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Model 162 - Cessna Flight Training

1. SECTION 6 CESSNA EMERGENCY PROCEDURES MODEL 162 GARMIN G300 MAXIMUM GLIDE B10719 12 000 MN AHAH Propeller Windmilling Flaps Up Zero Wind 10 000 8000 c 9 a 6000 gt o lt x D E 4000 est Glide Speed 70 KIAS aoe 2000 0 0 2 4 6 8 10 12 14 16 18 20 Ground Distance Nautical Miles Figure 6 1 6 28 U S 162PHUS 00 CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 FORCED LANDINGS If all attempts to restart the engine fail and a forced landing is imminent select a suitable field and prepare for the landing as discussed under the Emergency Landing Without Engine Power checklist Transmit Mayday message on 121 5 MHz giving location intentions and squawk 7700 Before attempting an off airport landing with engine power available one should fly over the landing area at a safe but low altitude to inspect the terrain for obstructions and surface conditions proceeding as discussed in the Precautionary Landing With 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 messages on 121 5 MHz giving location intentions and squawk 7700 Avoid a landing flare because of the difficulty in judging height over a water surface The checklist assumes the
2. PERFORMANCE MODEL 162 GARMIN G300 CROSSWIND COMPONENT B3094 35 9 3 30 PS E 5 NG O 95 ot AE M inr I O S Lo gt A 20 ERG 2 SS AN Ox o Y 15 SO KO T 25 gt 10 P 10 3 5 5 Ims 80 O E 0 90 Anos UA bon 1 0 o o 5 5 e N Op nage Wing 0 O 75 UN yy Z 10 PA FE 0 5 10 15 20 25 30 35 Crosswind Component Knots NOTE Maximum demonstrated crosswind velocity is 12 knots not a limitation Figure 5 9 5 18 U S 162PHUS 00 CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 EMERGENCY PROCEDURES TABLE OF CONTENTS Page Introductio KA nde ds 6 5 Airspeeds For Emergency Operations 6 5 EMERGENCY PROCEDURES 6 6 ENGINE FAILURES AND MALFUNCTIONS 6 6 Engine Failure During Takeoff Roll 6 6 Engine Failure Immediately After Takeoff 6 6 Engine Failure During Flight Restart Procedures 6 7 Oil PSI Indicator In Red Band Range Red Digits 6 7 Carb F Indicator In Yellow Band Range Yellow Digits 6 8 FORCED LANDINGS 024 4200 KEER teeny BARE E EE EE 6 9 Emergency Landing Without Engine Power 6 9 Precautionary Landing With Engine Power 6 10 DIGDITIO ous at A tta EE tee AINE d cS VOE 6 11 FIRES 220 AG AG PALAD AANGAL NAG T ER RD DLE 6 12 During Start On Ground tosca tr RS 6 12 Engine Fire In Flight ad
3. i H Basic Empty Weight Figure 4 2 Sheet 3 162PHUS 00 U S 4 11 SECTION 4 CESSNA WEIGHT AND BALANCE MODEL 162 EQUIPMENT LIST GARMIN G300 AIRPLANE WEIGHING FORM METRIC UNITS B13962 Locating CG with Airplane on Landing Gear X Inches Aft of Datum A Nosowhes Weight x B 2540 mm Total Weight J Locating Percent MAC Nose L R Wheel Weights CG Percent MAC CG Arm of Airplane 3086 1 mm 12 2 mm Measuring A and B casio Measure A and B per Pilot s Leveling Provisions ee 3 Operating Handbook Longitudinal Left side of tailcone instructions to assist in locating at FS 5552 7 mm and 6365 5 mm CG with airplane weighed on landing gear Airplane as Weighed Table Position Scale reading Scale drift Tare Net weight Left Wheel Right Wheel Nose Wheel Airplane total as weighed Basic Empty Weight and Center of Gravity Table gt Moment Weight CG Arm Item Kilograms mm mm kg 1000 i Airplane calculated or as weighed includes all undrainable fluids and full oil Drainable unusable fuel at 0 72 Kilograms 3 98 3638 8 14 48 per liter 5 53 L 1 i i Basic Empty Weight Figure 4 2 Sheet 4 4 12 U S 162PHUS 00 CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE GARMIN G300 EQUIPMENT LIST SAMPLE WEIGHT AND BALANCE RE
4. Preflight inspection should include inspection of the propeller blades for nicks and scratches Small nicks on the propeller particularly near the tips and on the leading edges should be monitored WARNING OPERATION WITH NICKS OR SCRATCHES IN THE LEADING EDGE GREATER THAN 0 125 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 Manual for proper lubrication of controls and components after engine cleaning The induction air filter should be replaced when its condition warrants not to exceed 500 hours Continued Next Page 18 24 U S 162PHUS 01 CESSNA SECTION 8 MODEL 162 AIRPLANE HANDLING SERVICE GARMIN G300 AND MAINTENANCE CLEANING AND CARE Continued INTERIOR CARE To remove dust and loose dirt from the upholstery and interior clean the interior regularly with a vacuum cleaner Blot up any spilled liquid promptly with cleansing tissue or rags Do not pat the spot press the blotting material firmly and hold it for several seconds Continue blotting until no more liquid is taken up Scrape off sticky materials with a dull knife then spot clean the area Oily spot
5. 6 C use an external preheater and an external power source if external power receptacle is installed whenever possible to obtain positive starting and to reduce wear and abuse to both the engine and electrical system Preheat will thaw the oil 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 cycles by hand to loosen the oil so the engine cranks motors more easily and uses less battery power When the propeller is turned manually turn it in the opposite direction to normal engine rotation for greater safety Opposite rotation disengages the magneto impulse couplings and prevents possible unwanted ignition When using an external power source the MASTER Switch ALT and BAT sections must be in the OFF position before connecting the external power source to the external power receptacle Refer to Section 7 Starting Engine with External Power for system description and operations Continued Next Page 162PHUS 00 U S 7 43 SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 COLD WEATHER OPERATION Continued STARTING Continued Cold weather starting procedures
6. 8 Locate this point 1320 at 180 6 on the Center of Gravity Moment Envelope and since this point falls within the envelope the loading is acceptable Figure 4 4 Sheet 1 of 4 162PHUS 00 U S 4 17 SECTION 4 CESSNA WEIGHT AND BALANCE MODEL 162 EQUIPMENT LIST GARMIN G300 SAMPLE LOADING PROBLEM METRIC UNITS WEIGHT AND MOMENT TABULATION SAMPLE YOUR ITEM DESCRIPTION AIRPLANE AIRPLANE Weight Moment Weight Moment kgs kg mm kgs kg mm 1000 1000 1 Basic Empty Weight Use the data pertaining to your airplane as it is presently equipped Includes unusable 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 2084 1 8 Locate this point 597 9 at 2084 1 on the Center of Gravity Moment Envelope and since this point falls within the envelope the loading is acceptable Figure 4 4 Sheet 2 4 18 U S 162PHUS 00 CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE GARMIN G300 EQUIPMENT LIST SAMPLE LOADING PROBLEM U S UNITS YOUR YOUR YOUR AIRPLANE AIRPL
7. MERE ELE LE LOD Ms in Pilot s Operating Handbook And Flight Training Supplement ERE FTE HE CESSNA MODEL 162 Serials 16200001 and On SUPPLEMENT 7 GARMIN SL 40 VHF COMM TRANSCEIVER SERIAL NO REGISTRATION NO This supplement must be inserted into Section 10 of the Pilot s Operating Handbook and Airplane Flight Manual when the Garmin SL 40 VHF Comm Transceiver is installed D Member of GAMA 2 NOVEMBER 2009 COPYRIGHT 2009 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 162PHUS S7 00 U S S7 1 SECTION 10 SUPPLEMENTS CESSNA SUPPLEMENT 7 MODEL 162 GARMIN G300 SUPPLEMENT 7 GARMIN SL 40 VHF COMM TRANSCEIVER Use the Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number Supplement Status Date Original Issue 2 November 2009 LOG OF EFFECTIVE PAGES Page Page Revision Number Status Number S7 1 thru S7 8 Original 0 FAA APPROVED S7 2 U S 162PHUS S7 00 CESSNA SECTION 10 SUPPLEMENTS MODEL 162 SUPPLEMENT 7 GARMIN G300 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that are currently active Number Title Airplane Serial Revision Incorporated Effectivity Incorporated in Airplane FAA
8. 162PHUS 01 U S 6 25 SECTION 6 CESSNA EMERGENCY PROCEDURES MODEL 162 GARMIN G300 ELECTRIC PITCH TRIM FAILURE 1 2 AVN MASTER Switch VERIFY ON TRIM AP Circuit Breaker CHECK IN a If open reset close circuit breaker If circuit breaker opens again do not reset b If closed pull open TRIM AP Circuit Breaker then reset close the circuit breaker ELECTRIC PITCH TRIM SYSTEM REMAINS INOPERATIVE 3 Reduce pitch 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 control force increases uncomfortably when lowering landing flaps 7 Land as soon as practical ELECTRIC PITCH TRIM SYSTEM RESUMES NORMAL OPERATION 3 6 26 Land as soon as practical U S 162PHUS 01 CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 AMPLIFIED EMERGENCY PROCEDURES The following Amplified Emergency Procedures provide additional information beyond that in the Emergency Procedures Checklists portion of this section These procedures also include information not readily adaptable to a checklist format and material to which a pilot could not be expected to r
9. Flaps FULL Maximum Braking Power IDLE Zero Wind Paved Level Dry Runway Speed at 50 ft 50 KIAS NOTE e Short field technique as specified in Section 7 e Decrease distances 10 for each 7 knots headwind For operation with tail winds up to 10 knots increase distances by 10 for each 1 5 knots e If landing with Flaps UP increase the approach speed by 6 KIAS and allow for 20 longer distances Figure 5 4 162PHUS 01 U S 5 13 SECTION 5 CESSNA PERFORMANCE MODEL 162 GARMIN G300 MAXIMUM RATE OF CLIMB AT 1320 POUNDS CONDITIONS Flaps UP Full Throttle Pressure Climb Rate of Climb FPM Sea Level 2000 4000 6000 8000 10 000 12 000 Figure 5 5 5 14 U S 162PHUS 01 CESSNA SECTION 5 MODEL 162 PERFORMANCE GARMIN G300 TIME FUEL AND DISTANCE TO CLIMB AT 1320 POUNDS MAXIMUM RATE OF CLIMB CONDITIONS Flaps UP Full Throttle Standard Temperature From Sea Level Pressure Altitude Feet Sea Level 1000 2000 3000 4000 5000 6000 7000 8000 9000 10 000 11 000 12 000 NOTE Add 0 6 gallons of fuel for engine start taxi and takeoff allowance Increase time fuel and distance by 10 for each 10 C above standard temperature Distances shown are based on zero wind Figure 5 6 162PHUS 01 U S 5 15 SECTION 5 CESSNA PERFORMANCE MODEL 162 GARMIN G300 CRUISE PERFORMANCE CONDITIONS 1320 Pounds Recommended Lean Mixture at All Altitudes 20 C BELOW STANDA
10. 3 14 U S 162PHUS 00 CESSNA SECTION 3 MODEL 162 OPERATING LIMITATIONS GARMIN G300 SYSTEM LIMITATIONS 12V POWER OUTLET The 12 Volt Power Outlet POWER OUTLET 12V 7 5A is not certified for supplying power to flight critical communications or navigation devices Use of the 12 Volt Power Outlet is prohibited during takeoff and landing G300 LIMITATIONS NOTE It is recommended that a current Garmin G300 Pilot s Guide or at a minimum the current Garmin G300 Cockpit Reference Guide CRG be available to the pilot during flight Use of the MAP page for pilotage navigation is prohibited The navigation map is intended only 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 authorized north of 70 North latitude or south of 70 South latitude due to unsuitability of the magnetic fields near the Earth s poles In addition operations are not authorized in the following two regions 1 North of 65 North latitude between longitude 75 W and 120 W Northern Canada 2 South of 55 South latitude between longitude 120 E and 165 E region south of Australia and New Zealand
11. MIXTURE Control ADJUST if necessary to make engine run smoothly Altimeter SET Wing Flaps AS DESIRED UP 10 below 100 KIAS 10 25 below 85 KIAS 25 FULL below 70 KIAS CARB HEAT Control Knob ON as required BEFORE LANDING 7 20 UI mo MA MES Seats and Seat Belts SECURED and LOCKED MIXTURE Control RICH push full in below 5000 feet pressure altitude CARB HEAT Control Knob ON pull full out apply full heat before reducing power LDG Light Switch ON Autopilot OFF if installed U S 162PHUS 01 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 LANDING NORMAL LANDING 1 Airspeed 60 70 KIAS Flaps UP 2 Wing Flaps AS DESIRED UP 10 below 100 KIAS 10 25 below 85 KIAS 25 FULL below 70 KIAS Airspeed 55 65 KIAS Flaps FULL Elevator Trim Control Switch ADJUST Touchdown MAIN WHEELS FIRST Landing Roll LOWER NOSEWHEEL GENTLY Braking MINIMUM REQUIRED Directional Control MAINTAIN with rudder and differential braking O OT E SHORT FIELD LANDING Airspeed 60 70 KIAS Flaps UP Wing Flaps FULL Airspeed 50 KIAS until flare Elevator Trim Control ADJUST Power REDUCE TO IDLE as obstacle is cleared Touchdown MAIN WHEELS FIRST Brakes APPLY HEAVILY while maintaining directional control Wing Flaps UP DAD PL DE BALKED LANDING THROTTLE Control FULL push full in CARB HEAT Control Knob OFF push full in Wi
12. 162PHUS 01 U S 2 3 SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 162 GARMIN G300 FLIGHT CONTROLS Continued Dual under panel control sticks are used for aileron and elevator control The under panel control sticks mimic the control movement of a floor mounted control stick while providing ease of entry to the cabin The control stick location is designed so that the pilot s hand naturally falls on the control stick with the outboard arm on the door arm rest Rudder pedals with toe brakes provide rudder control through forward and aft individually adjustable pilot and copilot pedal assemblies Rudder pedals should be adjusted so that it is possible to have full brake pedal deflection when the same side rudder is fully deflected Wing flaps are manually operated down by a flap handle located between the seats and returned to faired UP position by air load and return spring assist Flap detent position UP 10 25 or FULL may be selected only after depressing the release button in the end of the flap handle JA 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 allerons into an over centered position by moving the aileron down from the centered or faired with the flaps UP flaps position The dow
13. EMERGENCY PROCEDURES MODEL 162 GARMIN G300 FORCED LANDINGS Continued PRECAUTIONARY LANDING WITH ENGINE POWER 1 Seats and Seat Belts SECURE 2 Airspeed 70 KIAS 3 Wing Flaps 10 or 25 4 Radio ALERT ATC or TRANSMIT MAYDAY ON 121 5 MHZ give location intentions and SQUAWK 7700 5 Selected Field FLY OVER noting terrain and obstructions 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 prohibited 11 Touchdown SLIGHTLY TAIL LOW 12 MIXTURE Control IDLE CUTOFF pull full out 13 MAGNETOS Switch OFF 14 Brakes APPLY HEAVILY 6 10 U S 162PHUS 00 CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 FORCED LANDINGS Continued DITCHING 1 Radio TRANSMIT MAYDAY on 121 5 MHz give location intentions and SQUAWK 7700 Heavy Objects in baggage area SECURE OR JETTISON if possible Seats and Seat Belts SECURE Wing Flaps 25 or FULL Power ESTABLISH 300 FT MIN DESCENT AT 60 KIAS aED N NOTE If no power is available approach at 70 KIAS with Flaps UP or at 65 KIAS with Flaps 10 6 Approach High Winds Heavy
14. SERVICE CEILING 14 625 Feet 4457 7 m 13 8 U S 162PHUS 01 CESSNA SECTION 3 MODEL 162 OPERATING LIMITATIONS GARMIN G300 MANEUVER LIMITS This airplane is approved under ASTM standard F2245 and is intended for recreational and instructional flight operations In the acquisition of various pilot certificates certain maneuvers are required and these maneuvers are permitted in this airplane MANEUVERS AND RECOMMENDED ENTRY SPEED Chandelles s 35 AN AA aS RETIRER 102 KIAS LIZ EOS cocaina Reese S V 102 KIAS Steep TUIS ciiin dotem go D pee inc eode Mee eg Malo d On 102 KIAS Stalls Except Whip Stalls Slow Deceleration Power On tale opu idm SERE ERE fas 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 FACTORS FLIGHT LOAD FACTOR LIMITS Flight Load Factors Maximum Takeoff Weight 1320 POUNDS mens d RR ae 4 0g 2 0g Flaps FUE ae es qtti o ti CR nude DR e D eae ren wee 2 0g 162PHUS 01 U S 3 9 SECTION 3 CESSNA OPERATING LIMITATIONS MODEL 162 GARMIN G300 KINDS OF OPERATIONS LIMITS The Cessna 162 airplane is approved for DAY NIGHT VFR operations only Flight into known icing conditions is prohibited The minimum equipment for approved operations required under the
