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Cessna 162 SKYLANE, Pilot'S Operating Handbook And Flight Training Supplement

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Cessna 162 SKYLANE Pilot'S Operating Handbook And Flight Training Supplement Download Page 27

CESSNA

SECTION 2

MODEL 162

AIRPLANE AND SYSTEM DESCRIPTION

GARMIN G300

U.S.

AIRPLANE AND SYSTEMS DESCRIPTION

TABLE OF CONTENTS

Page

Introduction  . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3
Airframe . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3
Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3
Instrument Panel, Flight and System Instruments . . . . . . . . . . . . . . . 2-5
Landing Gear and Brake System. . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6
Miscellaneous Cabin Features  . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-7
Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .   2-8

Engine Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8
Engine Instruments  . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9
Tachometer (RPM) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9
Oil Pressure (OIL PSI) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-10
Oil Temperature (OIL °F) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11

Exhaust Gas Temperature (EGT °F) (if installed) . . . . . . . . . . . . . 2-11
Carburetor Temperature (CARB °F)   . . . . . . . . . . . . . . . . . . . . . . 2-12
New Engine Break-In And Operation . . . . . . . . . . . . . . . . . . . . . . 2-12
Engine Lubrication System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-13
Ignition And Starter System  . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-13
Air Induction System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14
Exhaust System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14
Cooling System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14

Propeller  . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15
Fuel System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15

Fuel Distribution  . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15
Fuel Indicating System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-16
Fuel Venting  . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-17
Reduced Tank Capacity  . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-18
Fuel Drain Valves  . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-19

162PHUS-01

2-1

Summary of Contents for 162 SKYLANE

Page 1: ...CHITA KANSAS USA SERIAL NUMBER REGISTRATION NUMBER Model 162 Serials 16200001 and On This publication includes the material required to be furnished to the pilot by ASTM F2245 ORIGINAL ISSUE 22 JULY 2009 REVISION 2 26 APRIL 2010 U S 162PHUS 02 ...

Page 2: ......

Page 3: ...ON MODEL 162 GARMIN G300 U S PILOT S OPERATING HANDBOOK AND FLIGHT TRAINING SUPPLEMENT CESSNA MODEL 162 SERIALS 16200001 AND ON ORIGINAL ISSUE 22 JULY 2009 REVISION 2 26 APRIL 2010 PART NUMBER 162PHUS 02 162PHUS 02 i ii ...

Page 4: ......

Page 5: ...ns worldwide Warranty provisions and other important information are contained in the Customer Care Handbook supplied with your airplane The Customer Care Card assigned to you at delivery will establish your eligibility under warranty and should be presented to your local Cessna Service Station at the time of warranty service FACTORY TRAINED PERSONNEL to provide you with courteous expert service F...

Page 6: ...r 50 Foot Obstacle 1369 FEET 417 3 m STALL SPEED Flaps UP Power Idle 41 KIAS Flaps FULL Power Idle 37 KIAS NOTE Speed performance is shown for airplanes not equipped with the optional speed fairings Airplanes equipped with optional speed fairings will notice a increase in speeds by approximately 2 knots There is a corresponding difference in range while all other performance figures are unchanged ...

Page 7: ... STANDARD EMPTY WEIGHT 834 POUNDS 378 3 kg MAXIMUM USEFUL LOAD 490 POUNDS 220 4 kg BAGGAGE ALLOWANCE 50 POUNDS 22 68 kg WING LOADING 11 0 lbs sq ft 53 7 kg sq m POWER LOADING 13 2 lbs HP FUEL CAPACITY Usable 24 GALLONS 90 8 l OIL CAPACITY Sump 5 QUARTS 4 73 I ENGINE Teledyne Continental Motors O 200D 100 BHP at 2750 RPM PROPELLER Fixed Pitch Diameter 67 INCHES 1 70 m 162PHUS 01 v ...

Page 8: ...on This POH consists of ten sections that cover all operational aspects of a standard equipped airplane Section 10 contains the supplements which provide amended operating limitations operating procedures performance data and other necessary information for airplanes conducting special operations for both standard and optional equipment installed in the airplane Supplements are individual document...

Page 9: ...ample below for a breakdown It is the responsibility of the owner to maintain this POH in a current status when it is being used for operational purposes Owners should contact a Cessna Service Station whenever the revision status of their POH is in question Revisions are distributed to owners of U S Registered aircraft according to FAA records at the time of revision issuance and to Internationall...

Page 10: ...ay be issued These temporary revisions are to be filed in the applicable section in accordance with filing instructions appearing on the first page of the temporary revision Temporary Revisions will remain current until they have either been incorporated into the next POH revision or another temporary revision has been issued that supersedes that temporary revision Each temporary revision is issue...

Page 11: ...pelling grammar changes and or that information has slipped to or from that page A bar located adjacent to the figure number in the margin on the left side of the page will be used to indicate that the figure number only has changed An asterisk located at the end of a figure number will be used to indicate that an illustration has been revised or is all new material Ex Figure 3 4 All revised pages...

Page 12: ...ts to the text are used to highlight or emphasize important points WARNING OPERATING PROCEDURES TECHNIQUES ETC WHICH CAN RESULT IN PERSONAL INJURY OR LOSS OF LIFE IF NOT CAREFULLY FOLLOWED CAUTION OPERATION PROCEDURES TECHNIQUES ETC WHICH CAN RESULT IN DAMAGE TO EQUIPMENT IF NOT CAREFULLY FOLLOWED NOTE An operating procedure technique etc which is considered essential to emphasize 162PHUS 00 x ...

Page 13: ... Issue 22 July 2009 Revision 2 26 April 2010 Revision 1 2 November 2009 Page Number Page Status Revision Number Title Revised 2 i ii Revised 2 iii thru vi Revised 1 vii thru x Original 0 xi thru xiv Revised 2 xv xvi Added 1 1 1 1 2 Original 0 1 3 thru 1 5 Revised 1 1 6 thru 1 7 Original 0 1 8 Revised 1 2 1 thru 2 8 Revised 1 2 9 thru 2 10 Original 0 2 11 thru 2 12 Revised 1 2 13 Original 0 2 14 th...

Page 14: ...6 Original 0 4 7 Revised 1 4 8 Original 0 4 9 thru 4 10 Revised 1 4 11 thru 4 14 Original 0 4 15 thru 4 16 Revised 1 4 17 thru 4 22 Original 0 4 23 thru 4 26 Revised 1 4 27 thru 4 30 Original 0 5 1 5 2 Original 0 5 3 thru 5 9 Revised 1 5 10 thru 5 11 Original 0 5 12 thru 5 16 Revised 1 5 17 thru 5 18 Original 0 6 1 thru 6 4 Original 0 6 5 Revised 2 6 6 Original 0 6 7 thru 6 8 Revised 1 6 9 thru 6 ...

Page 15: ... 7 2 Revised 1 7 3 Revised 2 7 4 Original 0 7 5 Revised 1 7 6 thru 7 7 Original 0 7 8 thru 7 10 Revised 1 7 11 thru 7 12 Original 0 7 13 thru 7 16 Revised 1 7 17 Original 0 7 18 thru 7 21 Revised 1 7 22 thru 7 24 Original 0 7 25 thru 7 26 Revised 1 7 27 thru 7 29 Original 0 7 30 thru 7 41 Revised 1 7 42 thru 7 43 Original 0 7 44 thru 7 45 7 46 Revised 1 8 1 Original 0 8 2 thru 8 10 Revised 1 8 11 ...

Page 16: ...EL 162 GARMIN G300 U S LOG OF EFFECTIVE PAGES Continued Page Number Page Status Revision Number 9 1 9 2 Original 0 9 3 Revised 1 9 4 thru 9 5 Original 0 9 6 Revised 2 9 7 thru 9 8 Revised 1 10 1 10 2 Original 0 162PHUS 02 xiv ...

Page 17: ...ENERAL 1 AIRPLANE AND SYSTEM DESCRIPTION 2 OPERATING LIMITATIONS 3 WEIGHT AND BALANCE EQUIPMENT LIST 4 PERFORMANCE 5 EMERGENCY PROCEDURES 6 NORMAL PROCEDURES 7 AIRCRAFT HANDLING SERVICE AND MAINTENANCE 8 PLACARDS AND MARKINGS 9 SUPPLEMENTARY INFORMATION 10 162PHUS 01 xv xvi ...

Page 18: ......

Page 19: ...5 Descriptive Data 1 5 Engine 1 5 Propeller 1 5 Fuel 1 6 Fuel Capacity 1 6 Oil 1 7 Oil Specification 1 7 Oil Capacity 1 7 Maximum Certificated Weights 1 8 Maximum Weight In Baggage Compartment 1 8 Standard Airplane Weights 1 8 Cabin And Entry Dimensions 1 8 Baggage Space And Entry Dimensions 1 8 Specific Loadings 1 8 1 1 1 2 162PHUS 00 ...

Page 20: ......

Page 21: ...CESSNA SECTION 1 MODEL 162 GENERAL GARMIN G300 U S THREE VIEW NORMAL GROUND ATTITUDE Figure 1 1 Sheet 1 of 2 1 3 162PHUS 01 ...

Page 22: ...E VIEW NORMAL GROUND ATTITUDE NOTE Wing span shown with standard strobe lights installed Wheel base length is 62 40 inches 1 58 m Propeller ground clearance is 8 50 inches 215 90 mm Wing area is 120 0 square feet 11 15 sq m Figure 1 1 Sheet 2 162PHUS 01 1 4 ...

Page 23: ... information of general interest DESCRIPTIVE DATA ENGINE Number of Engines 1 Engine Manufacturer Teledyne Continental Motors Engine Model Number O 200 D Engine Type Normally aspirated direct drive air cooled horizontally opposed carburetor equipped four cylinder engine with 201 0 cu in displacement Horsepower Rating and Engine Speed 100 rated BHP at 2750 RPM PROPELLER Propeller Manufacturer McCaul...

Page 24: ...ALLONS 96 34 l Total Usable 24 00 U S GALLONS 90 82 l Total Capacity Each Tank 12 73 U S GALLONS 48 17 l Total Usable Each Tank 12 00 U S GALLONS 45 41 l NOTE To ensure maximum fuel capacity and minimize crossfeeding when refueling always park the airplane in a wings level normal ground attitude Refer to Figure 1 1 for normal ground attitude dimensions The fuel filler assembly is equipped with ind...

Page 25: ...al Motors TCM Service Information Letter SIL99 2B and all revisions and supplements thereto must be used after first 50 hours or oil consumption has stabilized RECOMMENDED VISCOSITY FOR TEMPERATURE RANGE Multiviscosity or straight grade oil may be used throughout the year for engine lubrication Refer to the following table for temperature versus viscosity ranges NOTE When operating temperatures ov...

Page 26: ...ion 155 to 190 50 POUNDS 22 68 kg STANDARD AIRPLANE WEIGHTS Standard Empty Weight 834 POUNDS 378 3 kg Maximum Useful Load 486 POUNDS 220 4 kg CABIN AND ENTRY DIMENSIONS Detailed dimensions of the cabin interior and entry door openings are illustrated in Section 4 BAGGAGE SPACE AND ENTRY DIMENSIONS Dimensions of the baggage area are illustrated in detail in Section 4 SPECIFIC LOADINGS Wing Loading ...

