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Cessna T182 1982, Pilot Operating Handbook

The Cessna T182 1982 Pilot Operating Handbook (POH) is an essential manual for pilots who want to operate this aircraft with confidence and safety. Available for free download at manualshive.com, this comprehensive guide offers detailed information on the aircraft's systems, procedures, and performance, ensuring smooth and efficient flights.

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Summary of Contents for T182 1982

Page 1: ...ENT MUST BE Serial No I tog lOy CARRIED IN THE AIRPLANE AT ALL TIME Registration No J ret fP t THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY CAR PART 3 AND CONSTITUTES THE FAA APPROVED AIRPLANE FLIGHT MANUAL COPYRIGHT 1981 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA f Member of GAMA 21 August 1981 ...

Page 2: ...NUAL WAS PROVIDED FOR THE AIRPLANE IDENTIFIED ON THE TITLE PAGE ON _ SUBSEQUENT REVISIONS SUPPLIED BY CESSNA AIRCRAFT COMPANY MUST BE PROPERLY IN SERTED CESSNA AIRCRAFT COMPANY PAWNEE DIVISION Cessna Aircraft ...

Page 3: ...ic 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 with courteous expe...

Page 4: ... 50 Ft Obstacle 1350 FT STALL SPEED KCAS Flaps Up Power Off 54 KNOTS Flaps Down Power Off 49 KNOTS MAXIMUM WEIGHT Ramp 3112 LBS Takeoff 3100 LBS Landing 2950 LBS STANDARD EMPTY WEIGHT Turbo Skylane 1740 LBS Turbo Skylane II 1793 LBS MAXIMUM USEFUL LOAD Turbo Skylane 1372 LBS Turbo Skylane II 1319 LBS BAGGAGE ALLOWANCE 200 LBS WING LOADING Pounds Sq Ft 17 8 POWER LOADING Pounds HP 13 2 FUEL CAPACIT...

Page 5: ...to the applicable revised area on the outer margin of the page All revised pages will carry the revision number and date on the applicable page The following log of Effective Pages provides the dates of issue for original and revised pages and a listing of all pages in the handbook Pages affected by the current revision are indicated by an asterisk j preceding the pages listed LOG OF EFFECTIVE PAG...

Page 6: ... 1981 5 33 4 December 1981 5 34 Blank 21 August 1981 6 1 21 August 1981 6 2 Blank 21 August 1981 6 3 lhru 6 29 21 August 1981 Page Date 6 30 Blank 7 1 thru 7 42 8 1 8 2 Blank 8 3 thru 8 19 8 20 Blank 9 1 thru 9 3 9 4 Blank 21 August 1981 21 August 1981 21 August 1981 21 August 1981 21 August 1981 21 August 1981 21 August 1981 21 August 1981 NOTE Refer to Section 9 Table of Contents for supplements...

Page 7: ...ERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT BALANCE EQUIPMENT LIST 6 AIRPLANE SYSTEMS DESCRIPTIONS 7 AIRPLANE HANDLING SERVICE MAINTENANCE 8 SU PPLEMENTS Optional Systems Description Operating Procedures I n1 26 flz s 11 1J4 1 i tjr IJ G 36 ttl v vi blank 21 August 1981 9 ...

Page 8: ... 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 6 Engine Power Terminology 1 7 Airplane Performance And Flight Planning Terminology 1 7 Weight And Balance Terminology 1 7 WARNING PITOT HEATER MUST BE ON WHEN OPERATING BelOW 40 F IN INS...

Page 9: ...rObe lights installed 3 Maximum height shown with nose gear depressed as far as possible and flashing beacon installed 4 Wheel base length is 66 1 2 5 Propeller ground clearance is 103 4 6 Wing area is 174 square feet 7 Minimum tuming radius I pivot point to outboard wing tip is 27 7 umJiIITITl 1llII TIJJI iIITIlm PIVOT POINT __ PIVOT POINT 1 3 6 0 r _ Figure 1 1 Three View 21 August 1981 1 2 ...

Page 10: ...er Rating and Engine Speed 235 rated BHP at 31 inches Hg and 2400 RPM k PROPELLER 2 BLADED Propeller Manufacturer McCauley Accessory Division Propeller Model Number B2D34C219 90DHB 8 Number of Blades 2 Propeller Diameter Maximum 82 inches Minimum 80 5 inches Propeller Type Constant speed and hydraulically actuated with a low pitch setting of 15 80 and a high pitch setting of 31 90 30 inch station ...

Page 11: ...eral Oil Use to replenish supply during first 25 hours and at the first 25 hour oil change Continue to use until a total of 50 hours has accumulated or oil consumption has stabilized 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 All temperatur...

Page 12: ...areas A Band C is 200 lbs The maximum allowable weight capacity for baggage in areas Band Cis 80 lbs STANDARD AIRPLANE WEIGHTS Standard Empty Weight Turbo Skylane 1740 lbs Turbo Skylane II 1793 lbs Maximum Useful Load Turbo Skylane 1372 lbs Turbo Skylane II 1319 lbs CABIN AND ENTRY DIMENSIONS Detailed dimensions of the cabin interior and entry door openings are illustrated in Section 6 BAGGAGE SPA...

Page 13: ...d is the highest speed FE permissible with wing flaps in a prescribed extended position V Maximum Structural Cruising Speed is the speed that NO should not be exceeded except in smooth air then only with caution V Never Exceed Speed is the speed limit that may not be NE exceeded at any time V Stalling Speed or the minimum steady flight speed at s which the airplane is controllable V Stalling Speed...

Page 14: ...RMINOLOGY Demon strated Crosswind Velocity Usable Fuel Unusable Fuel GPH NMPG g Demonstrated Crosswind Velocity is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing was actually demon strated during certification tests The value shown is not considered to be limiting Usable Fuel is the fuel available for flight planning Unusable Fuel is t...

Page 15: ...ng the total moment by the total weight of the airplane Center of Gravity Arm is the arm obtained by adding the airplane s individual moments and dividing the sum by the total weight Center of Gravity Limits are the extreme center of gravity locations within which the airplane must be operated at a given weight Standard Empty Weight is the weight of a standard air plane including unusable fuel ful...

Page 16: ...SSNA MODEL T182 SECTION 1 GENERAL 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 21 August 1981 1 9 1 10 blank ...

Page 17: ... Markings 2 5 Power Plant Limitations 2 5 Power Plant Instrument Markings 2 6 Weight Limits 2 7 Center Of Gravity Limits 2 7 Maneuver Limits 2 7 Flight Load Factor Limits 2 8 Kinds Of Operation Limits 2 8 Fuel Limitations 2 8 Maximum Operating Altitude Limit 2 9 Other Limitations 2 9 Flap Limitations 2 9 Placards 2 9 21 August 1981 2 1 2 2 blank ...

Page 18: ... 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 19: ... exceed this speed except in smooth air and then only with caution VA Maneuvering Speed 3100 Pounds 2600 Pounds 2100 Pounds 110 100 90 111 101 90 Do not make full or abrupt control movements above this speed VFE Maximum Flap Extended Speed To 100 Flaps 100 FULL Flaps 138 95 140 95 Do not exceed these speeds with the given flap settings Maximum Window Open Speed 175 178 Do not exceed this speed wit...

Page 20: ...0 178 Operations must be conducted with caution and only in smooth air Red Line 178 Maximum speed for all operations Figure 2 2 Airspeed Indicator Markings POWER PLANT LIMITATIONS Engine Manufacturer Avco Lycoming Engine Model Number 0 540 L3C5D Maximum Power 235 BHP rating Engine Operating Limits for Takeoff and Continuous Operations Maximum Engine Speed 2400 RPM Maximum Manifold Pressure 31 in H...

Page 21: ... 16 00 3 Bladed High 31 70 POWER PLANT INSTRUMENT MARKINGS Power plant instrument markings and their color code significance are shown in figure 2 3 INSTRUMENT RED LINE GREEN ARC RED LINE MINIMUM NORMAL MAXIMUM LIMIT OPERATING LIMIT Tachometer 2100 2400 RPM 2400 RPM Manifold Pressure 17 25 31 in Hg in Hg Oil Temperature 100 245 F 245 F Cylinder Head 200 500 F 500 F Temperature Fuel Pressure 3 0 ps...

Page 22: ...LIMITS Center of Gravity Range Forward 33 0 inches aft of datum at 2250 lbs or less with straight line variation to 35 5 inches aft of datum at 2700 lbs with straight line variation to 38 9 inches aft of datum at 2950 lbs landing with straight line variation to 40 9 inches aft of datum at 3100 lbs takeoff Aft 46 0 inches aft of datum at all weights Reference Datum Front face of firewall MANEUVER L...

Page 23: ...suance Flight into known icing conditions is prohibited FUEL LIMITATIONS 2 Standard Tanks 46 0 U S gallons each Total Fuel 92 0 U S gallons Usable Fuel all flight conditions 88 U S gallons Unusable Fuel 4 0 U S gallons NOTE To ensure maximum fuel capacity when refueling and prevent cross feeding when parked on a sloping surface place the fuel selector valve in either LEFT or RIGHT position Takeoff...

Page 24: ... placards installed in this airplane contain operating limitations which must be complied with when operat ing this airplane in the Normal Category Other operating limita tions 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 k...

Page 25: ...oor 120 POUNDS MAXIMUM BAGGAGE AND 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 0 to 10 Partial flap range with blue color code and 140 kt callout also me chanical detent at 10 10 to 20 to FULL Indices at these posi...

Page 26: ...tion card must be provided to indicate the accuracy of the magnetic compass in 30 increments 9 On oil filler cap I 8 ci s I 10 Forward of each fuel tank filler cap in line with fwd arrow FUEL CAP FWD ARROW ALIGNMENT CAP MUST NOT ROTATE DURING CLOSING WARNING PITOT HEATER MUST BE ON WHEN OPERATING BELOW 40 F IN INSTRUMENT METEROLOGICAL CONDITIONS 0890018 2 21 August 1981 2 11 2 12 blank ...

Page 27: ...tely After Takeoff 3 4 Engine Failure During Flight Restart Procedures 3 4 Forced Landings 3 4 Emergency Landing Without Engine Power 3 4 Precautionary Landing With Engine Power 3 5 Ditching 3 5 Fires 3 6 During Start On Ground 3 6 Engine Fire In Flight 3 6 Electrical Fire In Flight 3 6 Cabin Fire 3 7 Wing Fire 3 7 Icing 3 8 Inadvertent Icing Encounter 3 8 Suspected 3 8 Landing With A Flat ivlain ...

Page 28: ...n Clouds 3 13 Emergency Descent Through Clouds 3 13 Recovery From A Spiral Dive 3 14 Inadvertent Flight Into Icing Conditions 3 14 Static Source Blocked 3 15 Spins 3 15 Rough Engine Operation Or Loss Of Power 3 16 Carburetor Icing 3 16 Spark Plug Fouling 3 16 Magneto Malfunction 3 16 Engine Driven Fuel Pump Failure 3 17 Low Oil Pressure 3 17 Electrical Power Supply System Malfunctions 3 17 Excessi...

Page 29: ...ered However should an emergency arisl the basic guidelines described in this section should be considered am 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 75 KIAS Wing Flaps Down 70 KIAS Maneuvering Speed 3100 Lbs 111 KIAS 2600 Lb...

Page 30: ...INE FAILURE IMMEDIATELY AFTER TAKEOFF 1 Airspeed 75 KIAS flaps UP 70 KIAS flaps DOWN 2 Mixture IDLE CUT OFF 3 Fuel Selector Valve OFF 4 Ignition Switch OFF I 5 Wing Flaps AS REQUIRED FULL recommended 6 Master Switch OFF ENGINE FAILURE DURING FLIGHT RESTART PROCEDURES 1 Airspeed 75 KIAS 2 Carburetor Heat ON 3 Fuel Selector Valve BOTH 4 Mixture RICH 5 Ignition Switch BOTH or START if propeller is st...