15. 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 X U S 162PHUS 00 CESSNA MODEL 162 GARMIN G300 INTRODUCTION LOG OF EFFECTIVE PAGES Use this page to determine the currency and applicability of your POH Pages affected by the current revision are indicated by an asterisk preceding the pages listed under the Page Number column Revision Level Date of Issue Original Issue 22 July 2009 Revision 2 Revision 1 2 November 2009 Page Page Number Status Title Revised ilii Revised iii thru vi Revised vii thru x Original Xi thru xiv Revised xv xvi Added 1 1 1 2 Original 1 3 thru 1 5 Revised 1 6 thru 1 7 Original 1 8 Revised 2 1 thru 2 8 Revised 2 9 thru 2 10 Original 2 11 thru 2 12 Revised 2 13 Original 2 14 thru 2 25 2 26 Revised 3 1 3 2 Revised 3 3 Original 3 4 Revised 3 5 thru 3 6 Revised 3 7 Original Continued Next Page 162PHUS 02 U S 26 April 2010 Revision Number 2 nr OT Os a Ds O AA N O s NY Ds N O xi INTRODUCTION CESSNA MODEL 162 GARMIN G300 LOG OF EFFECTIVE PAGES Continued Page Page Revision Number Status Number 3 8 thru 3 13 Revised 1 3 14 Original 0 3 15 Revised 1 3 16 Original 0 3 17 Revised 2 3
16. THROTTLE Control FULL push full in 4 MIXTURE Control LEAN as required 5 CARB PF Indicator CHECK IF ENGINE ROUGHNESS CONTINUES 6 CARB PF 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 ABOVE YELLOW BAND RANGE 6 CARB PF Indicator MONITOR 7 CARB HEAT Control Knob AS REQUIRED 8 Continue flight as normal 6 8 U S 162PHUS 01 CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 FORCED LANDINGS EMERGENCY LANDING WITHOUT ENGINE POWER Seats and Seat Belts SECURE Airspeed 70 KIAS Flaps UP 65 KIAS Flaps 10 FULL MIXTURE Control IDLE CUTOFF pull full out FUEL SHUTOFF Valve OFF pull full out Radio ALERT ATC or TRANSMIT MAYDAY ON 121 5 MHZ give location intentions and SQUAWK 7700 MAGNETOS Switch OFF Wing Flaps AS REQUIRED FULL recommended MASTER Switch ALT and BAT OFF when landing is assured ELT ACTIVATE 0 Doors UNLATCH just prior to touchdown NI mk c p TR RAY 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 prohibited 11 Touchdown SLIGHTLY TAIL LOW 12 Brakes APPLY HEAVILY Continued Next Page 162PHUS 00 U S 6 9 SECTION 6 CESSNA
17. This will ensure proper seating of the piston rings Low cruise power settings should be used for extended descents during the first 25 hours of new engine operations Avoid extended descents with reduced power settings Continued Next Page 2 12 U S 162PHUS 01 CESSNA SECTION 2 MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION GARMIN G300 ENGINE Continued ENGINE LUBRICATION SYSTEM The engine utilizes a full pressure wet sump type lubrication system with aviation grade oil as the lubricant The capacity of the engine sump located on the bottom of the engine along with the engine oil filter and oil cooler is 5 5 quarts Oil is drawn from the sump through a filter screen on the end of a pickup tube to the engine driven oil pump Oil from the pump then passes through a full flow oil filter a pressure relief valve at the rear of the right oil gallery and an oil cooler before lubricating engine parts The oil returns to the sump by gravity The filter adapter in the full flow 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 filler tube is located at the left rear of the engine case The oil dipstick filler tube is accessed through a door located on the left side 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
18. rotation difficult the magenta turn rate trend vector in the heading strip over the PFD Attitude Indicator will show the rate and direction of the turn The HSI compass card will rotate in the opposite direction Hold full rudder opposite the direction of the turn indicated by the turn rate trend vector 162PHUS 00 U S 6 35 SECTION 6 CESSNA EMERGENCY PROCEDURES MODEL 162 GARMIN G300 ROUGH ENGINE OPERATION OR LOSS OF POWER CARBURETOR ICING A gradual loss of RPM and eventual engine roughness may result from the formation of carburetor ice To clear the ice apply full throttle and pull the CARB HEAT control knob full out until the engine runs smoothly then reduce carburetor heat and readjust throttle as necessary Monitor the G300 CARB F indicator to verify the carburetor temperature rises out of the amber caution range If conditions require the continued use of carburetor heat in cruise flight use the minimum amount of heat necessary to prevent ice from forming and lean the mixture for smoothest engine operation The G300 CARB F indicator provides advisory information but does not replace the need to monitor engine condition and adjust carburetor heat or mixture as needed for safe engine performance 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 MAGNETOS switch momentarily from BOTH to either L or
19. the Basic Empty Weight and C G can be determined by completing Figure 4 2 Sheet 3 or Sheet 4 Changes to the Airplane Weight and Balance due to alteration or repair must be documented in a permanent record within the POH similar to that shown in Figure 4 3 A new Basic Empty Weight and CG Arm based on actual airplane weight as weighed is required after a major repair or alteration It is recommended that the airplane be weighed to verify Basic Empty Weight and CG Arm at intervals not to exceed 5 years U S 162PHUS 00 CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE GARMIN G300 EQUIPMENT LIST AIRPLANE WEIGHING FORM U S UNITS Reference Datum Firewall front face 2507 lower portion FS 100 0 200 MAC 48 00 21 50 gt 150 o 3100 5 Level at leveling screws g 50 X on left side of tailcone E e A B 0 E 0 50 100 150 200 250 300 350 400 Fuselage Station FS Inches NOTE It is the responsibility of the pilot to make sure that the airplane is loaded properly 091071002 Figure 4 2 Sheet 1 of 4 162PHUS 01 U S 4 9 SECTION 4 CESSNA WEIGHT AND BALANCE MODEL 162 EQUIPMENT LIST GARMIN G300 AIRPLANE WEIGHING FORM METRIC UNITS B13961 Reference Datum Firewall front face g 63507 lower portion 9 FS 2540 0 5080 MAC gt 1219 20 i 546 10 3810 ees 5 25404 E Level at leveling screws 1270 l
20. 1 sr os Os O a QD ss QO sa O ss O sz QO sz 0 O N a DO ss O o xiii INTRODUCTION xiv CESSNA MODEL 162 GARMIN G300 LOG OF EFFECTIVE PAGES Continued Page Number 9 1 9 2 9 3 9 4 thru 9 5 9 6 9 7 thru 9 8 10 1 10 2 U S Page Status Original Revised Original Revised Revised Original Revision Number A N OO 162PHUS 02 CESSNA INTRODUCTION MODEL 162 GARMIN G300 TABLE OF CONTENTS SECTION GENERAL cs SAG DONE SEE aida 1 AIRPLANE AND SYSTEM DESCRIPTION 2 OPERATING LIMITATIONS 3 WEIGHT AND BALANCE EQUIPMENT LIST 4 PERFORMANCE z0 sie vy bha be GAL ache 5 EMERGENCY PROCEDURES 6 NORMAL PROCEDURES 4 7 AIRCRAFT HANDLING SERVICE AND MAINTENANCE 22222 8 PLACARDS AND MARKINGS 9 SUPPLEMENTARY INFORMATION 10 162PHUS 01 U S xv xvi CESSNA SECTION 1 MODEL 162 GENERAL GARMIN G300 GENERAL TABLE OF CONTENTS Page Three View Normal Ground Attitude o o o ooo 1 3 IMMOGUCION s ee o scere lr ta ena 1 5 ljesctpuVe Data s adr AE edi PEE 1 5 gcc C re 1 5 PTODSIIGI s oa etse thi Sa RAM PURPOSE Eta 1 5 UC cee cT PRENNE 1 6 Fuel Capacity cus xac Devi aeta dig Ku xa vae RE ERE TAS 1 6 Cl dai leac DE oC RR AN eee tS EO BARE 1 7 Si A EE DE DIER AR Rd AS Dk En 1 7 Oil Capacity AO IE RE OE OE OE de Fee ae 1 7 Maximum Certificated Weights EE EE e
21. 162PHUS 01 U S 3 15 SECTION 3 CESSNA OPERATING LIMITATIONS MODEL 162 GARMIN G300 PLACARDS The following information must be displayed in the form of composite or individual placards 1 In full view of the pilot The DAY NIGHT VFR entry shown on the example below will vary with installed equipment 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 airplane is approved for the following flight operations as of the date of original airworthiness certificate DAY NIGHT VFR 2 On control lock B6143 CAUTION CONTROL LOCK REMOVE BEFORE STARTING ENGINE o o 3 Silk screened on left instrument panel above magnetos switch MIN TAKEOFF PROHIBITED WITH LESS THAN 1 4 FUEL TO Continued Next Page 3 16 U S 162PHUS 00 CESSNA SECTION 3 MODEL 162 OPERATING LIMITATIONS GARMIN G300 PLACARDS Continued 4 Silk screened on the lower left instrument panel WARNING Assure that all contaminants including water are removed from fuel and fuel systems before flight Failure to assure contaminant free fuel and heed all safety instructions and
22. 3 30 HOURS RATE OF CLIMB AT SEALEVEL 880 FPM 268 2 mpm SERVICE CEILING cogar tad oe 14 625 FEET 4457 7 m TAKEOFF PERFORMANCE AT SEA LEVEL Ground Toll 2253 2 22 trado ea 640 FEET 195 1 m Total Distance Over 50 Foot Obstacle 1138 FEET 346 9 m LANDING PERFORMANCE AT SEA LEVEL Grouiid Fol cado caet con pex bats 671 FEET 204 6 m Total Distance Over 50 Foot Obstacle 1369 FEET 417 3 m STALL SPEED Flaps UP Power Idle 2 is ss ox ea ker hy s 41 KIAS Flaps FULL Power ldle o o 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 when speed fairings are installed The above performance figures are based on airplane weights at 1320 pounds 598 7 kg standard atmospheric conditions level hard surfaced dry runways and no wind They are calculated values derived from flight tests conducted by Cessna Aircraft Company under carefully documented conditions and will vary with individual airplanes and numerous factors affecting flight performance Continued Next Page IV U S 162PHUS 01 CESSNA INTRODUCTION MODEL 162 GARMIN G300 PERFORMANCE SPECIFICATIONS Continued MAXIMUM WEIGHT nri pr C P 1324 POUNDS 600 5 kg TOO Milla
23. APPROVED 162PHUS S7 00 U S S7 3 SECTION 10 SUPPLEMENTS CESSNA SUPPLEMENT 7 MODEL 162 GARMIN G300 GARMIN SL 40 VHF COMM TRANSCEIVER GENERAL The Garmin SL 40 VHF Comm Transceiver consists of a panel mounted receiver transmitter which includes a 760 channel VHF communications receiver transmitter capable of receiving and transmitting signals between 118 000 and 136 975 MHz with 25 kHz spacing Active and standby frequencies along with operational annunciators are displayed on a photocell controlled LCD matrix display Control buttons including those operating the frequency flip flop feature standby frequency monitoring and single button emergency frequency selection are located under the display panel An internal intercom is also included as a standard feature of the SL40 Refer to the Garmin SL40 Pilot s Guide Garmin P N 190 00488 00 Rev A or later for a complete listing of system description and operational information Garmin publications can be obtained by 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 supplemental information FAA APPROVED S7 4 U S 162PHUS S7 00 CESSNA SECTION 10 SUPPLEMENTS MODEL 162 SUPPLEMENT 7 GARMIN G300 OPERATING LIMITATIONS Headsets are required for all audio communications Headsets with microphones or a hand
24. BATTERIES WILL VOID MANUFACTURERS TSO 91A AND PRODUCT WARRANTIES The remote switch controls ELT operating modes from the flight crew station When the ELT main unit control switch is set to the ARM position the transmitter is energized only when the internal G switch senses longitudinal inertia forces per TSO C91a TSO C126 In emergency situations the transmitter can also be immediately energized by pressing the ON switch located within the remote switch assembly The AK 451 transmitter unit is located in the tailcone behind the baggage area On the ELT transmitter unit is a panel containing an ON OFF ARM switch and a transmitter ON light The ELT installation uses two different warnings to tell the pilot when the ELT is energized The aural warning is an unusual sound that is easily heard by the pilot The visual warning is a flashing GREEN ON light located within the panel mounted remote switch that shows the pilot that the ELT has been activated Continued Next Page S2 4 U S 162PHUS S2 00 CESSNA SECTION 10 SUPPLEMENTS MODEL 162 SUPPLEMENT 2 GARMIN G300 GENERAL Continued When the AK 451 is energized the ELT transmits the standard swept tone signal on the international VHF frequency of 121 5 MHz and UHF frequency of 243 0 MHz until battery power is gone The 121 5 MHz signal is mainly used to pinpoint the beacon during search and rescue operations and is monitored by general aviation commercial aircraft and
25. ES Ee C sae ee N ES ADS EE OS ies oe Ses i es e se sagasa aas e 56 SEA LA CR ed SS ede oe SS aa RUN OR OR REIR oe ER KN T RANT E E N EE IE Ee EE EE RRO ER DQ III DQ ORDE NG uhog ES NG e lt A a a BO AS E RE senate es oS ite ESE Erea ee d nt SS SG No o os ae a 2 on m dm s a a Rg HE oo Ses NA it Me Se ui 2 oon os a O55 ma 2 SA Xx KIA KO LR NG x s et baba AGA Ky kg s pos pos ko GIO DEN oe ss oe SG IYO SG oe NS se LS mo 1 eds eise OOS eed Ee gapan naaa RS ee Io OI ee AS Ie Pana ER KX RE es ANANAS SERRA SIR OS REKE eS XX SI VERO 09101001 162PHUS 00 ice or snow from wing tail and control surfaces Also make sure that control Figure 7 1 NOTE Visually check airplane for general condition during walk If a night flight is planned check operation of all lights and U S surfaces contain no internal accumulations of ice or debris make sure a flashlight is available drain valves allow for accurate sampling In cold weather around inspection Airplane should be parked in a normal ground attitude refer to Figure 1 1 to make sure that fuel remove even small accumulations of frost r4 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 PREFLIGHT INSPECTION Continuea D CABIN 1 el I qus ep vl 10
26. Frequently check all components of the landing gear strut tires and brakes If the airplane has been operated from muddy fields or in snow or slush check the main and nose gear wheel fairings for obstructions and cleanliness Operation from a gravel or cinder field will require extra attention to propeller tips and abrasion on leading edges of the horizontal tail Stone damage to the propeller can seriously reduce the fatigue life of the blades 7 24 U S 162PHUS 00 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 BEFORE STARTING ENGINE Rudder pedals should be adjusted fore and aft as needed to ensure the pilot has full brake deflection with the rudder fully deflected A small percentage of pilots may require additional cushions to correctly position themselves for visibility and control Ideally the pilot should be positioned so that the outboard elbow naturally rests on the door armrest and the control stick falls within the hand of that arm Correct positioning allows for relaxed flying using wrist movements and assists the new pilot to adjusting to the Skycatcher flight controls STARTING ENGINE Engine starting can differ depending on the temperature of the engine and surrounding ambient air which affects the amount of fuel priming required Standard priming is done using the throttle control Pumping the throttle by rapidly advancing the throttle control fully in and out works an accelerator pump in the engine c
27. GPS ground speed and STOP when the airplane slows below 30 KTS c COUNT UP TIMER Controlled by the START STOP key Use CLR key to reset timer to 0 00 d COUNT DOWN TIMER Enter time using numerical keys and use START STOP key to activate Use CLR key to reset timer to 0 00 CRSR Initiates starting time entry for the Count Down timer and cancels transponder code entry CLR Resets the Count Up Count Down and Flight timers Cancels the previous keypress during code selection and Count Down entry Returns cursor to the fourth code digit within five seconds after entry Numerical keys 8 and 9 are not used for code entry only for entering the number 8 or 9 into the count down timer PHOTOCELL Automatically controls the intensity of the display from low brightness at night to high brightness during daylight operations Display brightness may also be controlled manually using the FUNC key REPLY INDICATOR The Reply Symbol will blink each time the transponder replies to ground interrogations The Reply Symbol will remain illuminated during the 18 second IDENT time interval CODE SELECTION Code selection is accomplished using the numerical keys 0 7 Pushing one of these keys begins the code selection sequence The new code will not be active until the fourth digit is entered Pressing the CLR key will move the cursor back to the previous digit Pressing the CLR key when the cursor is on the first digit or pressing the CRSR
28. IN FLIGHT DA PM a MIXTURE Control IDLE CUTOFF pull full out FUEL SHUTOFF Valve OFF pull full out MASTER Switch ALT Only OFF Cabin Vents OPEN as needed CABIN HEAT Control Knob OFF push full in to avoid drafts Airspeed 85 KIAS If fire is not extinguished increase glide speed to find an airspeed within airspeed limitations which will provide an incombustible mixture Forced Landing EXECUTE refer to EMERGENCY LANDING WITHOUT ENGINE POWER Continued Next Page U S 162PHUS 00 CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 FIRES Continued ELECTRICAL FIRE OR CABIN FIRE IN FLIGHT 1 MASTER Switch ALT and BAT OFF WARNING OUTSIDE VISUAL REFERENCE MUST BE USED TO MAINTAIN SITUATIONAL AWARENESS ALL FLIGHT INSTRUMENTS RADIOS AND PITCH TRIM WILL BE INOPERATIVE WHEN MASTER SWITCH IS TURNED OFF 2 Cabin Vents CLOSED to avoid drafts 3 CABIN HEAT Control Knob OFF push full in to avoid drafts 4 Fire Extinguisher ACTIVATE if available 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