Page 27: ...trols 2 8 Engine Instruments 2 9 Tachometer RPM 2 9 Oil Pressure OIL PSI 2 10 Oil Temperature OIL F 2 11 Exhaust Gas Temperature EGT F if installed 2 11 Carburetor Temperature CARB F 2 12 New Engine Break In And Operation 2 12 Engine Lubrication System 2 13 Ignition And Starter System 2 13 Air Induction System 2 14 Exhaust System 2 14 Cooling System 2 14 Propeller 2 15 Fuel System 2 15 Fuel Distri...

Page 28: ... Electrical System Monitoring 2 21 Main Battery Current Amps 2 21 System Voltage Volts 2 21 Circuit Breakers 2 22 12V Power Outlet 2 23 External Power Receptacle if installed 2 23 Lighting Systems 2 24 Exterior Lighting 2 24 Interior Lighting 2 24 Cabin Heating and Ventilating System 2 25 2 26 Stall Warning System 2 25 2 26 162PHUS 01 2 2 ...

Page 29: ...ft fuselage empennage tail assembly consists of horizontal and vertical stabilizers the rudder a left elevator and a right elevator with elevator trim tab Attaching on either side the fuselage above the cabin the wing contains fuel tanks at the wing root between the forward and aft spars Aft of the rear wing spar are mounted the flaps inboard and ailerons outboard In addition to the fuselage carry...

Page 30: ...andle A control gust lock is provided The control lock pins the left control stick through a bracket to immobilize the ailerons and elevator Rudder is held centered by the springs used for increasing rudder pedal force During the preflight walk around inspection it is possible to move the ailerons into an over centered position by moving the aileron down from the centered or faired with the flaps ...

Page 31: ...top row with two rows of circuit breakers underneath On the right end of the switch row is the PANEL LIGHT control knob Under the electrical system panel is the radio stack with the Garmin SL40 Communication radio over the Garmin 327GXT Transponder An optional Garmin Multifunction Display MFD if installed is located to the right of the electrical system switch circuit breaker panel The MFD when in...

Page 32: ... holes for full and the bottom of the tab indicates minimum takeoff See Fuel System description section for more information The optional magnetic compass if installed is mounted to the airplane structure above the center of the windshield LANDING GEAR AND BRAKE SYSTEM The tricycle type landing gear on the Model 162 features tapered spring steel main gear legs and a spring steel nose gear with ela...

Page 33: ...he door latch handle as indicated by the placard Externally the door latch handle is operated through a vertical arc as indicated by the placard Pulling the external handle horizontally may damage the mechanism and door The baggage area is accessed by tilting the seats forward and can accommodate up to 50 pounds of cargo Tie down rings are supplied to secure cargo A tailcone close out net is insta...

Page 34: ... forward position and closed in the full aft position A friction lock located at the base of the throttle control knob is operated by rotating the lock clockwise to increase friction or counterclockwise to decrease friction Engine fuel mixture is controlled by the mixture control The mixture control is a red knob with raised points around the circumference located immediately to the right of the t...

Page 35: ...configuration if installed During engine start or when the AVN MASTER is OFF the EIS is only displayed on the PFD even if the optional MFD is installed TACHOMETER RPM A speed sensor mounted on the right magneto provides a digital signal to the ADAHRS which processes and outputs the RPM data to the EIS Engine speed RPM is shown by the tachometer indicator found on all EIS pages The tachometer indic...

Page 36: ...I or 100 to 140 PSI the pointer digital value and label OIL PRES will change to red to show that oil pressure is outside normal limits A red X is displayed when the instrument is invalid or out of the data range When the engine speed RPM is in the green arc and the oil temperature is in the green band the oil pressure should be in the green band If oil pressure is below the green band or above the...

Page 37: ...nter indicates actual oil temperature When oil temperature is in the red band 240 to 265 F the pointer and OIL TEMP turn red and flash to show oil temperature is higher than the limit A red X is displayed when the instrument is invalid or out of the data range EXHAUST GAS TEMPERATURE EGT F if installed A thermocouple installed in the exhaust down pipe measures EGT and provides a signal to the engi...

Page 38: ...data range NOTE Although carburetor ice is more likely to form at temperatures within the yellow band range it can form at temperatures outside the yellow caution range If engine roughness or unexplained RPM loss is encountered full carburetor heat should be immediately applied NEW ENGINE BREAK IN AND OPERATION The initial engine run in was accomplished at the factory and is ready for the full ran...

Page 39: ...of the engine cowling The engine should not be operated on less than 3 5 quarts of oil For extended flight fill to 5 0 quarts dipstick indication only For engine oil grade and specifications refer to Section 8 of this POH IGNITION AND STARTER SYSTEM Engine ignition is provided by two engine driven magnetos and two spark plugs in each cylinder The left magneto fires the lower left and lower right s...

Page 40: ...tely 200 250 RPM due to the increased intake temps After passing through the air box induction air enters a carburetor under the engine and is then ducted to the engine cylinders through intake manifold tubes EXHAUST SYSTEM Exhaust gas from each cylinder passes through a riser assembly to a common muffler located below the engine and then overboard through a single exhaust outlet Outside air is su...

Page 41: ...G UNUSABLE FUEL LEVELS FOR THIS AIRPLANE WERE DETERMINED IN ACCORDANCE WITH ASTM INTERNATIONAL COMPLIANCE STANDARDS FAILURE TO OPERATE THE AIRPLANE IN COMPLIANCE WITH FUEL LIMITATIONS SPECIFIED IN SECTION 3 MAY FURTHER REDUCE THE AMOUNT OF FUEL AVAILABLE IN FLIGHT FUEL QUANTITY DATA IN U S GALLONS FUEL DISTRIBUTION Fuel flows by gravity from the two wing tanks to a fuel shutoff valve the fuel stra...

Page 42: ...luminum balls for increased readability There are two scales displayed on each fuel sight gage The aft scale shows fuel levels to be read in level flight The markings should not be relied upon for accurate readings during skids slips or unusual attitudes The forward scale shows fuel levels as read on level ground Minimum takeoff is indicated when the center of the ball is at the MIN TO line on the...

Page 43: ...el and indicated fuel quantity to accurately estimate usable fuel WARNING TAKEOFF IS PROHIBITED IF EITHER FUEL SIGHT GAGE INDICATES BELOW THE MIN TO INDICATION LESS THAN 1 4 TANK OR BELOW THE BOTTOM OF THE IN TANK FUEL FILLER INDICATOR TAB FUEL VENTING Fuel system venting is essential to system operation Complete blockage of the fuel venting system will result in decreasing fuel flow and eventual ...

Page 44: ...lling each tank to the bottom edge of the fuel filler indicator tab thus giving a reduced fuel load of 3 gallons usable minimum takeoff fuel in each tank Continued filling to each subsequent hole in the indicator tab will add an additional 3 gallons usable fuel per tank Do not fuel above top hole as fuel expansion may cause overflow from fuel vent IN TANK FUEL FILLER INDICATOR TAB Continued Next P...

Page 45: ...lled by the MASTER switch found on the switch circuit breaker panel The alternator and main battery power is supplied to a relay panel located on the left forward side of the firewall Power for all electrical circuits except the secondary power circuit is supplied from the relay panel to the electrical bus located in the switch circuit breaker panel The electrical bus is supplied with power anytim...

Page 46: ...SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 162 GARMIN G300 U S ELECTRICAL SYSTEM Continued Figure 2 4 162PHUS 01 2 20 ...

Page 47: ...tion is shown on all G300 EIS pages A positive number indicates a charging battery while a negative number indicates a discharging battery The tape display range is 35 to 35 amps with digital information range from 50 to 50 amps A red X is displayed when the instrument is invalid or out of the data range A white pointer indicates actual current value SYSTEM VOLTAGE VOLTS Electrical system voltage ...

Page 48: ...of the circuit breaker The relay panel located forward of the firewall contains three circuit breakers associated with the alternator main power feeder and secondary power feeder The alternator and main power circuit breakers are capable of being reset in flight by momentarily pushing the MAIN CB RESET switch located on the switch circuit breaker panel Pushing the MAIN CB RESET switch activates th...

Page 49: ... POWER ADAPTER CABLES IN THE CABIN TO AVOID ENTANGLING OCCUPANTS OR CABIN FURNISHINGS AND TO PREVENT DAMAGE TO CABLES SUPPLYING LIVE ELECTRIC CURRENT DISCONNECT POWER ADAPTER CABLES WHEN NOT IN USE EXTERNAL POWER RECEPTACLE if installed The External Power Receptacle if installed allows the use of an external power source for cold weather starting or for lengthy maintenance work on electrical equip...

Page 50: ... light assembly mounted on the overhead cabin structure Individual LEDs are directed at various instrument panel locations and both fuel quantity indicators for night and low light illumination Airplanes equipped with the BRS parachute option will also have a LED light directed at the parachute deployment handle The PANEL LIGHTS dimming knob located on the right side of the electrical system switc...

Page 51: ... the wing root openings to fresh air valves located overhead at the outboard corners of the windshield These fresh air valves are equipped with directional control as well as variable flow adjustment settings STALL WARNING SYSTEM Stall warning is a pneumatically operated by localized pressure differential created by low pressure airflow around the wing and higher static pressure internally The sta...

Page 52: ......

Page 53: ...Electrical Instrument Markings 3 7 Weight Limits 3 8 Maximum Weight in Baggage Compartment 3 8 Center of Gravity Limits 3 8 Service Ceiling 3 8 Maneuver Limits 3 9 Load Factors 3 9 Flight Load Factor Limits 3 9 Kinds of Operations Limits 3 10 Kinds of Operations Equipment List 3 11 Fuel Limitations 3 14 Flaps Limitations 3 14 System Limitations 3 15 12V Power Outlet 3 15 G300 Limitations 3 15 Plac...

Page 54: ......

Page 55: ... have been approved Observance of these operating limitations is required by Federal Aviation Regulations NOTE Refer to Section 10 Supplements of this Pilot s Operating Handbook for amended operating limitations operating procedures performance data and other necessary information for airplanes equipped with specific options The airspeeds listed in Figure 3 1 Airspeed Limitations are based on Airs...

Page 56: ...0 Do not exceed this speed with flaps down VO Maximum Operating Maneuvering Speed 1320 Pounds 1200 Pounds 1100 Pounds 88 84 81 89 85 80 Maximum speed at which the airplane may be stalled without exceeding structural limitations VA Design Maneuvering Speed 100 102 Do not make full or abrupt control movements above this speed Does not provide protection from possible overstressing the airplane VNE N...

Page 57: ...ation Upper limit is maximum speed permissible with flaps extended Green Band 41 124 Normal Operating Range Lower limit is maximum weight VS1 at most forward C G with flaps retracted Upper limit is maximum structural cruising speed Yellow Band 124 148 Operations must be conducted with caution and only in smooth air Red Line 149 Maximum speed for all operations Flaps 25 Tick Mark 85 Maximum Flaps 2...

Page 58: ...sure Minimum 10 PSI Oil Pressure Maximum 100 PSI CAUTION ENGINE OPERATION WITH INDICATED OIL PRESSURE BELOW THE GREEN BAND RANGE WHILE IN CRUISE OR CLIMB CONFIGURATION IS CONSIDERED ABNORMAL REFER TO SECTION 3 AMPLIFIED EMERGENCY PROCEDURES LOW OIL PRESSURE Fuel Grade Refer to Fuel Limitations Oil Grade Specification SAE J1966 Aviation Grade Non Dispersant Mineral Oil or SAE J1899 Aviation Grade A...