Page 31: ...OFF 9 Touchdown SLIGHTLY TAIL LOW 10 Ignition Switch OFF 11 Brakes APPLY HEAVILY DITCHING 1 Radio TRANSMIT MAYDAY on 121 5 MHz giving location and intentions and SQUAWK 7700 if transponder is installed 2 Heavy Objects in baggage area SECURE OR JETTISON 3 Flaps 20 to FULL I 4 Power ESTABLISH 300 FT MIN DESCENT at 65 KIAS 5 Approach High Winds Heavy Seas INTO THE WIND Light Winds Heavy Swells PARALL...

Page 32: ... OFF 9 Fire EXTINGUISH using fire extinguisher wool blanket or dirt 10 Fire Damage INSPECT repair damage or replace damaged components or wiring before conducting another flight ENGINE FIRE IN FLIGHT 1 Mixture IDLE CUT OFF 2 Fuel Selector Valve OFF 3 Master Switch OFF 4 Cabin Heat and Air OFF except overhead vents 5 Airspeed 100 KIAS If fire is not extinguished increase glide speed to find an airs...

Page 33: ... Cabin Air Heat OPEN when it is ascertained that fire is completely extinguished CABIN FIRE 1 Master Switch OFF 2 Vents Cabin Air Heat CLOSED to avoid drafts 3 Fire Extinguisher ACTIVATE if available J WARNING I After discharging an extinguisher within a closed cabin ventilate the cabin 4 Land the airplane as soon as possible to inspect for damage WING FIRE 1 Pitot Heat Switch if installed OFF 2 N...

Page 34: ...antly higher stall speed 8 Leave wing flaps retracted With a severe ice build up on the horizontal tail the change in wing wake airflow direction caused by wing flap extension could result in a loss of elevator effective ness 9 Open the window and if practical scrape ice from a portion of the windshield for visibility in the landing approach 10 Perform a landing approach using a forward slip if ne...

Page 35: ...GE LIGHT ILLUMINATES DURING FLIGHT Ammeter Indicates Discharge NOTE Illumination of the low voltage light may occur during low RPM conditions with an electrical load on the system such as during a low RPM taxi Under these conditions the light will go out at higher RPM The master switch need not be recycled since an over voltage condition has not occurred to de activate the alternator system 1 Avio...

Page 36: ...FULL ON 5 Propeller HIGH RPM 6 Mixture LEAN TO SMOOTH ENGINE IDLE 7 Cowl Flaps CLOSED 8 Wing Flaps 10 ROUGH AIR 1 Seat Belts and Shoulder Harnesses SECURE 2 Throttle IDLE 3 Weights and Airspeeds 3100 Lbs 111 KIAS 2600 Lbs 101 KIAS 2100 Lbs 90 KIAS 4 Carburetor Heat FULL ON 5 Propeller HIGH RPM 6 Mixture LEAN TO SMOOTH ENGINE IDLE 7 Cowl Flaps CLOSED 8 Wing Flaps UP 3 10 21 August 1981 ...

Page 37: ...extra items on the checklist will provide added safety after a failure of this type Prompt lowering of the nose to maintain airspeed and establish a glide attitude is the first response to an engine failure after takeoff In most cases the landing should be planned straight ahead with only small changes in direction to avoid obstructions Altitude and airspeed are seldom sufficient to execute a 1800...

Page 38: ... Engine Power checklist Prepare for ditching by securing or jettisoning heavy objects located in the baggage area and collect folded coats for protection of occupants face at touchdown Transmit Mayday messag e on 121 5 MHz giving location and intentions and squawk 7700 if a transponder is installed A void a landing flare because of difficul ty in judging height over a water surface In a forced lan...

Page 39: ...TING A 1800 TURN IN CLOUDS Upon inadvertently entering the clouds an immediate plan should be made to turn back as follows 1 Note the compass heading 2 Note the time of the minute hand and observe the position of the sweep second hand on the clock 3 When the sweep second hand indicates the nearest half minute initiate a standard rate left turn holding the turn coordinator symbolic airplane wing op...

Page 40: ... force if present 8 Check trend of compass card movement and make cautious corrections with rudder to stop turn 9 Upon breaking out of clouds resume normal cruising flight RECOVERY FROM A SPIRAL DIVE If a spiral 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 horiz...

Page 41: ... static source cabin pressure can be supplied to the static pressure instruments by breaking the glass in the face of the vertical speed indicator SPINS Intentional spins are prohibited in this airplane Should an inadvert ent spin occur the following recovery procedure should be used 1 RETARD THROTTLE TO IDLE POSITION 2 PLACE AILERONS IN NEUTRAL POSITION 3 APPLY AND HOLD FULL RUDDER OPPOSITE TO TH...

Page 42: ... SPARK PLUG FOULING A slight engine roughness in flight may be caused by one or more spark plugs becoming fouled by carbon or lead deposits This may be verified by turning the ignition switch momentarily from BOTH to either L or 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 mix...

Page 43: ...L POWER SUPPLY SYSTEM MALFUNCTIONS Malfunctions in the electrical power supply system can be detected by periodic monitoring of the ammeter and low voltage warning light however the cause of these malfunctions is usually difficult to determine A broken alternator drive belt or wiring is most likely the cause of alternator failures although other factors could cause the problem A defective alternat...

Page 44: ...r voltage condition has not occurred to de activate the alternator system If the over voltage sensor should shut down the alternator or if the alternator output is low a discharge rate will be shown on the ammeter followed by illumination of the low voltage warning light Since this may be a nuisance trip out an attempt should be made to reactivate the alternator system To do this turn the avionics...

Page 45: ...g 4 5 Nose 4 6 Left Wing 4 6 Left Wing Leading Edge 4 7 Left Wing Trailing Edge 4 7 Before Starting Engine 4 7 Starting Engine 4 7 Before Takeoff 4 8 Takeoff 4 9 Normal Takeoff 4 9 Short Field Takeoff 4 9 Enroute Climb 4 10 Normal Climb 4 10 Maximum Performance Climb 4 10 Cruise 4 10 Descent 4 10 Before Landing 4 11 Landing 4 11 Normal Landing 4 11 Short Field Landing 4 11 Balked Landing 4 11 Afte...

Page 46: ...eck Wing Flap Settings Crosswind Takeoff Enroute Climb Cruise Stalls Landing Normal Landing Short Field Landing Crosswind Landing Balked Landing Cold Weather Operation Starting Operation Hot Weather Operation Noise Characteristics CESSNA MODEL T182 Page 4 13 4 14 4 14 4 16 4 16 4 16 4 16 4 16 4 16 4 17 4 17 4 18 4 18 4 20 4 20 4 20 4 21 4 21 4 21 4 21 4 21 4 23 4 23 4 24 21 August 1981 4 2 ...

Page 47: ...particular weight must be used Takeoff Normal Climb Out 70 80 KIAS Short Field Takeoff Flaps 20 Speed at 50 Feet 58 KIAS Enroute Climb Flaps Up Normal 90 100 KIAS Best Rate of Climb Sea Level 87 KIAS Best Rate of Climb 20 000 Feet 84 KIAS Best Angle of Climb Sea Level 73 KIAS Best Angle of Climb 10 000 Feet 75 KIAS Landing Approach Normal Approach Flaps Up 70 80 KIAS Normal Approach Flaps FULL 60 ...

Page 48: ...ons In cold weather remove even small accumula tions of frost ice or snow from wing tail and control surfaces Also make sure that control surfaces contain no internal accumulations of ice or debris Prior to flight check that pitot heater if installed is warm to touch within 30 seconds with battery and pitot heat switches on If a night flight is planned check operation of all lights and make sure a...

Page 49: ...in 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 Avionics Cooling Fan CHECK AUDIBLY FOR OPERATION 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 EMPENNAGE ...

Page 50: ...e Induction Air Inlet CHECK for restrictions 5 Nose Wheel Strut and Tire CHECK for proper inflation 6 Nose Tie Down DISCONNECT 7 Engine Oil Dipstick CHECK oil level then check dipstick SECURE Do not operate with less than five quarts Fill to eight quarts for extended flight NOTE To check oil level remove dipstick wipe clean and rein sert Wait five seconds and then check oil level for an accurate r...

Page 51: ...DISCONNECT LEFT WING Trailing Edge 1 Aileron CHECK freedom of movement and security BEFORE STARTING ENGINE 1 Preflight Inspection COMPLETE 2 Passenger Briefing COMPLETE 3 Seats Seat Belts Shoulder Harnesses ADJUST and LOCK 4 Brakes TEST and SET 5 Avionics Power Switch OFF CAUTION The avionics power switch must be OFF during engine start to prevent possible damage to avionics 6 Electrical Equipment...

Page 52: ...0 Oil Pressure CHECK 11 Avionics Power Switch ON 12 Navigation Lights and Flashing Beacon ON as required 13 Radios ON BEFORE TAKEOFF 1 Parking Brake SET 2 Seats Seat Belts Shoulder Harnesses CHECK SECURE 3 Cabin Doors CLOSED and LOCKED 4 Flight Controls FREE and CORRECT 5 Flight Instruments CHECK and SET 6 Auxiliary Fuel Pump ON check for rise in pressure then OFF 7 Mixture RICH NOTE In flight gra...

Page 53: ...tion Lock ADJUST 14 Strobe Lights if installed AS DESIRED 15 Radios and Avionics SET 16 Autopilot if installed OFF 17 Air Conditioner if installed OFF 18 Wing Flaps SET for takeoff see Takeoff checklists 19 Brakes RELEASE TAKEOFF NORMAL TAKEOFF 1 Wing Flaps 0 20 2 Carburetor Heat COLD 3 Power 31 INCHES Hg Maximum and 2400 RPM NOTE To avoid overboosting the engine do not use full throttle for takeo...

Page 54: ... NORMAL CLIMB 1 Airspeed 90 100 KIAS 2 Power 25 INCHES Hg and 2400 RPM I 3 Fuel Selector Valve BOTH I 4 Mixture FULL RICH 5 Cowl Flaps OPEN as required I MAXIMUM PERFORMANCE CLIMB i 1 Airspeed 87 KIAS at sea level to 84 KIAS at 20 000 feet 2 Power 31 INCHES Hg and 2400 RPM 3 Fuel Selector Valve BOTH 4 Mixture FULL RICH 5 Cowl Flaps FULL OPEN CRUISE 1 Power 17 25 INCHES Hg 2100 2400 RPM 2 Elevator ...

Page 55: ...installed OFF LANDING NORMAL LANDING 1 Airspeed 70 80 KIAS flaps UP 2 Wing Flaps AS DESIRED 0 10 below 140 KIAS 10 FULL be low 95 KIAS 3 Airspeed 60 70 KIAS flaps DOWN 4 Trim ADJUST 5 Touchdown MAIN WHEELS FIRST 6 Landing Roll LOWER NOSE WHEEL GENTLY 7 Braking MINIMUM REQUIRED I SHORT FIELD LANDING 1 Airspeed 70 80 KIAS flaps UP 2 Wing Flaps FULL below 95 KIAS 1 3 Airspeed MAINTAIN 61 KIAS 4 Trim ...

Page 56: ...buretor Heat COLD 8 Power READJUST as desired AFTER LANDING 1 Carburetor Heat COLD 2 Wing Flaps UP 3 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 Cowl Flaps CLOSE 9 Fuel Selector Valve RIGHT or LEFT to prevent crossfeedi...

Page 57: ...gation and anti collision lights and avionics antennas Outside storage for long periods may result in dust and dirt accumula tion on the induction air filter obstructions in airspeed system lines and condensation in fuel tanks If any water is detected in the fuel system the fuel tank sump quick drain valves fuel selector quick drain valve and fuel strainer drain should all be thoroughly drained un...

Page 58: ...rottle 1 8 inch open and crank again When the engine starts slowly adjust the throttle to the desired idle speed 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 co...

Page 59: ...Strong quartering tail winds require caution WIND DIRECTION Avoid sudden bursts of the throttle and sharp braking when the airplane is in this attitude Use the steerable nose wheel and rudder to ma ntain direction Fig ure 4 2 Taxiing Diagram 21 August 1981 4 15 ...

Page 60: ...cerning 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 faul ty 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 verificati on of proper alternator ...