29. LANDING WITH ENGINE POWER NOTE The G300 self test and ADAHRS alignment may take several minutes to establish thus delaying display of flight instrument data lt may be necessary to execute landing without airspeed or altitude information Continued Next Page 162PHUS 00 U S 6 13 SECTION 6 CESSNA EMERGENCY PROCEDURES MODEL 162 GARMIN G300 FIRES Continued ELECTRICAL FIRE OR CABIN FIRE IN FLIGHT Continued IF FIRE HAS BEEN EXTINGUISHED AND ELECTRICAL POWER IS NECESSARY FOR CONTINUED FLIGHT TO NEAREST SUITABLE AIRPORT OR LANDING AREA 7 8 9 WARNING AFTER THE FIRE EXTINGUISHER HAS BEEN USED MAKE SURE THAT THE FIRE IS EXTINGUISHED BEFORE EXTERIOR AIR IS USED TO REMOVE SMOKE FROM THE CABIN Cabin Vents OPEN when sure that fire is completely extinguished CABIN HEAT Control Knob ON pull full out when sure that fire is completely extinguished 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 2 3 4 6 14 LDG Light Switch OFF NAV Light Switch OFF STROBE Light Switch OFF NOTE Perform a sideslip to keep the flames away from the fuel tank and cabin Land as soon as possible U S 162PHUS 00 CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 ICING INADVERTENT ICING ENCOUNTER DURING FLIGHT 1 Turn back
30. MODEL 162 GARMIN G300 EMERGENCY PROCEDURES Procedures in the Emergency Procedures Checklist portion of this section shown in bold faced type are immediate action items which should be committed to memory ENGINE FAILURES AND MALFUNCTIONS ENGINE FAILURE DURING TAKEOFF ROLL THROTTLE Control IDLE pull full out Brakes APPLY Wing Flaps RETRACT MIXTURE Control IDLE CUTOFF pull full out MAGNETOS Switch OFF MASTER Switch ALT and BAT OFF DAAN ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF Airspeed 70 KIAS Flaps UP 65 KIAS Flaps 10 FULL MIXTURE Control IDLE CUTOFF pull full out FUEL SHUTOFF Valve OFF pull full out MAGNETOS Switch OFF Wing Flaps AS REQUIRED FULL recommended MASTER Switch ALT and BAT OFF when landing is assured Land STRAIGHT AHEAD Doors UNLATCH just prior to touchdown N DA PM 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 prohibited Continued Next Page 6 6 U S 162PHUS 00 CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 ENGINE FAILURES AND MALFUNCTIONS Continued ENGINE FAILURE DURING FLIGHT Restart Procedures Airspeed 70 KIAS best glide speed THROTTLE Control IDLE pull full out CARB HEAT Control Knob ON pull full out FUEL SHUTOFF Va
31. Oo ene t ee eee PS 1320 POUNDS 598 7 kg BSAA AA E 1320 POUNDS 598 7 kg 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 2 220 11 0 Ibs sq ft 53 7 kg sq m POWER LOADING ees km e pte SER Pee mda 13 2 Ibs HP FUEL CAPACITY Usable 24 GALLONS 90 8 1 OIL CAPACITY Sump 005 5 QUARTS 4 73 1 ENGINE Teledyne Continental Motors O 200D 100 BHP at 2750 RPM PROPELLER Fixed Pitch Diameter ske EED dae 67 INCHES 1 70 m 162PHUS 01 U S V INTRODUCTION CESSNA MODEL 162 GARMIN G300 COVERAGE The Pilot s Operating Handbook POH in the airplane at the time of delivery from Cessna Aircraft Company contains information applicable to the Model 162 airplanes by serial number and registration number shown on the Title Page This POH is applicable to Model 162 airplanes Serials 16200001 and On All information is based on data available at the time of publication 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 indiv
32. 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 p3 10 U S 162PHUS 01 CESSNA SECTION 3 MODEL 162 OPERATING LIMITATIONS GARMIN G300 KINDS OF OPERATIONS EQUIPMENT LIST KIND OF OPERATION System Instrument Equipment and or Function COMMENTS PLACARDS AND MARKINGS 1 162 POH AFM Garmin G300 0 0 Recommended to be accessible to pilot in flight 2 162 Pilot s Checklist 1 1 Required to be 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 0 0 Recommended to be Guide accessible to pilot in flight AIR CONDITIONING 1 Avionics Fan 1 1 COMMUNICATIONS 1 VHF COM 0 0 ELECTRICAL POWER 1 12V Main Battery 2 14V Alternator 3 Standby Battery 4 Ammeter EQUIPMENT AND FURNISHINGS 1 Seat Belt Assembly Each Seat Occupant 1 Shoulder Harness 1 1 Each Seat Occupants FLIGHT CONTROLS 1 Elevator Trim System 1 1 O O ss gt md md md 2 Elevator Trim Indicator 1 1 Continued Next Page 162PHUS 01 U S 3 11 SECTION 3 OPERATING LIMITATIONS CESSNA MODEL 162 GARMIN G300 KINDS OF OPERATIONS EQUIPMENT LIST continued KIND OF OPERATION Syste
33. The Isolation Mode ISO connects the pilot directly to the SL40 Comm radios when the pilot must have priority to all radio transmissions With the mode selector switch in the ALL mode both pilot and copilot have transmit capabilities over the SL40 Comm radios Continued Next Page S3 4 U S 162PHUS S3 00 CESSNA SECTION 10 SUPPLEMENTS MODEL 162 SUPPLEMENT 3 GARMIN G300 GENERAL Continued The PM3000 only allows the voice of the person who presses the push to talk switch PTT first to be transmitted over the Comm radios using remote microphones When either the pilot or copilot presses the PTT switch the other microphone is disabled If both pilot and copilot press the PTT switch at the same time the copilot will override any transmission from the pilot The pilot can regain priority of radio transmissions by pressing the PM3000 VOLUME control knob to power the intercom off With the intercom powered off an internal relay will connect the pilot s headset directly to the SL40 Comm radio allowing uninterrupted radio communications to the pilot s headset only AUDIO ENTERTAINMENT The entertainment input function of the PM3000 ICS allows the pilot and copilot the option of listening to audio files during flight from either the XM radio feed if installed or from any entertainment audio device connected to the AUX AUDIO INPUT jack located on the center pedestal It allows entertainment audio devices such as cassette compact disc
34. aircraft of U S registry must undergo a complete inspection annual each twelve calendar months In addition to the required annual inspection aircraft operated for in flight instruction must have a complete inspection every 100 hours of operation Cessna and the FAA may require other inspections by the issuance of Service Bulletins Safety Alerts and Airworthiness Directives applicable to the airplane engine propeller and components It is the responsibility of the owner operator to ensure compliance with all applicable Service Bulletins Safety Alerts and Airworthiness Directives 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 Specific benefits and provisions of the Cessna Warranty plus other important benefits for you are contained in your Customer Care Handbook supplied with your airplane The Customer Care Handbook should be thoroughly reviewed and kept in the airplane at all times You will also want to return to your Cessna Service Station at 25 50 and 100 hours inspections These important inspections will be performed for you by any Cessna Service Station in most cases you will prefe
35. al 6 12 Electrical Fire or Cabin Fire In Flight 6 13 Wind Eie pra id dus Va ees ALL GA 6 14 le sm ENE EET EE EE TO EE DR 6 15 Inadvertent Icing Encounter During Flight 6 15 ABNORMAL LANDINGS 2 2 2222 6 17 Landing With Partial or No Flight Instrument Information 6 17 Landing With A Flat Main Tire liliis 6 17 Landing With A Flat Nose Tire 00 6 18 Door Open in Elbe EE E t ERR DR 6 18 Landing With Door Open 00000 eee eee 6 18 Continued Next Page 162PHUS 00 U S 6 1 SECTION 6 CESSNA EMERGENCY PROCEDURES MODEL 162 GARMIN G300 TABLE OF CONTENTS Continued Page ELECTRICAL POWER SUPPLY SYSTEM MALFUNCTIONS 6 19 Loss Of All Electrical Power Except PFD 6 19 LOW VOLTS Annunciator Comes On or Volts Indication Below Green Band Range or Volts Less Than 12 5 6 20 Volts Indication Above Green Band Range or Volts More Nan T5 sr ur e a DE PU eat aes 6 22 AIR DATA ATTITUDE AND HEADING REFERENCE SYSTEM ADAHRS FAILURE cats xe OPERI e oR SRR 6 23 Red X PFD or MFD Indicators Airspeed Altitude Attitude Horizontal Situation Indicator HSI or Engine Indicating System ETS ouis ie a pole e tbn 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 Updating 6 25 Electric Pitch Trim Failure seek Dod ari
36. and MP3 players to play music over the airplane s headsets During intercom communication or airplane radio reception the entertainment audio level will automatically mute to allow communications without distraction When the communication activity ceases the circuitry gradually returns the entertainment audio level to the original listening volume The optional XM weather and XM radio data link provides weather information and digital audio entertainment in the cockpit through a input on the optional MFD display A subscription to the XM satellite radio service is required for the XM weather and radio data link to be used Refer to the Garmin G300 Pilot s Guide for operational instructions for the XM weather and XM radio data link NOTE Audio input from the optional XM radio data link will be disconnected when any audio device is connected to the AUX AUDIO INPUT jack Continued Next Page 162PHUS S3 00 U S S3 5 SECTION 10 SUPPLEMENTS CESSNA SUPPLEMENT 3 MODEL 162 GARMIN G300 GENERAL Continued AUDIO ENTERTAINMENT Continued Since the entertainment audio input is not controlled by a switch there is no way to deselect the entertainment source except to disconnect the source at the audio input connector In the event of a high pilot workload and or heavy traffic it is wise to disable the entertainment audio to eliminate a source of distraction for the flight crew NOTE Passenger briefing should specify that AU
37. and government agencies Continued Next Page S1 4 U S 162PHUS S1 00 CESSNA SECTION 10 SUPPLEMENTS MODEL 162 SUPPLEMENT 1 GARMIN G300 AMERI KING AK 450 ELT MAIN CONTROL PANEL B14687 5 6 Fi ON OFF MIC A ARM REMOTE o 0918T1027 ANT Antenna receptacle connects to the antenna mounted on top of tailcone REMOTE Remote cable jack connects to the ELT remote switch assembly located on the upper right instrument panel RESET Reset button deactivates transmitter TRANSMITTER WARNING LIGHT Light comes on RED to indicate the transmitter is transmitting a distress signal ELT PANEL SWITCH 3 Position Toggle Switch a ON Activates transmitter instantly The ON position bypasses the automatic activation switch The RED warning light on ELT main control panel and the remote panel mounted switch assembly will come on and aural warning will sound b OFF Turns OFF transmitter for handling following rescue and to reset the automatic activation function if unable to reset using the remote panel mounted reset button c ARM ARMS transmitter for automatic activation if G switch senses a predetermined deceleration level N depo O 162PHUS S1 00 U S 91 5 SECTION 10 SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 162 GARMIN G300 AMERI KING AK 450 ELT REMOTE SWITCH PANEL B14688 4 2 3 O A ELT O OJO O ON ON RESET O 1 ON Button Remote
38. are evidence of tire deterioration caused by age improper storage or prolonged exposure to weather Check the tread of the tire for depth wear and cuts Replace the tire if fibers are visible After major maintenance has been performed the flight and trim tab controls should be double checked for free and correct movement and security The security of all inspection 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 Check for damage to the nosewheel travel stops and wheel fairings if installed resulting from exceeding nosewheel turning limits while towing Outside storage for long periods may result in dust and dirt accumulation on the induction air filter obstructions in airspeed system lines water contaminants in fuel tanks and insect bird rodent nests in any opening If any water is detected in the fuel system the fuel tank sump quick drain valves fuel sump quick drain valve and fuselage sump quick drain valve should all be thoroughly drained again The wings should then be gently rocked and the tail lowered to the ground to move any further contaminants to the sampling points Repeated
39. are the same as the normal starting procedures Refer to Amplified Normal Procedures Starting Engine in this section The amount of fuel priming required for engine start is dependant upon temperature The colder the engine the more prime is required In extremely cold temperatures it may be necessary to continue priming while cranking the engine If the engine is under primed it will not fire at all and additional priming 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 ENGINE FIRE CONTINUE CRANKING TO SUCK THE FLAMES INTO THE ENGINE REFER TO SECTION 6 EMERGENCY PROCEDURES FIRES DURING START ON GROUND NOTE If the engine does not start during the first few attempts or if engine firing diminishes in strength the spark plugs may be frosted over Preheat must be used before another start is attempted Continued Next Page 17 44 U S 162PHUS 01 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 COLD WEATHER OPERATION Continued STARTING Continued During cold weather operations the oil temperature indicator may not be in the green band range when ready to perfo
40. as required 0 Maintain descent procedure will provide 500 TO 800 FT MIN descent rate 11 Upon breaking out of clouds resume normal cruising flight ED ON S Continued Next Page 6 32 U S 162PHUS 01 CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 EMERGENCY OPERATION IN CLOUDS Continued RECOVERY FROM SPIRAL DIVE IN THE CLOUDS ADAHRS FAILED ADAHRS FAILURE If a spiral is entered while in the clouds continue as follows 1 THROTTLE Control IDLE pull full out 2 Remove feet from rudder pedals 3 Stop turn by carefully leveling the wings using aileron control while referencing COMPASS ARC or optional magnetic compass if installed and moving 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 Elevator Trim ADJUST maintain 70 75 KIAS glide speed Use aileron control to maintain wings level and constant heading CARB HEAT Control Knob ON pull full out Clear engine occasionally but avoid using enough power to disturb the trimmed glide Resume EMERGENCY DESCENT THROUGH THE CLOUDS procedure 10 Upon breaking out of clouds resume normal cruising flight o ON DA 162PHUS 01 U S 6 33 SECTION 6 CESSNA EMERGENCY PROCEDURES MODEL 162 GARMIN G300 INADVERTENT FLIGHT
41. 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 MASTER switch before the landing is assured unless specifically instructed by the emergency procedure checklist Premature deactivation of these switches will disable all airplane electrical systems Note however there are specific emergency procedures such as Electrical Fire which do require the MASTER switch ALT side to be turned off Exercise caution when performing these procedures to ensure that only the ALT side is selected off Before completing a forced landing especially in remote and mountainous areas activate the ELT by pressing the ELT ON switch located on the right instrument panel For complete information on ELT operation refer to Section 10 Supplements 162PHUS 00 U S 6 29 SECTION 6 CESSNA EMERGENCY PROCEDURES MODEL 162 GARMIN G300 LANDING WITHOUT ELEVATOR CONTROL Using throttle and electric elevator trim switch trim for horizontal flight at 55 60 KIAS with flaps 25 selected Then do not change the elevator trim or the flap setting control the glide angle by making small changes in power Power changes should be made slowly and smoothly The electric elevator trim is powerful It is best to bump or pulse the trim switch
