions receiver using sense antenna only NOTE In this position an automatic pointer stow feature will alert the pilot to non ADF operation by positioning and retaining the painter at the 3 00 o clock position when the 400ADF is in the REC function 8 ADF Pushed in Selects ADF mode set operates as auto...

Page 282: ... PUSH in NOTE ADF indicator pointer will stow at a 90 degree position to alert the pilot to non ADF operation 3 PRI Frequency Selectors SELECT desired operating frequency 4 SEC Frequency Selectors SELECTdesired operating frequency 5 1 2 Selector Switch 1 position NOTE 1 2 selector switch can be placed in the 2 position for operation Onsecondary frequency The re select lamp will flash only when fre...

Page 283: ...elative magnetic or true bearing to station 8 VOL Control ADJUST to desired listening level NOTE When switching stations place function pushbutton in the REC position Then after station has been selected place function pushbutton in the ADF position to resume auto matic direction finder operation This practice pravonts the bearing indicator from swinging back and forth as frequency dial is rotated...

Page 284: ...ening level NOTE A 1000 Hztone is heard in the audio output when CWsignal Morse Code is tuned in properly SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounted antenna or several related external antennas will result in a minor reduction in cruise performance 6 1 October 1978 ...

Page 285: ... waypoint information which enhances autopilot operation The 400RNAV is coupled to the number 2 Nav Com and includes storage for 3 waypoints Ground speed time to station information to the selected VOR not the waypoint is available on this system This capability along with the course scalloping suppression radial straightening may be used to an advantage while tracking inbound or outbound from the...

Page 286: ...Y READOUT Depending on position of DSPL Switch displays distance programmed for waypoint 1 or waypoint 2 6 BEARING MINILEVER SWITCHES 4 Select bearing of desired waypoint from VOR DME station May be used to store bearing of 3rd waypoint 7 ENROUTE APPROACH SWITCH ENR APPR Controls width of navigation corridor ENR position provides standard 5 NM enroute sensitivity APPR position provides standard 1 ...

Page 287: ...R LOC OPERATION VOR NAVIGATION CIRCUITS VERIFICATION TESTS 1 See appropriate Nav Com supplement VOR LOC NAVIGATION As a convenience to the pilot a separate supplement Avionic Opera tion Guide is supplied to explain the various procedures for using the VHF Navigation Set for VOR and localizer navigation Refer to the Avionic Operations Guide for flight procedures AREA NAVIGATION OPERATION NOTE Prope...

Page 288: ...e being used for navigation This does not affect operation of the unit 6 BEARING Minilever Switches SET to first waypoint bearing 7 DISTANCE Minilever Switches SET to first waypoint distance 8 XFER Pushbutton Switch PUSH in a First waypoint bearing and distance are placed in memory as waypoint 1 b BEARING Display Readout DISPLAYS readout of first waypoint bearing c DISTANCE Display Readout DISPLAY...

Page 289: ...d FLASHES 3 RNAV DSPL and FLY Switches DSPL set to 2 FLY set to 1 a Readout DISPLAYS second waypoint bearing and distance b Fly Display Lamp On RNAV Control Head FLASHES 4 RNAV DSPL and FLY Switches BOTH SET to same number a Readout DISPLAYS waypoint bearing and distance as selected by DSPL switch b Fly Display Lamp On RNAV Control Head NOT LIGHTED 5 DME Mode Selector Switch SET to RNAV a Both RN ...

Page 290: ...sted a BEARING Display READOUT is waypoint bearing b DISTANCE Display READOUT is waypoint distance c Course Indicator RN LAMP lights 7 Course Indicator OBS or ARC SET to waypoint bearing 8 VHF Navigation Receiver ID VOX T Switch HOLD in T posi tion a Course Deviation Pointer CENTERS h Course Deviation Indicator OFF or NAV TO FROM Flag Shows TO c DME Distance Display READOUTis the same as the RNAV ...

Page 291: ...ntains all of the operating controls and displays and a remotely mounted RTA 476AReceiver Transmitter The RTA 476A transmits interrogating pulse pairs on 200 channels between 1041 MHz and 1150 MHz it receives associated ground to air replies between 978MHz and 1213MHz The C 476AControl Unit digitally displays distances up to 200 nautical miles and either ground speed or time to station information...