Page 59: ...R WARNING YELLOW LOWER CAUTION GREEN NORMAL OPERATING RANGE YELLOW UPPER CAUTION RED UPPER WARNING Tachometer RPM 2000 to 2750 RPM 2750 to 3500 RPM Oil Temperature OIL F 0 to 75 F 75 to 220 F 220 to 240 F 240 to 265 F Oil Pressure OIL PSI 0 to 10 PSI 10 to 30 PSI 30 to 60 PSI 60 to 100 PSI 100 to 140 PSI Exhaust Gas Temperature if installed EGT F 1000 to 1600 F White Advisory Carburetor Temperatur...

Page 60: ...Area Station 155 to 190 50 POUNDS 22 68 kg NOTE Maximum baggage compartment loading must not exceed 8 pounds per square foot CENTER OF GRAVITY LIMITS Center Of Gravity Range Forward 134 5 inches aft of datum at 1320 pounds or less with straight line variation to 132 0 inches aft of datum at 1050 pounds Aft 136 9 inches aft of datum at all weights Reference Datum Lower portion of front face of fire...

Page 61: ...ANEUVERS AND RECOMMENDED ENTRY SPEED Chandelles 102 KIAS Lazy Eights 102 KIAS Steep Turns 102 KIAS Stalls Except Whip Stalls Slow Deceleration Power On Stalls Slow Deceleration limit pitch to 30 nose up attitude Abrupt use of the controls is prohibited above 102 KIAS WARNING AEROBATIC MANEUVERS INCLUDING SPINS ARE PROHIBITED CAUTION INTENTIONAL OPERATION WITH CABIN DOORS OPEN IS PROHIBITED LOAD FA...

Page 62: ...t into known icing conditions is prohibited The minimum equipment for approved operations required under the Operating Rules are defined by 14 CFR 91 and ASTM standard F2245 as applicable The following Kinds of Operations Equipment List KOEL identifies the equipment required to be operational for airplane airworthiness in the listed kind of operations 162PHUS 01 3 10 ...

Page 63: ...accessible to pilot in flight 3 Garmin G300 Pilot s Guide 0 0 Recommended to be accessible to pilot in flight 4 Garmin G300 Cockpit Reference Guide 0 0 Recommended to be accessible to pilot in flight AIR CONDITIONING 1 Avionics Fan 1 1 COMMUNICATIONS 1 VHF COM 0 0 ELECTRICAL POWER 1 12V Main Battery 1 1 2 14V Alternator 1 1 3 Standby Battery 0 1 4 Ammeter 0 1 EQUIPMENT AND FURNISHINGS 1 Seat Belt ...

Page 64: ...Cockpit Fuel Quantity Indicator R Tank 1 1 INDICATING RECORDING SYSTEM 1 Stall Warning System 1 1 2 G300 System Annunciator and Warning Displays 1 1 LANDING GEAR 1 Wheel Fairings 0 0 Removable LIGHTING 1 PFD Bezel Lighting 0 0 2 PFD Display Backlighting 1 1 3 MFD Bezel Lighting 0 0 4 MFD Display Backlighting 1 1 5 Cockpit Overhead Panel Lighting 0 1 6 Aircraft Position NAV Lights 0 1 7 STROBE Ligh...

Page 65: ...cator HSI 0 0 6 G300 Turn Coordinator 0 0 7 G300 Magnetic Heading Indicator 1 1 8 GPS Receiver Navigator A R A R As Required Per Procedure 9 GTX 327 Mode C Transponder A R A R As Required Per Procedure 10 Blind Altitude Encoder A R A R As Required Per Procedure 11 Clock 0 0 12 Magnetic Compass if installed 0 0 ENGINE INDICATING 1 Tachometer RPM 1 1 2 Carburetor Temperature Indicator CARB F if inst...

Page 66: ...HE BOTTOM OF THE FUEL INDICATOR TAB NOTE To ensure maximum fuel capacity and minimize crossfeeding when refueling always park the airplane in a wings level normal ground attitude Refer to Figure 1 1 for normal ground attitude definition Fuel remaining in the tank after the fuel quantity indicator reads E cannot be safely used in flight Approved Fuel Grades And Colors 100LL Grade Aviation Fuel Blue...

Page 67: ... to enhance situational awareness Navigation is to be conducted using only current charts data and authorized navigation facilities Use of the TERRAIN information for primary terrain and obstacle avoidance is prohibited The terrain map is intended only to enhance situational awareness It is the pilot s responsibility to provide terrain clearance at all times Navigation using the G300 is not author...

Page 68: ...The markings and placards installed in this airplane contain operating limitations which must be complied with when operating this airplane Other operating limitations which must be complied with when operating this airplane in this category are contained in the Pilot s Operating Handbook No acrobatic maneuvers including spins are approved Flight into known icing conditions prohibited This airplan...

Page 69: ...to flight can result in bodily injury or death 5 Silk screened on the upper left instrument panel NO INTENTIONAL SPINS 6 On the instrument panel directly above the PFD MAXIMUM OPERATING MANEUVERING SPEED 89 KIAS DESIGN MANEUVERING SPEED 102 KIAS 7 Silk screened on the upper right instrument panel 8 Silk screened on the right instrument panel This aircraft was manufactured in accordance with Light ...

Page 70: ...NG LIMITATIONS MODEL 162 GARMIN G300 U S PLACARDS Continued 9 On the right side of the baggage compartment below the window 10 Near both fuel tank filler cap 11 On the engine oil access door Continued Next Page 162PHUS 01 3 18 ...

Page 71: ...S GARMIN G300 U S PLACARDS Continued 12 On firewall adjacent to battery box and second placard on external power receptacle door if external power receptacle option is installed 13 Located on both left and right fuel sight tubes 162PHUS 01 3 19 3 20 ...

Page 72: ......

Page 73: ...ensive Equipment List 4 4 Airplane Weighing Procedures 4 8 Airplane Weighing Form 4 9 Sample Weight and Balance Record 4 13 Weight And Balance 4 15 Baggage Tiedown 4 16 Sample Loading Problem 4 17 Loading Graph 4 21 Loading Arrangements 4 23 Internal Cabin Dimensions 4 25 Center Of Gravity Moment Envelope 4 27 Center of Gravity Limits 4 29 162PHUS 00 4 1 4 2 ...

Page 74: ......

Page 75: ...procedures refer to the Aircraft Weight and Balance Handbook FAA H 8083 1 A comprehensive list of Cessna equipment available for this airplane is included in this section Specific information regarding the weight arm moment and installed equipment for this airplane as delivered from the factory can be found in the plastic envelope in the back of this POH WARNING IT IS THE RESPONSIBILITY OF THE PIL...

Page 76: ...EQUIPMENT LIST DESCRIPTION column each item is assigned a descriptive name to help identify its function In the REF DRAWING column a Cessna drawing number is provided which corresponds to the item NOTE If additional equipment is to be installed it must be done in accordance with the reference drawing service bulletin or a separate ASTM approval In the WT LBS and ARM INS columns information is prov...

Page 77: ...4 01 R ALTERNATOR 12 VOLT 60 AMP 0950000 6 80 83 36 24 02 R BATTERY 12 VOLT 14 0 AMP HOUR PC545 0918130 11 40 98 35 24 03 S BATTERY STANDBY 12 VOLT PS 1208 0918104 0 8 109 44 24 04 O GROUND SERVICE POWER RECEPTACLE 0918505 3 21 97 84 25 EQUIPMENT FURNISHINGS 25 01 R SEAT PILOT 0919021 7 79 146 23 25 02 S SEAT FRONT PASSENGER 0919021 7 79 146 23 25 03 R SEAT BELT AND SHOULDER HARNESS MANUAL ADJUST ...

Page 78: ...RECORDING SYSTEM 31 01 R PNEUMATIC STALL WARNING SYSTEM 0914300 0 61 127 24 31 02 R OUTSIDE AIR TEMPERATURE OAT PROBE 0918121 0 30 166 03 32 LANDING GEAR 32 01 R WHEEL BRAKE AND TIRE 5 00 X 5 MAIN 2 0941000 WHEEL ASSY EACH 4 16 149 52 BRAKE ASSY EACH 1 46 151 73 TIRE AND TUBE 4 PLY 5 00 X 5 BLACKWALL EACH 5 62 149 52 32 02 R WHEEL AND TIRE ASSY 4 00 X 5 NOSE 0942000 WHEEL ASSY 3 50 86 92 TIRE AND ...

Page 79: ...45 0 90 65 03 SPINNER FRONT SUPPORT ASSEMBLY C 7961 0 20 65 03 SPINNER BULKHEAD ASSEMBLY D 7962 1 05 65 03 MOUNTING HARDWARE 1 50 65 03 71 POWERPLANT 71 01 R FILTER INDUCTION AIR 0950000 0 50 83 00 71 02 O WINTERIZATION KIT INSTALLATION STOWED INSTALLED ARM SHOWN 0901260 1 12 70 71 BREATHER TUBE INSULATION 0901250 5 10 0 20 75 06 COWL INLET COVERS INSTALLED 0901250 1 2 0 92 69 77 COWL INLET COVERS...

Page 80: ... each reading 4 Measure a Obtain measurement A by measuring horizontally along the airplane centerline from a line stretched between the main wheel centers to a plumb bob dropped from the firewall b Obtain measurement B by measuring horizontally and parallel to the airplane centerline from center of nosewheel axle left side to a plumb bob dropped from the line between the main wheel centers Repeat...

Page 81: ...CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE GARMIN G300 EQUIPMENT LIST U S AIRPLANE WEIGHING FORM U S UNITS Figure 4 2 Sheet 1 of 4 162PHUS 01 4 9 ...

Page 82: ...SECTION 4 CESSNA WEIGHT AND BALANCE MODEL 162 EQUIPMENT LIST GARMIN G300 U S AIRPLANE WEIGHING FORM METRIC UNITS Figure 4 2 Sheet 2 162PHUS 01 4 10 ...

Page 83: ...CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE GARMIN G300 EQUIPMENT LIST U S AIRPLANE WEIGHING FORM U S UNITS Figure 4 2 Sheet 3 162PHUS 00 4 11 ...

Page 84: ...SECTION 4 CESSNA WEIGHT AND BALANCE MODEL 162 EQUIPMENT LIST GARMIN G300 U S AIRPLANE WEIGHING FORM METRIC UNITS Figure 4 2 Sheet 4 162PHUS 00 4 12 ...

Page 85: ...CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE GARMIN G300 EQUIPMENT LIST U S SAMPLE WEIGHT AND BALANCE RECORD U S Figure 4 3 Sheet 1 of 2 162PHUS 00 4 13 ...

Page 86: ...SECTION 4 CESSNA WEIGHT AND BALANCE MODEL 162 EQUIPMENT LIST GARMIN G300 U S SAMPLE WEIGHT AND BALANCE RECORD METRIC Figure 4 3 Sheet 2 162PHUS 00 4 14 ...

Page 87: ...00 on the loading problem Use the Loading Graph to determine the moment 1000 for each additional item to be carried then list these on the loading problem NOTE Loading Graph information for the pilot passenger and baggage is based on baggage loaded in the center of the baggage areas as shown on the Loading Arrangements diagram For loadings which may differ from these the Sample Loading Problem lis...