42. basic empty weight and moment 1000 from the weight and balance records for your airplane in the YOUR AIRPLANE column of the Sample Loading Problem NOTE In addition to the basic empty weight and moment noted on these records the C G arm FS is also shown but need not be used on the Sample Loading Problem The moment which is shown must be divided by 1000 and this value used as the moment 1000 on the loading problem Use the Loading Graph to determine the moment 1000 for each additional item to be carried then list these on the loading problem NOTE Loading Graph information for the pilot 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 lists fuselage stations FS for these items to indicate their forward and aft C G range limitations baggage area limitation Refer to Figures 4 6 and 4 7 for additional loading information Additional moment calculations based on the actual weight and C G arm FS of the item being loaded must be made if the position of the load is different from that shown on the Loading Graph Total the weights and moments 1000 and plot these values on the Center of Gravity Moment Envelope to determine whether the point falls within the envelope and if the loading is acceptable Continued Next Page 162PHUS 01 U S 4 15 SECTION 4 CESSNA WEIGHT AND BAL
43. data and 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 McCauley Propeller Systems Propeller Model Number 1A162 TCD6754 Number of Blades 2 Propeller Diameter 67 inches 1 70 m Propeller Type Fixed Pitch Continued Next Page 162PHUS 01 U S 1 5 SECTION 1 CESSNA GENERAL MODEL 162 GARMIN G300 DESCRIPTIVE DATA Continued FUEL WARNING USE OF UNAPPROVED FUELS MAY RESULT IN DAMAGE TO THE ENGINE AND FUEL SYSTEM COMPONENTS RESULTING IN POSSIBLE ENGINE FAILURE Approved Fuel Grades and Colors 100LL Grade Aviation Fuel Blue 100 Grade Aviation Fuel Green NOTE Isopropyl alcohol or Diethylene Glycol Monomethyl Ether DIEGME may be added to the fuel supply in accordance to TCM Service Information Letter SIL99 2B Refer to Section 8 for additional information FUEL CAPACITY Total Capacity sies sek edd ws 25 46 U S GALLONS 96 34 I Total Usable 24 00 U S GALLONS 90 82 1 Total Capacity Each Tank 12 73 U S GALLONS 48 17 I Total Usable Each Tank 12 00 U S GALLONS 45 41 1 NOTE e To ensure m
44. dimming function can be disabled by setting the high display level to zero 2 ACTIVE FREQUENCY Displays active communication frequency 3 ANNUNCIATOR Displays Transmit TX Standby Frequency s Monitor m and Intercom I operational modes a Transmit TX A capital TX will illuminate whenever the radio is transmitting b Standby Frequency s A small s will be displayed to the left of the standby frequency display window c Monitor Mode m A small m will be displayed in front of the standby frequency when the frequency monitoring MON button is selected d Intercom l A capital I will be displayed when the intercom function is being used 4 STANDBY FREQUENCY Displays standby communication frequency 5 LARGE OUTER KNOB Rotating the large outer knob will change the standby frequency values in 1 MHz increments and is also used to display available selections within the System Functions mode 6 SMALL INNER KNOB Rotating the small inner knob will change the standby frequency values in 25 kHz increments and is also used to make adjustments within the System Functions mode Continued Next Page FAA APPROVED 57 6 U S 162PHUS S7 00 CESSNA SECTION 10 SUPPLEMENTS MODEL 162 SUPPLEMENT 7 GARMIN G300 NORMAL PROCEDURES Continued 7 MEM Pressing of the memory button will store the displayed standby frequency into memory Refer to the Garmin Pilot s Guide for detailed description and op
45. displayed on the G300 ENGINE Page when selected In normal operation EIS information is displayed on the Primary Flight Display PFD in the single display installation and on the optional Multifunction Display MFD in the dual display 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 indicator uses a circular scale with moving pointer and a digital value The pointer moves through a range from 0 to 3000 RPM The numerical RPM value is displayed in increments of 10 RPM in white numerals below the pointer The normal engine speed operating limit top of green arc is 2750 RPM When engine speed is more than 2750 RPM the pointer digital value and label RPM turn red to show engine speed is more than the limit The digital value and label RPM will flash A red X is displayed when the instrument is invalid or out of the data range Continued Next Page 162PHUS 00 U S 2 9 SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 162 GARMIN G300 ENGINE Continued ENGINE INSTRUMENTS Continued OIL PRESSURE OIL PSI The oil pressure transducer connected to the engine for
46. gallons hour 3 0 Gallons 60 The total estimated fuel required is as follows Engine start taxi and takeoff 0 6 Gallons Climb 1 0 Gallons Cruise 15 6 Gallons Reserve 3 0 Gallons Total fuel required 20 2 Gallons Once the flight is underway ground speed checks will provide a more accurate basis for estimating the time enroute and the corresponding fuel required to complete the trip with ample reserve Continued Next Page 5 8 U S 162PHUS 01 CESSNA SECTION 5 MODEL 162 PERFORMANCE GARMIN G300 SAMPLE PROBLEM Continued LANDING A procedure similar to takeoff should be used for estimating the landing distance at the destination airport Figure 5 4 presents landing distance information for the short field technique The distances corresponding to 2000 feet and 30 C are as follows Ground roll 760 Feet Total distance to clear a 50 foot obstacle 1485 Feet 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 be made to Section 2 for engine operating limitations 162PHUS 01 U S 5 9 SECTION 5 CESSNA PERFORMANCE MODEL 162 GARMIN G300 AIRSPEED CALIBRATION NORMAL ST
47. government agencies In addition for the first 24 hours of the ELT being energized a 406 028 MHz signal is transmitted at 50 second intervals This transmission lasts 520 milliseconds and contains identification data programmed into the ELT and is received by COSPAS SARSAT satellites The transmitted data may include the Aircraft ID ELT Serial Number Country Code and COSPAS SARSAT ID 162PHUS S2 00 U S S2 5 SECTION 10 SUPPLEMENTS CESSNA SUPPLEMENT 2 MODEL 162 GARMIN G300 GENERAL Continued AMERI KING AK 451 ELT MAIN CONTROL PANEL B14857 4 ITS ARM REMOTE 0918T1027 1 ANT Antenna receptacle connects to the antenna mounted on top of tailcone REMOTE Remote cable jack connects to the ELT remote switch assembly located on the upper right instrument panel RESET Reset button deactivates transmitter TRANSMITTER ON LIGHT Light flashes GREEN to indicate the transmitter is transmitting a distress signal ELT PANEL SWITCH 3 Position Toggle Switch a ON Activates transmitter instantly The ON position bypasses the automatic activation switch The GREEN ON light on ELT main control panel and the remote panel mounted switch assembly will flash and aural warning will sound at a rate of 1 second ON 4 seconds OFF b OFF Turns OFF transmitter for handling following rescue and to reset the automatic activation function if unable to reset using the remote panel moun
48. 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 spark plugs and the right magneto fires the upper left and upper right spark plugs Normal operation is conducted with both magnetos due to the more complete burning of the fuel air mixture with dual ignition Ignition and starter operation is controlled by a rotary type switch located on the left instrument panel The MAGNETOS switch is labeled clockwise OFF R L BOTH and START The engine should be operated on both magnetos BOTH position except for magneto checks The R and L positions are for checking purposes and emergency use only When the MAGNETOS switch is rotated to the spring loaded START position with the MASTER switch in the ON position the starter contactor is closed and the starter now energized will crank the engine When the switch is released it will automatically return to the BOTH position Continued Next Page 162PHUS 00 U S 2 13 SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 162 GARMIN G300 ENGINE Continued AIR INDUCTION SYSTEM The engine air induction system receives ram air through an intake on the lower front portion of the engine cowling The intake is covered by an air filter which removes dust and other foreign mat
49. kept full between flights provided weight and balance considerations will permit to reduce the possibility of water condensing on the walls of partially filled tanks To further reduce the possibility of contaminated fuel routine maintenance of the fuel system should be performed in accordance with the airplane Maintenance Manual Only the proper fuel as recommended in this POH should be used and fuel additives should not be used unless approved by Cessna and the Federal Aviation Administration 62PHUS 01 U S 8 21 SECTION 8 CESSNA AIRPLANE HANDLING SERVICE MODEL 162 AND MAINTENANCE GARMIN G300 LANDING GEAR Consult the following table for servicing information on the landing gear COMPONENT SERVICING CRITERIA Nose Wheel 4 00 5 8 Ply Rated Tire 38 0 PSI 2 0 PSI Main Wheel 5 00 5 4 Ply Rated Tire 30 0 PSI 2 0 PSI CLEANING AND CARE WINDSHIELD AND WINDOWS The plastic windshield and windows should be cleaned with an airplane windshield cleaner Apply the cleaner sparingly with soft cloths and rub with moderate pressure until all dirt oil scum and bug stains are removed Allow the cleaner to dry then wipe it off with soft flannel cloths The inside of the windshield should be cleaned with a anti fog cleaning agent CAUTION NEVER USE GASOLINE BENZENE ALCOHOL ACETONE FIRE EXTINGUISHER ANTI ICE FLUID LACQUER THINNER OR GLASS CLEANER TO CLEAN THE PLASTIC THESE MATERIALS WILL ATTACK THE PLASTIC A
50. microbes or bacterial growth In addition additives that are not compatible with fuel or fuel system components can cause the fuel to become contaminated Before each flight and after each refueling use a clear sampler cup and drain at least a cupful of fuel from each fuel tank drain location and from the fuel strainer quick drain valve to determine if contaminants are present and to ensure the airplane has been fueled with the proper grade of fuel If contamination is detected drain all fuel drain points again including the fuel strainer and fuel sump valve and then gently rock the wings and lower the 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 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 with contaminated or unapproved fuel In addition Owners Operators who are not acquainted with a particular 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 Fuel tanks should be
51. of cool down If the engine still does not start try to find the cause 17 26 U S 162PHUS 01 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 LEANING FOR GROUND OPERATIONS For all ground operations after starting the engine and when the engine is running smoothly 1 THROTTLE Control 1200 RPM 2 Mixture Control ADJUST lean for maximum RPM 3 THROTTLE Control ADJUST for ground operation 800 to 1000 RPM recommended NOTE If ground operation will be required after the BEFORE TAKEOFF checklist is completed lean the mixture again as described above until ready for the TAKEOFF checklist TAXIING CAUTION DUE TO LOWER WEIGHTS AND SLOWER STALL SPEEDS THAN LARGER AIRPLANES PROPER TAXI TECHNIQUES SHOULD BE USED IN WINDY CONDITIONS OPERATIONS 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 brake should be avoided since this can cause brake heating brake fade or loss of braking effectiveness resulting in loss of control or stopping ability It is important that taxi speed be held to that of a brisk walk and all flight controls be utilized up to their maximum de
52. of ice accumulation Perform landing in level attitude Missed approaches should be avoided whenever possible because of severely reduced climb capability U S 162PHUS 00 CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 ABNORMAL LANDINGS LANDING WITH PARTIAL OR NO FLIGHT INSTRUMENT INFORMATION 1 Transponder Select Pressure Alt display using FUNC button ADAHRS may be providing altitude information to transponder 2 Selected Field FLY OVER noting terrain obstructions and any visual cues that may be used for speed references i e traffic on nearby highway etc Approach NORMAL Wing Flaps AS REQUIRED FULL recommended Speed Use best pilot judgment and experience to reference 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 9 ds co 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 from locked brakes and skidding tires due to over braking LANDING WITH A FLAT MAIN TIRE 1 Approach NORMAL 2 Wing Flaps FULL 3 Touchdown GOOD MAIN TIRE FIRST hold airplane off flat tire as long as possible with aileron control 4 Directional Control MAINTAIN using rudder and brake on good wheel as re
53. of the latest Federal Aviation Regulations to ensure that all data requirements are met To be displayed in the airplane at all times 1 Aircraft Special Airworthiness Certificate FAA Form 8130 7 2 Aircraft Registration Certificate FAA Form 8050 3 3 Aircraft Radio Station License if applicable To be carried in the airplane at all times 1 Current Pilot s Checklist Recommended to be carried in the airplane at all times 1 Current Pilots 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 items listed are required by the United States Federal Aviation Regulations Since the regulations of other nations may require other documents and data owners of airplanes not registered in the United States should check with their own aviation officials to determine their individual requirements Cessna recommends that these items plus the Customer Care Handbook and Customer Care Card be carried in the airplane at all times 162PHUS 01 U S 8 7 SECTION 8 CESSNA AIRPLANE HANDLING SERVICE MODEL 162 AND MAINTENANCE GARMIN G300 AIRPLANE INSPECTION PERIODS FAA REQUIRED INSPECTIONS As required by U S Federal Aviation Regulations all civil
54. operational Airplane Weight and Balance CHECKED and ENTERED AVN MASTER Switch OFF MASTER Switch ALT and BAT OFF Fire Extinguisher CHECK if installed verify gage pointer in green arc LEFT WING QUU Sue INN 7 6 Cabin Door CHECK security and condition Main Wheel Tire CHECK proper inflation and general condition weather checks tread depth and wear etc Brake Line CHECK security and condition Wheel Fairings CHECK security and condition if installed Fresh Air Vent CHECK blockage Fuel Quantity CHECK VISUALLY for desired level WARNING TAKEOFF IS PROHIBITED WITH LESS THAN Y TANK OF FUEL MIN GRND gt MARKING ON FUEL INDICATOR Fuel Filler Cap SECURE and VENT CLEAR Continued Next Page U S 162PHUS 00 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 PREFLIGHT INSPECTION Continuea LEFT WING Continued 8 Fuel Tank Sump Quick Drain Valves DRAIN Drain at least a cupful of fuel using sampler cup from each sump location 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 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
55. owner advisories prior 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 B6151 SMOKING PROHIBITED 8 Silk screened on the right instrument panel This aircraft was manufactured in accordance with Light Sport Aircraft airworthiness standards and does not conform to standard category airworthiness requirements Continued Next Page 162PHUS 02 U S 3 17 SECTION 3 CESSNA OPERATING LIMITATIONS MODEL 162 GARMIN G300 PLACARDS Continued 9 On the right side of the baggage compartment below the window B14615 BAGGAGE ALLOWANCE 50 POUNDS MAXIMUM FOR ADDITIONAL LOADING INSTRUCTIONS SEE WEIGHT AND BALANCE DATA 10 Near both fuel tank filler cap B14617 FUEL 100LL 100 MIN GRADE AVIATION GASOLINE CAP 12 00 U S GAL 45 LITERS USABLE TO UPPER INDICATOR HOLE CAP 3 00 U S GAL 11 LITERS USABLE TO BOTTOM OF FILLER INDICATOR TAB 11 On the engine oil access door B14541 Cessna ENGINE OIL ALL TEMP USE MULTIVISC OR ABOVE 4 C 40 F USE SAE 50 BELOW 4 C 40 F USE SAE 30 WHEN OPERATING TEMPERATURES OVERLAP USE THE LIGHTER EF DIL BATE HOURS OikCHANGED L Ll oiLusep S USE ONLY DETERGENT OIL THAT COMPLIES WITH THE LATE
56. push full in Continued Next Page 62PHUS 01 U S 7 13 SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 STARTING ENGINE With Battery Continued 5 6 7 10 11 MAGNETOS Switch START release when engine starts 13 14 NAV Light Switch ON as required 16 17 18 17 14 AVN MASTER Switch OFF MASTER Switch ALT and BAT ON Engine Indicating System CHECK PARAMETERS verify no red X s through indicators VOLTS CHECK ElS 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 eventually unreadable If the starter fails to crank the engine or the G300 display becomes unreadable service battery or apply external power AMPS CHECK verify discharge shown negative Propeller Area CLEAR verify that all people and equipment are at a safe distance from the propeller STROBE Light Switch ON 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 engine starts advance the mixture control to the FULL RICH position and promptly retard the throttle control Oil Pressure CHECK verify that oil pressure increases above 10 PSI into the YELLOW BAND range in 30 seconds AMPS CHECK verify charge shown p