Page 61: ...ately 20 per cent Flap deflections greater than 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 58 KIAS should be used Soft field takeoffs are performed with 20 flaps by lifting the airplane off ...

Page 62: ... be done at 75 power as much as practical until a total of 25 hours has accumulated or oil consump tion has stabilized Operation at this higher power will ensure proper seating of the rings and is applicable to new engines and engines in service following cylinder replacement or top overhaul of one or more cylinders The Cruise Performance Table figure 4 3 illustrates the true airspeed and nautical...

Page 63: ...companied by approximately 4 knots decrease in speed When leaning the mixture under some conditions engine roughness may occur before peak EGT is reached In this case continue to lean until peak EGT is established then enrichen to any desired mixture setting that allows smooth engine operation The mixture may be leaned during descent to provide smooth engine operation and improved fuel economy Any...

Page 64: ...and mixture should be readjusted as necessary STALLS The stall characteristics are conventional and aural warning is provided by a stall warning horn which sounds between 5 and 10 knots above the stall in all configurations Altitude loss during stall recovery may be as much as 300 feet Power off stall speeds at maximum weight for both forward and aft C G positions are presented in Section 5 LANDIN...

Page 65: ...ately after full power is applied After all obstacles are cleared and a safe altitude and airspeed are obtained the wing flaps should be retracted To prevent overboosting the engine power should then be reduced to approximately 25 inches of manifold pressure before the carburetor heat control is placed in the cold position COLD WEATHER OPERATION STARTING Prior to starting on cold mornings it is ad...

Page 66: ...equipped with an accelerator pump 5 Propeller HIGH RPM 6 Mixture FULL RICH 7 Propeller Area CLEAR 8 Master Switch ON 9 Auxiliary Fuel Pump ON check for rise in fuel pressure then OFF 10 Ignition Switch START release to BOTH when engine starts 11 Oil Pressure CHECK Without Preheat 1 Prime 2 to 4 STROKES 2 Primer LOCKED 3 Carburetor Heat COLD 4 Throttle CLOSED until engine starts NOTE Pumping of the...

Page 67: ...nd distribution of the fuel air mixture to the cylinders The effects of these conditions are especially noticeable during operation on one magneto in ground checks where only one spark plug fires in each cylinder For optimum operation of the engine in cold weather the appropriate use of carburetor heat may be necessary The following procedures are indicated as a guideline 1 Use the minimum carbure...

Page 68: ...t with the provisions of government regulations 2 During departure from or approach to an airport climb after takeoff and descent for landing should be made so as to avoid prolonged flight at low altitude near noise sensitive areas NOTE The above recommended procedures do not apply where they would conflict with Air Traffic Control clearances or instructions or where in the pilot s judgment an alt...

Page 69: ...GE z ATIENTION AIRCRAFT OWNER OPERATOR w This important notice must be 1 read and understood and followed before operating the aircraft into which this air pump is installed 2 distributed to all pilots using the aircraft and 3 permanently retained in the a Pilot s Operating Handbook for this aircraft FAILURE TO DO SO MAY RESULT IN DEATH BODILY INJURY OR PROPERTY DAMAGE Parker Hannlfln Corporation ...

Page 70: ... aircraft control This could result in an accident causing death bodily injury or property damage C Use of single engine aircraft in IMC is increasing Many single engine o J aircraft do not have a back up pneumatic power source or back up electric attitude gyro instruments In aircraft without such back up a devices the pilot due to added workload may not be able to fly the Z aircraft with only par...

Page 71: ...Maximum Rate Of Climb Time Fuel And Distance To Climb Normal Climb Figure 5 8 Cruise Performance 2000 Feet Cruise Performance 4000 Feet Cruise Performance 6000 Feet Cruise Performance 8000 Feet Cruise Performance 10 000 Feet Cruise Performance 12 000 Feet Cruise Performance 14 000 Feet Cruise Performance 16 000 Feet Cruise Performance 18 000 Feet Cruise Performance 20 000 Feet Figure 5 9 Range Pro...

Page 72: ...eller condition and air turbulence may account for variations of 100 0 or more in range and endurance Therefore it is mportant 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 ...

Page 73: ...nce information presented for a weight of 3100 pounds pressure altitude of 4000 feet and a temperature of 30 C should be used and results in the following Ground roll 1165 Feet Total distance to clear a 50 foot obstacle 2145 Feet These distances are well within the available takeoff field length How ever a correction for the effect of wind may be made based on Note 2 of the takeoff chart The corre...

Page 74: ...respond to the planned altitude and expected temperature conditions The power setting chosen is 2300 RPM and 23 inches of manifold pressure which results in the following Power 66 True airspeed 141 Knots Cruise fuel flow 12 6 GPH The power computer may be used to determine power and fuel consump tion more accurately during the flight FUEL REQUIRED The total fuel requirement for the flight may be e...

Page 75: ...esults are obtained Time to climb 21 Minutes Distance to climb 38 Nautical Miles The distances shown on the climb chart are for zero wind A correction for the effect of wind may be made as follows Distance with no wind 38 Decrease in distance due to wind 21 60 x 10 knot headwind 3 Corrected Distance to Climb 35 Nautical Miles The resultant cruise distance is Total distance 480 Climb distance 35 Cr...

Page 76: ...used for estimating the landing distance at the destination airport Figure 5 11 presents landing distance information for the short field technique The distances corres ponding to 3000 feet pressure altitude and a temperature of 30 C are as follows Ground roll 695 Feet Total distance to clear a 50 foot obstacle 1525 Feet A correction for the effect of wind may be made based on Note 2 of the landin...

Page 77: ...r descent FLAPS UP KIAS KCAS FLAPS 200 KIAS KCAS FLAPS FULL KIAS I KCAS 50 61 40 54 40 52 60 65 50 58 50 57 70 72 60 63 60 63 80 80 70 71 70 71 90 89 80 80 80 80 100 99 90 89 90 90 110 109 95 94 95 95 120 130 140 150 118 128 138 147 160 157 170 167 I I Figure 5 1 Airspeed Calibration Sheet 1 of 2 21 August 1981 Revision 1 4 December 1981 5 9 ...

Page 78: ...50 60 70 80 90 95 50 61 72 82 92 97 50 60 70 80 90 95 50 62 72 82 91 95 OPTIONAL AIR CONDITIONER INSTALLED HEATER OFF VENTS CLOSED AIR CONDITIONER OFF FLAPS UP NORMAL KIAS ALTERNATE KIAS FLAPS 20 NORMAL KIAS ALTERNATE KIAS FLAPS FULL NORMAL KIAS ALTERNATE KIAS 60 70 80 90 100 110 120 130 140 150 160 60 70 80 89 99 109 118 128 137 147 157 50 60 70 80 90 95 50 60 70 80 90 95 50 60 70 80 90 95 50 60 ...

Page 79: ...N 5 MODEL T182 PERFORMANCE TEMPERATURE CONVERSION CHART o t 100 80 f UJ I Z UJ a I u f UJ UJ a l UJ Cl 60 40 20 o 20 40 40 20 Figure 5 2 o 10 20 40 DEGREES CELSIUS Temperature Conversion Chart 60 21 August 1981 5 11 ...

Page 80: ...NGLE OF BANK 0 30 45 60 KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS 3100 UP 20 FULL 44 37 33 54 50 49 47 40 35 58 54 53 52 44 39 64 60 58 62 52 47 76 71 69 I I MOST FORWARD CENTER OF GRAVITY WEIGHT LBS FLAP DEFLECTION ANGLE OF BANK 0 30 45 60 KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS 3100 UP 20 FULL 48 43 40 56 53 52 52 46 43 60 57 56 57 51 48 67 63 62 68 61 57 79 75 74 Figure 5 3 Stall Speeds 21 August...

Page 81: ...emonstrated crosswind velocity is 15 knots not a limitation 40 j i i i i i i 35 30 Q c 25 a I z w _ QJ 20 j2 l 1 UJ CJ I tfl f a z 15r j f 10 Z Z UJ a c 2 5 a u a z 0 a z 5 J f lO 0 5 10 15 20 25 CROSSWIND COMPONENT KNOTS Figure 5 4 Wind Components 21 August 1981 5 13 30 ...

Page 82: ...D PRESS WEIGHT KIAS ALT TOTAL TOTAL LBS FT GRND TO CLEAR ROLL TO CLEAR GRND 50 FT OBS 50 FT OBS ROLL ro TOTAL TOTAL TOTAL LIFT AT GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR OFF 50 FT ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS 3100 49 58 S L 700 1310 760 1415 820 1535 890 1665 960 1805 1000 750 1390 810 1505 880 1630 950 1770 1025 1925 2000 800 1475 870 1600 940 1735 1015 1885 1100 2050 3000 855 1...

Page 83: ...80 3000 680 1245 740 1345 800 1455 860 1575 4000 730 1320 790 1430 855 1550 925 1675 1 5000 780 1405 845 1525 915 1650 990 1790 1 6000 840 1500 910 1625 985 1765 1065 1915 1 7000 900 1600 980 1740 1060 1885 1145 20M 1 8000 970 1710 1050 1860 1140 2020 1230 2195 1 2500 44 52 S L 435 815 470 880 505 945 545 1020 1000 460 865 500 930 540 1000 580 1080 2000 495 915 535 985 575 1060 625 1145 3000 530 9...

Page 84: ...ixture Full Rich Cowl Flaps Open WEIGHT LBS PRESS ALT FT CLIMB SPEED KIAS RATE OF CLIMB FPM 20 C OOC 20 C I 40 C 3100 S L 4000 8000 12 000 16 000 20 000 87 86 86 85 85 84 1175 1085 970 825 670 505 1055 965 845 700 550 390 935 840 720 580 435 815 715 595 Figure 5 6 Maximum Rate of Climb 5 16 21 August 1981 ...

Page 85: ...d 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 87 965 0 0 0 2000 11 87 945 2 0 9 3 4000 7 86 920 4 1 7 6 6000 3 86 885 6 2 6 10 8000 1 86 850 9 3 6 13 10 000 5 86 805 11 4 5 17 12 000 9 85 755 14 5 6 22 14 000 13 85 705 17 6 7 27 16 000 17 85 650 20 7 ...

Page 86: ...ce 2 Increase time fuel and distance by 10 for each 70 C above standard temperature 3 Distances shown are based on zero wind PRESSURE RATE OF FROM SEA LEVE L WEIGHT ALTITUDE TEMP CLIMB LBS FT c FPM TIME FUEL USED DISTANCE MIN GALLONS NM 3100 S L 15 500 0 0 0 2000 11 500 4 1 4 6 4000 7 495 B 2 8 13 6000 3 485 12 4 3 20 8000 1 470 16 5 7 27 10 000 5 450 21 7 3 35 12 000 9 425 25 8 9 44 Figure 5 7 Ti...

Page 87: ... 54 137 131 124 116 14 8 13 3 11 8 10 5 74 66 59 51 137 130 123 115 14 0 12 6 11 3 10 0 2300 25 23 21 19 78 70 62 54 135 129 122 114 14 9 13 3 11 8 10 4 74 67 59 51 135 128 121 113 14 1 12 7 11 3 10 0 71 63 56 49 134 128 120 112 13 4 12 1 10 8 9 6 2200 25 23 21 19 75 67 59 51 132 126 119 111 14 2 12 7 11 3 9 9 71 64 56 49 132 126 118 110 13 5 12 1 10 8 9 5 67 60 53 46 131 125 117 108 12 8 11 5 10 ...

Page 88: ...71 63 56 140 134 127 120 15 0 13 5 12 1 10 7 75 67 60 53 140 134 127 118 14 2 12 8 11 5 10 2 2300 25 23 21 19 79 71 64 56 138 132 125 117 15 0 13 6 12 1 10 7 75 68 60 53 138 132 125 117 14 3 12 9 11 5 10 3 71 64 57 50 137 131 124 115 13 6 12 3 11 0 9 8 2200 25 23 21 19 76 68 60 53 135 129 122 114 14 4 12 9 11 5 10 2 72 65 57 50 135 129 122 113 13 7 12 3 11 0 9 8 68 61 54 48 134 128 120 112 13 0 11...