Page 292: ...d 3 DME MODE SELECTOR SWITCH Selects DME operating mode as follows RNA v Selects area navigation operation selects display of nautical miles distance to selected RNAV waypornt NAV 1 Selects DME operation with No 1 VHF navigation set enables channel selection by NAV 1 frequency selector switches HOLD Selects DME memory circuit DME remains channeled to station to which it was channeled when HOLD was...

Page 293: ...llows a With GS TTS Switch set to GS displays ground speed component to or from station in knots aircraft must be flying directly to or from the VOR DME station for true ground speed indication b With GS TTS Switch set to TTS displays time to VOR DME station in minutes at the ground speed component indicated c With GS TTS in RNAV mode will display ground speed component or time to station at that ...

Page 294: ...refore the sys tem does not provide independent operation ofthe DMEfor reception of the DME Morse Code identifier 4 GS TTS Switch SET as desired 5 TEST ON OFF Switch HOLD to TEST a Distance to Station Display readout is 188 8 h Knots Minutes Display readout is 888 6 TEST ON OFF Switch RELEASE to ON display readouts return to normal SECTION 5 PERFORMANCE There is no change to the airplane performan...

Page 295: ...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 automati cally Operation of the Cessna 400 Glide Slope system is controlled by the associated navigation syste...

Page 296: ...e flag disappears when a re liable glide slope signal is being received lCAUTION Spurious glide slope signals may exist in the area of the localizer back course approach which can cause the glide slope OFF or GS flag to dis appear and present unreliable glide slope informa tion Disregard all glide slope signal indications when making a localizer back course approach un less a glide slope ILS BC is...

Page 297: ... 100 RPM on airplanes equipped with a three bladed propeller dur ing ILS approaches to avoid oscillations of the glide slope deviation pointer caused by propeller interference 1 NAV Frequency Select Knobs SELECT desired localizer frequency glide slope frequency 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...

Page 298: ......

Page 299: ...r beacon antenna 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 Fan Continuous 6 dots see 300 Hz White Middle Alternate dots and dashes 1300 Hz Amber Outer 2 dashes see 400 Hz Blue Wh...

Page 300: ...AN light is white 3 SPEAKER PHONE SWITCH SPKR PHN Selects speaker or phone for aural reception 4 HI LO TEST SWITCH In the HI position Up receiver sensitivity is posi tioned for airway flying In the LO position Center receiver sensitivity is positioned for ILS approaches In the TEST position Down the marker lights will illuminate indicating the lights are operational the test position is a lamp tes...

Page 301: ...ening level 2 HIILO Sens Switch SELECT HI position for airway flying or LO position for ILS approaches 3 SPKR PHN 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 performance when ...

Page 302: ......

Page 303: ...tage prevents loss of the preset frequencies when the Nav Com is turned off Both the communications and navigation operating frequen cies are digitally displayed by incandescent readouts on the front panel of the Nav COIn A DME receiver transmitter or a glide slope receiver or both may be interconnected with the Nav Com set for automatic selection of the associated DME or glide slope frequency Whe...

Page 304: ...ckwise until noise is heard then back off slightly until it is quiet and you will have automatic squelch with the lowest practical threshold This adjustment should be rechecked periodically during each flight to assure optimum reception All controls for the Nav Com except the omni bearing selector OBS knob or automatic radial centering ARC knob which is located on the course deviation indicator ar...

Page 305: ...G HANDBOOK SUPPLEMENT CESSNA 400 NAV COM TYPE RT 485A TYPICAL 300 SERIES INDICATORS TYPICAL 400 SERIES INDICATORS Figure 1 Cessna 400 Nav Com Type RT 485A Operating Controls and Indicators Sheet 1of 4 1 October 1978 3 ...

Page 306: ...on by holding Cpushbutton pressed for more than 1 7 seconds This lights each COM and NAV MEMORY pushbutton in turn and displays the corresponding preset frequency in MEMORY 4 NAVIGATION OPERATING FREQUENCY READOUT Indicates NAV fre quency in use 5 NAV MEMORY 1 2 3 PUSHBUTTONS When a NAV MEMORY pushbutton is pressed the preset selected frequency will appear in the NAV frequency window for use as th...