57. s responsibility to make sure that he or she has the latest revision to each supplement of a Pilot s Operating Handbook and the latest issued Log Of Approved Supplements This Log Of Approved Supplements was the latest version as of the date it was shipped by Cessna however some changes may have occurred and the owner should verify this is the latest most up to date version by contacting Cessna Customer Service at 316 517 5800 Supplement Name Revision Equipment Number Level Installed 1 Ameri King AK 450 Emergency 0 Locator Transmitter ELT 2 Ameri King AK 451 Emergency Locator Transmitter ELT 0 3 PS Engineering PM3000 Intercom System 0 4 Reserved 5 Reserved 6 Garmin GTX 327 Transponder 0 T Garmin SL 40 VHF Comm Transceiver 0 162PHUSLOG 01 19 November 2009 U S Log 1 Log 2 il ATextron Company Pilot s Operating Handbook And Flight Training Supplement CESSNA MODEL 162 Serials 16200001 and On SUPPLEMENT 1 AMERI KING AK 450 EMERGENCY LOCATOR TRANSMITTER ELT SERIAL NO REGISTRATION NO This supplement must be inserted into Section 10 of the Pilot s Operating Handbook and Airplane Flight Manual when the Ameri King AK 450 Emergency Locator Transmitter ELT is installed D Member of GAMA COPYRIGHT 2009 2 NOVEMBER 2009 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 162PHUS S1 00 US S1 1 SECTION 10 SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 162 GARMIN
58. samples should then be taken at all quick drain points until all contamination has been removed Continued Next Page 162PHUS 00 U S 7 23 SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 PREFLIGHT INSPECTION Continued 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 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 When parked on the ramp care should be exercised to make sure wings are level or the left wing slightly higher to prevent fuel from dripping from the fuel vent when fuel tanks are full To prevent loss of fuel in flight make sure the fuel tank filler caps are tightly sealed after 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 that are operated from rough fields especially at high altitudes are subjected to abnormal landing gear abuse
59. ss ER KEER rea 11 0 Ibs sq ft 53 7 kg sq m Power Loading E PP 13 2 Ibs HP 1 8 U S 162PHUS 01 CESSNA SECTION 2 MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION GARMIN G300 AIRPLANE AND SYSTEMS DESCRIPTION TABLE OF CONTENTS Page ae ke TION EE add 2 3 NG cierta id a APP Gee ees 2 3 fign derum 2 3 Instrument Panel Flight and System Instruments 2 5 Landing Gear and Brake System iliius 2 6 Miscellaneous Cabin Features 0000 cece eee eee 2 7 Be CU E ea E O EAE RS 2 8 Engine GontrolS etorri Ad bie dde 2 8 Engine INSIMUMEMS cscasesunercdiwetides es 2 9 Tachometer RPM a ad 2 9 Oil Pressure OIL PS isi ae REEDE da ARE EES 2 10 Oil Temperature OIL PF eesi Naa REEVES A 2 11 Exhaust Gas Temperature EGT F if installed 2 11 Carburetor Temperature CARB PF 2 12 New Engine Break In And Operation 2 12 Engine Lubrication SySIOITI redet Kaka had ESAE ES 2 13 Ignition And Starter System a 2 13 Air Induction SYSTCMM as ooa A Ee ANA 2 14 Exhaust O SIM A NGA Ar urs 2 14 COCINAS VS My se uu ia er sd d kes 2 14 pisei 2 15 Fuel Systeme ner ost uS Na Ae RSS 2 15 Fuel DISIIDULOE x lent Peete ad nee Y ade x aes 2 15 Fuel Indicating System 0 0 0 0 Ee es 2 16 Fuel VENUNG coss SERE RSA DEERE dG EE OD ES DLL 2 17 Reduced Tank Capacity ii uc RE RR EE RE dead RERO EE 2 18 Fuel Drain Valves naaa a bee des SERE EE ete d bk 2 19 16
60. stations Figure 4 6 Sheet 2 4 24 U S 162PHUS 01 CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE GARMIN G300 EQUIPMENT LIST INTERNAL CABIN DIMENSIONS U S UNITS B10724 Cabin Height Measurements Baggage Area Y 36 67 54 64 Cabin Width Measurements Face of Instrument Panel Firewall En E A 43 60 Be c r 220 210 200 190 180 170 160 150 140 130 120 110 100 NOTE e Maximum weight in the baggage compartment area is 50 pounds with a maximum floor loading of 8 pounds per square foot e All dimensions shown are in inches Figure 4 7 Sheet 1 of 2 162PHUS 01 U S 4 25 SECTION 4 WEIGHT AND BALANCE EQUIPMENT LIST INTERNAL CABIN DIMENSIONS METRIC UNITS B10725 Baggage Area ED gese CESSNA MODEL 162 GARMIN G300 Cabin Height Measurements 931 42 gt 1387 86 Cabin Width Measurements Face of Instrument Panel Firewall 99060 1107 44 ERN oe r Es 5334 4826 4318 3810 3302 2794 5588 5080 4572 4064 3556 3048 2540 NOTE e Maximum weight in the baggage compartment area is 22 68 kilograms with a maximum floor loading of 39 05 kilograms per square meter e All dimensions shown are in millimeters Figure 4 7 Sheet 2 4 26 162PHUS 01 CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE GARMIN G300 EQUIPMENT LIST CENTER OF GRA
61. techniques also contribute to greater range and are figured into cruise performance tables To achieve the recommended lean mixture fuel consumption figures shown in Section 5 the mixture should be leaned per recommended procedures In the event that unusual conditions cause the intake air filter to become clogged or iced over apply carburetor heat immediately to bypass the intake air filter therefore providing unfiltered heated air as the alternate air intake Engine RPM can decrease from a cruise power setting This RPM loss should be recovered by increasing the throttle setting to maintain desired power Continued Next Page 17 34 U S 162PHUS 01 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 CRUISE Continued Carburetor ice as evidenced by an unexplained drop in RPM can be removed by application of full carburetor heat Upon regaining the original RPM with heat off use the minimum amount of heat reference EIS CARB F display to prevent ice from forming Since the heated air causes a richer mixture readjust the mixture setting when carburetor heat is to be used continuously in cruise flight The use of full carburetor heat is recommended during flight in heavy rain to avoid the possibility of engine stoppage due to excessive water ingestion or carburetor ice The mixture setting should be readjusted for smoothest operation Power changes should be made cautiously followed by prompt adjustment of the mixture f
62. the engine and oil warm up the oil pressure will come down into the green band range Continued Next Page 2 10 U S 162PHUS 00 CESSNA SECTION 2 MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION GARMIN G300 ENGINE Continued ENGINE INSTRUMENTS Continued OIL TEMPERATURE OIL F The oil temperature sensor is installed in the engine oil filter adapter and provides a signal to the engine display that is processed and shown as oil temperature Engine oil temperature is shown on all ElS pages The instrument range is 0 to 250 F with digital information range from 30 to 265 F The instrument has a yellow band from 0 to 75 F low caution a green band from 75 to 220 F normal operating range a yellow band from 220 to 240 high caution and a red band from 240 to 265 F high warning A white pointer 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 engine display that is processed and shown on the EIS ENGINE page by the EGT F vertical tape display and digital information The tape indicator range is from 1000 to 1600 F and the digital information range is from 1000 to 2000 F
63. to make changes Holding the trim switch can result in over trimming and may start a Pilot Induced Oscillation PIO condition resulting in chasing the trim If this occurs it is best to let the airplane stabilize then start again by just bumping the trim switch When in the flare the elevator trim switch should be pulsed aft toward the full nose up position at the same time slowly reducing power so that the airplane is rotated to a slightly nose above the horizon attitude for touchdown During the landing 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 a forced landing Do not attempt to restart the engine The first sign of an electrical fire is usually the smell of burning insulation The checklist procedure for electrical fires calls for electrical power to be turned off All flight instruments and navigation will be lost at this time The checklist procedure should result in the elimination of the fire When the fire is extinguished electrical power may be turned on to those systems not involved Navigation and flight information if unaffected should be reposted to instruments within 1 2 mi
64. volt main storage battery is located on the right forward side of the firewall The alternator and main battery are controlled 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 anytime the MASTER switch is turned on The electrical bus provides power to the avionics bus through the AVN MASTER switch The avionics bus is supplied with power anytime the MASTER switch and AVN MASTER switch are turned on The electrical system is equipped with a secondary battery located between the firewall and the instrument panel This secondary battery supplies power to the secondary power circuit for PANEL LIGHTS dimming as well as stable power to the G300 avionics and displays during engine start This prevents undesired panel light dimming and loss of G300 information resulting from voltage drop during the engine start The secondary battery is also controlled by the MASTER switch found on the switch circuit breaker panel Power is supplied to equipment on the secondary power circuit anytime the MASTER switch is turned on Continued Next Page 162PHUS 01 U S 2 19 SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTI
65. yellow range POWERPLANT AND ELECTRICAL INSTRUMENT MARKINGS INSTRUMENT RED LOWER WARNING YELLOW LOWER CAUTION GREEN NORMAL OPERATING RANGE 2000 to 2750 RPM YELLOW UPPER CAUTION RED UPPER WARNING 2750 to 3500 RPM 0 to 75 F 75 to 220 F 220 to 240 F 240 to 265 F 0 to 10 PSI 10 to 30 PSI 30 to 60 PSI 60 to 100 PSI 100 to 140 PSI Exhaust Gas Temperature 1000 to 1600 F White Advisory Carburetor Temperature CARB F 5 to 40 F 35 to 35 White Advisory 30 to 12 5 Maximum operating limit is lower end of red 12 5 to 15 15 to 16 16 to 30 Figure 3 3 162PHUS 00 U S SECTION 3 CESSNA OPERATING LIMITATIONS MODEL 162 GARMIN G300 WEIGHT LIMITS Maximum Ramp Weight 1324 POUNDS 600 6 kg Maximum Takeoff Weight 1320 POUNDS 598 8 kg Maximum Landing Weight 1320 POUNDS 598 8 kg MAXIMUM WEIGHT IN BAGGAGE COMPARTMENT Baggage 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 firewall
66. 0 PS ENGINEERING PM3000 INTERCOM SYSTEM GENERAL The PM3000 is a 2 place panel mounted InterCom System ICS allowing voice activated radio communications through the Garmin SL40 VHF Comm radio conversations between the pilot and copilot and a audio input function connected to the AUX AUDIO INPUT jack or the optional XM radio receiver The PM3000 utilizes integrated volume and squelch controls for both pilot and copilot headsets Both output amplifiers are changed simultaneously whenever an adjustment is made utilizing the VOLUME control knob Likewise when an adjustment is made to the SQUELCH control knob both Voice Activated Squelch VOX circuits are changed at the same time Since the PM3000 ICS is designed to use modern aviation style stereo headsets it is not necessary to balance the volume and squelch controls The PM3000 has an automatic fail safe interconnect to the Garmin SL40 VHF Comm radios If power is disrupted to the PM3000 intercom for any reason an internal relay will connect the pilot s headset directly to the SL40 Comm radio allowing uninterrupted radio communications to the pilot s headset only If there is a power failure of the PM3000 ICS or the power switch is selected to the off position the copilot will not hear radio communications The PM3000 is also equipped with a two position mode selector switch located in the center of the control panel with positions for ISO Pilot Only and ALL Pilot and Copilot
67. 0 F 240 to 265 F 0 to 10 PSI 10 to 30 PSI 30 to 60 PSI 60 to 100 PSI 100 to 140 PSI Exhaust Gas Temperature 1000 to 1600 F White Advisory Carburetor Temperature CARB F 5 to 40 F 35 to 35 White Advisory 30 to 12 5 Maximum operating limit is lower end of red U S 12 5 to 15 Figure 9 2 15 to 16 16 to 30 162PHUS 00 CESSNA SECTION 9 MODEL 162 PLACARDS AND MARKINGS GARMIN G300 PLACARDS The following information must be displayed in the form of composite or individual placards 1 In full view of the pilot The DAY NIGHT VFR entry shown on the example below will vary with installed equipment 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 airplane is approved for the following flight operations as of the date of original airworthiness certificate DAY NIGHT VFR 2 On control lock B6143 CAUTION CONTROL LOCK REMOVE BEFORE STARTING ENGINE o o 3 Silk screened on left instrument panel above magnetos switch MIN TAKEOFF PROHIBITED WITH LESS THAN 1 4 FU
68. 0 U S GAL 11 LITERS USABLE TO BOTTOM OF FILLER INDICATOR TAB 11 On the engine oil access door B14541 Cessna ENGINE OIL ALL TEMP USE MULTIVISC OR ABOVE 4 C 40 F USE SAE 50 BELOW 4 C 40 F USE SAE 30 WHEN OPERATING TEMPERATURES OVERLAP USE THE LIGHTER GRADE OIL DATE TACH OIL CHANGED 2 ot usen L II USE ONLY DETERGENT OIL THAT COMPLIES WITH THE LATEST ISSUE OF TEM SPEC MHS 24 CESSNA DEALERS HAVE LIST OF APPROVED OILS HOURS Continued Next Page 162PHUS 01 U S 9 7 SECTION 9 CESSNA PLACARDS AND MARKINGS MODEL 162 GARMIN G300 PLACARDS Continued 12 On firewall adjacent to battery box and second placard on external power receptacle door if external power receptacle option is installed B14616 CAUTION 12 VOLTS D C THIS AIRCRAFT IS EQUIPPED WITH ALTERNATOR AND NEGATIVE GROUND SYSTEM OBSERVE PROPER POLARITY REVERSE POLARITY WILL DAMAGE ELECTRICAL COMPONENTS 13 Located on both left and right fuel sight tubes B14537 E LVL FLT 3 4 G R N 1 2 D 1 2 1 4 MIN E TO O s C J 091471028 19 8 U S 162PHUS 01 CESSNA SECTION 10 MODEL 162 SUPPLEMENTS GARMIN G300 SUPPLEMENTS INTRODUCTION The supplements in this section contain amended operating limitations operating procedures performance data and other necessary information for airplanes conducting special operations for both standard and optional equipme
69. 00 TABLE OF CONTENTS Continued Page ARA eal dou dete ocean ee EE estu 8 17 Approved Fuel Grades And Colors 8 17 Fuel Gabpaclly acercarse aa ae PAGA Unas 8 17 Fuel Additives 5 9 eva ita a 8 18 Fuel ContamiratioImes sucus eese 82 EER GG NA NG E ERU 8 21 PANGING Sedis ns E d s OG eda en orbe 8 22 Cleaning And Cares erp oye dte E E 8 22 Windshield And Windows 00000 eee eeeeeee 8 22 Painted Surfaces ocu cse eara d ed Wt PEE EAE 8 23 Propeller Gate see eee adem D px a EE EE x 8 24 Engine Cares Ls voces ara e det 8 24 Interior Care RR E 8 25 8 26 AVIONICS Cale is ar EER dE DE EE bed qr tenere a dio 8 25 8 26 8 2 U S 162PHUS 01 CESSNA SECTION 8 MODEL 162 AIRPLANE HANDLING SERVICE GARMIN G300 AND MAINTENANCE INTRODUCTION This section contains factory recommended procedures for proper ground handling and routine care and servicing of your airplane lt also identifies certain inspection and maintenance requirements which must be followed if your airplane is to retain that new airplane performance and dependability It is important to follow a planned schedule of lubrication and preventive maintenance based on climatic and flying conditions encountered in your local area Keep in touch with a Cessna Service Station and take advantage of their knowledge and experience Your Cessna Service Station knows your airplane and how to maintain it and will remind you when lubrications and oil changes a