Page 88: ...nt to secure baggage on the cabin floor Six eyebolts serve as attaching points for the net A placard located on the right side of the baggage compartment below the window defines the weight limitations in the baggage areas NOTE Maximum weight in the baggage compartment area is 50 pounds 22 68 kg with a maximum floor loading of 8 pounds per square foot 39 05 kilograms per square meter 162PHUS 01 4 ...

Page 89: ...l and full oil 834 110 1 2 Usable Fuel At 6 Lbs Gal Standard Fuel 24 Gallons Maximum 144 20 6 Reduced Fuel 12 Gallons 3 Pilot and Front Passenger FS 142 300 42 6 4 Baggage FS 155 to 190 50 Pounds Maximum 46 7 9 5 RAMP WEIGHT AND MOMENT 1324 181 2 6 Fuel allowance for engine start taxi and runup 4 0 0 6 7 TAKEOFF WEIGHT AND MOMENT Subtract Step 8 from Step 7 1320 180 6 8 Locate this point 1320 at 1...

Page 90: ...le fuel and full oil 378 3 1268 4 2 Usable Fuel At 0 72 Kg Liter Standard Fuel 90 82 Liters Maximum 65 4 244 5 Reduced Fuel 45 41 Liters 3 Pilot and Front Passenger FS 3607 136 1 490 9 4 Baggage FS 3937 to 4826 22 6 Kilograms Maximum 19 9 86 9 5 RAMP WEIGHT AND MOMENT 599 7 2090 7 6 Fuel allowance for engine start taxi and runup 1 8 6 6 7 TAKEOFF WEIGHT AND MOMENT Subtract Step 8 from Step 7 597 9...

Page 91: ...NT LIST U S SAMPLE LOADING PROBLEM U S UNITS NOTE When several loading configurations are representative of your operations it may be useful to fill out one or more of the above columns so specific loadings are available at a glance Figure 4 4 Sheet 3 162PHUS 00 4 19 ...

Page 92: ...ading configurations are representative of your operations it may be useful to fill out one or more of the above columns so specific loadings are available at a glance Figure 4 4 Sheet 4 YOUR AIRPLANE YOUR AIRPLANE YOUR AIRPLANE Weight Kgs Moment Kgs mm 1000 Weight Kgs Moment Kgs mm 1000 Weight Kgs Moment Kgs mm 1000 162PHUS 00 4 20 ...

Page 93: ...CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE GARMIN G300 EQUIPMENT LIST U S LOADING GRAPH U S UNITS Figure 4 5 Sheet 1 of 2 162PHUS 00 4 21 ...

Page 94: ...SECTION 4 CESSNA WEIGHT AND BALANCE MODEL 162 EQUIPMENT LIST GARMIN G300 U S LOADING GRAPH METRIC UNITS Figure 4 5 Sheet 2 162PHUS 00 4 22 ...

Page 95: ...ty for average occupant Arm measured to the center of the areas shown NOTE All dimensions shown are in inches The usable fuel C G arm is located at FS 143 26 The aft baggage wall approximate FS 190 00 can be used as a convenient interior reference point for determining the location of baggage area fuselage stations Figure 4 6 Sheet 1 of 2 162PHUS 01 4 23 ...

Page 96: ...vity for average occupant Arm measured to the center of the areas shown NOTE All dimensions shown are in millimeters The usable fuel C G arm is located at FS 3638 80 The aft baggage wall approximate FS 4826 can be used as a convenient interior reference point for determining the location of baggage area fuselage stations Figure 4 6 Sheet 2 162PHUS 01 4 24 ...

Page 97: ...300 EQUIPMENT LIST U S INTERNAL CABIN DIMENSIONS U S UNITS NOTE Maximum weight in the baggage compartment area is 50 pounds with a maximum floor loading of 8 pounds per square foot All dimensions shown are in inches Figure 4 7 Sheet 1 of 2 162PHUS 01 4 25 ...

Page 98: ...ARMIN G300 U S INTERNAL CABIN DIMENSIONS METRIC UNITS NOTE Maximum weight in the baggage compartment area is 22 68 kilograms with a maximum floor loading of 39 05 kilograms per square meter All dimensions shown are in millimeters Figure 4 7 Sheet 2 162PHUS 01 4 26 ...

Page 99: ...CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE GARMIN G300 EQUIPMENT LIST U S CENTER OF GRAVITY MOMENT ENVELOPE U S Figure 4 8 Sheet 1 of 2 162PHUS 00 4 27 ...

Page 100: ...SECTION 4 CESSNA WEIGHT AND BALANCE MODEL 162 EQUIPMENT LIST GARMIN G300 U S CENTER OF GRAVITY MOMENT ENVELOPE METRIC UNITS Figure 4 8 Sheet 2 162PHUS 00 4 28 ...

Page 101: ...CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE GARMIN G300 EQUIPMENT LIST U S CENTER OF GRAVITY LIMITS U S UNITS Figure 4 9 Sheet 1 of 2 162PHUS 00 4 29 ...

Page 102: ...SECTION 4 CESSNA WEIGHT AND BALANCE MODEL 162 EQUIPMENT LIST GARMIN G300 U S CENTER OF GRAVITY LIMITS METRIC UNITS Figure 4 9 Sheet 2 162PHUS 00 4 30 ...

Page 103: ...nding 5 9 Demonstrated Operating Temperature 5 9 Airspeed Calibration 5 10 Stall Speeds At 1320 Pounds 5 11 Short Field Takeoff Distance At 1320 Pounds 5 12 Short Field Landing Distance At 1320 Pounds 5 13 Maximum Rate Of Climb At 1320 Pounds 5 14 Time Fuel And Distance To Climb At 1320 Pounds 5 15 Cruise Performance 5 16 Temperature Conversion Chart 5 17 Crosswind Component 5 18 162PHUS 00 5 1 5 ...

Page 104: ......

Page 105: ...ng at all altitudes Some indeterminate variables such as mixture leaning technique fuel metering characteristics engine and propeller condition and air turbulence may account for variations of 10 or more in range and endurance Therefore it is important to utilize all available information to estimate the fuel required for the particular flight and to flight plan in a conservative manner USE OF PER...

Page 106: ...AIRPLANE CONFIGURATION Takeoff weight 1320 Pounds Usable fuel 24 0 Gallons TAKEOFF CONDITIONS Field pressure altitude 1500 Feet Temperature 28 C 16 C Above Standard Wind component along runway 14 Knot Head Wind Field length 3500 Feet CRUISE CONDITIONS Total distance 260 Nautical Miles Pressure altitude 5500 Feet Temperature 20 C 16 C Above Standard Expected wind enroute 10 Knot Head Wind LANDING C...

Page 107: ...lts in the following These distances are well within the available takeoff field length However a correction for the effect of wind may be made based on information presented in the note section of the takeoff chart The correction for a 14 knot head wind is This results in the following distances corrected for wind Continued Next Page Ground roll 860 Feet Total distance to clear a 50 foot obstacle...

Page 108: ... considerations These include the cruise performance characteristics presented in Figure 5 7 the maximum rate of climb chart presented in Figure 5 5 and the time fuel and distance to climb chart presented in Figure 5 6 The cruise performance chart Figure 5 7 is entered at 6000 feet pressure altitude and 20 C above standard temperature These values most nearly correspond to the planned altitude and...

Page 109: ...d on the climb chart The approximate effect of a nonstandard temperature is to increase the time fuel and distance by 10 for each 10 C above standard temperature due to the lower rate of climb In this case assuming a temperature 16 C above standard the correction would be With this factor included the fuel estimate would be calculated as follows Using a similar procedure for the distance to climb ...

Page 110: ...ted fuel required is as follows Once the flight is underway ground speed checks will provide a more accurate basis for estimating the time enroute and the corresponding fuel required to complete the trip with ample reserve Continued Next Page 108 Knots 10 Knots 98 Knots 253 Nautical Miles 2 6 Hours 98 Knots 2 6 hours 6 0 gallons hour 15 6 Gallons 30 6 0 gallons hour 3 0 Gallons 60 Engine start tax...

Page 111: ...s A correction for the effect of wind may be made based on information presented in the note section of the landing chart using the same procedure as outlined for takeoff DEMONSTRATED OPERATING TEMPERATURE Satisfactory engine cooling has been demonstrated for this airplane with an outside air temperature 23 C above standard This is not to be considered as an operating limitation Reference should b...

Page 112: ...SECTION 5 CESSNA PERFORMANCE MODEL 162 GARMIN G300 U S Figure 5 1 162PHUS 00 5 10 ...

Page 113: ...CESSNA SECTION 5 MODEL 162 PERFORMANCE GARMIN G300 U S NOTE Altitude loss during a stall recovery may be as much as 250 feet KIAS values are approximate Figure 5 2 162PHUS 00 5 11 ...

Page 114: ...SECTION 5 CESSNA PERFORMANCE MODEL 162 GARMIN G300 U S Figure 5 3 162PHUS 01 5 12 ...

Page 115: ...CESSNA SECTION 5 MODEL 162 PERFORMANCE GARMIN G300 U S Figure 5 4 5 13 162PHUS 01 ...

Page 116: ...SECTION 5 CESSNA PERFORMANCE MODEL 162 GARMIN G300 U S Figure 5 5 162PHUS 01 5 14 ...

Page 117: ...CESSNA SECTION 5 MODEL 162 PERFORMANCE GARMIN G300 U S Figure 5 6 162PHUS 01 5 15 ...

Page 118: ...SECTION 5 CESSNA PERFORMANCE MODEL 162 GARMIN G300 U S Figure 5 7 162PHUS 01 5 16 ...

Page 119: ...CESSNA SECTION 5 MODEL 162 PERFORMANCE GARMIN G300 U S TEMPERATURE CONVERSION CHART Figure 5 8 162PHUS 00 5 17 ...

Page 120: ...SECTION 5 CESSNA PERFORMANCE MODEL 162 GARMIN G300 U S CROSSWIND COMPONENT NOTE Maximum demonstrated crosswind velocity is 12 knots not a limitation Figure 5 9 162PHUS 00 5 18 ...

Page 121: ... 6 7 Carb F Indicator In Yellow Band Range Yellow Digits 6 8 FORCED LANDINGS 6 9 Emergency Landing Without Engine Power 6 9 Precautionary Landing With Engine Power 6 10 Ditching 6 11 FIRES 6 12 During Start On Ground 6 12 Engine Fire In Flight 6 12 Electrical Fire or Cabin Fire In Flight 6 13 Wing Fire 6 14 ICING 6 15 Inadvertent Icing Encounter During Flight 6 15 ABNORMAL LANDINGS 6 17 Landing Wi...

Page 122: ...Than 12 5 6 20 Volts Indication Above Green Band Range or Volts More Than 15 6 22 AIR DATA ATTITUDE AND HEADING REFERENCE SYSTEM ADAHRS FAILURE 6 23 Red X PFD or MFD Indicators Airspeed Altitude Attitude Horizontal Situation Indicator HSI or Engine Indicating System EIS 6 23 PFD MFD DISPLAY MALFUNCTION OR FAILURE 6 24 PFD or MFD Display Black No Information 6 24 PFD or MFD Display Information Not ...