Page 89: ...143 137 130 123 15 0 13 6 12 2 10 9 75 68 61 54 142 136 129 121 14 2 12 9 11 6 10 4 2300 25 23 21 19 80 72 64 57 140 135 128 120 15 1 13 7 12 2 10 9 76 68 61 54 140 134 127 119 14 4 13 0 11 7 10 4 72 65 58 51 140 133 126 118 13 6 12 4 11 1 10 0 2200 25 23 21 19 76 69 61 54 138 132 125 117 14 5 13 1 11 7 10 4 72 65 58 51 138 131 124 116 13 7 12 4 11 2 10 0 69 62 55 49 137 130 123 115 13 0 11 8 10 7...

Page 90: ...13 0 21 68 134 13 0 65 133 12 4 62 132 11 8 19 61 126 11 6 58 126 11 1 55 124 10 6 2300 25 80 143 15 2 76 143 14 5 72 143 13 7 23 73 137 13 8 69 137 13 1 66 136 12 5 21 65 131 12 4 62 130 11 9 59 129 11 3 19 58 123 11 1 55 123 10 6 52 121 10 1 2200 25 77 141 14 6 73 140 13 9 69 140 13 1 23 70 135 13 2 66 134 12 6 63 133 12 0 21 62 128 11 9 59 127 11 3 56 126 10 8 19 55 121 10 6 53 120 10 2 50 118 ...

Page 91: ... 148 142 136 128 15 1 13 8 12 5 11 2 75 69 62 56 148 142 135 127 14 3 13 1 11 9 10 7 2300 25 23 21 19 80 73 66 59 146 140 134 126 15 2 13 9 12 5 11 3 76 70 63 56 146 140 133 125 14 5 13 2 12 0 10 8 72 66 60 53 145 139 132 124 13 7 12 5 11 4 10 3 2200 25 23 21 19 77 70 63 56 143 137 131 123 14 6 13 3 12 0 10 8 73 67 60 53 143 137 130 122 13 9 12 7 11 5 10 3 69 63 57 51 142 136 129 120 13 2 12 0 10 ...

Page 92: ... 5 72 147 13 7 23 73 143 13 9 70 142 13 2 66 141 12 6 21 66 136 12 6 63 136 12 0 60 134 11 5 19 60 129 11 4 57 128 10 9 54 126 10 4 2200 25 77 146 14 6 73 146 13 9 69 145 13 2 23 70 140 13 3 67 139 12 7 63 138 12 1 21 64 133 12 1 61 133 11 6 57 131 11 0 19 57 126 11 0 54 125 10 5 51 123 10 0 2100 25 74 143 14 0 70 143 13 3 66 142 12 6 23 67 137 12 8 64 136 12 2 61 135 11 6 21 61 131 11 6 58 130 11...

Page 93: ...13 0 21 69 141 13 2 66 141 12 5 63 140 11 9 19 63 135 11 9 60 134 11 4 57 132 10 9 2300 25 80 151 15 1 76 151 14 4 72 150 13 6 23 73 145 13 9 70 145 13 2 66 144 12 6 21 67 139 12 7 63 138 12 1 60 137 11 5 19 60 132 11 5 57 131 11 0 54 129 10 5 2200 25 77 148 14 6 73 148 13 8 69 147 13 1 23 70 142 13 4 67 142 12 7 63 141 12 1 21 64 136 12 2 61 135 11 6 58 133 11 1 19 58 129 11 1 55 128 10 6 52 125 ...

Page 94: ... 148 141 135 15 1 13 9 12 7 11 6 75 70 64 58 153 147 141 133 14 3 13 2 12 1 11 1 72 66 60 55 152 146 139 131 13 6 12 6 11 5 10 6 2200 25 23 21 19 76 70 64 58 150 145 139 132 14 5 13 4 12 3 11 2 73 67 61 56 150 144 138 130 13 8 12 7 11 7 10 7 69 64 58 53 149 143 136 128 13 1 12 1 11 1 10 2 2100 25 23 21 19 17 73 68 62 56 50 148 142 136 129 120 14 0 12 9 11 8 10 8 9 8 70 64 59 53 48 147 141 135 127 ...

Page 95: ...57 151 145 138 14 6 13 6 12 5 11 5 73 68 62 57 156 150 143 136 13 9 12 9 11 9 10 9 2300 25 23 21 19 78 73 67 61 155 149 143 137 14 9 13 8 12 7 11 6 74 69 63 58 155 149 142 135 14 1 13 1 12 1 11 1 71 65 60 55 154 147 141 133 13 4 12 4 11 5 10 6 2200 25 23 21 19 76 70 64 59 152 14 4 147 13 3 141 i 12 2 134 11 2 72 67 61 56 152 146 140 132 13 7 12 6 11 7 10 7 68 63 58 53 151 145 138 129 12 9 12 0 11 ...

Page 96: ... 155 13 3 23 72 152 13 7 69 151 13 0 65 149 12 4 21 67 146 12 7 63 145 12 1 60 142 11 5 19 61 139 11 7 58 137 11 1 55 134 10 6 2200 25 75 154 14 2 71 154 13 5 68 152 12 8 23 70 149 13 2 66 148 12 6 63 146 12 0 21 64 143 12 2 61 142 11 7 58 139 11 1 19 59 136 11 3 56 134 10 8 53 131 10 3 2100 25 72 152 13 8 69 151 13 1 65 150 12 4 I 23 67 146 12 8 64 45 12 2 61 143 11 6 21 62 140 118 59 1 19 11 3 5...

Page 97: ...and the distance during a normal climb up to 12 000 feet and maximum climb above 12 000 feet 20 000 16 000 I w w l L 12 000 w 0 J I 8000 I J 4000 S L 158 147 I I 112 3 KTAS KTAS KTAS KTAS 145 135 1 124 f 110 f f KTAS vKTAS t KTAS t KTAS f f f f 0 0 ex w w U I f 3 3 3 1 1 1 I 0 0 0 0 0 1 1 D LO I 115 iF 1 1 I lO lO lO It l 133 I 125 i 104 c KTAS I KTAS t KTAS KTAS 450 500 550 600 650 700 RANGE NAUT...

Page 98: ...00 feet and maximum climb above 12 000 feet f LJJ LJJ LL w 0 f f t I 20 000 16 000 12 000 8000 4000 J S L I I r 158 _ 147 112 I II KTAS KTAS 133 f KTAS I _L l _ _Lt KTAS I I 1 1 I I l I fr_l L I Ll t l I 1 I 145 I 135 124 I 110 I KTASJ KTAS KTAS 1 1 KTAS a _ a I I a 0 I I I I UJ 61 61 ll 3 1 0 0 o J Q Q 0 til I f 1 oR I II I I CDI trll t I il I I I 1 t 115 133 T rt 125 i I 104 j KTAS I V KTAS I KT...

Page 99: ... for engine start taxi takeoff and climb and the time during a normal climb up to 12 000 feet and maximum climb above 12 000 feet I w W L L w o J I i J l 5 6 7 ENDURANCE HOURS 20 000 r r nrr r T I I I I I I 1 16 000 I f t JH f If I l l 12 000 I 1 I I 1 I I I I I I I I I I I I I 1 8000 ilil t f 7f l 4000 W I I l l H 1 t i r rIH t1i S L I I I 1 I I I 3 4 1 1 Figure 5 10 Endurance Profile Sheet 1 of ...

Page 100: ... This chart allows for the fuel used for engine start taxi takeoff and climb and the time during a normal climb up to 12 000 feet and maximum climb above 12 000 feet 20 000 16 000 I LU LU u 12 000 I LU 0 I 8000 I l i 4000 S L I _0 0 Ul Ul 3 3 6 6 0 0 0 0 0 0 r if if l l l l l l iI r 0 l l 1 Ic 4 5 6 7 8 9 ENDURANCE HOURS Figure 5 10 Endurance Profile Sheet 2 of 2 5 32 21 August 1981 ...

Page 101: ... the approach speed by 9 KIAS and allow for 40 longer dis n Y SPEED OOC 10 C 20 C 30 C PRESS WEIGHT AT ALT LBS 50 FT TOTAL TOTAL TOTAL TOTAL KIAS FT 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 2950 61 S L 560 1300 580 1335 600 1365 620 1400 1000 580 1335 600 1365 620 1400 645 1440 2000 600 1370 625 1405 645 1440 670 1480 3000 ...

Page 102: ...ALANCE EQUIPMENT LIST SECTION 6 WEIGHT BALANCE EQUIPMENT LIST TABLE OF CONTENTS Page Introduction 6 3 Airplane Weighing Procedures 6 3 Weight And Balance 6 6 Baggage and Cargo Tie Down 6 6 Equipment List 6 15 21 Aueust 1981 6 1 6 2 blank ...

Page 103: ...eight E Old Useful Load 1919 306 Pounds 37 09 Inches 71190 3 loch Pounds 3112 Pounds 1192 69 Pounds A New Empty Weight 1924 266 Pounds B New Empty CG 37 33812 Inches C New Empty Weight CG Moment 71848 47 Inch Pounds D Max Gross Weight 3112 Pounds E New Useful Load 1 18 7 73 47 Pounds This new weight balance information supersedes all previous weight and balance data For aircraft loading see instru...

Page 104: ...he following equipment Dorne Margolin ELT 6 1 1 90 153 00 290 70 ELT Antenna 0 13 145 00 18 13 Installed the following equipment Artex G406 4 ELT sIn 170 01894 4 40 145 00 638 00 Remote Switch pIn 345 6196 04 0 10 15 00 1 50 406 Whip Antenna pIn 110 329 0 16 145 00 22 62 Whip Antenna wllnductor pIn 110 324 0 13 153 00 19 13 453 6500 ELT NAV Interface sIn 06539 2 70 145 00 391 50 TOTAL 1919 306 37 ...

Page 105: ...ngine oil as required to obtain a normal full indica tion 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 6 1 ...

Page 106: ...ht 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 Weight Lbs X C G Arm In Moment 1 000 Lbs In Airplane Weight From Item 5 Page 6 3 Add Unusable Fuel 4 Gal at 6 Lbs Gal 24 48 0 1 2 Equipment Changes Airplane Basic Empty Weight J Figure 6 1 Sample Airplane Weighing 21 August 1981 6 4 ...

Page 107: ...pment Affecting Weight and Balance Otl c C AIRPLM ODEL I SERIAL NUMBER I PAGE WE IGHT CHANGE ITEM NO r ADDED 1 REMOVED DATE DESCRIPTION OF ARTICLE OR MODIFICATION WI Arm Moment WI Arm Moment In Out lb In 11000 lb In 11000 As Delivered rJl c D 00 1 Figure 6 2 Sample Weight and Balance Record ...

Page 108: ...the loading problem NOTE Loading Graph information for the pilot passengers and baggage cargo is based on seats positioned for average occupants and baggage cargo items loaded in the center of these areas as shown on the Loading Arrangements dia gram 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 ran...

Page 109: ... bottom of the forward portion of the shelf area and the eyebolts near the upper forward surface of the shelf area should be used Cargo tie down blocks and latch assemblies are available from any Cessna Dealer if it is desired to remove the rear seat and child s seat if installed and utilize the rear cabin area to haul cargo Two tie down blocks may be clamped to the aft end of the two outboard fro...

Page 110: ... occupant center of gravity range 11 AArms measured to the center of the areas shown NOTES 1 The usable fuel e G arm is located at station 46 5 2 The aft baggage wall approximate station 134 can be used as a convenient interior reference point for determining the location of baggage area fuselage stations e G e G e G ARM ARM ARM 37 37 37 32 501 32 50 1325 CARGO 74 74 74 BAGGAGE A 97 97 97 116 AGEB...

Page 111: ...MENSIONS WIDTH TOP CABIN DOOR I32 BAGGAGE DOOR 15 I WIDTH IHEIGHT BOTTOM FRONT I 36 1 I 41 15 1 22 IHEIGHT REAR I 38Y 20 1 WIDTH eLWR WINDOW LINE CABIN FLOOR CABIN WIDTH MEASUREMENTS REAR DOOR POST BULKHEAD r m OWNRINGS 81 7 1 Iv 1 1 42 36 1 1 l CABIN I I I I I I I I I STATIONS 0 40 50 60 70 80 90 100 C G ARMSI 65 3 Figure 6 4 Internal Cabin Dimensions 21 August 1981 6 9 ...