70. 01240 0 06 90 08 Figure 4 1 Sheet 3 162PHUS 01 U S 4 7 SECTION 4 CESSNA WEIGHT AND BALANCE MODEL 162 EQUIPMENT LIST GARMIN G300 AIRPLANE WEIGHING PROCEDURES 1 Preparation a Inflate tires to recommended operating pressures b Defuel airplane Refer to the Maintenance Manual c Service engine oil as required to obtain a normal full indication approximately 5 quarts on dipstick d Raise flaps to the fully retracted position e Place all control surfaces in neutral position f Remove all non required items from airplane Level a Place scales under each wheel minimum scale capacity 1000 pounds b Deflate the nose tire to properly center the bubble in the level Refer to Figure 4 2 Weigh a Weigh airplane in a closed hangar to avoid errors caused by air Currents b With the airplane level and brakes released record the weight shown on each scale Deduct the tare if any from each reading 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 on right side and average the measurements Using weights from step 3 and measurements from step 4
71. 11 12 13 Pilot s Operating Handbook AS REQUIRED Garmin G300 Pilot s Guide AS REQUIRED Pilot s Checklist AS REQUIRED Parking Brake SET Control Stick Lock REMOVE Wing Flaps UP Fuel Quantity Indicators CHECK L and R WARNING e TAKEOFF IS PROHIBITED WITH LESS THAN Ya TANK OF FUEL MIN T O GRND MARKING ON FUEL INDICATOR WHEN THE MASTER SWITCH IS ON USING AN EXTERNAL POWER 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 MAGNETOS Switch OFF MASTER Switch ALT and BAT ON AVN MASTER Switch ON Primary Flight Display PFD CHECK verify PFD is ON and software current Multifunction Flight Display MFD CHECK if installed verify MFD is ON PFD ADAHRS Test and MFD SELF TEST COMPLETE verify no red X s shown Continued Next Page 162PHUS 01 U S 7 5 SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 PREFLIGHT INSPECTION Continued D CABIN Continued 14 LOW VOLTS Annunciator CHECK verify annunciator is shown NOTE LOW VOLTS Annunciator will only be shown if battery voltage is less than 12 5 volts Verify battery voltage on PFD MFD ENG page Elevator Trim Control T O POSITION Avionics Cooling Fan CHECK verify fan is
72. 18 thru 3 19 3 20 Revised 1 4 1 4 2 thru 4 4 Original 0 4 5 Revised 1 4 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 14 Original 0 6 15 Revised 1 6 16 Original 0 6 17 thru 6 18 Revised 1 6 19 Original 0 Continued Next Page pi U S 162PHUS 02 CESSNA MODEL 162 GARMIN G300 INTRODUCTION LOG OF EFFECTIVE PAGES Continued Page Number 6 20 6 21 thru 6 22 6 23 thru 6 26 6 27 thru 6 30 6 31 thru 6 33 6 34 thru 6 39 6 40 7 1 thru 7 2 7 3 7 4 7 5 7 6 thru 7 7 7 8 thru 7 10 7 11 thru 7 12 7 13 thru 7 16 7 17 7 18 thru 7 21 7 22 thru 7 24 7 25 thru 7 26 7 27 thru 7 29 7 30 thru 7 41 7 42 thru 7 43 7 44 thru 7 45 7 46 8 1 8 2 thru 8 10 8 11 thru 8 12 8 13 8 14 thru 8 18 8 19 thru 8 25 8 26 162PHUS 02 Page Status Revised Original Revised Original Revised Original Revised Revised Revised Original Revised Original Revised Original Revised Original Revised Original Revised Original Revised Original Revised Original Revised Original Revised Original Revised Continued Next Page U S Revision Number
73. 2 MODEL 162 GARMIN G300 EMERGENCY PROCEDURES If a forced landing is necessary press the ON switch within the remote switch panel before landing This is very important in remote or mountainous terrain The GREEN ON light will flash and the aural warning will be heard After a landing when search and rescue aid is needed use the ELT as follows NOTE The ELT remote switch assembly could be inoperative if damaged during a forced landing If inoperative the inertia G switch will activate automatically However to turn the ELT OFF and ON again requires manual switching of the ELT main control panel switch which is located on the ELT transmitter unit located in the tailcone 1 MAKE SURE THE ELT IS ENERGIZED a If the GREEN ON light in the remote switch panel is not flashing press the ON switch within the remote switch panel to energize the ELT transmitter b Listen for the aural warning If the COM radio s operate and can be energized safely no threat of fire or explosion energize a COM radio and set the frequency to 121 5 MHz The ELT tone should be heard on the COM radio if the ELT is working correctly When done de energize the COM radio s to conserve the airplane battery power c Make sure that nothing is touching or blocking the ELT antenna 2 AFTER RESCUE Press the RESET button in the remote switch panel to de energize the ELT If the remote switch does not de energize the ELT press the RESET button on th
74. 2PHUS 01 U S 2 1 SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 162 GARMIN G300 TABLE OF CONTENTS Page Electrical OSI al eK RE 2 19 Master SWIICH acorta mo x E ER OE ER D Meme are ca le 2 21 Electrical System Monitoring oocococoooooo 2 21 Main Battery Current Amps lille 2 21 System Voltage Volts RS E STE OES ERA EE DE PR RR iS 2 21 GlreditBreakels ERGE EERS DE Bo NADERA DEd SS ER 2 22 ANA AA 2 23 External Power Receptacle if installed 2 23 Lighting Systems eit cece RE CR be PRICE de ONIS M 2 24 EXPO IN oie 2 24 Menor Lighting caciacee cases io obe te ER OE mes 2 24 Cabin Heating and Ventilating System 2 25 2 26 Stall Warning System 00 000 eee eee 2 25 2 26 2 2 U S 162PHUS 01 CESSNA SECTION 2 MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION GARMIN G300 INTRODUCTION This section provides description and operation of the airplane and its systems Some equipment described herein is optional and may not be installed in the airplane Refer to Section 10 Supplements for details of other optional systems and equipment AIRFRAME The airplane is an all metal two place high wing single engine airplane equipped with tricycle landing gear and is designed for sport flying and introductory training purposes The sheet metal fuselage bulkhead stringer and skin semi monocoque construction provide safe and comfortable environment for pilot pa
75. 350 Maximum Takeoff Weight 1320 Pounds 1320 AHA 1300 1250 1200 1150 1100 1050 k e e e 950 900 850 800 132 0 133 0 134 0 135 0 136 0 137 0 1138 0 131 5 1325 1335 1345 135 5 136 5 137 5 Airplane C G Location Inches Aft of Datum FS 0 0 Figure 4 9 Sheet 1 of 2 162PHUS 00 U S 4 29 SECTION 4 CESSNA WEIGHT AND BALANCE MODEL 162 EQUIPMENT LIST GARMIN G300 CENTER OF GRAVITY LIMITS METRIC UNITS B13959 Airplane C G Location Millimeters Aft of Datum FS 0 0 3340 3360 3380 3400 3420 3440 3460 3480 3500 620 Maximum Takeoff Weight 598 74 Kilograms 600 580 560 ra 540 O 2 520 x 5 500 n 480 S 3 460 X jo o O 440 3 420 400 380 360 Figure 4 9 Sheet 2 4 30 U S 162PHUS 00 CESSNA SECTION 5 MODEL 162 PERFORMANCE GARMIN G300 PERFORMANCE TABLE OF CONTENTS Page INFOdUCION Le ESE RE EE a ds ae o eae 5 3 Use of Performance Charts 0 000 SS EE ss EE eee 5 3
76. 5 volts no immediate action is required Continue monitoring and land as soon as practical Continued Next Page 6 38 U S 162PHUS 00 CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 ELECTRICAL POWER SUPPLY SYSTEM MALFUNCTIONS Continued INSUFFICIENT RATE OF CHARGE When the overvoltage circuit or other fault opens the alternator START ALT circuit breaker and de energizes the alternator a discharge current will be shown on the main battery ammeter AMPS and the red LOW VOLTS annunciator will be displayed on the PFD The Alternator Internal Control Unit AICU can de energize the alternator due to minor disturbances in the electrical system resulting in a nuisance opening of the START ALT circuit breaker If this happens an attempt should be made to energize the alternator system To energize the alternator 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 still shown on the AMPS Indicator there is an alternator system problem Do not repeat steps to energize the alternator system Decrease the electrical load on the battery by de energizing none
77. 62PHUS 01 CESSNA SECTION 5 MODEL 162 PERFORMANCE GARMIN G300 SAMPLE PROBLEM Continued TAKEOFF The takeoff distance chart Figure 5 3 should be consulted keeping in mind that distances shown are based on the short field technique Conservative distances can be established by reading the chart at the next higher value of weight altitude and temperature For example in this particular sample problem the takeoff distance information presented for a weight of 1320 pounds pressure altitude of 2000 feet and a temperature of 30 C should be used and results in the following I Ground roll 860 Feet Total distance to clear a 50 foot obstacle 1495 Feet 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 14 Knot AA X 10 20 Decrease 7 Knots This results in the following distances corrected for wind Ground roll zero wind 860 Feet Decrease in ground roll 860 feet X 20 172 Feet Corrected ground roll 688 Feet Total distance to clear a 50 foot obstacle zero wind 1495 Feet Decrease in total distance 1495 feet X 20 299 Feet Corrected total distance to clear 50 foot obstacle 1196 Feet Continued Next Page 162PHUS 01 U S 5 5 SECTION 5 CESSNA PERFORMANCE MODEL 162 GARMIN G300 SAMPLE PROBLEM Continued
78. A CONCENTRATION IN EXCESS OF THAT RECOMMENDED 0 15 BY VOLUME MAXIMUM MAY RESULT IN DETRIMENTAL EFFECTS TO THE FUEL TANK AND SEALANT AND DAMAGE TO O RINGS AND SEALS USED IN THE FUEL SYSTEM AND ENGINE COMPONENTS A CONCENTRATION OF LESS THAN THAT RECOMMENDED 0 10 BY TOTAL VOLUME MINIMUM WILL RESULT IN INEFFECTIVE TREATMENT USE ONLY BLENDING EQUIPMENT THAT IS RECOMMENDED BY THE MANUFACTURER TO OBTAIN PROPER PROPORTIONING Continued Next Page p162PHUS 01 U S 8 19 SECTION 8 CESSNA AIRPLANE HANDLING SERVICE MODEL 162 AND MAINTENANCE GARMIN G300 FUEL Continued FUEL ADDITIVES Continued FUEL MIXING RATIO B14781 40 Fluid Ounces of Additive NO O O O o 0 10 20 30 Gallons of Gasoline Figure 8 1 Prolonged storage of the airplane will result in a water 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 18 20 U S 162PHUS 01 CESSNA SECTION 8 MODEL 162 AIRPLANE HANDLING SERVICE GARMIN G300 AND MAINTENANCE FUEL Continued FUEL CONTAMINATION Fuel contamination is usually the result of foreign material present in the fuel system and may consist of water rust sand dirt
79. AKEOFF IS PROHIBITED WITH LESS THAN 4 TANK OF FUEL MIN GRND TO MARKING ON FUEL INDICATOR Continued Next Page p162PHUS 01 U S 7 9 SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 PREFLIGHT INSPECTION Continued RIGHT WING Continued SINE TOO Fuel Filler Cap SECURE and VENT CLEAR Main Wheel Tire CHECK proper inflation and general condition weather checks tread depth and wear etc Brake Line CHECK security and condition Wheel Fairings CHECK security and condition if installed Fuel Tank Sump Quick Drain Valves DRAIN Drain at least a cupful of fuel using sampler cup from each sump location 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 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 nat 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 EVIDENCE OF CONTAMINATION STILL EXISTS THE AIRPLANE SHOULD NOT BE FLOWN TANKS SHOULD BE DRAINED AND SYSTEM PURGED BY QUALIFIED MAINTENANCE PERSONNEL ALL EVIDENCE O
80. ALT and BAT ON Continued Next Page 1 162PHUS 01 U S 7 15 SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 STARTING ENGINE With External Power if installed Continued 13 Engine Indicating System CHECK PARAMETERS verify no 14 15 16 17 18 19 20 EXTERNAL POWER DISCONNECT FROM GROUND 22 23 24 25 17 16 red X s through indicators VOLTS CHECK EIS ENGINE PAGE verify 12 5 to 15 0 volts indication and LOW VOLTS annunciation is not shown AMPS CHECK verify charge shown positive Propeller Area CLEAR verify that all people and equipment are ata safe distance from the propeller STROBE Lights Switch ON 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 engine starts advance the mixture control to the FULL RICH position and promptly retard the throttle control Oil Pressure CHECK verify that oil pressure increases above 10 PSI into the YELLOW BAND range in 30 seconds Power REDUCE TO IDLE POWER latch external power receptacle door Power INCREASE to approximately 1500 RPM for several minutes to charge battery AMPS CHECK verify charge shown positive VOLTS CHECK ElS ENGINE PAGE verify 12 5 VOLTS minimum shown LOW VOLTS Annunciator CHEC
81. ANCE MODEL 162 EQUIPMENT LIST GARMIN G300 WEIGHT AND BALANCE Continued BAGGAGE TIEDOWN A nylon baggage net having four tiedown straps is provided as standard equipment 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 4 16 U S 162PHUS 01 CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE GARMIN G300 EQUIPMENT LIST SAMPLE LOADING PROBLEM U S UNITS WEIGHT AND MOMENT TABULATION SAMPLE YOUR ITEM DESCRIPTION AIRPLANE AIRPLANE Weight Moment Weight Moment lbs Ib ins lbs Ib ins 1000 1000 1 Basic Empty Weight Use the data pertaining to your airplane as it is presently equipped Includes unusable fuel 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 1812 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
82. ANE AIRPLANE Moment Moment Nei Moment Lb ins Weight Lb ins Weight pins Ibs 1000 Weight Ibs 1000 1000 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 U S 4 19 SECTION 4 CESSNA WEIGHT AND BALANCE MODEL 162 EQUIPMENT LIST GARMIN G300 SAMPLE LOADING PROBLEM METRIC UNITS YOUR YOUR AIRPLANE AIRPLANE Weight Moment Weight Moment Kgs Kgs mm Kgs Kgs mm 1000 1000 YOUR AIRPLANE Weight Moment Kgs Kgs mm 1000 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 4 4 20 U S 162PHUS 00 CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE GARMIN G300 EQUIPMENT LIST LOADING GRAPH U S UNITS B10722 ee RU Sosa l maan paaa Sa naaa Y E j T TERT TE ase a EDS aa e s E 4 d H ft 5 j 300 pa AA a EE epe X soe i E EN Pilot and Front t Passenger A WE ung Yos EE aS DEE eee EE ELE HER wa ec a H sev GN ac mc NO al o N e o F gt Lisi a EE CO AR esset DEER A ERWE E t E T E 1 oe c
83. ATIC SOURCE ALL FLAP SETTINGS CONDITIONS Power required for level flight or maximum power decent KIAS 40 50 60 70 80 90 100 110 120 130 140 148 KCAS 43 52 61 71 80 89 98 108 117 126 135 143 Figure 5 1 5 10 U S 162PHUS 00 CESSNA SECTION 5 MODEL 162 PERFORMANCE GARMIN G300 STALL SPEED AT 1320 POUNDS CONDITIONS Power IDLE MOST FORWARD CENTER OF GRAVITY Se er BANK us asas FLAP SETTINGS usps Lus eus us as 44 10 43 tit 40 NOTE e Altitude loss during a stall recovery may be as much as 250 feet e KIAS values are approximate Figure 5 2 162PHUS 00 U S 5 11 SECTION 5 CESSNA PERFORMANCE MODEL 162 GARMIN G300 SHORT FIELD TAKEOFF DISTANCE AT 1320 POUNDS CONDITIONS Flaps 10 Zero Wind Full Throttle Prior to Brake Release Lift Off 50 KIAS Paved Level EE Runway Speed at 50 ft 55 KIAS br 0G li 0G Ai MOES MOE Ground Ground Ground Ground Ground P Roll a Roll Roll i pa ft ft ft NOTE e Short field technique as specified in Section 7 e Prior to takeoff from fields above 3000 feet elevation the mixture should be leaned to give maximum RPM in a full throttle static runup e Decrease distances 10 for each 7 knots headwind For operation with tail winds up to 10 knots increase distances by 10 for each 1 5 knots Figure 5 3 5 12 U S 162PHUS 01 CESSNA SECTION 5 MODEL 162 PERFORMANCE GARMIN G300 SHORT FIELD LANDING DISTANCE AT 1320 POUNDS CONDITIONS
84. ATOR 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 0 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 0919022 1 47 1161 57 MANUAL ADJUST PILOT 25 04 S SEAT BELT AND SHOULDER HARNESS 0919022 1 47 1161 57 MANUAL ADJUST FRONT PASSENGER 25 05 S BAGGAGE RESTRAINT NET 0919030 0 10 176 21 25 06 S PILOT S OPERATING HANDBOOK 2 00 160 59 25 07 R 7 PILOT S CHECKLIST 1 00 160 59 25 08 S GARMIN G300 PILOT S GUIDE 1 00 160 59 25 09 S GARMIN COCKPIT REFERENCE GUIDE 1 0 160 59 25 10 S FUEL SAMPLING CUP 1 00 160 59 25 11 S AK 450 C 2 FREQUENCY ELT 0918114 2 50 201 79 ANTENNA AND CABLE 450017 C 0 16 198 34 N 25 120 AK 451 C 3 FREQUENCY ELT 0918508 2 22 201 79 ANTENNA AND CABLE 450017 1B C 0 16 198 34 25 13 O SUN VISORS 0911010 1 65 126 44 25 14 O BALLISTIC RECOVERY SYSTEM 0901105 34 97 1168 57 Figure 4 1 Sheet 1 of 3 162PHUS 01 U S 4 5 SECTION 4 CESSNA WEIGHT AND BALANCE MODEL 162 EQUIPMENT LIST GARMIN G300 REF WT ARM ITEM NO EQUIPMENT LIST DESCRIPTION DRAWING LBS INS 26 FIRE PROTECTION 24 01 O FIRE EXTINGUISHER 0901600 1 2 77 160 59 FIRE EXTINGUISHER HAND TYPE A344T 2 53 160 59 MOUNTING CLA