Page 123: ...rgency Descent Through Clouds ADAHRS FAILED 6 32 Recovery From Spiral Dive In The Clouds ADAHRS FAILED 6 33 Inadvertent Flight Into Icing Conditions 6 34 Spins 6 35 Rough Engine Operation Or Loss Of Power 6 36 Carburetor Icing 6 36 Spark Plug Fouling 6 36 Magneto Malfunction 6 36 Idle Power Engine Roughness 6 37 Low Oil Pressure 6 37 Electrical Power Supply System Malfunctions 6 38 Excessive Rate ...

Page 124: ......

Page 125: ...ines described in this section should be considered and applied as necessary to correct the problem In any emergency situation the most important task is continued control of the airplane and maneuver to execute a successful landing Emergency procedures associated with optional or supplemental equipment are found in Section 10 Supplements AIRSPEEDS FOR EMERGENCY OPERATIONS ENGINE FAILURE AFTER TAK...

Page 126: ...MASTER Switch ALT and BAT OFF ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF 1 Airspeed 70 KIAS Flaps UP 65 KIAS Flaps 10 FULL 2 MIXTURE Control IDLE CUTOFF pull full out 3 FUEL SHUTOFF Valve OFF pull full out 4 MAGNETOS Switch OFF 5 Wing Flaps AS REQUIRED FULL recommended 6 MASTER Switch ALT and BAT OFF when landing is assured 7 Land STRAIGHT AHEAD 8 Doors UNLATCH just prior to touchdown NOTE Both cabi...

Page 127: ...ine will restart automatically within a few seconds If propeller has stopped possible at low speeds turn MAGNETOS switch to START advance throttle slowly from idle and lean the mixture from full rich as required to obtain smooth operation OIL PSI INDICATOR IN RED BAND RANGE RED DIGITS 1 OIL F CHECK IF OIL F ABOVE GREEN BAND RANGE OR OIL F RISING engine failure immanent 2 Throttle Control REDUCE PO...

Page 128: ...AND OR RPM LOSS IS DETECTED CARB F IN YELLOW BAND RANGE 2 CARB HEAT Control Knob ON pull full out 3 THROTTLE Control FULL push full in 4 MIXTURE Control LEAN as required 5 CARB F Indicator CHECK IF ENGINE ROUGHNESS CONTINUES 6 CARB F Indicator MONITOR 7 ALTITUDE CONSIDER CHANGE to warmer or drier air mass if terrain permits 8 Land as soon as practical IF ENGINE ROUGHNESS IS NOT DETECTED CARB F ABO...

Page 129: ...location intentions and SQUAWK 7700 6 MAGNETOS Switch OFF 7 Wing Flaps AS REQUIRED FULL recommended 8 MASTER Switch ALT and BAT OFF when landing is assured 9 ELT ACTIVATE 10 Doors UNLATCH just prior to touchdown NOTE Both cabin doors are equipped with gas struts and should open automatically when unlatched Delaying opening until just prior to touchdown will reduce cabin buffeting and wind noise No...

Page 130: ...tions 6 Wing Flaps FULL on final approach 7 Airspeed 60 KIAS 8 MASTER Switch ALT and BAT OFF when landing assured 9 ELT ACTIVATE 10 Doors UNLATCH Just prior to touchdown NOTE Both cabin doors are equipped with gas struts and should open automatically when unlatched Delaying opening until just prior to touchdown will reduce cabin buffeting and wind noise Non emergency flight with doors open is proh...

Page 131: ...AS with Flaps UP or at 65 KIAS with Flaps 10 6 Approach High Winds Heavy Seas INTO THE WIND Light Winds Heavy Swells PARALLEL TO SWELLS 7 ELT ACTIVATE 8 Doors UNLATCH just prior to touchdown NOTE Both cabin doors are equipped with gas struts and should open automatically when unlatched Delaying opening until just prior to touchdown will reduce cabin buffeting and wind noise Non emergency flight wi...

Page 132: ...isher OBTAIN have ground attendants obtain if not installed 11 Airplane EVACUATE 12 Fire EXTINGUISH using fire extinguisher wool blanket or dirt 13 Fire Damage INSPECT repair or replace damaged components and or wiring before conducting another flight ENGINE FIRE IN FLIGHT 1 MIXTURE Control IDLE CUTOFF pull full out 2 FUEL SHUTOFF Valve OFF pull full out 3 MASTER Switch ALT Only OFF 4 Cabin Vents ...

Page 133: ...e 5 AVN MASTER Switch OFF 6 All Other Switches except MAGNETOS switch OFF IF FIRE HAS NOT BEEN EXTINGUISHED 7 MASTER Switch ALT and BAT ON 8 Rapid Descent EXECUTE Perform sideslip to rapidly loose altitude and shorten exposure time 9 AVN MASTER Switch ON 10 Radio ALERT ATC or TRANSMIT MAYDAY ON 121 5 MHZ give location intentions and SQUAWK 7700 11 Forced Landing EXECUTE refer to PRECAUTIONARY LAND...

Page 134: ...S USED TO REMOVE SMOKE FROM THE CABIN 7 Cabin Vents OPEN when sure that fire is completely extinguished 8 CABIN HEAT Control Knob ON pull full out when sure that fire is completely extinguished 9 Circuit Breakers CHECK for OPEN circuit s do not reset 10 MASTER Switch ALT and BAT ON 11 AVN MASTER Switch ON 12 Land the airplane as soon as possible to inspect for damage WING FIRE 1 LDG Light Switch O...

Page 135: ...ICING CONDITIONS 4 Watch for signs of induction air filter icing and apply carburetor heat as required Monitoring the G300 Carb F Indicator may assist early detection A loss of engine RPM could be caused by carburetor ice or ice blocking the air intake filter Adjust the throttle as necessary to hold engine RPM Adjust mixture as necessary for any change in power settings or if carburetor heat is us...

Page 136: ...remely rapid ice build up select a suitable off airport landing site 7 With an ice accumulation of 0 25 inch 6 35mm or more on the wing leading edges be prepared for significantly higher power requirements higher approach and stall speeds and a longer landing roll Gently pitch and yaw the airplane periodically to keep ice bridging on the controls to a minimum 8 Leave wing flaps retracted With a se...

Page 137: ...rence speed cues such as flap extension forces slipstream sounds etc Stall warning horn will function and provide approximately 5 knot stall warning 6 Touchdown NORMAL 7 Directional Control MAINTAIN NOTE Without accurate speed information landing may be made at faster than normal speeds Gently apply brakes while continuing to fly the airplane during roll out Loss of directional control may result ...

Page 138: ...ol MAINTAIN using full rudder control Attempt to limit differential braking 7 Braking Use brakes only as needed to lessen chance of prop strike Rolling drag of the flat nose tire will increase braking effect DOOR OPEN IN FLIGHT WARNING INTENTIONAL FLIGHT WITH DOOR S OPEN IS PROHIBITED 1 CABIN DOOR LEAVE OPEN do not attempt to close 2 THROTTLE Control REDUCE as necessary 3 Airspeed 80 KIAS or less ...

Page 139: ...nd as soon as possible NOTE The PFD will be operating on the secondary battery only The secondary battery is not a back up battery It is included in the electrical system to limit display presentation issues that might arise during the voltage drop which occurs during engine start In good condition the secondary battery may provide 5 to 10 minutes of PFD operation 3 Prepare for total loss of elect...

Page 140: ...5 0 volts at higher RPM The master switch need not be recycled since an overvoltage condition has not occurred to deactivate the alternator system 1 AVN MASTER Switch OFF NOTE Radio Transponder Pitch Trim and options MFD Autopilot and PS Intercom if installed will be inoperative with AVN MASTER Switch in the OFF position 2 START ALT Circuit Breaker CHECK IN if open reset close circuit breaker If c...

Page 141: ... follows a LDG Light Switch OFF use as required for landing b NAV Light Switch OFF c STROBE Light Switch OFF d AVN MASTER Switch OFF NOTE Radio Transponder Pitch Trim and options MFD Autopilot and PS Intercom if installed will be inoperative with AVN MASTER Switch in the OFF position 11 Land as soon as practical NOTE A fully charged battery in good condition should provide power under reduced load...

Page 142: ... Load REDUCE as follows a LDG Light Switch OFF use as required for landing b NAV Light Switch OFF c STROBE Light Switch OFF d AVN MASTER Switch OFF NOTE Radio Transponder Pitch Trim and options MFD Autopilot and PS Intercom if installed will be inoperative with AVN MASTER OFF 3 Land as soon as practical NOTE A fully charged battery in good condition should provide power under reduced load for 30 m...

Page 143: ...rmation to determine an approximate airspeed b Select COMPASS ARC from G300 MAP SET UP for approximate GPS derived heading information or monitor magnetic compass if installed c Reference GPS ALTITUDE on TERRAIN PROFILE page GPS altitude is the white arrowhead on left side or MFD INFO page if installed for approximate altitude d Navigate using pilotage and GPS moving map if available e Land as soo...

Page 144: ...not reset b If closed pull open PFD MFD Circuit Breaker and pull open SEC PWR Circuit Breaker overhead Panel Light will go off then reset close both circuit breakers 3 Affected Display Continued BLACK Screen No information displayed Use other display if installed a Transponder Select Pressure Alt display using FUNC button ADAHRS may be providing altitude information to transponder b Navigate using...

Page 145: ...t breakers a ADAHRS Circuit Breaker CLOSE b PFD MFD Circuit Breaker CLOSE c SEC PWR Circuit Breaker CLOSE 3 Affected Display s NOT UPDATING use other display if installed a Transponder Select Pressure Altitude display using FUNC button ADAHRS may be providing altitude information to transponder b Navigate using pilotage and magnetic compass if installed to nearest suitable landing site c Land as s...

Page 146: ...h control forces by changing speed or flap configuration within airspeed limitations 4 CRUISE Consider range reduction and destination change if cruise speed is reduced by flap speed limitations 5 APPROACH Establish stabilized approach using normal speeds is preferred This may include change of destination for longer runway 6 LANDING WITH FAILED TRIM Consider making Flaps UP landing if pitch contr...

Page 147: ...ecklist will provide added safety after a failure of this type If an engine failure occurs immediately 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 the 180 gliding turn necessary to return to the runway The checklist procedures assume that adequate time exis...

Page 148: ...SECTION 6 CESSNA EMERGENCY PROCEDURES MODEL 162 GARMIN G300 U S MAXIMUM GLIDE Figure 6 1 162PHUS 00 6 28 ...

Page 149: ...oid a landing flare because of the difficulty in judging height over a water surface The checklist assumes the availability of power to make a precautionary water landing If power is not available use of the airspeeds noted with minimum flap extension will provide a more favorable attitude for a power off ditching In a forced landing situation DO NOT turn off the MASTER switch BAT side or AVN MAST...

Page 150: ...anding flare or round out the nose will come down when power is reduced and the airplane may touch down on the nosewheel before the main wheels Maintain directional control and close the throttle at touchdown FIRES Although engine fires are extremely rare in flight if a fire is encountered the steps of the appropriate checklist should be followed After completion of the checklist procedure execute...

Page 151: ...ation is not available The G300 map display should be configured with the COMPASS ARC from the MAP SET UP menu The COMPASS ARC will provide GPS derived heading information on the moving map display GPS derived heading information is not as accurate as magnetic heading it will provide a means of situational awareness and the moving map can provide navigation Other GPS information such as track TRK ...