Page 307: ... reverse sense switch or autopilot s back course function is engaged and receiver is tuned to a localizer frequency indicates course deviation pointer is reversed 15 COURSE INDEX Indicates selected VOR COURSE 16 COURSE DEVIATION POINTER Indicates course deviation from selected omni course or localizer centerline 17 GLIDE SLOPE GS FLAG When visible red GS flag indicates unreliable glide slope signa...

Page 308: ...illuminates when Automatic Radial Centering is in use 23 COURSE CARD Indicates selected VOR course under course index 24 OMNI BEARING SELECTOR OBS Rotal is course card to select desired VOlt radial 25 TO FROM INDICATOR TO FR Operates only with a usable VOR or localizer signal When white flag is in view indicates whether selected course is TO or FROM station With usable localizer signal shows TO 26...

Page 309: ...e selecting fractional frequencies or you will activate the MEMORY test function 4 MEMORY 2 and 3 Pushbuttons REPEAT STEPS 2 and 3 using next desired NAV or COMMEMORYto be stored Up to 3 NAV and 3 COM frequencies may be stored for automatic recall frequency selection NOTE The operating frequency set in the selected MEMORY position will automatically be changed in the MEMORY bank any time the opera...

Page 310: ...uld avoid use of 2700 100 RPM on air planes equipped with a two bladed propeller or 1800 100 RPM on airplanes equipped with a three bladed propeller during ILS approaches to avoid oscillations of the glide slope deviation pointer caused by propeller interference 1 COM OFF VOL Control TURN ON 2 SPEAKER PHONE or AUTO Switch on audio control panel SET to desired mode 3 NAV Frequency Selection SELECT ...

Page 311: ...the center detent by the pilot 7 AP CPLD Annunciator Light CHECK ON light is only operational if a 400B Autopilot or 400B IFCS is engaged amber light illuminated VOR SELF TEST OPERATION 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 course index course deviation pointer centers or deflects left or right depending on b...

Page 312: ...rrupted the MEMORY test will always start with the last COM ME MORY selected and cycle through the remaining COMand NA V preset frequencies The MEMORY test will always stop on the last selected COMand NA V preset frequencies 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 seve...

Page 313: ...R localizer navigation is presented in this supplement Operating information for area navigation and for DME is presented in separate supplements Microprocessor frequency management provides storage for 3 preset NAV and 3 preset COMfrequencies in MEMORY A keep alive voltage prevents loss of the preset frequencies when the NAV COM Switch Avionics Power Switch or Master Switch is turned OFF The RT 4...

Page 314: ...tor and an optional IN l048AC Course Deviation Indicator is also offered when Automatic Radial Centering ARC is desired When the optional IN l048AC Course Deviation Indicator is installed an Automatic Radial Centering lamp ARC is incorporated in the CDI to alert the pilot that the Automatic Radial Centering feature has been selected All operating controls and indicators for the Cessna 400Nav Com a...

Page 315: ...es may be stored in MEMORY and selected as desired by merely pressing the appropriate COM MEMORY pushbutton to recall the desired operating frequency If electrical power to the set s keep alive circuit has not been interrupted upon turn on the set will automatically recall the last COM MEMORY frequency selected by the MEMORY pushbutton If electrical power is removed from the set s keep alive circu...

Page 316: ... alive circuit has not been interrupted upon turn on the set will automatically recall the last NAV MEMORY frequency selected by the MEMORY pushbutton If electrical power is removed from the set s keep alive circuit such as radio removal or battery replacement for more than 15 seconds upon turn on the NAV MEMORY circuits will have to be reset and NAV 1 MEMORY will automatically be selected with th...

Page 317: ...OINTER Indicates course deviation from selected VOR or RNA V course or localizer centerline 20 OFF TO FROM INDICATOR Operates only with usable VOR or localizer signal OFF position flag indicates unusable signal With usable VOR signal when OFF position disappears indicates whether selected course is TO or FROM station or waypoint With usable localizer signal shows TO 21 RECIPROCAL COURSE INDEX Indi...