85. CK 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 the BOTH position RPM decrease should not be more than 150 RPM on either magneto or be greater than 50 RPM differential between magnetos If there is a doubt concerning operation of the ignition system RPM checks at higher engine speeds will usually confirm whether a deficiency exists No RPM drop may indicate a faulty ground to one magneto or magneto timing set in advance of the angle specified Continued Next Page 17 30 U S 162PHUS 01 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 BEFORE TAKEOFF Continued ALTERNATOR CHECK The alternator should be checked for proper operation before every flight Electrical power is essential for all flight instrumentation navigation and radio operation Check the electrical system during the IMAGNETO check 1700 RPM by setting all electrical equipment required for the flight to the ON position When the alternator is operating properly the ammeters will show zero or positive current amps the voltmeter will show 13 to 15 volts and the LOW VOLTS annunciator will not be shown on the PFD Reduce the electrical load before reducing engine speed so the battery will not discharg
86. CORD U S B3099 Running basic empty weight Removed Weight change Added modification Description of article or As delivered SAMPLE WEIGHT AND BALANCE RECORD Continuous history of changes in structure or equipment affecting weight and balance Airplane model 0585T1009 Figure 4 3 Sheet 1 of 2 162PHUS 00 U S 4 13 SECTION 4 CESSNA WEIGHT AND BALANCE MODEL 162 EQUIPMENT LIST GARMIN G300 SAMPLE WEIGHT AND BALANCE RECORD METRIC B13963 Running basic empty weight a o E 2 c D O O a Y UO o gt o E o Ne o ola 2153 2 O c SG Io 2 S OD eb oizi c 5 eb O 5 E 699 oc 0 O 25o D O ES D g o gt S58 3 5 2 Dn lt x Airplane model D O a 0585T 1009 SAMPLE WEIGHT AND BALANCE RECORD Continuous history of changes in structure or equipment affecting weight and balance Item no Figure 4 3 Sheet 2 4 14 U S 162PHUS 00 CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE GARMIN G300 EQUIPMENT LIST WEIGHT AND BALANCE The following information will enable you to operate your Cessna within the prescribed weight and center of gravity limitations To determine weight and balance use the Sample Loading Problem Figure 4 4 Loading Graph Figure 4 5 and Center of Gravity Moment Envelope Figure 4 8 as follows Enter the appropriate
87. CRUISE The cruising altitude should be selected based on a consideration of trip length winds aloft and the airplane s performance A typical cruising altitude and the expected wind enroute have been given for this sample problem However the power setting selection for cruise must be determined based on several 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 expected temperature conditions The engine speed chosen is 2750 RPM which results in the following Power 64 True airspeed 108 Knots Cruise fuel flow 6 0 GPH Continued Next Page 5 6 U S 162PHUS 01 CESSNA SECTION 5 MODEL 162 PERFORMANCE GARMIN G300 SAMPLE PROBLEM Continued FUEL REQUIRED The total fuel requirement for the flight may be estimated using the performance information in Figure 5 6 and Figure 5 7 For this sample problem the time fuel and distance to climb may be determined from Figure 5 6 for maximum rate of climb The difference between the values shown in the table for 5500 feet and 1500 feet results in the following Time 6 5 Minutes Fuel 0 9 Gallons Distance 6 0 Nautical Miles These v
88. DEL 162 GARMIN G300 ICING Continued INADVERTENT ICING ENCOUNTER DURING FLIGHT Continued 6 7 11 12 c Reference GPS ALTITUDE on MFD INFO page if installed or select G300 TERRAIN Profile page GPS Altitude is provided by the white arrowhead on the left side of the TERRAIN Profile display d Navigate using Heading Strip Lateral Deviation and GPS moving map GPS moving map and TERRAIN Profile can not be displayed at the same time NOTE GPS information is not as accurate as barometric data but will provide an approximate value for comparison to pitot static instruments or a back up if barometric instruments become unreliable Plan a landing at the nearest airport With an extremely rapid ice build up select a suitable off airport landing site 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 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 effectiveness Perform a landing approach using a forward slip if necessary for improved visibility Approach at 65 to 70 KIAS estimated 70 KIAS if using GPS depending upon the amount
89. ED A Cessna ATextron Company Pilot s Operating Handbook And Flight Training Supplement SEUL ATL HEF Model 162 SERIAL NUMBER Serials 16200001 and On REGISTRATION NUMBER This publication includes the material required to be furnished to the pilot by ASTM F2245 COPYRIGHT 2009 E o UN ORIGINAL ISSUE 22 JULY 2009 WICHITA KANSAS USA REVISION 2 26 APRIL 2010 162PHUS 02 U S CESSNA INTRODUCTION MODEL 162 GARMIN G300 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 U S i ii CESSNA INTRODUCTION MODEL 162 GARMIN G300 CONGRATULATIONS Congratulations on your purchase and welcome to Cessna ownership Your Cessna has been designed and constructed to give you the most in performance value and comfort This Pilot s Operating Handbook has been prepared as a guide to help you get the most utility from your airplane It contains information about your airplane s equipment operating procedures performance and suggested service and care Please study it carefully and use it as a reference The worldwide Cessna Organization and Cessna Customer Service are prepared to serve you The following services are offered by each Cessna Service Station THE CESSNA AIRPLANE WARRANTIES which provide coverage for parts and labor are upheld through Cessna Servi
90. EL TO Continued Next Page 162PHUS 00 U S 9 5 SECTION 9 CESSNA PLACARDS AND MARKINGS MODEL 162 GARMIN G300 PLACARDS Continued 4 Silk screened on the lower left instrument panel B6151 9 6 WARNING Assure that all contaminants including water are removed from fuel and fuel systems before flight Failure to assure contaminant free fuel and heed all safety instructions and owner advisories prior to flight can result in bodily injury or death Silk screened on the upper left instrument panel NO INTENTIONAL SPINS On the instrument panel directly above the PFD MAXIMUM OPERATING MANEUVERING SPEED 89 KIAS DESIGN MANEUVERING SPEED 102 KIAS Silk screened on the upper right instrument panel SMOKING PROHIBITED Silk screened on the right instrument panel This aircraft was manufactured in accordance with Light Sport Aircraft airworthiness standards and does not conform to standard category airworthiness requirements Continued Next Page U S 162PHUS 02 CESSNA SECTION 9 MODEL 162 PLACARDS AND MARKINGS GARMIN G300 PLACARDS Continued 9 On the right side of the baggage compartment below the window B14615 BAGGAGE ALLOWANCE 50 POUNDS MAXIMUM FOR ADDITIONAL LOADING INSTRUCTIONS SEE WEIGHT AND BALANCE DATA 10 Near both fuel tank filler cap B14617 FUEL 100LL 100 MIN GRADE AVIATION GASOLINE CAP 12 00 U S GAL 45 LITERS USABLE TO UPPER INDICATOR HOLE CAP 3 0
91. F CONTAMINATION MUST BE REMOVED BEFORE FURTHER FLIGHT 10 Cabin Door CHECK security and condition 11 Fresh Air Vent CHECK blockage 17 10 U S 162PHUS 01 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 PREFLIGHT INSPECTION Continued NOSE ee Oe ea Engine Cooling Air Inlets CHECK clear of obstructions Propeller and Spinner CHECK for nicks and security Air Filter CHECK for condition and blockage by dust or other foreign matter Nosewheel Strut and Tire CHECK strut and general condition of tire weather checks tread depth and wear etc Nosewheel Fairing CHECK security and condition if installed Engine Exhaust Outlet CHECK security and condition Engine Oil Dipstick Filler Cap a Oil level CHECK b Dipstick filler cap SECURE lever horizontal and facing aft NOTE Do not operate with less than 3 5 quarts Fill to 5 quarts for extended flight 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 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 h
92. G SERVICE AND MAINTENANCE TABLE OF CONTENTS Page INMOGUCIION OE ER rra ELI iS TER rd 8 3 identification Plale ss etes eee SEE tind de ee EE DAD ME 8 4 Cessna Owner Advisories ccc tee 8 4 United States Airplane Owners 2 0000000 0 eee 8 4 International Airplane Owners 200000 o 8 4 PUDIGAIONS jess ed areata ine eave Saeed aye AA 8 5 AIDIANG Files tence ce later SR Ea te SE hd Se eh bees 8 7 Airplane Inspection Periods 0200ee eee ees 8 8 FAA Required Inspections 200 22 eee eee 8 8 Cessna Inspection Programs 0000 cece eee eee 8 8 Cessna Customer Care Program 00 aaa 8 8 Pilot Conducted Preventive Maintenance 8 9 Alterations Or Repairs 6064 daa hana SEER SG nba Eg 8 9 Ground Handling apes Apa e ce EXPERS CHE Sd de 8 10 NOWING 22 ctas esa ddr m e RC I N 8 10 E AAA A SR EE eee sen 8 11 MELO WALLS Os 8 11 JACKING 2x EL AO ie aks 8 12 LSSI dt direis de 8 13 Flyable Storage 4 un E qe C RENS 8 13 SCIVICING 2 3 EE abi BEE EED ea DEE eee tale a eared en 8 14 GIL agan da Ihain ta a ale Bab ace daa 8 15 Oil Specificatio ia aaa dad 8 15 Recommended Viscosity For Temperature Range 8 15 Capacity Of Engine Sump 0000 0c eee eee 8 16 Oil And Oil Filter Change eese EER EDE E Se eee ee ALI 8 16 Continued Next Page 162PHUS 00 U S 8 1 SECTION 8 CESSNA AIRPLANE HANDLING SERVICE MODEL 162 AND MAINTENANCE GARMIN G3
93. G300 SUPPLEMENT 1 AMERI KING AK 450 EMERGENCY LOCATOR TRANSMITTER ELT Use the Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number Supplement Status Date Original Issue 2 November 2009 LOG OF EFFECTIVE PAGES Page Page Revision Number Status Number S1 1 thru S1 8 Original 0 S1 2 U S 162PHUS S1 00 CESSNA SECTION 10 SUPPLEMENTS MODEL 162 SUPPLEMENT 1 GARMIN G300 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that are currently active Airplane Serial Revision Incorporated Number Title Effectivity Incorporated in Airplane 162PHUS S1 00 U S S1 3 SECTION 10 SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 162 GARMIN G300 AMERI KING AK 450 EMERGENCY LOCATOR TRANSMITTER ELT GENERAL The Ameri King AK 450 Emergency Locator Transmitter ELT installation uses a solid state 2 frequency transmitter 121 5 and 243 0 MHz powered by six D cell alkaline batteries Duracell MN 1300 or manufactures approved equivalent The AK 450 is also equipped with an panel mounted remote switch assembly and an external antenna mounted on the top of the tailcone The remote switch assembly is installed on the right instrument
94. GC STO 10 9 8 7 0914G1062 Figure S6 1 1 MODE SELECTION a OFF Powers off the GTX 327 transponder b STBY Powers on the GTX 327 transponder displaying the last active identification code but will not allow a reply to any interrogations c ON Powers on the GTX 327 transponder displaying the last active identification code and selects Mode A operation Mode A operation replies to any interrogations as indicated by the Reply Symbol but does not include altitude information d ALT Powers on the GTX 327 transponder displaying the last active identification code and allows for both Mode A and Mode C operations When operating in the ALT mode the transponder replies to any identification and altitude interrogations as indicated by the Reply Symbol 2 Display Screen LED display provides information for all active functions 3 START STOP Starts and stops the Count Up Count Down and Flight timers Continued Next Page FAA APPROVED 162PHUS S6 00 U S S6 5 SECTION 10 SUPPLEMENTS CESSNA SUPPLEMENT 6 MODEL 162 GARMIN G300 NORMAL PROCEDURES Continued 4 10 S6 6 FUNC Multiple presses of the FUNC key changes the function page displayed on the right side of the display screen to one of the following pages a PRESSURE ALT Displays pressure altitude in hundreds of feet b FLIGHT TIME Controlled by the START STOP key or can be configured to START when the airplane exceeds 30 KTS
95. HEADING REFERENCE SENSOR ADAHRS GSU 73 ADAHRS 0918109 3 33 1104 32 34 04 R TRANSPONDER GTX 327 TRANSPONDER 0918101 2 40 118 76 TRANSPONDER ANTENNA 0918122 0 06 116 91 34 05 0 COMPASS MAGNETIC 0918509 1 15 124 94 61 PROPELLER 61 01 R FIXED PITCH PROPELLER ASSEMBLY MCCAULEY 67 INCH PROPELLER 1A162 TCD6754 24 40 165 03 MCCAULEY 3 115 INCH PROPELLER SPACER B 7925 2 00 65 03 61 02 R SPINNER INSTALLATION PROPELLER SPINNER SHELL D 7945 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 50 183 00 71 02 O WINTERIZATION KIT INSTALLATION STOWED 0901260 142 70 71 INSTALLED ARM SHOWN BREATHER TUBE INSULATION 0901250 5 10 0 20 75 06 COWL INLET COVERS INSTALLED 0901250 1 2 0 92 69 77 COWL INLET COVERS STOWED 0901250 1 2 0 92 176 21 72 ENGINES 72 01 R ENGINE TELEDYNE CONTINENTAL MOTORS 0950000 213 78 83 95 O 200D 77 ENGINE INDICATING 77 01 R ENGINE TACHOMETER SENSOR 0918003 0 02 92 29 77 02 0 EXHAUST THERMOCOUPLE 0918506 0 04 78 64 78 EXHAUST 78 01 R EXHAUST SYSTEM 9950100 8 00 77 67 79 OIL 79 01 R OIL COOLER INSTALLATION 0950000 3 83 83 36 79 02 R OIL PRESSURE SENSOR P165 5281 0950000 0 32 80 81 79 03 R OIL TEMPERATURE SENSOR S2335 1 0950000 0 15 80 81 79 04 O OIL QUICK DRAIN INSTALLATION 09
96. IN G300 INSTRUMENT PANEL FLIGHT AND SYSTEM INSTRUMENTS Continued Behind the instrument panel are the servo units for the optional autopilot Garmin ADAHRS Air Data Attitude and Heading Reference System Unit and the Secondary Battery The ADAHRS unit is a multifunctional processing unit which takes pitot static pressures from the pitot tube on the left wing and the static source button aft of the left cowl for altitude airspeed and vertical speed information tailcone mounted magnetometer data for heading and engine data for display on the Engine Indication System EIS portion of the displays Fuel indicators are mounted in each wing root with silver float balls for visual ease The fuel placards are differentiated between level flight LVL FLT and on ground GRND The MIN TO reference mark on the GRND side indicates the 1 4 fuel requirement for take off In tank fuel tabs are equipped with indicator holes for full 34 V2 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 he tricycle type landing gear on the Model 162 features tapered spring steel main gear legs and a spring steel nose gear with elastimetric pucks for shock absorption The nose gear is free castoring and directional control is done via differenti
97. INTO ICING CONDITIONS Flight into icing conditions is prohibited and extremely dangerous While an inadvertent encounter with these conditions can be resolved using the checklist procedures the best action is to turn back or change altitude immediately to escape icing conditions Watch for signs of pitot static icing and ice accretion on the unheated pitot tube If airspeed and altimeter indications become unreliable GPS derived flight information can provide approximate values for back up GPS derived ground speed GS and GPS ALTITUDE on the MFD INFO page if installed may be used for comparison to barometric instruments GPS ALTITUDE information also replaces barometric altitude in the TERRAIN Page PROFILE window indicated by a white arrowhead when the ADAHRS is inoperative In the event of an icing encounter an unexplained loss of engine power could be caused by carburetor 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 CARBUETOR ICING AMPLIFIED EMERGENCY PROCEDURE section Maximum cabin heat should be applied by pulling the CABIN HEAT Control Knob to the full out position in an at
98. ION Unless otherwise noted the following speeds are based on a maximum weight of 1320 pounds and may be used for any lesser weight TAKEOFF Normal Climb ie EES cada RA eee DEE arene 65 75 KIAS Short Field Takeoff Flaps 10 Speed at 50 Feet 55 KIAS ENROUTE CLIMB FLAPS UP Normal Sea Level o o oooooooooo 65 75 KIAS Best Rale or Climb 255 REEDE ESE EE eee eee eee 62 KIAS Best Angle of CliMb ooooooooommoooo 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 o oooooooomoooo o 50 KIAS MAXIMUM RECOMMENDED TURBULENT AIR PENETRATION SPEED 1920 POUND Sic EE tuk deere PG PAA a d 89 KIAS 1200 POUNDS ditate p ppa aida neta 85 KIAS 1100 POUNDS sopresa AA RA 80 KIAS MAXIMUM DEMONSTRATED CROSSWIND VELOCITY Takeoff or Landing 5 3 23 23 RARA 12 KNOTS MAXIMUM RECOMMENDED WIND VELOCITY AIL Operstions x sane X s ORE ed ites oe ex ed Eas 22 KNOTS 162PHUS 02 U S 7 3 CESSNA MODEL 162 GARMIN G300 X S Z PRES 22 A KA SS y B10717 NORMAL PROCEDURES NORMAL PROCEDURES PREFLIGHT INSPECTION SECTION 7 PARAS RAS OS RR Qd 25 RR 1 REK RE SRS ees Re ES tee SE ee acs ISI NAE Hee IO RIN ee TIS SEA ORIENTAR HRS LEO Banaag asd SS ont AA