Page 152: ...ect the INFO page and reference the GPS ALTITUDE GPS ALTITUDE is not the same as barometric altitude but it will give an altitude approximation 3 TERRAIN Select G300 TERRAIN ON If RED terrain warning is issued apply full power and climb at 58 KIAS estimated Stall warning will provide approximate 5 knot stall warning margin 4 Monitor Ground Speed GS GPS derived GS in combination with GPS derived wi...

Page 153: ...ing map for heading and turn information 4 Cautiously apply elevator back pressure to slowly reduce airspeed to approximately 70 KIAS Monitor speed and do not reduce airspeed below 70 KIAS Slowly advance throttle to approximate 1700 1800 RPM as speed reaches 70 75 Knots 5 Elevator Trim ADJUST maintain 70 75 KIAS glide speed 6 Use aileron control to maintain wings level and constant heading 7 CARB ...

Page 154: ... ice or ice blocking the air intake filter Should this happen apply full carburetor heat and adjust throttle to obtain maximum RPM In some instances the throttle may need to be reduced for maximum power The mixture should then be adjusted as required to obtain maximum RPM The G300 CARB F indicator should be monitored during carb heat application to ensure carb temperature rises Refer to the CARBUE...

Page 155: ...eries 4 HOLD THESE CONTROL INPUTS UNTIL ROTATION STOPS Premature relaxation of the control inputs may extend the recovery 5 AS ROTATION STOPS NEUTRALIZE RUDDER WINGS LEVEL FLAPS UP AND MAKE A SMOOTH RECOVERY FROM THE RESULTING DIVE AVOID OVERSTRESSING AND OVERSPEEDING THE AIRFRAME NOTE If the rate of the spin makes determining the direction of rotation difficult the magenta turn rate trend vector ...

Page 156: ...ight may be caused by one or more spark plugs becoming fouled by carbon or lead deposits This may be verified by turning the MAGNETOS switch momentarily from BOTH to either L or R position An obvious power loss in single magneto operation is evidence of spark plug or magneto trouble Leaning the mixture to the recommended lean setting for cruising flight may resolve a spark plug fouling issue If th...

Page 157: ... loss and you need to restart the engine during flight In all cases you should land the airplane at the nearest airport for repairs if low speed engine roughness requires you to adjust the fuel mixture control to improve engine operation LOW OIL PRESSURE If the low oil pressure indicator OIL PSI turns red and oil temperature indicator OIL F remains normal it is possible that the oil pressure sendi...

Page 158: ...the battery condition may be low enough to accept above normal charging during the initial part of a flight However after thirty minutes of cruising flight the main battery ammeter AMPS should be indicating less than 5 amps of charging current If the charging current remains above this value on a long flight the battery electrolyte could overheat and evaporate Electronic components in the electric...

Page 159: ...lternator system 1 MASTER Switch ALT Only OFF 2 START ALT Circuit Breaker CHECK IN 3 MASTER Switch ALT Only ON If the problem was a minor AICU disturbance in the electrical system normal main battery charging will start A charge current will be shown on the main battery ammeter AMPS and the LOW VOLTS annunciator will go off If the red LOW VOLTS annunciator is displayed and a discharge current is s...

Page 160: ...way for the engine data displayed on the Primary Flight Display PFD and optional Multi Function Display MFD Failure of the ADAHRS unit or the individual sensors may leave only GPS derived flight data for situational awareness and navigation The pilot should be thoroughly familiar with the G300 operation page and information location and methods of accessing the GPS flight data before beginning any...

Page 161: ...ge 7 8 Empennage 7 8 Right Wing Trailing Edge 7 9 Right Wing 7 9 Nose 7 11 Before Starting Engine 7 13 Starting Engine With Battery 7 13 Starting Engine With External Power 7 15 Before Takeoff 7 18 Takeoff 7 19 Normal Takeoff 7 19 Short Field Takeoff 7 19 Enroute Climb 7 20 Cruise 7 20 Descent 7 20 Before Landing 7 20 Landing 7 21 Normal Landing 7 21 Short Field Landing 7 21 Balked Landing 7 21 Af...

Page 162: ...levator Trim 7 31 Takeoff 7 31 Power Check 7 31 Wing Flap Settings 7 32 Crosswind Takeoff 7 33 Enroute Climb 7 33 Cruise 7 34 Leaning Without Exhaust Gas Temperature EGT Indicator 7 35 Leaning With Exhaust Gas Temperature EGT Indicator 7 36 Fuel Savings Procedures For Flight Training Operations 7 38 Stalls 7 39 Descent 7 39 Landing 7 40 Normal Landing 7 40 Short Field Landing 7 40 Crosswind Landin...

Page 163: ...ed for any lesser weight TAKEOFF Normal Climb 65 75 KIAS Short Field Takeoff Flaps 10 Speed at 50 Feet 55 KIAS ENROUTE CLIMB FLAPS UP Normal Sea Level 65 75 KIAS Best Rate of Climb 62 KIAS Best Angle of Climb 57 KIAS LANDING APPROACH Normal Approach Flaps UP 60 70 KIAS Normal Approach Flaps FULL 55 65 KIAS Short Field Approach Flaps FULL 50 KIAS BALKED LANDING Maximum Power Flaps 25 50 KIAS MAXIMU...

Page 164: ...l ground attitude refer to Figure 1 1 to make sure that fuel drain valves allow for accurate sampling In cold weather remove even small accumulations 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 If a night flight is planned check operation of all lights and make sure a flashlight is available Figure...

Page 165: ...R SOURCE OR MANUALLY ROTATING THE PROPELLER TREAT THE PROPELLER AS IF THE MAGNETOS SWITCH WERE ON DO NOT STAND NOR ALLOW ANYONE ELSE TO STAND WITHIN THE ARC OF THE PROPELLER SINCE A LOOSE OR BROKEN WIRE OR A COMPONENT MALFUNCTION COULD CAUSE THE ENGINE TO START 8 MAGNETOS Switch OFF 9 MASTER Switch ALT and BAT ON 10 AVN MASTER Switch ON 11 Primary Flight Display PFD CHECK verify PFD is ON and soft...

Page 166: ...ED 18 AVN MASTER Switch OFF 19 MASTER Switch ALT and BAT OFF 20 Fire Extinguisher CHECK if installed verify gage pointer in green arc 2LEFT WING 1 Cabin Door CHECK security and condition 2 Main Wheel Tire CHECK proper inflation and general condition weather checks tread depth and wear etc 3 Brake Line CHECK security and condition 4 Wheel Fairings CHECK security and condition if installed 5 Fresh A...

Page 167: ...tional contaminants to the sampling points Take repeated samples from all fuel drain points until all contamination has been removed If contaminants are still present refer to WARNING below and do not fly airplane NOTE Collect all sampled fuel in a safe container Dispose of the sampled fuel so that it does not cause a nuisance hazard or damage to the environment WARNING IF AFTER REPEATED SAMPLING ...

Page 168: ... pushing the aileron up from the neutral or faired with the flaps in the Flaps UP position and returning the aileron back to the neutral or faired position Pushing down on the aileron may create an over centered condition requiring re centering of the cockpit control stick 2 Flap DEFLECT and CHECK flap aileron cables up spring tension and general condition 3 Com Antenna and OAT Temp Probe CHECK se...

Page 169: ...e aileron back to the neutral or faired position Pushing down on the aileron may create an over centered condition requiring re centering of the cockpit control stick 7RIGHT WING 1 Strobe Nav Light CHECK condition operation and cleanliness of cover 2 Wing Tiedown DISCONNECT check security and condition 3 Stall Warning Opening CHECK blockage NOTE To check the system place a clean handkerchief over ...

Page 170: ...r samples until clear and then gently rock wings and lower tail to the ground to move any additional contaminants to the sampling points Take repeated samples from all fuel drain points until all contamination has been removed If contaminants are still present refer to WARNING below and do not fly airplane NOTE Collect all sampled fuel in a safe container Dispose of the sampled fuel so that it doe...

Page 171: ... 3 5 quarts Fill to 5 quarts for extended flight 8 Fuel Strainer Quick Drain Valve DRAIN bottom left side of engine cowling Drain at least a cupful of fuel using sampler cup from valve to check for water sediment and proper fuel grade before each flight and after each refueling If water is observed take further samples until clear and then gently rock wings and lower tail to the ground to move any...

Page 172: ...til clear and then gently rock wings and lower tail to the ground to move any additional contaminants to the sampling points Take repeated samples from all fuel drain points including the fuel strainer and fuel sump valve until all contamination has been removed If contaminants are still present refer to WARNING below and do not fly the airplane NOTE Collect all sampled fuel in a safe container Di...

Page 173: ...SSIBLE DAMAGE TO AVIONICS 10 FUEL SHUTOFF Valve ON push full in STARTING ENGINE With Battery IF FUEL PRIMER CONTROL INSTALLED 1 Fuel PRIMER Control AS REQUIRED a Engine COLD PUMP 1 to 3 strokes b Engine WARM NONE IF FUEL PRIMER CONTROL NOT INSTALLED 1 THROTTLE Control AS REQUIRED a Engine COLD PUMP 3 to 6 strokes b Engine WARM PUMP ONCE push full in and pull full out STARTING ENGINE With Battery C...

Page 174: ...verify discharge shown negative 10 Propeller Area CLEAR verify that all people and equipment are at a safe distance from the propeller 11 STROBE Light Switch ON 12 MAGNETOS Switch START release when engine starts NOTE If the engine is primed too much flooded place the mixture control in the IDLE CUTOFF position open the throttle control 1 2 to full and engage the starter motor START When the engin...

Page 175: ...ine WARM CLOSED 4 MIXTURE Control FULL RICH push full in 5 AVN MASTER Switch OFF 6 MASTER Switch ALT and BAT ON 7 Engine Indicating System CHECK PARAMETERS verify no red X s through indicators 8 VOLTS CHECK EIS ENGINE PAGE NOTE A red LOW VOLTS annunciator will come on when battery voltage is less than 12 5 volts As battery voltage decreases the Garmin G300 display will become less bright and event...

Page 176: ...oo much flooded place the mixture control in the IDLE CUTOFF position open the throttle control 1 2 to full and engage the starter motor START When the engine starts advance the mixture control to the FULL RICH position and promptly retard the throttle control 19 Oil Pressure CHECK verify that oil pressure increases above 10 PSI into the YELLOW BAND range in 30 seconds 20 Power REDUCE TO IDLE 21 E...

Page 177: ...E Control REDUCE TO IDLE e MASTER Switch ALT ON f THROTTLE Control INCREASE to approximately 1500 RPM g AMPS CHECK verify charge shown positive WARNING IF AMMETER DOES NOT SHOW POSITIVE CHARGE AMPS REMOVE THE BATTERY FROM THE AIRPLANE AND SERVICE OR REPLACE THE BATTERY BEFORE FLIGHT 27 LDG Light Switch OFF as required 28 STROBE Light Switch OFF 29 AVN MASTER Switch ON 30 MIXTURE Control LEAN as re...

Page 178: ... and LOCKED 10 MIXTURE Control RICH 11 Autopilot ENGAGE if installed push AP button on autopilot control panel a Flight Controls CHECK verify autopilot can be overpowered in both pitch and roll axes b A P DISC Button PRESS if installed verify autopilot disengages and aural alert is heard 12 Elevator Trim Control Switch SET FOR T O 13 THROTTLE Control 1700 RPM once oil temperature is above 75 F and...