Page 112: ...aximum 7 Baggage Area C Sta 124 to 134 80 Lbs Maximum 1815 64 0 I q I i 528 24 6 lfD i 3 fD If d 340 12 6 oo IS C 340 25 2 00 I 70 6 8 50 0 19 2 2 5 G 8 RAMP WEIGHT AND MOMENT 3112 135 4 9 Fuel allowance for engine start taxi and runup 12 6 10 TAKEOFF WEIGHT AND MOMENT Subtract step 9 from step 8 3100 134 8 oo l no 11 Locate this point 3100 at 134 8 on the Center of Gravity Moment Envelope and sin...

Page 113: ...ight Ibs Moment lb ins 11000 Weight Ibs Moment lb ins 11000 Weight Ibs Moment lb ins 11000 I When several loading configurations are representative of your operations it may be useful to fill out one or more of the above columns so that specific loadings are available at a glance Figure 6 5 Sample Loading Problem Sheet 2 of 2 21 August 198 1 6 11 ...

Page 114: ...A B I BO LBS MAX 20 1 7 37 9 BAGGAGE AREA C 80 LB M X j 011 lIJ o 5 10 15 20 25 30 LOAD MOMENT lOoo POUND INCHES NOTE 1 Line representing adjustable seats sh ws pilot and front seat passenger center 350 400 25 22 r J 20 f 17 12 10 75 50 25 o of gravity on adjustable seats positioned for an average occupant Refer to the rn Loading Arrangements diagram for forward and aft limits of occupant C G rang...

Page 115: ...0 l 2600 z 6 2700 t J 2600 W w 2500 z J 2400 o 2300 o CODE J 2200 _____ TAKEOFF AND LAND ILL TAKEOFF ONLY 2100 If takeoH weight is more than landing weight of 2950 pounds 2000 1 allow flight time for fuel burn off to 2950 pounds before landing 1900 1600 40 55 60 65 70 75 eo 85 90 95 100 105 110 115 i20 125 130 135 LOADED AIRPLANE MOMENT l000 POUND INCHES VJ Figure 6 7 Center of Gravity Moment Enve...

Page 116: ... ONLY 2500 w If takeoff weight is more than z landing weight of 2950 pounds J allow flight time for fuel burn oH 2400 lr to 2950 pounds before landing_ 0 w 2300 0 0 J 2200 CENTER OF GRAVITY LIMITS II II 2100 2000 1900 r l 1800 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 AIRPLANE C G LOCATION INCHES AFT OF DATUM STA 0 01 fJJ M CO 00 Figure 6 8 Center of Gravity Limits t ...

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: ...ELLER TURBOCHARG R ASSEMbLY TAOIt TURBOCHARGER WA TEGATE ASSEMeLY TURBOCHARGER OVERbOOST RELIEF VALVE VACUUM SYSTEM ENGINE URIVEN I NGIN LYCOMING 0 540 LjC50 b NUIX MAGN TO IMPUL COUPLING CARbURETOR MARVEL SCHEBLER STARTER PRE lOLITE 24 VOLT SPARK PLUGS SHl LO D FUtL PUMP FILTEk CARbUR TOR AIk ALT RNATUR La VOLT oe AMP ALT RNATOR INSTL 95 AMP ALTtRNATOR 2250Co DbLN 2031 TYP HA 6 MHb 401U RHb HE 1 ...

Page 119: ...NG IN lALLAIIUN WHE EL I SE T Of 3 NUSf whEE L AIKINv MAIN WHE cL AlI ING I eACH bRA E Ul C Al INv ItACH IAXLt SIANuAKu uulY MAIN GtAk ISE T OF 2 AXLE htAVY DUTy MAIN bE AK SE T OF 2 C E LtClkICAL SYSIE MS tlATTE kY It VOLT SlANUAKD DUlY bATTI I Y It VULT l tAVY DUlY ALTE kNATOK CONlRUL UNIT 28 VOLT REF DRAWING C 31003 101 5 1951 5 C163019tlOL06 C163006 o 103 C163032 0 L05 C163032 0206 C262003 020...

Page 120: ...S NAVI ATION LIGHT ISET OF 21 0700615 14 0101013 0 NEG C 3 A OMNI FLA hING BtALON LIGHT LIGHT A SY IN fIN TIPI 01010 2 40 C621001 o102 1 0 FLASHER ASSV IN AFT TAIL CONEI C594502 o102 0 LOADING RtSI TOR OR 95 6 0 C46 A STROBE Ll hT WHIT lEACH WING lIPI POWER SUPPLY AtKOfLASH 152 00091 2201008 1 Cb22008 o102 2 2 LIGHT A Y Aa ROFLASH 73 1451 121 C622006 o101 0 C49 Ll HT INSTL COWL MOUNTED LANDING TAX...

Page 121: ...1005 1 1 02 C OCK i LEClKIL DIAL REAU C6b4508 l102 0 3 025 0 CLOCK ELECTRIC ulGITAL READOUT Cbb45U J 102 0 3 D28 R COMPASS i lAbNETIC MOUNT 1213b79 3 1 1 034 R IN TRUMENl LLUSTER l NGINE FUEL I Cbo95 t5 J lOll 1 3 049 S INDICATOR INSTL i CUNOMY MIXTU i EGTI HMPI KAluRE INOICATQ R V Sk h_ E1e c 2205008 1 Cb68501 J211 0 1 0 4 THERMUCOuPLE PRObE u 1 r THI Ki lOCOUP t Ll AO WIKi ICI C66d501 J204 Cbb85...

Page 122: ...RDINATOR f Ok NOM S INDICATOR TUkN t BANK INDICATOR VERTl AL SPEED t CAbIN ACCOMMODATIONS ADJU TABLE FURE AfT PILOT ARlICuLATIN VERT ADJ PILOT ADJUSlABLE f UH f AFT CO PILOT ARTiCULATING VtKT ADJ CO PILOT SEAT BELT 2ND ROW Bf NCh INSTALLATION AuXIL FACTUf Y IN TALLt D A SY fULDAWAY ASSY LAP IARY 1120 C LB HILDS MAX CAP sS t J tit I REF DRAWING Coo1070 102 2201004 1 Cb04503 10 I SI111 1 Co08507 101...

Page 123: ... R INE T CHANGtl I INTE RlUK uPhLJLSlkY SlD PANtL LEATHER STYLING NET CHANGE 1 0 1 0 E3S A SI 11 41 t RIOR UPHOLSTRY SIDE PANEL LEATHER AND I VINYL ffi F AbR Ie STy ING NET CHANGE e ES llS4 0 5 E37 0 OPENABLE KH CAbIN UOOR WINDOW INET CI1A E I 07010c 5 o 2 3 E39 A WINDOWS OVERHtAu e ABIN TOP INET CHANGE 0701017 4 0 6 E 43 A VENIILATIUN YSTI M NO RUW SEATING 220l041 1 2 4 E47 S OXYGEN SYSTEM PROVIS...

Page 124: ...AND CONTROLS INSTALLATION INSTLu ARA WITH IS lARA I CONTROL WHHL PILOT ALL PURPOSE INCLUDES CONTROL WhEEL MAP LIGhT MIKE SWITCH I h ATING YSlt I CABIN CARB ETOR AIR INCLUDt S t N INE eXHAUST SYSTeM F PLACARDS WAKNINGS MANUALS I REF DRAWING 1215073 1 0514166 1 0715083 1 1215171 1 0760101 10 0701128 C 13001 o115 0519159 C701128 C413001 oU5 0519159 2260126 1 I 0750201 WT lBS I 0 9 1 0 0 1 0 5 7 3 81 ...

Page 125: ...T FACTORY INSTALLEO CORROSIuN PKOOFIN6 INTERNAL STAlIC DISChARGERS SET OF 10 TA6ILiZEK A KASIDN OOTS TOWBAR AIRCRAFT ISTOWeD ARM hOwN PAINT OVERALL EXTEKluK ODIfIED POLY URETHANE OVERALL WhiTe ASE COLORED STKIPE CABLeS CURRUSION R ISTANT NET CHANGE FIRE EXTINbuiSHER HANU TfPE FOR USE WITH STANDARD PILOT SEAT FIKE eXTINGUISHeR HAND TYPE FOR USE WITH VeRTICAL ADJUSTING PILUT SEAT REFUELINb ASSIST lE...

Page 126: ...INf BOx MIse ITEMS I AM FM STEREO REl E IVEK CASSE TTE PLAYER HEADStT lS T uf 2 4 MAY BE U D ARM IS fOR OCCUPANT POSITION STEREO RtCI IVEK INSTL ANTENNA MISl ITEMS I COLLINS UME OC RECEIVER TRANSMITTER TCR 451 iNDICATOR CONTkOL IN0 450C ANTENNA ANT 451 I CESSNA 400 uMe INSTALLATION RECEIVER TRANSMIlltR AND MOUNT INDICATOR ANTEIliNA ICESSNA 400 R NAV USED WITH NAV COM AND DM IIINOICATUR NET CHANGE ...

Page 127: ... ITEM H07 A ONL ARCI LS INDICATOR IN 38bAC ADDED VOR ILS INDICATOR IN 386A DELETI D Hll A 1SUNAIR SSfl HF lRANSCt lVER l2ND UNIT RE I000 INGLE SIDE BAND XCVR ASB 125 PAI010A REMOTt POWER AMPLIFIE CU I10 ANTI NNA COUPLE LOAD BOX ANTENNA INSTL 351 INCH LONG H13 A ICESSNA OO MA Kl k bl ACON RECEIVER lR OlA ANTENNA FLUSH MOUNTED IN TAILCONE Hlb A I CESSNA 400 TRANSPUNDER RECEIV K TRANSMITTER RT 459A A...

Page 128: ...1 ANTENNA AS Y H28 A 2 IEMERGENCY LOCATuR TRANSMITTER USED IN H31 A l N l rJl J X H31 A 2 CANAuA TRAN Ml1TtR A S1 0 M DMELT b lCI ANTENNA INAV o MATIC 200A INSTALLATIuN CAf 295BI CCNTRwLLlR AMPLlflER TURN COOKuINAIOR CU88 0 11 wING LKVD iNSTALLATION 088 5 1 TUk COUROINATOR DELETED INAV O MATIC 300A IN TALLATION AF 395 AI eONTRuLLtR AM LIfI R C 395AI GYRO INSTALLATION CNET CHANGE I D88 0 1 lURN COO...

Page 129: ... BY AND AVAIL ABLE WITH 1ST UNIT ONLY CABIN SPEAKeR INS IL RADIO COOLING FAN INSTL RAlII0 ceOLIN TUbING NOISe FILltR ON ALTERNAToRJ RECtIV R INSTALLATION KIT CAbLe FOR COM ANTENNA CABLE FUR OMNI ANTENNA OMNI ANl NNA INSIALLATION COM ANTtNNA KH PIKE ON CAbiN TOP AUDIO CUNTkOL PANEL AND WIRING HEAOStT INSTALLATION MICRUPHONE INSTALLATION 3910180 8 0770750 741 3930216 1 393021 6 2 3940148 2 3930186 3...

Page 130: ...blNAT ION PAGOEO C596531 0101 1 H50 A Ht ALJSET f UR SH NEL NEAR SET 21 C590 2 0101 H64 A AVIONICS OPTION At PKOVl IONS FOR SINGLE NAV COM AVAILAbL ON EXPORT A C ONLY CAI lIN SPf AKEk CAbLE KH VhF COM ANTENNA CAbU INSTL VhF OMNl NAVIGATION COM ANTtNNA VhF kf I SIDE OMNI ANTENNA ON VtkTICAL FINI HEADPHONE INSTALLATIUN MIKt IN TALLATION 391020D 11 0770750 Hl 39 0126 40 3950120 51 3960113 2 396G142 0...