Page 318: ...OR or localizer signal When white flag is in view indicates whether selected course is TO or FROM station With usable localizer signal shows TO 25 AUTOMATIC RADIAL CENTERING ARC LAMP Amber light illuminates when Automatic Radial Centering is in use Figure 1 Cessna 400 Nav Oom Set Operating Controls and Indicators Sheet 4 of 4 6 1 October 1978 ...

Page 319: ...Mpushbut ton 1 momentarily to alert the memory bank of a forthcoming frequency to be stored 3 FREQUENCY SELECTORS MANUALLYROTATE correspond ing NAV or COM frequency selectors press C pushbutton as required to select the desired third fractional COM digit until the desired frequency is shown in the operating frequency readout window The frequency displayed will be automatically trans ferred into ME...

Page 320: ...e AUTO selector switch on audio control panel in either the SPEAKER or PHONE position Adjustment of sidetone may be accomp lished by adjusting the sidetone pot located inside the audio control panel b XMIT Annunciator Light CHECK ON green light illumi nated c To Receive RELEASE mike button NAVIGATION OPERATION NOTE The pilot should be aware that on many Cessna airplanes equipped with the windshiel...

Page 321: ...l centering will automatically shut down causing the ARC lamp to go out and the ARCknob to return to center detent position and function as a normal OBS c To obtain Continuous Bearing FROM VOR Station PULL ARC PULL FR knob to outer detent NOTE ARC lamp will illuminate amber OBS course card will turn to center the course deviation pointer with a FROM flag to indicate bearing from VOR station This s...

Page 322: ...OM 6 ID VOX T Switch RELEASE for normal operation NOTE This test does not fulfill the requirements of FAR 91 25 MEMORY TEST OPERATION 1 C Pushbutton PUSH for about 2 seconds Each COM and NAV MEMORY pushbutton 1 2 3 will illuminate white in turn with the corresponding preset frequency displayed NOTE If the keep alive circuit has not been interrupted the MEMORY test will always start with the last C...

Page 323: ...s coded pulse train reply signals on 1090 MHz It is capable of replying to Mode A aircraft identification and also to Mode C altitude reporting interrogations on a selective reply basis on any of 4096information code selections When an optional panel mounted EA 401A Encoding Altimeter not part of 400 Transponder System is included in the avionic configuration the transponder can provide altitude r...

Page 324: ...uipment warm up or stand by power ON Turns set on and enables transponder to transmit Mode A aircraft identification reply pulses ALT Turns set on and enables transponder to transmit either Mode A aircraft identification reply pulses or Mode C altitude reporting pulses selected automatically by the interrogating signal Figure 1 Cessna 400 Transponder and Encoding Altimeter Operating Controls Sheet...

Page 325: ...A reply code 8 1000 FOOT DRUM TYPE INDICATOR Provides digital altitude readout in 1000 foot increments between 1000 feet and 35 000feet When altitude is below 10 000 feet a diagonally striped flag appears in the 10 OOO foot window 9 OFF INDICATOR WARNING FLAG Flag appears across altitude readout when power is removed from the altimeter to indicate that readout is not reliable 10 100 FOOT DRUM TYPE...

Page 326: ... 7700 operating code TO TRANSMIT A SIGNAL REPRESENTING LOSS OF ALL COMMUNICATIONS WHEN IN A CONTROLLED ENVIRONMENT 1 Function Switch ON 2 Reply Code Selector Switches SELECT 7700operating code for 1 minute then SELECT 7600operating code for 15minutes and then REPEAT this procedure at same intervals for remainder of flight SECTION 4 NORMAL PROCEDURES BEFORE TAKEOFF 1 Function Switch SBY TO TRANSMIT...

Page 327: ...altimeter 2 Altitude Encoder Altimeter Setting Knob SET IN assigned local altimeter setting 3 Reply Code Selector Switches SELECT assigned code 4 Function Switch ALT NOTE When directed by ground controller to stop altitude squawk turn Function Switch to ON for Mode A opera tion only NOTE Pressure altitude is transmitted by the transponder for altitude squawk and conversion to indicated altitude is...

Page 328: ...ance regardless of DIM control setting 4 TEST Button RELEASE for normal operation 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 6 IOctober 1978 ...

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