Page 179: ...E Control RICH above 5000 feet pressure altitude lean for maximum RPM 5 Directional Control MAINTAIN use differential braking until rudder control becomes effective 6 Elevator Control LIFT NOSEWHEEL AT 50 KIAS 7 Climb Airspeed 65 75 KIAS 8 Wing Flaps RETRACT at safe altitude SHORT FIELD TAKEOFF 1 Wing Flaps 10 2 CARB HEAT Control Knob OFF push full in 3 Brakes APPLY 4 THROTTLE Control FULL push fu...

Page 180: ...l Switch ADJUST 3 MIXTURE Control LEAN for best power setting DESCENT 1 Power AS DESIRED 2750 RPM maximum 2 MIXTURE Control ADJUST if necessary to make engine run smoothly 3 Altimeter SET 4 Wing Flaps AS DESIRED UP 10 below 100 KIAS 10 25 below 85 KIAS 25 FULL below 70 KIAS 5 CARB HEAT Control Knob ON as required BEFORE LANDING 1 Seats and Seat Belts SECURED and LOCKED 2 MIXTURE Control RICH push ...

Page 181: ...r and differential braking SHORT FIELD LANDING 1 Airspeed 60 70 KIAS Flaps UP 2 Wing Flaps FULL 3 Airspeed 50 KIAS until flare 4 Elevator Trim Control ADJUST 5 Power REDUCE TO IDLE as obstacle is cleared 6 Touchdown MAIN WHEELS FIRST 7 Brakes APPLY HEAVILY while maintaining directional control 8 Wing Flaps UP BALKED LANDING 1 THROTTLE Control FULL push full in 2 CARB HEAT Control Knob OFF push ful...

Page 182: ...itch OFF 4 Transponder STBY SECURING AIRPLANE 1 Parking Brake SET a Brakes APPLY b PARKING BRAKE Control Knob ON pull full out 2 THROTTLE Control IDLE pull full out 3 Electrical Equipment OFF 4 AVN MASTER Switch OFF 5 MIXTURE Control IDLE CUTOFF pull full out 6 MAGNETOS Switch OFF 7 MASTER Switch ALT and BAT OFF 8 Control Lock INSTALL 162PHUS 00 7 22 ...

Page 183: ...ction plates on the airplane should be checked following periodic inspections If the airplane has been waxed or polished check the external static pressure source hole for stoppage If the airplane has been kept in a crowded hangar it should be checked for dents and scratches on wings fuselage and tail surfaces damage to navigation strobe light assemblies wing tip fairings and avionics antennas Che...

Page 184: ...ter any fuel system check or servicing Fuel system vents should also be inspected for obstructions ice or water especially after exposure to cold wet weather If the airplane has been stored outside in windy or gusty areas or tied down adjacent to taxiing airplanes special attention should be paid to control surface stops hinges and brackets to detect the presence of potential wind damage Airplanes...

Page 185: ...ncing the throttle control fully in and out works an accelerator pump in the engine carburetor for priming In this way the throttle may be pumped or given some number of strokes to provide the required prime An optional plunger style primer may be used to provide fuel prime if installed If the engine is already warm pump the throttle once then leave the throttle closed to start No additional primi...

Page 186: ...rting avoid the use of carburetor heat unless icing conditions prevail NOTE Additional details concerning cold weather starting and operation may be found under COLD WEATHER OPERATION paragraphs in this section After the completion of normal engine starting procedures it is a good practice to verify that the engine starter has disengaged If the starter contactor were to stick closed causing the st...

Page 187: ...ATIONS IN WIND CONDITIONS ABOVE 22 KNOTS ARE NOT RECOMMENDED When taxiing the combination of differential braking and free castoring nose wheel provide excellent ground maneuvering in tight spaces as well as control during normal taxiing Differential brake application should be done by firm short taps of the brake pedal so as to nudge the airplane in the desired direction Excess speed and riding a...

Page 188: ...ly reset before takeoff The CARB HEAT control knob should be pushed full in to the OFF position during all ground operations unless carb heat is absolutely necessary to correct engine roughness When the CARB HEAT control knob is pulled out to the ON position air entering the engine is not filtered However if needed use FULL CARB HEAT until engine roughness clears Monitoring the CARB ºF Indicator w...

Page 189: ... TAXIING Continued TAXIING DIAGRAM NOTE Strong quartering tail winds require caution Avoid sudden bursts of the throttle and sharp braking when the airplane is in this attitude Use differential braking and rudder to maintain direction Figure 7 2 162PHUS 00 7 29 ...

Page 190: ...TURE IS ABOVE 75ºF AND OIL PRESSURE IS WITHIN THE GREEN BAND RANGE PRIOR TO PREFORMING A MAGNETO CHECK The magneto check must be made at 1700 RPM Turn the MAGNETOS switch from the BOTH position to the R position Note the new RPM then turn the MAGNETOS switch back to the BOTH position to clear the spark plugs Turn the MAGNETOS switch to the L position note the new RPM then turn the switch back to t...

Page 191: ...he engine is at idle ELECTRIC ELEVATOR TRIM Make sure the elevator trim tab is in the takeoff position when the trim pointer is aligned with the T O index mark on the EIS TRIM indicator Adjust the trim during flight as necessary to make control wheel forces more neutral TAKEOFF POWER CHECK It is important to check full throttle engine operation early in the takeoff roll Any sign of rough engine op...

Page 192: ...hold the throttle setting WING FLAP SETTINGS Normal takeoffs use wing flaps UP 10 Using 10 wing flaps reduces the ground roll to lift off while keeping the total distance over an obstacle by equivalent to the flaps UP distances Flap deflections greater than 10 are not approved for takeoff If 10 wing flaps are used for takeoff the flaps should stay at 10 until all obstacles are cleared and a safe f...

Page 193: ...he ground make a coordinated turn into the wind to correct for drift ENROUTE CLIMB Normal enroute climbs are performed with flaps up at full throttle and 65 to 75 KIAS for the best combination of performance visibility and engine cooling The mixture should be full rich during climb at altitudes up to 5000 feet pressure altitude Above 5000 feet pressure altitude the mixture can be leaned as needed ...

Page 194: ...ation The Cruise Performance charts should be used as a guide along with the available winds aloft information to determine the most favorable altitude power setting and fuel needed for a given flight The selection of cruise altitude on the basis of the most favorable wind conditions and the use of low power settings are significant factors that should be considered on every trip to reduce fuel co...

Page 195: ...peration LEANING WITHOUT EXHAUST GAS TEMPERATURE EGT INDICATOR BEST POWER CRUISE Use the mixture control vernier adjustment to lean the fuel mixture by slowly turning the mixture control knob in the counterclockwise direction while monitoring engine RPM As RPM increases continue to carefully lean the mixture until it reaches peak RPM Slightly enrichen mixture turn mixture control knob clockwise un...

Page 196: ...n the fuel mixture by slowly turning the mixture control knob in the counterclockwise direction while monitoring EGT As EGT F increases continue to lean the mixture until it reaches peak EGT Enrichen the mixture by slowly turning the mixture control clockwise and monitor EGT F until EGT decreases slightly NOTE The Model 162 engine manufacturer Teledyne Continental Motors has not approved operation...

Page 197: ...ER RETARD THROTTLE THEN ADJUST THE MIXTURE CONTROL NOTE Any change in altitude or power setting will require a change in the recommended lean mixture setting and a recheck of the EGT setting The EGT indicator takes several seconds after a mixture adjustment to start to show an EGT change Finding peak EGT and adjusting the mixture to the applicable setting should take approximately one minute when ...

Page 198: ...ing full throttle climbs above 5000 feet The mixture may remain leaned maximum RPM at full throttle for practicing maneuvers such as stalls and slow flight 3 Lean the mixture for maximum RPM during all operations at any altitude including those below 3000 feet when using 75 or less power NOTE When cruising or maneuvering at 75 power or less the mixture may be further leaned to best power cruise Th...

Page 199: ...OPER RECOVERY TECHNIQUES ARE USED IN THE EVENT AN INADVERTENT SPIN IS ENCOUNTERED Refer to Section 5 Figure 5 2 for power off stall speeds at 1320 pounds DESCENT Normal descent from altitude may be made with flaps retracted or with flaps extended to increase drag for a steepened descent angle Caution should be used to observe flap limit speeds Slips may be made in all flap configurations and are u...

Page 200: ...ortant for rough or soft field landings Directional control should be maintained using up to full rudder deflection and differential braking as necessary SHORT FIELD LANDING For a short field landing in smooth air conditions approach at 50 KIAS with FULL flaps using enough power to control the glide path Slightly higher approach speeds should be used in turbulent air conditions After all approach ...

Page 201: ...ING In a balked landing go around climb reduce the flap setting to 25 immediately after full power is applied and climb at 50 KIAS Above 3000 feet pressure altitude lean the mixture to obtain maximum RPM After clearing any obstacles allow the airplane to accelerate to 60 KIAS and carefully retract the flaps to 10 After clearing any obstacles carefully retract the flaps and allow the airplane to ac...

Page 202: ...y extended as the snow or slush depth increases The depth and consistency of this cover can in fact prevent takeoff in many instances The Garmin G300 Instrumentation Liquid Crystal Displays LCD may acquire a frosted or cloudy appearance at extremely cold temperatures The displays may also be very slow to update information when cold soaked Proper flight display clarity and flight data update rates...

Page 203: ...trapped in the oil cooler which probably will be congealed prior to starting in extremely cold temperatures WARNING WHEN TURNING THE PROPELLER BY HAND TREAT IT AS IF THE MAGNETOS SWITCH IS IN THE ON POSITION A LOOSE OR BROKEN GROUND WIRE ON EITHER MAGNETO COULD ENERGIZE THE ENGINE Prior to starting on cold mornings it is advisable to turn the propeller manually through several engine compression c...

Page 204: ...ming will be necessary As soon as the cylinders begin to fire open the throttle slightly to keep it running Use caution to prevent inadvertent forward movement of the airplane during starting when parked on snow or ice CAUTION HEAVY PRIMING AND THROTTLE PUMPING DURING START INCREASES THE RISK OF INDUCTION SYSTEM FIRE RESULTING FROM A BACKFIRE OR OTHER ABNORMALITY DURING START IN THE EVENT OF AN EN...

Page 205: ...llowed by a immediate takeoff If engine is allowed to idle for a extended period of time between the completion of the BEFORE TAKEOFF checklist and prior to TAKEOFF oil temperature may fall below 75 F 24 C requiring a slow engine acceleration to warm the engine oil prior to performing TAKEOFF WINTERIZATION KIT An optional winterization kit is available and may be utilized when cold weather operati...

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Page 207: ...rplane File 8 7 Airplane Inspection Periods 8 8 FAA Required Inspections 8 8 Cessna Inspection Programs 8 8 Cessna Customer Care Program 8 8 Pilot Conducted Preventive Maintenance 8 9 Alterations Or Repairs 8 9 Ground Handling 8 10 Towing 8 10 Parking 8 11 Tiedown 8 11 Jacking 8 12 Leveling 8 13 Flyable Storage 8 13 Servicing 8 14 Oil 8 15 Oil Specification 8 15 Recommended Viscosity For Temperatu...