Page 131: ... 546E I Mlo A LE S NA 400 TRANSPONDER RT 459A h22 A l Ct NA 3uO NAV COM RT 385A H 2l l A 1 t L T H31 A l LI NA iUUA AuTOPILOT h34 A bA IC AVIONICS KIT 2270017 2 3930210 0700015 1 t 0701013 070 10 t2 1201108 22 070 101 10 391015 1 1 39lCa2b U 3 101b3 0 t70419 27 j910102 15 39101l l6 2 0 0 NE 1 l U 7 7 t 7 3 8 8 J04 A INAV PAL TUKbU KYLANI II ONLY I NE T CHAN t ti U7 A 400 GLIDI LOPI IR 4 t3A H IrA ...

Page 132: ...s 7 12 Shoulder Harnesses 7 13 Integrated Seat Belt Shoulder Harnesses With Inertia Reels 7 13 Entrance Doors And Cabin Windows 7 15 Control Locks 7 16 Engine 7 16 Engine Controls 7 16 Engine Instruments 7 17 New Engine Break In And Operation 7 19 Engine Oil System 7 19 Ignition Starter System 7 19 Air Induction System 7 20 Exhaust System 7 20 Carburetor And Priming System 7 21 Cooling System 7 21...

Page 133: ...hting 7 33 Interior Lighting 7 33 Ca bin Heating Ventilating And Defrosting System 7 35 Pitot Static System And Instruments 7 37 Airspeed Indicator 7 38 Vertical Speed Indicator 7 38 Altimeter 7 38 Va cuum System And Instruments 7 38 Attitude Indicator 7 40 Directional Indicator 7 40 Suction Gage 7 40 Stall Warning System 7 40 Avionics Support Equipment 7 41 Avionics Cooling Fan 7 41 Microphone He...

Page 134: ...re 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 hinged ailerons and single slot type flaps are attached to the trailing edge of the wings The ailerons are constructed of a forward spar containing balance weights fo...

Page 135: ...SECTION 7 CESSNA AIRPLANE SYSTEMS DESCRIPTIONS MODEL T182 AILERON CONTROL SYSTEM RUDDER AND RUDDER TRIM CONTROL SYSTEMS Figure 7 1 Flight Control and Trim Systems Sheet 1 of 2 21 August 1981 7 4 ...

Page 136: ...CESSNA SECTION 7 MODEL T182 AIRPLANE SYSTEMS DESCRIPTIONS ELEVATOR CONTROL SYSTEM ELEVATOR TRIM CONTROL SYSTEM Figure 7 1 Flight Control and Trim Systems Sheet 2 of 2 21 August 1981 7 5 ...

Page 137: ... r nE r n l rilril 00 0 r n Z 0 E P p 0 r n ril 0 r n ril E r n r n c 3 ril ZZ O t l E P Op ril r n t 0 Ol Ol c Q l Il P l Ol E l Ul l cJ Ol l blI r 61 BI L1 9l I vI I II It 01 6 B v l OCJ m Ul l blI l t C J 0 ...

Page 138: ...uel Selector Light 15 Marker Beacon Indicator Lights 42 Fuel Selector Valve Handle i d a and Switches 43 Rudder Trim Control Wheel t J 1 16 DME and Position Indicator l Z rt 17 Audio Control Panel 44 Elevator Trim Control Wheel and trl I d 18 NAV COM Radios Position Indicator 0 l 19 ADF Radio 45 Carburetor Heat Control J 20 Transponder 46 Static Pressure Alternate J en 2I Manifold Pressure Fuel Pr...

Page 139: ...tall 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 remOVb the extensions reverse the above procedures TRIM SYSTEMS Manually operated rudder and elevator trim is provided see figure 7 1 Rudder trimming is accomplished through a bungee connected to ...

Page 140: ...ls 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 bracket The fuel selector valve handle is located at the base of the pedestal A parking brake handle is mounted below the switch and control panel in front of the pilot A static pressure alternate source valve is installed below the...

Page 141: ...e 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 and control panel to the desired flap deflection position The switch lever is moved up or down in a slotted panel that provides mechanical stops...

Page 142: ...o Section 6 When loading the airplane children should not be placed or permitted in the baggage compartment and any material that might be hazardous to the airplane or occupants should not be placed anywhere in the airplane For baggage area and door dimensions refer to Section 6 SEATS The seating arrangement consists of two individually adjustable four way or six way seats for the pilot and front ...

Page 143: ...r lock release button is pushed up A child s seat may be installed aft of the rear passengers seat and is held in place by two brackets mounted on the floorboard The seat is designed to swing upward into a stowed position against the aft cabin bulkhead when not in use To stow the seat rotate the seat bottom up and aft as far as it will go When not in use the seat should be kept in the stowed posit...

Page 144: ...r harness fasten and adjust the seat belt first Lengthen the harness as required by pulling on the connecting link on the end of the harness and the narrow release strap Snap the connecting link firmly onto the retaining stud on the seat belt link half Then adjust to length A properly adjusted harness will permit the occupant to lean forward enough to sit completely erect but prevent excessive for...

Page 145: ...E NAI1ROW fiELEASE STI1J P i Pull up hen lenb 1henjlll harness i n EE END Of HARNESS Pu down 10 lIghten SHOUI DER HAfiNESS CONNECTING LINK inap onlu l dainilll stud Illl SI I I 1 11 1 1 SHOIII I o H lIi 1Wl SS D IIIST lll I INK POl IlI 111 hllk JllSl 11 lllMllllt r 11 1 1 111 ltll tIltl h lnw I I WI1 wanl ltl ClJIHIl l l til sC J 1 h U huckld I j SEA T lit J r BUCK LE NHll arllll talll Figure 7 4 ...

Page 146: ...the pilot and front passenger doors be extended out whenever the doors are open When closing the door do not attempt to push the door handle in until the door is fully shut To open the doors from outside the airplane utilize the recessed door handle near the aft edge of each door Grasp the forward end of the handle and pull outboard To close or open the doors from inside the airplane use the combi...

Page 147: ...ck align the hole in the right side of the pilot s control wheel shaft with the hole in the right side of the shaft collar on the instrument panel and insert the rod into the aligned holes Installa tion of the lock will secure the ailerons in a neutral position and the elevators in a slightly trailing edge down position Proper installation of the lock will place the flag over the ignition switch I...

Page 148: ...lock button in the end of the knob The rich position is full forward and full aft is the idle cut off position For small adjustments the control may be moved forward by rotating the knob clockwise and aft by rotating the knob counterclockwise For rapid or large adjustments the knob may be moved forward or aft by depressing the lock button in the end of the control and then positioning the control ...

Page 149: ...panel above the tachome ter The gage indicates fuel pressure to the carburetor Gage markings indicate that minimum pressure is 3 0 PSI red line normal operating range is 3 0 to 30 PSI green arc and maximum pressure is 30 PSI red line The economy mixture EGT indicator is located on the right side of the instrument panel A thermocouple probe in the left exhaust collector assembly measures exhaust ga...

Page 150: ...pter in the full flow oil filter is equipped with a bypass valve which will cause lubricating oil to bypass the filter in the event the filter becomes plugged or the oil temperature is extremely cold An oil dipstick is located at the rear of the engine on the right side and an oil filler tube is on top of the crankcase near the front of the engine The dipstick and oil filler are accessible through...

Page 151: ...inders In the event carburetor ice is encountered or the induction air filter becomes blocked alternate heated air may be obtained from a shroud which covers the exhaust manifold located on the left side of the engine The shroud receives unfiltered air from inside the engine cowling After the airflow passes through the shroud it is ducted to a valve in the airbox operated by a control knob labeled...

Page 152: ... front of the engine cowling The cooling air is directed around the cylinders by baffling and through the remote oil cooler and is then exhausted through cowl flaps on the lower aft edge of the cowling The cowl flaps are mechanically operated from the cabin by means of a cowl flap lever on the right side of the control pedestal The pedestal is labeled OPEN COWL FLAPS CLOSED Before starting the eng...

Page 153: ...have an effect on the engine However if the waste gate is still open its position can be changed manually with the throttle control figure 7 5 in order to maintain a constant compressor discharge pressure The compressor has the capability of producing manifold pressures in excess of 31 in Hg In order not to exceed the maximum manifold pressure should be monitored closely and the throttle control a...

Page 154: ...OSITION ON POSITION CAUTION FULL WASTE GATE CLOSED CONTROL POSITION WILL NOT BE NECe5 c ARY TO MAINTAIN MAXIMUM ALlOWABLE MANIFOLD PRESSURE 1 1 IN HG 1 WITH A POSSIBLE EXCEPTION DURING HOT DAY CONDITIUNS Af tm iH AL IITUDE THROTTLE JJ _ 1 r FINAL 112 CONTROL lNtTtAL 2 CONTROL HROTTLE WAST WASTE GAT INli RCONNECT E GATe lRAVEL WASlE GATE TRAVEL THRorTll PORTION OF CONTROL por 1rON OF CONTROL 4 THRO...

Page 155: ...y above the maximum continuous manifold pressure of 31 in Hg This is most likely to be experienced during the takeoff roll or during a change to maximum continuous power in flight The compressor discharge pressure relief valve will normally limit the overboost to 2 to 3 inches An inadvertent overboost of 2 to 3 inches of manifold pressure is not considered detrimental to the engine as long as it i...

Page 156: ... The airplane fuel system see figure 7 6 consists of two vented integral fuel tanks one in each wing a four position selector valve fuel strainer manual primer auxiliary fuel pump engine driven fuel pump and carburetor Refer to figure 7 7 for fuel quantity data for the system Fuel flows by gravity from the two integral wing tanks to a four position selector valve labeled BOTH RIGHT LEFT and OFF Wi...

Page 157: ...9 1 M r IXTltHr LON1 HOL TO lNc WtL f tAXtMUM f U L 1 1 TY Will j HI lUI II r 1m M1NlM1 l CROSS Fl OINt Wt11 rJ j A fH 11lWI A IW 1 UHI L pv n THl fUrl C lLltIOH VAlVi 1 I tTIH H If r I fiJi HHil1l P I I lOtI TO Ef INE CONDIT10 J SYSTEM SHOWN I rII FUEL SELECTon VALVE IN UOTH POSITION 10 lNGINl Flit l PRE UA GAGE RIGHT HALF OF II DUAL INSTRUMENT CODE FuEL SUPPLY c J VENT c J MECHANICAL LINKAGE ELE...

Page 158: ...he letter E When an indicator shows an empty tank approximately 2 gallons remain in a tank as unusable fuel The indicators cannot be relied upon for accurate readings during skids slips or unusual flight attitudes If both indicator pointers should rapidly move to a zero reading check the cylinder head temperature and oil temperature gages for operation If these gages are not indicating an electric...

Page 159: ...re some sloshing of fuel between tanks can be expected when the tanks are nearly full and the wings are not level If a fuel tank quantity is completely exhausted in flight it is recom mended that the fuel selector valve be switched back to the BOTH position for the remainder of the flight This will allow some fuel from the fuller tank to transfer back through the selector valve to the empty tank w...

Page 160: ... 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 ELECTRICAL SYSTEM The airplane is equipped with a 28 volt direct current electr...

Page 161: ...OLUMINESCENT PANELS L lo a TO AUDIO W UTlNG RELAY 10 COlolrAOL WHHL MAP LIGHT TQPOSTLIGHTING CItA N S TO IHSTRUWENT CLUSTEA PEDESTAL liGHTING l T GLARE SHIELD MOUNTED MAP LIGHT COMPASS lIGHT GLARESHIHO LlGHTSAHO OXYGEN LIGHTS J TO FLASHING BEACON TOSTAOBELIGHTS TO AVIONICS CODlI G FAN TO TAXI LIGHT TO ELECTAIC fLEVATOR TRIM SYSTUI TO INSf LIGHTS CIRCUIT BREAKER TOHQAIZQHTALSlTUATIOH INDICATOR COD ...

Page 162: ...wall 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 of the 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 breake...

Page 163: ...meter 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 The warning light may be tested by turning on the landing lights and momentarily tu...

Page 164: ...upplements The courtesy lights are operated by a switch located on the 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 dr...