Page 208: ...nued Page Fuel 8 17 Approved Fuel Grades And Colors 8 17 Fuel Capacity 8 17 Fuel Additives 8 18 Fuel Contamination 8 21 Landing Gear 8 22 Cleaning And Care 8 22 Windshield And Windows 8 22 Painted Surfaces 8 23 Propeller Care 8 24 Engine Care 8 24 Interior Care 8 25 8 26 Avionics Care 8 25 8 26 162PHUS 01 8 2 ...

Page 209: ...ur airplane and how to maintain it and will remind you when lubrications and oil changes are necessary as well as other seasonal and periodic services The airplane should be regularly inspected and maintained in accordance with information found in the airplane maintenance manual and in company issued Service Bulletins Safety Alerts and Service Newsletters All service bulletins pertaining to the a...

Page 210: ...ins are available from Cessna Service Stations and Cessna Propeller Aircraft Customer Services UNITED STATES AIRPLANE OWNERS If your airplane is registered in the U S appropriate Cessna Owner Advisories will be mailed to you automatically according to the latest airplane registration name and address which you have provided to Cessna Therefore it is important that you provide correct and up to dat...

Page 211: ...may contact Cessna Customer Service at 316 517 5800 Fax 316 517 7271 or write to Cessna Aircraft Company P O Box 7706 Wichita KS 67277 Dept 569C To obtain additional Garmin publications you may contact Garmin Customer Service at Garmin International Inc 913 397 8200 Fax 913 397 8282 1200 East 151st Street Olathe Kansas 66062 USA or visit the Garmin website www Garmin com for current updates and su...

Page 212: ...ave a Customer Care Supplies and Publications Catalog covering all available items many of which the Service Station keeps on hand The Service Station can place an order for any item which is not in stock NOTE A Pilot s Operating Handbook which is lost or destroyed may be replaced by contacting a Cessna Service Station 162PHUS 01 8 6 ...

Page 213: ...Recommended to be carried in the airplane at all times 1 Current Pilot s Operating Handbook and Flight Training Supplement 2 Garmin G300 Pilot s Guide 190 00921 00 latest revision 3 Garmin G300 Cockpit Reference Guide CRG latest revision 4 Weight and Balance and associated papers 5 Equipment List To be made available upon request 1 Airframe Logbook 2 Engine Logbook 3 Propeller Logbook Most of the ...

Page 214: ...tives and when the inspections are repetitive to take appropriate steps to prevent inadvertent noncompliance CESSNA INSPECTION PROGRAMS Airplane owners should keep in mind that 14 CFR 61 and 14 CFR 65 establishes the requirement that properly certified agencies or personnel accomplish all required FAA inspections and most of the manufacturer recommended inspections CESSNA CUSTOMER CARE PROGRAM Spe...

Page 215: ...rrent Maintenance Manual must be obtained prior to performing any preventive maintenance to ensure that proper procedures are followed A Cessna Service Station should be contacted for further information or for required maintenance which must be accomplished by appropriately licensed personnel ALTERATIONS OR REPAIRS It is essential that a Cessna Service Station be contacted prior to any alteration...

Page 216: ...N REMOVE ANY INSTALLED RUDDER LOCK BEFORE TOWING If the airplane is towed or pushed over a rough surface during hangaring watch that the normal cushioning action of the nose strut does not cause excessive vertical movement of the tail and the resulting contact with low hangar doors or structure A flat nose tire will also increase tail height CAUTION DO NOT APPLY PRESSURE ON THE ELEVATOR OR HORIZON...

Page 217: ...he brakes are overheated Install the control stick lock and chock the wheels In severe weather and high wind conditions tie the airplane down as outlined in the following paragraph TIEDOWN Proper tiedown procedure is the best precaution against damage to the parked airplane by gusty or strong winds To tiedown the airplane securely proceed as follows 1 Set the parking brake and install the control ...

Page 218: ...o not jack both main wheels simultaneously using the individual main gear jack pads CAUTION DO NOT APPLY PRESSURE ON THE ELEVATOR OR HORIZONTAL STABILIZER SURFACES WHEN PUSHING ON THE TAILCONE ALWAYS APPLY PRESSURE AT A FUSELAGE BULKHEAD TO AVOID BUCKLING THE SKIN If nose gear maintenance is required the nosewheel may be raised off the ground by pressing down on a aft fuselage tailcone bulkhead ju...

Page 219: ...i takeoff and landing time with oil temperatures of 170 F to 220 F every 30 days or less depending on location and storage conditions Airplanes operated close to oceans lakes rivers and in humid regions are in greater need of engine preservation than airplanes operated in arid regions Appropriate engine preservation procedures must be practiced by the owner or operator of the airplane based on pre...

Page 220: ...Service Stations conduct all service inspection and test procedures in accordance with applicable Maintenance Manuals it is recommended that you contact a Cessna Service Station concerning these requirements and begin scheduling your airplane for service at the recommended intervals Depending on various flight operations your local government aviation agency may require additional service inspecti...

Page 221: ...shless Dispersant Oil Oil conforming to Teledyne Continental Motors TCM Service Information Letter SIL99 2B and all revisions and supplements thereto must be used after first 50 hours or oil consumption has stabilized RECOMMENDED VISCOSITY FOR TEMPERATURE RANGE Multiviscosity or straight grade oil may be used throughout the year for engine lubrication Refer to the following table for temperature v...

Page 222: ...ged at time intervals set forth by the engine manufacturer NOTE During the first 25 hour oil and filter change a general inspection of the overall engine compartment is required Items which are not normally checked during a preflight inspection should be given special attention Hoses metal lines and fittings should be inspected for signs of oil and fuel leaks and checked for abrasions chafing secu...

Page 223: ...S 90 82 l Total Capacity Each Tank 12 73 U S GALLONS 48 17 l Total Usable Each Tank 12 00 U S GALLONS 45 41 l NOTE To ensure maximum fuel capacity and minimize crossfeeding when refueling always park the airplane in a wings level normal ground attitude Refer to Figure 1 1 for normal ground attitude dimensions The fuel filler assembly is equipped with indicator tabs for 3 4 1 2 and 1 4 fuel quantit...

Page 224: ...s are quite rare and will not normally pose a problem to owners and operators they do exist in certain areas of the world and consequently must be dealt with when encountered Therefore to help alleviate the possibility of fuel icing occurring under these unusual conditions it is permissible to add isopropyl alcohol or Diethylene Glycol Monomethyl Ether DiEGME compound to the fuel supply The introd...

Page 225: ... a separate clean container approximately 2 3 gallon capacity and then transferring this mixture to the tank prior to the fuel operation Diethylene Glycol Monomethyl Ether DiEGME compound must be carefully mixed with the fuel in concentrations between 0 10 minimum and 0 15 maximum of total fuel volume Refer to Figure 8 1 for a DiEGME to fuel mixing chart WARNING ANTI ICING ADDITIVE IS DANGEROUS TO...

Page 226: ...buildup in the fuel which leeches out the additive An indication of this is when an excessive amount of water accumulates in the fuel tank sumps The concentration can be checked using a differential refractometer It is imperative that the technical manual for the differential refractometer be followed explicitly when checking the additive concentration Continued Next Page Figure 8 1 162PHUS 01 8 2...

Page 227: ... has been removed If after repeated sampling evidence of contamination still exists the airplane should not be flown Tanks should be drained and system purged by qualified maintenance personnel All evidence of contamination must be removed before further flight If the airplane has been serviced with the improper fuel grade defuel completely and refuel with the correct grade Do not fly the airplane...

Page 228: ...CK THE PLASTIC AND MAY CAUSE IT TO CRAZE If a windshield cleaner is not available the plastic can be cleaned with soft cloths moistened with Stoddard solvent to remove oil and grease 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 att...

Page 229: ...ax applied in accordance with the manufacturer s instructions If the airplane is operated in a seacoast or other salt water environment it must be washed and waxed more frequently to assure adequate protection Special care should be taken to seal around rivet heads and skin laps which are the areas most susceptible to corrosion A heavier coating of wax on the leading edges of the wings and tail an...

Page 230: ...INCHES MAY RESULT IN CRACKS OR FAILURE OF THE PROPELLER BLADE ENGINE CARE The engine may be cleaned using a suitable solvent in accordance with instructions in the Maintenance Manual Most efficient cleaning is done using a spray type cleaner Before spray cleaning ensure that protection is afforded for components which might be adversely affected by the solvent Refer to the airplane Maintenance Man...

Page 231: ... 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 may be cleaned with foam type detergent used according to the manufacturer s instructions To minimize wetting the fabric keep the foam as dry as possible and remove it with a vacuum cleaner CAUTION HARSH OR AB...

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Page 233: ...SNA SECTION 9 MODEL 162 PLACARDS AND MARKINGS GARMIN G300 U S PLACARDS AND MARKINGS TABLE OF CONTENTS Page Airspeed Indicator Markings 9 3 Powerplant Instrument Markings 9 4 Placards 9 5 162PHUS 00 9 1 9 2 ...

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Page 235: ...ation Upper limit is maximum speed permissible with flaps extended Green Band 41 124 Normal Operating Range Lower limit is maximum weight VS1 at most forward C G with flaps retracted Upper limit is maximum structural cruising speed Yellow Band 124 148 Operations must be conducted with caution and only in smooth air Red Line 149 Maximum speed for all operations Flaps 25 Tick Mark 85 Maximum Flaps 2...

Page 236: ...NT RED LOWER WARNING YELLOW LOWER CAUTION GREEN NORMAL OPERATING RANGE YELLOW UPPER CAUTION RED UPPER WARNING Tachometer RPM 2000 to 2750 RPM 2750 to 3500 RPM Oil Temperature OIL F 0 to 75 F 75 to 220 F 220 to 240 F 240 to 265 F Oil Pressure OIL PSI 0 to 10 PSI 10 to 30 PSI 30 to 60 PSI 60 to 100 PSI 100 to 140 PSI Exhaust Gas Temperature if installed EGT F 1000 to 1600 F White Advisory Carburetor...

Page 237: ... The markings and placards installed in this airplane contain operating limitations which must be complied with when operating this airplane Other operating limitations which must be complied with when operating this airplane in this category are contained in the Pilot s Operating Handbook No acrobatic maneuvers including spins are approved Flight into known icing conditions prohibited This airpla...

Page 238: ...to flight can result in bodily injury or death 5 Silk screened on the upper left instrument panel NO INTENTIONAL SPINS 6 On the instrument panel directly above the PFD MAXIMUM OPERATING MANEUVERING SPEED 89 KIAS DESIGN MANEUVERING SPEED 102 KIAS 7 Silk screened on the upper right instrument panel 8 Silk screened on the right instrument panel This aircraft was manufactured in accordance with Light ...

Page 239: ...62 PLACARDS AND MARKINGS GARMIN G300 U S PLACARDS Continued 9 On the right side of the baggage compartment below the window 10 Near both fuel tank filler cap 11 On the engine oil access door Continued Next Page 162PHUS 01 9 7 ...

Page 240: ... 162 GARMIN G300 U S PLACARDS Continued 12 On firewall adjacent to battery box and second placard on external power receptacle door if external power receptacle option is installed 13 Located on both left and right fuel sight tubes 162PHUS 01 9 8 ...

Page 241: ...d as a checklist to ensure all applicable supplements have been placed in the Pilot s Operating Handbook POH Supplements for both standard and installed optional equipment must be maintained to the latest revision Those supplements applicable to optional equipment which is not installed in the airplane do not have to be retained Each individual supplement contains its own Log of Effective Pages Th...

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