Page 165: ...for the digital readouts in the radio equipment This is accomplished by rotating the ENG RADIO knob full counterclockwise Check that the flood lights post lights and electroluminescent lights are turned off for day light operation by rotating the FLOOD POST and EL PANEL knobs full counterclockwise The control pedAstal has two integral lights and if the airplane is equipped with oxygen the overhead...

Page 166: ...be regulated by manipulation of the push pull CABIN HEAT and CABIN AIR control knobs see figure 7 9 Both control knobs are the double button type with locks to permit intermediate settings NOTE For improved partial heating on mild days pull out the CABIN AIR knob slightly when the CABIN HEAT knob is out This action increases the airflow through the system r increasing efficiency and blends cool ou...

Page 167: ...IR OUTlETS I VENTILATORS AIRFLOW ADJUSTMENT WHEElS ADJUSTABLE7 AIR OUTlETS n CABIN HEAT SHROUD VENTILATING AIR DOOR CABIN AIR CONTROL DEFROSTER CONTROL CODE J RAM AIR FLOW P VENTILATING AIR HEATED AIR BLENDED AIR MECHANICAL CONNECTION Figure 7 9 Cabin Heating Ventilating and Defrosting System 7 36 21 August 1981 ...

Page 168: ...imeter The system is composed of either an unheated or heated pitot tube mounted on the lower surface of the left wing two external static ports on the 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...

Page 169: ...ure 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 VERTICAL SPEED INDICATOR The vertical speed indicator depicts airplane rate of c...

Page 170: ...N LET AI R VENT LINE E 1 VACUUM DISCHARGE AI R ATTITUDE INDICATOR SUCTION GAGE mr j t 1 ______ l 1 DIRECTIONAL INDICATOR o 0 0 o 0 0 0 o 0 0 o 0 0 0 o 0 0 o co It I 1 VACUUM SYSTEM AIR FILTER I VACUUM PUMP VACUUM RE LI EF VALVE I ___ Figure 7 10 Vacuum System 21 August 1981 7 39 ...

Page 171: ...adjusted on extended flights A knob on the lower left edge of the instrument is used to adjust the compass card to correct for any precession 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 5 to 5 4 inches of mercury A suction...

Page 172: ...ibility of moisture contamination using an external cooling air source Power to the electric fan is supplied directly from a pull off type circuit breaker labeled STROBE AVN FAN located on the left switch and control panel Hence power is supplied to the fan anytime the master switch is ON This arrangement provides air circulation through the radios to remove a possible heat soak condition before t...

Page 173: ...uent IFR flights are planned installation of wick type static dischargers is recommended to improve radio communications during flight through dust or various forms of precipitation rain snow or ice crystals Under these conditions the build up and discharge of static electricity from the trailing edges of the wings rudder elevator propeller tips and radio antennas can result in loss of usable radi...

Page 174: ...gram Pilot Conducted Preventive Maintenance Alterations or Repairs Ground Handling Towing Parking Tie Down Jacking Leveling Flyable Storage Servicing Engine Oil Fuel Landing Gear Oxygen Cleaning and Care Windshield Windows Painted Surfaces Stabilizer Abrasion Boot Care Propeller Care Engine Care Interior Care Bulb Replacement During Flight 21 August 1981 Page 8 3 8 3 8 3 8 3 8 4 8 5 8 5 8 6 8 6 8 ...

Page 175: ...Number 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 of the airplane The code may be used in conjunction with an applicable Parts Catalog if finish and trim information is ...

Page 176: ...ich he keeps on hand He will be happy to place an order for any item which is not in stock NOTE I 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 contain ing the owner s name airplane serial num...

Page 177: ... 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 PERIODS FAA REQUIRED INSPECTIONS As required by Federal Aviation ...

Page 178: ...ons 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 200 hours or more per year and the 100 hour inspection for all other airplanes The procedures for the Progressive Care P...

Page 179: ...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 for a list of the specific maintenance operations which are allowed NOTE Pilots op...

Page 180: ...itions 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 airplane securely proceed as follows 1 Set the parking brake and install the control wheel lock 2 Install a surface control lock over the fin and rudder 3 Tie sufficiently strong ropes or chains ...

Page 181: ... stands or supports under weight supporting bulkheads near the nose of the 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 t...

Page 182: ... or testing at special intervals Since Cessna Dealers conduct all service inspection 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 require...

Page 183: ...s required OIL AND OIL FILTER CHANGE After the first 25 hours of operation drain engine oil sump and change the filter Refill 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 100 hour inte...

Page 184: ...e added to the fuel supply in quantities not to exceed 1 or 15 by volume respectively of the total Refer to Fuel Additives in later paragraphs for additional informa tion CAPACITY EACH TANK 46 0 U S Gallons t REDUCED CAPACITY EACH TANK WHEN FILLED TO BOTTOM OF FUEL FILLER NECK 34 5 U S Gallons NOTE To ensure maximum fuel capacity when refueling and minimize cross feeding when parked on a sloping s...

Page 185: ...g temperature depressant effect Alcohol if used is to be blended with the fuel in a concentration of 1 by volume Concentrations greater than 1 are not recommended since they can be detrimental to fuel tank materials The manner in which the alcohol is added to the fuel is significant because alcohol is most effective when it is completely dissolved in the fuel To ensure proper mixing the following ...

Page 186: ...ioration of protective primer and sealants and damage to O rings and seals in the fuel system and engine components Use only blending equipment that is recommended by the manufac turer to obtain proper proportioning CAUTION Do not allow the concentrated EGME compound to come in contact with the airplane finish or fuel cell as damage can result Prolonged storage of the airplane will result in a wat...

Page 187: ...rrect grade Do not fly the airplane with contaminated or unapproved fuel In addition Owners Operators who are not acquainted with a particu lar fixed base operator should be assured that the fuel supply has been checked for contamination and is properly filtered before allowing the airplane to be serviced Also fuel tanks should be kept full between flights provided weight and balance consideration...

Page 188: ...aze Follow by carefully washing with a mild detergent and plenty of water Rinse thoroughly then dry with a clean moist chamois Do not rub the plastic with a dry cloth since this builds up an electrostatic charge which attracts dust Waxing with a good commercial wax will finish the cleaning job A thin even coat of wax polished out by hand with clean soft flannel cloths will fill in minor scratches ...

Page 189: ...he isopropyl alcohol away from the windshield and cabin windows since it will attack the plastic and may cause it to craze STABILIZER ABRASION BOOT CARE If the airplane is equipped with stabilizer abrasion boots keep them clean and free from oil and grease which can swell the rubber Wash them with mild soap and water using Form Tech AC cleaner or naphtha to remove stubborn grease Do not scrub the ...

Page 190: ...h household spot removers used sparingly Before using any solvent read the instructions on the container and test it on an obscure place on the fabric to be cleaned Never saturate the fabric with a volatile solvent it may damage the padding and backing materials Soiled upholstery and carpet may be cleaned with foam type deter gent used according to the manufacturer s instructions To minimize wetti...

Page 191: ...or this airplane CONTROL WHEEL MAP LIGHT Grasp rim of bulb push straight up and turn counterclockwise as far as possible then pull bulb straight down and out of socket Replace with 24RB bulb To install new bulb in socket align pins on bulb with slots in socket then push straight up and rotate bulb clockwise as far as possible POST LIGHTS Grasp lens cap and pull straight out from socket Pull bulb f...

Page 192: ...B 125 14 Unslaved Horizontal Situation Indicator Type IG 832C 15 200A Navomatic Autopilot Type AF 295B 16 300 ADF Type R 546E 17 300 Nav Com Type RT 385A 18 300 Nav Com Type RT 385A With 400 Area Navigation System Type RN 478A 19 300A Navomatic Autopilot Type AF 395A 20 400 ADF Type R 446A 21 400 Area Navigation System Type RN 478A 22 400 DME Type R 476A 23 400 Glide Slope Type R 443B 24 400 Marke...

Page 193: ...ystem Type RN 478A 400 Nav Com Type RT 485B With 400 Area Navigation System Type RN 478A 400 Transponder Type RT 459A And Optional Altitude Encoder Blind With Optional DENT Switch 400 Transponder Type RT 459A And Optional Encoding Altimeter Type EA 401A With Optional IDENT Switch 10 pages 12 pages 6 pages 6 pages 21 August 1981 9 2 ...

Page 194: ...s are classified under the headings of General and Avionics and have b en provided with reference numbers Also the supplements 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 conta...

Page 195: ...e attached to the Pilot s Operating Handbook FAA Approved Airplane Flight Manual when the Secondary Seat Stop modification is installed in accordance with Cessna Single Engine Service Bulletin SEB89 2 The information contained herein supplements or supersedes the information of the basic Pilot s Operating Handbook FAA Approved Airplane Flight Manual and Checklists For limitations procedures and pe...

Page 196: ...ondary stop may be slightly aft of the entire seat or it may be in a position forward of the aft roller or one of the tabs on the seat stop plate when the seat is adjusted to the desired flight position Regardless of where the seat i positioned rearward seat travel will be restricted in the event the sea l occupant fails to lock the seat in position by normal means When rearward seat movement is d...

Page 197: ...t On airplanes with a floorboard tunnel the retainer shape is modified to clear all tunnel structure rrm RETAINER AIRPLANES WITHOUT FLOORBOARD TUNNEL EAT STOP LEVER ENGAGED POSITION TYPICAL SEAT PEDESTAL OR SEAT FRAME POSITIONED FULL FORWARD ON SEAT RAIL 0 0 r __m J Lf U J L _ II _ c__ SEAT STOP AFT SEAT SEAT STOP LEVER ROLLER PLATE TAB Figure 1 Secondary Seat Stop Installation Original Issue 3 ...

Page 198: ...ment of the seat will be stopped when the aft roller housing on the seat contacts the secondary seat stop Then momentarily unlatch the secondary seat stop and move the seat farther aft to test that each seat stop plate tab contacts the secondary seat stop to restrict seat movement When the seat is again moved full forward the secondary seat stop should momentarily rotate to an unlatched position t...

Page 199: ... 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 of the back light is controlled by the ENG RADIO lights rheostat In addition the display incorporates a test function s...

Page 200: ...own 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 pres...

Page 201: ...econds lated total Figure 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 P...

Page 202: ...ut 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 blin...

Page 203: ...amage to the avionics equipment by transient voltage Do not crank or start the engine with the avionics power switch turned on A special fused circuit is included with the ground service plug receptacle which will close the battery contactor when external power is applied with the master switch turned on This circuit is intended as a servicing aid when battery power is too low to close the contact...

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 I WARNING When turning on the master switch using an external power source or pulling the propeller through by ha...

Page 205: ...engine start and removal of the external power source if there is any question as to the condition of the battery 1 Master Switch OFF 2 Taxi and Landing Light Switches ON 3 Engine RPM REDUCE to idle 4 Master Switch ON with taxi and landing lights turned on 5 Engine RPM INCREASE to approximately 1500 RPM 6 Ammeter and Low Voltage Warning Light CHECK NOTE If the ammeter does not show a charge or the...

Page 206: ...r the pilot and three disposable type masks are 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 a red band adjacent to the plug in fitting The passenger hoses are color coded with an orange band If the airpla...

Page 207: ...nge of alti tude The oxygen cylinder when fully charged contains approximately 48 cubic feet of oxygen under a pressure of 1800 psi at 70 F 21 C 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 Fi...

Page 208: ...oded oxygen line fitting 1 I and passengers with orange color I I I h coded line fittings_ I h I 200 1 l I l jf H H l I IH I 1 1 1 I I I I I I T I T i j1 l I i I 4 I I J I o o 2 3 4 5 6 7 8 9 OXYGEN DURATION HOURS 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 l bove 12 500 feet...

Page 209: ...ilot only for nearly 4 hours and 10 minutes The same pressure will sustain the pilot and three passengers for approximately 1 hour and 20 minutes NOTE The Oxygen Duration Chart is based on a standard config uration oxygen system having one red color coded hose assembly for the pilot and orange color coded hoses for the passengers If red color coded hoses are provided for pilot and passengers it wi...

Page 210: ... Adjustmask 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 Oxygen Supply Control Knob ON 4 Face Mask Hose Flow Indicator CHECK Oxygen is flowing if the indicator is being ...

Page 211: ...off type circuit breaker labeled STROBEl AVN FAN The rocker switch and circuit breaker are located on the left side of the switch and control panel SECTION 2 LIMITATIONS Strobe lights must be turned off when taxiing in the vicinity of other airplanes or during night flight through clouds fog or haze SECTION 3 EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when strobe ...

Page 212: ...7 STROBE LIGHT SYSTEM PILOT S OPERATING HANDBOOK MODEL T182 SUPPLEMENT SECTION 5 PERFORMANCE The installation of strobe lights will result in a minor reduction in cruise performance 21 August 1981 2 ...

Page 213: ...the transmitter selector switch simultaneously selects the audio amplifier associated with that transmitter to provide speaker audio For example if the number one transmitter is selected the audio amplifier in the number one NAV COM is also selected and is used for ALL speaker audio Headset audio is not affected by audio amplifier operation AUDIO SELECTOR SWITCHES Both audio control panels see fig...

Page 214: ...ected by the transmitter selector switch COM BOTH AUDIO SELECTOR SWITCH The audio control panel used with either one or two transmitters incorporates a three position toggle switch labeled COM BOTH which is provided to allow both COM receivers to be monitored at the same time AUTO AUDIO SELECTOR SWITCH The audio control panel used with three transmitters incorporates a three position toggle switch...

Page 215: ...nd utilizing the individual audio selector switches Adjust ment of speaker and headset sidetone volume can only be accomplished by adjusting the sidetone potentiometers located inside the audio control panel NOTE Sidetone is not available on HF Transceiver Type ASB 125 when installed OPTIONAL INTERCOM SYSTEM The optional intercom system is a pilot and copilot intercom phone system which is only of...

Page 216: ...rcom system is not being used the INT volume control should be turned full counterclockwise to eliminate any noise over the headphones NOTE When the intercom volume is turned up and an auxiliary mike is plugged in there will be a loud squeal over the speaker if the COM BOTH and COM AUTO switches are inadvertently placed in the opposite positions one in the SPEAKER position and the other in the PHO...

Page 217: ... 1 TRANSMITTER SELECTOR SWITCH XMTR A two position toggle switch used to activate the audio amplifier and switch the microphone to the desired transmitter The number 1 up position and 2 down position corresponds to the first and second from top to bottom transmitters respectively Figure 1 Audio Control Panel Operating Controls Sheet 1 of 2 21 August 1981 5 ...

Page 218: ...ector switches used to select either SPEAKER or PHONE operation for audio outputs Enables the operator to select anyone or more audio signals on either SPEAKER or PHONE at the same time or to silence audio when placed in the OFF position 7 COM BOTH AUDIO SELECTOR SWITCH COM BOTH A three position toggle switch used to allow both COM receivers to be monitored at the same time Placing the COM BOTH sw...

Page 219: ...o amplifier SECTION 4 NORMAL PROCEDURES AUDIO CONTROL PANEL OPERATIONS 1 Transmitter Selector XMTR or XMTR SEL Switch SELECT desired transmitter for transceiver operation 2 COM AUTO or AUTO Selector Switch SELECT SPEAKER or PHONE position to automatically select SPEAKER or PHONE audio NOTE If the NAV COM audio selector switch corresponding to the selected transmitter is in the PHONE position with ...

Page 220: ...e speaker and the headset simultaneously 4 Audio SPEAKER PHONE Selector Switches SELECT desired SPEAKER or PHONE audio position only if COM AUTO switch is not used 5 INT Control Knob ROTATE as desired to increase or decrease intercom audio volume 6 ANN LTS Switch a TEST Position SELECT to verify operation of marker beacon BC and RN annunciator lights when installed b DAY Position SELECT for typica...

Page 221: ...0 000 feet The ELT supplied in domestic aircraft transmits on both distress frequen cies simultaneously at 75 mw rated power output for 50 continuous hours in the temperature range of 4 F to 131 F 20 C to 55 C The ELT unit in export aircraft transmits on 121 5 MHz at 25 mw 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...

Page 222: ...OVER 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 act...

Page 223: ... 4 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 ELT for inadvertent activation select 121 5 MHz on your radio transceiver and listen for a...

Page 224: ...the airplane in the commanded lateral attitude or heading The actuator includes a thermostatic switch which monitors the operating temperature of the motor If the temperature becomes abnormal the thermostatic switch opens and disengages the autopilot to remove power from the actuator After approximately 10 minutes the switch will automatically close to reapply power to the actuator and autopilot s...

Page 225: ...300A AUTOPILOT PILOT S OPERATING HANDBOOK TYPE AF 395A SUPPLEMENT NAV 1 NAV 2 COMPUTER AMPLIFIER TURN COORDINATOR Figure 1 Cessna 300A Autopilot Operating Controls and Indicators Sheet 1 of 3 21 August 1981 15 2 ...

Page 226: ...ing indicated by the compass The compass card must be manually reset periodically to compensate for precessional errors in the gyro 9 TURN COORDIN ATOR Senses roll and yaw for wings leveling and command turn functions 10 HDG SEL PUSHBUTTON Aircraft will turn to and hold heading selected by the heading bug on the directional gyro 11 NAV INT PUSHBUTTON When heading bug on DG is set to selected cours...

Page 227: ...te a right standard rate turn when turned to the left L the airplane will execute a left standard rate turn When centered in detent and pushed in the operating mode selected by a pushbutton is engaged 18 TRIM Used to trim autopilot to compensate for minor variations in aircraft trim or lateral weight distribution For proper operation the aircraft s rudder trim if so equipped must be manually trimm...

Page 228: ...ed 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 engaging BACK CRS button with a LOC frequenc...

Page 229: ... on 180 185 U206 and TU206 Series Models COMMAND TURNS 1 PULL TURN Knob 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 T...

Page 230: ...atically turn to a 450 intercept angle NAV TRACKING VOR LOC 1 NAV TRK Button PUSH when CDI centers within one dot and airplane is within 100 of course heading 2 HI SENS Button Disengage for enroute omni tracking leave engaged for localizer NOTE Optional ARC function if installed should not be used for autopilot operation If airplane should deviate off course pull out PULL TURN knob and readjust ai...

Page 231: ... altitude reporting when coupled to an optional altitude encoder system The transponder is capable of replying on both modes of interrogation on a selective reply basis on any of 4096 informa tion code selections The optional altitude encoder system not part of a standard 400 Transponder system required for Mode C altitude reporting operation consists of a completely independent remote mounted dig...

Page 232: ...f SBY Turns set on for equipment warm up or standby 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 Altitude Encoder Bl...

Page 233: ...g duration of IDENT pulse transmission 4 DIMMER DIM CONTROL Allows pilot to control brilliance of reply lamp 5 SELF TEST TEST SWITCH When depressed causes transponder to generate a self interrogating signal to provide a check of transponder operation Reply lamp will glow steadily to verify self test operation 6 REPLY CODE SELECTOR SWITCHES 4 Select assigned Mode A reply code 7 REPLY CODE INDICATOR...

Page 234: ... ALTITUDE ENCODER EQUIPPED SECTION 3 EMERGENCY PROCEDURES TO TRANSMIT AN EMERGENCY SIGNAL 1 Function Selector Switch ON 2 Reply Code Selector Switches SELECT 7700 operating code TO TRANSMIT A SIGNAL REPRESENTING LOSS OF ALL COMMUNICATIONS WHEN IN A CONTROLLED ENVIRONMENT 1 Function Selector Switch ON 2 Reply Code Selector Switches SELECT 7700 operating code for 1 minute then SELECT 7600 operating ...

Page 235: ...rily when instructed by ground controller to squawk IDENT reply lamp will glow steadily indicating IDENT operation TO TRANSMIT MODE C ALTITUDE REPORTING CODES IN FLIGHT 1 Reply Code Selector Switches SELECT assigned code 2 Function Selector Switch ALT NOTE When directed by ground controller to stop altitude squawk turn Function Selector Switch to ON for Mode A operation only NOTE Pressure altitude...

Page 236: ...or Switch ON 3 TEST Button DEPRESS reply lamp should light brightly 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 perform...

Page 237: ...ts 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 4096 information code selections When an optional panel mounted EA 401A Encoding Altimeter not part of 400 Transponder System is included in the avionic configuration the transponder can provide altitude...

Page 238: ... Turns set on for equipment 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 repiy pulses or Mode C altitude reporting pulses selected automatically by the interrogating signal Figure 1 Cessna 400 Transponder and Encoding Altimeter Oper...

Page 239: ... reply code 8 1000 FOOT DRUM TYPE INDICATOR Provides digital altitude readout in 1000 foot increments between 1000 feet and 35 000 feet When altitude is below 10 000 feet a diagonally striped flag appears in the 1O 000 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 240: ...CY SIGNAL 1 Function Selector Switch ON 2 Reply Code Selector Switches SELECT 7700 operating code TO TRANSMIT A SIGNAL REPRESENTING LOSS OF ALL COMMUNICATIONS WHEN IN A CONTROLLED ENVIRONMENT 1 Function Selector Switch ON 2 Reply Code Selector Switches SELECT 7700 operating code for 1 minute then SELECT 7600 operating code for 15 minutes and then REPEAT this procedure at same intervals for remaind...

Page 241: ...er 2 Altitude Encoder Altimeter Setting Knob SET IN assigned local altimeter setting 3 Reply Code Selector Switches SELECT assigned code i Function Selector Switch ALT NOTE When directed by ground controller to stop altitude squawk turn Function Selector Switch to ON for Mode A operation only NOTE Pressure altitude is transmitted by the transponder for altitude squawk and conversion to indicated a...

Page 242: ...nce 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 21 August 1981 ...

Page 243: ... carb heat periodically open throttle during extended closed throttle descent for added heat to melt ice Refer to chart showing temperature dewpoint ranges of carb icing MOGAS warning Due to its higher volatility MOGAS IS more susceptible to the formation of carb icing n severe cases ice may form at OATs up to 20 degrees C higher than with AVGAS TP 27QOE 10 92 CARS ICING CAUTION chart not valid wh...

Page 244: ...PILOTS GUIDE ICEMAN IAS9386 ICEMAN AVIATION SUPPLIES can be reached by Tel 800 265 0643 or Fax 613 257 8430 REV I July 10 1995 86 2 ...

Page 245: ...d the photodetector probe in the carhureltor This system is independent of and is not affected by temperature or pressure changes In the absence of frost or ice the warning light remains off and the audio alarm remains silent 1 2 The ADJUST rotary control is provided to adjust the system sensitivity level for ice detection This setting should be just below the threshold of the CARE ICE warning lig...

Page 246: ...until the RESET switch is momentarily depressed The system operation is again in the ice detection mode 4 1 5 If the CARB ICE light illuminates and the audio alarm sounds indicating ice formation on the probe in the carburator throat immediately apply carb heat Then depress and release the RESET switch to mute the audio alarm This will deactivate and reset the audio alarm The CARB ICE warning ligh...

Page 247: ...lts be aware that carb or induction ice can form while climbing and apply carb heat prior to levelling off if ice is suspected t10R ICE Of O ICEMAN t l o CARB TEST ADJUST ICE TO EXTINGUISH CARB ICE LIGHT ON SONAlERT OFF RESET let BOD 26S 0643 4114VIATION SU l f prior to descent apply full carb heat periodically open throttle during extended closed throttle descent for added heat to melt ice MOGAS ...

Page 248: ...z 135 grams r Input voltage 9 to 28 volt Current draw 21 rnA 46 rnA in alert mode CARBUREITOR ICING GRAPH Tho CU OOI e td illN 1O 00 _il Olg lho_ ptOtlIMn varieI m ciftIt J tPII bullhIU curves 8 D IQtt Iirt raft CI l V il Olg _ may b8eQ n1lelb Is Yttlen fOJ tIC a W Iht DneIng noce tilt IetJlP8f1ILf8 IN I dew pOiItandcc nstA hlCMd A xr r y 110 17 I Dow rq 1 1 I I I 1 1 I I I I I 1 20 1 1 C1 lC1 20 ...

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