99. Internal Cabin Dimensions 2 2000000 0c eee 4 25 Center Of Gravity Moment Envelope 4 27 Center of Gravity Limits EE EE Ee ee 4 29 162PHUS 00 U S 4 1 4 2 CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE GARMIN G300 EQUIPMENT LIST INTRODUCTION This section describes the procedure for establishing the basic empty weight and moment of the airplane Sample forms are provided for reference Procedures for calculating the weight and moment for various operations are also provided For additional information regarding Weight and Balance 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 PILOT TO MAKE SURE THE AIRPLANE IS LOADED PROPERLY OPERATION OUTSIDE OF PRESCRIBED WEIGHT AND BALANCE LIMITATIONS COULD RESULT IN AN ACCIDENT AND SERIOUS OR FATAL INJURY 162PHUS 00 U S 4 3 SECTION 4 CESSNA WEIGHT AND BALANCE MODEL 162 EQUIPMENT LIST GARMIN G300 COMPREHENSIVE EQUIPMENT LIST Figure 4 1 is a comprehensive list of all Cessna equipment which is available for the Model 162 airplane equipped with Garmin G300 Integrated Cockpit System Serial
100. K verify annunciator is not shown Continued Next Page U S 162PHUS 01 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 STARTING ENGINE With External Power if installed Continued 26 Internal Power CHECK MASTER Switch ALT OFF LDG Light Switch ON NAV Light Switch ON THROTTLE Control REDUCE TO IDLE MASTER Switch ALT ON RPM Control INCREASE to approximately 1500 g AMPS CHECK verify charge shown positive 9 Q900 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 required 162PHUS 00 U S 7 17 SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 BEFORE TAKEOFF 1 PO de O ay 10 11 12 13 7 18 Parking Brake SET a Brakes Apply b PARKING BRAKE Control Knob ON pull full out Seats and Seat Belts CHECK SECURE Cabin Doors CLOSED and LOCKED Flight Controls FREE and CORRECT Flight Instruments PFD CHECK verify no red X s through indicators Engine Indicating System CHECK PARAMETERS verify no red X s through indicators Altimeter SET Fuel Quantity Indicators CHECK verify level is correct WARNING TAKEOFF IS PROHIBITED WITH LESS THAN Y TANK OF FUEL MIN GRND ES MARKING ON FUEL I
101. K 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 pilotage and magnetic compass if installed to nearest suitable landing site c Land as soon as possible Refer to LANDING WITH PARTIAL OR NO INSTRUMENTATION INFORMATION 4 Affected Display NORMAL SCREEN a Land as soon as practical Continued Next Page 6 24 U S 162PHUS 01 CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 PFD MFD DISPLAY MALFUNCTION OR FAILURE Continued PFD OR MFD DISPLAY INFORMATION NOT UPDATING 1 Pull open the following circuit breakers a ADAHRS Circuit Breaker OPEN b PFD MFD Circuit Breaker OPEN C man N Circuit Breaker OPEN overhead panel light will goo Reset close all three circuit breakers a ADAHRS Circuit Breaker CLOSE b PFD MFD Circuit Breaker CLOSE c SEC PWR Circuit Breaker CLOSE 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 soon as possible Refer to LANDING WITH PARTIAL OR NO INSTRUMENTATION INFORMATION Affected Display NORMAL SCREEN a Land as soon as practical
102. MP AND HARDWARE 0 24 160 59 27 FLIGHT CONTROLS 27 01 R DUAL CONTROLS CONTROL STICK ASSEMBLY 0961510 0 85 122 98 RUDDER AND BRAKE PEDALS 0961331 0 46 108 02 28 FUEL 28 01 R FUEL INDICATORS 28 02 O FUEL PRIMER ASSEMBLY 0901200 0 63 106 48 31 INDICATING 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 146 151 73 TIRE AND TUBE 4 PLY 5 00 X 5 BLACKWALL 5 62 149 52 EACH 32 02 R WHEEL AND TIRE ASSY 4 00 X 5 NOSE 0942000 WHEEL ASSY 8 50 86 92 TIRE AND TUBE 8 PLY 4 00 X 5 BLACKWALL 2 38 86 92 32 03 O WHEEL FAIRING AND INSTALLATION WHEEL FAIRING NOSE 0942200 2 56 87 57 WHEEL FAIRINGS MAIN EACH 0941200 3 48 151 72 33 LIGHTS 33 01 S COCKPIT LIGHT LED CL5190 0918103 012 146 00 33 02 R NAV STROBE LIGHT EACH 0928007 0 97 142 74 33 03 8 LANDING TAXI LIGHT 0928007 1 36 129 28 Figure 4 1 Sheet 2 4 6 U S 162PHUS 00 CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE GARMIN G300 EQUIPMENT LIST REF WT ARM ITEM NO EQUIPMENT LIST DESCRIPTION DRAWING LBS INS 34 NAVIGATION 34 01 R PFD DISPLAY GDU 370 DISPLAY 0918101 1 56 1121 56 34 02 O MFD DISPLAY GDU 375 DISPLAY 0918502 2 40 121 56 34 03 R ATTITUDE
103. NA KA EE EE 7 11 Before Starting Engine sssaaa a 7 13 Starting Engine With Battery aaaea 7 13 Starting Engine With External Power o o ocoo oo oo 7 15 Belore akeolt 4 S VEER DERE DASSE BEE SR DE E el 7 18 WEIR COU an EERS ta O N ES EE GR AN E 7 19 Normal Takeoff EE sep kaa wade weeds sa OA 7 19 Short Field Takeoff cia gee haa 7 19 Enroute Climb 5 8k e mem eu t osea d masa epa 7 20 ER EE OE ov van bea p he ge ew AA 7 20 DESCON m ped KERE AE EE ED EDE bb hee ee 7 20 Belote Landing rra cae gale a t e ee 7 20 CANINA PTT 7 21 Normal tanding ie BEE EE Sy Vi eer be malay laing 7 21 Short Field Landing sist EE DEE SE RR LAE GER ds 7 21 Balked Vanding ss oe AE AE RR ce ed ske NG 7 21 AitefsLandiid MEE SEER EER See 5 ad EE EE bd 7 22 Securing Airplane cos A CA 7 22 Continued Next Page 162PHUS 01 U S 7 1 SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 TABLE OF CONTENTS Continued Page AMPLIFIED NORMAL PROCEDURES 7 23 Preflight Inspection xi udis oe WER tm eee LA EED EIER ees 7 23 Before Starting Engine s o EERDER ERR PRESE SA de 7 25 Starling EnAING eie 252 hee GEOPEREER RA 7 25 Recommended Starter Duty Cycle 7 26 Leaning For Ground Operati0NS oooooooooo 7 27 FAXING oe pple un ie aha AA PAA dus ad haces ala eS 7 27 Before TaKegiT usu ats veda pene vd ete piles 3 7 30 Warm UP DE ro E aos 7 30 Magneto Check iaa i erc DE Ir
104. NCY PROCEDURES GARMIN G300 INTRODUCTION Section 6 provides checklist and amplified procedures for coping with emergencies that may occur Emergencies caused by airplane or engine malfunctions are extremely rare if proper preflight inspections and maintenance are practiced Enroute weather emergencies can be minimized or eliminated by careful flight planning and good judgment when unexpected weather is encountered However should an emergency arise the basic guidelines 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 TAKEOFF Mind Flabs UP SEER DEE rrr p 70 KIAS Wing Flaps 10 s FULL s 225 rn RR RR CR 65 KIAS OPERATING MANEUVERING SPEED 1320 POUNDS n a pman ty EE See Ee ee EG SR m DE 89 KIAS 1200 POUNDS LEER EE DO ta b ho doc dal 85 KIAS TTOD POUNDS EWE DE RE EER Xr he NA E ct 80 KIAS MAXIMUM GLIDE 0 0000 eee eee 70 KIAS PRECAUTIONARY LANDING WITH ENGINE POWER 60 KIAS LANDING WITHOUT ENGINE POWER A E eeu aee at pri ERA VASE DRESS eee GTA 70 KIAS Wing Flaps 10 FULL aia e mac daca E RD toes 65 KIAS 162PHUS 02 U S 6 5 SECTION 6 CESSNA EMERGENCY PROCEDURES
105. ND 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 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 and help prevent further scratching Do not use a canvas cover on the windshield unless freezing rain or sleet is anticipated since the cover may scratch the plastic surface Continued Next Page 18 22 U S 162PHUS 01 CESSNA SECTION 8 MODEL 162 AIRPLANE HANDLING SERVICE GARMIN G300 AND MAINTENANCE CLEANING AND CARE Continued PAINTED SURFACES The painted exterior surfaces of your new Cessna have a durable long lasting finish Generally the painted surfaces can be kept bright by washing with water and mild soap followed by a rinse with water and drying with cloths or a chamois Remove stubborn oil and grease with a cloth moistened with Stoddard solvent Take special care to make sure that the exterior graphics are not touched by the solvent For complete care of exterior graphics refer to the Maintenance Manual CAUTION HARSH OR ABRASIVE SOAPS OR DETERGENT
106. NDICATOR PRIMER Control Knob if installed IN and LOCKED MIXTURE Control RICH 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 Elevator Trim Control Switch SET FOR T O THROTTLE Control 1700 RPM once oil temperature is above 75 F and oil pressure in green band range a MAGNETOS Switch CHECK RPM drop should not exceed 150 RPM on either magneto or 50 RPM differential between magnetos b Engine Indicators CHECK c CARB HEAT Control Knob ON 1 Engine RPM CHECK verify RPM decreases 2 CARB PF CHECK verify temp increases d AMPS and VOLTS CHECK Continued Next Page U S 162PHUS 01 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 BEFORE TAKEOFF Continued 14 THROTTLE Control CHECK IDLE 900 RPM or LESS THROTTLE Control Friction Lock ADJUST COM Frequency SET GPS Flight Plan AS DESIRED XPDR SET Wing Flaps UP 10 10 recommended NAV Light Switch ON STROBE Light Switch ON PARKING BRAKE Control Knob OFF push full in Annunciators CHECK verify no annunciators are shown TAKEOFF NORMAL TAKEOFF DOO emo peo ms Wing Flaps UP 10 10 recommended CARB HEAT Control Knob OFF push full in THROTTLE Contr
107. ON MODEL 162 GARMIN G300 ELECTRICAL SYSTEM Continued Uu 2 e e a Ce To Primary Flight Display and EW Pm E Cooling Fan PFD MFDTo Multi Function Display A apa M If Installed c E eae To Air Data Attitude Heading t he peed To NAV Lights Na aral Reference System r NAV NAV i ToT T i o Transponder i FAR c XPDR 4 C O To Taxi Lights A a LPG LDG d cs To VHF Communication Lights B COM o To Wing Strobe S STROBE STROBE Lights u A Us a EE ie B Lights s TRIM AP BHIE sang If Installed SG O _ START ALT TEE e AVN l MASTER n To PFD a a To ADAHRS T To Interior Lights SEC E PWR R Ammeter OFF OFF OFF Starter Q Motor QO 12V POWER OUTLET Ignition Switch Power Isolation Module NAG n Secondary Battery External Power External Power Switch Control Relay If Installed Switch Control Power 14VDC Ground External Power Receptacle KG If Installed Main Battery 097471001 Figure 2 4 2 20 U S 162PHUS 01 CESSNA SECTION 2 MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION GARMIN G300 ELECTRICAL SYSTEM Continued MASTER SWITCH The MASTER switch is a rocker type switch with
108. OVED S6 2 U S 162PHUS S6 00 CESSNA SECTION 10 SUPPLEMENTS MODEL 162 SUPPLEMENT 6 GARMIN G300 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that are currently active Number Title Airplane Serial Revision Incorporated Effectivity Incorporated in Airplane FAA APPROVED 162PHUS S6 00 U S S6 3 SECTION 10 SUPPLEMENTS CESSNA SUPPLEMENT 6 MODEL 162 GARMIN G300 GARMIN GTX 327 TRANSPONDER GENERAL The Garmin GTX 327 Transponder is capable of both Mode A and Mode C operations In addition to altitude and location reporting functions the GTX 327 also provides a pressure altitude display with trend indications a flight time display a count up timer and a count down timer OPERATING LIMITATIONS There is no change to the airplane operating limitations when the Garmin GTX 327 Transponder is installed EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when the Garmin GTX 327 Transponder is installed Refer to current FAR AIM procedures for emergency codes and transponder inoperative situations FAA APPROVED S6 4 U S 162PHUS S6 00 CESSNA SECTION 10 SUPPLEMENTS MODEL 162 SUPPLEMENT 6 GARMIN G300 NORMAL PROCEDURES GARMIN GTX 327 TRANSPONDER B14723 11 12 1 2 9 4 5 6 FLIGHT TIME 81 23 20
109. PHUS 01 U S 8 9 SECTION 8 CESSNA AIRPLANE HANDLING SERVICE MODEL 162 AND MAINTENANCE GARMIN G300 GROUND HANDLING TOWING The airplane is most easily and safely maneuvered by hand with a tow bar attached to the nosewheel When towing with a vehicle do not exceed the nose gear turning angle of 57 5 either side of center or damage to the nose landing gear will result CAUTION 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 HORIZONTAL STABILIZER SURFACES WHEN PUSHING ON THE TAILCONE ALWAYS APPLY PRESSURE AT A FUSELAGE BULKHEAD TO AVOID BUCKLING THE SKIN Continued Next Page 8 10 U S 162PHUS 01 CESSNA SECTION 8 MODEL 162 AIRPLANE HANDLING SERVICE GARMIN G300 AND MAINTENANCE GROUND HANDLING Continued PARKING When parking the airplane head into the wind and set the parking brake Failure to park into the wind may allow wing flaps to blow down randomly If forced to park with the tail into the wind place the flaps FULL down and secure the airplane per the TIEDOWN procedure Do not set the parking brake during cold weather when accumulated moisture may freeze the b
110. POWER SUPPLY SYSTEM MALFUNCTIONS Continued VOLTS INDICATION ABOVE GREEN BAND RANGE OR VOLTS MORE THAN 15 1 MASTER Switch ALT Only OFF 2 Electrical 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 minutes 6 22 U S 162PHUS 00 CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 AIR DATA ATTITUDE AND HEADING REFERENCE SYSTEM ADAHRS FAILURE RED X PFD OR MFD INDICATORS AIRSPEED ALTITUDE ATTITUDE HORIZONTAL SITUTATION INDICATOR HSI OR ENGINE INDICATING SYSTEM EIS ADAHRS Circuit Breaker CHECK IN a If open reset close circuit breaker If circuit breaker opens again do not reset b If closed pull open ADAHRS Circuit Breaker and pull open SEC PWR Circuit Breaker overhead Panel Light will go off then reset close both circuit breakers 2 Affected Indicator other than EIS RED X STILL DISPLAYED a Reference GS ground speed in conjunction with GPS derived wind information to determine an approximate airspeed b Select COMPASS ARC from G300 MAP SET UP for approximate GPS derived heading information o
111. 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 the problem does not clear up in several minutes determine if a richer mixture setting will produce smoother operation If not proceed to the nearest airport for repairs using the BOTH position of the MAGNETOS switch unless extreme roughness makes the use of a single MAGNETO position necessary MAGNETO MALFUNCTION Sudden engine roughness or misfiring is usually a sign of a magneto problem Changing the MAGNETOS switch from BOTH to the L and R switch positions will identify which magneto is malfunctioning Select different power settings and enrichen the mixture to determine if continued operation on BOTH magnetos is possible If not change to the good magneto and continue to the nearest airport for repairs Continued Next Page 6 36 U S 162PHUS 00 CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 ROUGH ENGINE OPERATION OR LOSS OF POWER Continued IDLE POWER ENGINE ROUGHNESS An excessively rich idle fuel flow may cause low speed engine roughness during flight During most in flight low engine speeds power off stalls approach to landing etc the mixture control is normally in the full rich position However to improve engine roughness during low engine speeds while in flight you should rotate
112. RD 20 C ABOVE Altitude l RPM STANDARD TEMP TEMPERATURE STANDARD TEMP us E 6 6 2000 ES E 75 58 e E 46 E 38 4000 69 55 6000 8000 10 000 2650 2450 2250 12 000 2650 2450 2250 NOTE Maximum cruise power using recommended lean mixture is 75 MCP Values above 75 MCP are shown for interpolation purposes only Operations above 75 MCP must use full rich mixture e Cruise speeds are shown for an airplane equipped without speed fairings With speed fairings increase speeds shown by 2 knots Figure 5 7 5 16 U S 162PHUS 01 SECTION 5 PERFORMANCE CESSNA MODEL 162 GARMIN G300 TEMPERATURE CONVERSION CHART EER B3093 y t i n MEES EE N a UA a HH i H 7 4 f ion uy Y 4 AE EEE A f a 100 yeuuoJueJ saaibag Celsius Degrees Figure 5 8 5 17 U S 162PHUS 00 SECTION 5 CESSNA
113. RKINGS KIAS VALUE OR MARKING RANGE SIGNIFICANCE Red Band Low airspeed warning White Band Full Flap Operating Range Lower limit is maximum weight Vso in landing configuration Upper limit is maximum speed permissible with flaps extended J Green Band Normal Operating Range Lower limit is maximum weight Vs at most forward C G with flaps retracted Upper limit is maximum structural cruising speed Yellow 124 148 Operations must be conducted with caution Band and only in smooth air Red Line gt 149 Maximum speed for all operations Flaps 25 85 Maximum Flaps 25 Operation Tick Mark Flaps 10 100 Maximum Flaps 10 Operation Tick Mark Vx 57 Best Angle of Climb Air Speed Tick Mark Vy 62 Best Rate of Climb Air Speed Tick Mark Figure 9 1 162PHUS 01 U S 9 3 SECTION 9 CESSNA PLACARDS AND MARKINGS MODEL 162 GARMIN G300 POWERPLANT AND ELECTRICAL INSTRUMENT MARKINGS Powerplant and electrical instrument markings and their color code significance are shown in Figure 9 3 Operation with indications in the red range is prohibited Avoid operating with indicators in the yellow range POWERPLANT AND ELECTRICAL INSTRUMENT MARKINGS INSTRUMENT RED LOWER WARNING YELLOW LOWER CAUTION GREEN NORMAL OPERATING RANGE 2000 to 2750 RPM YELLOW UPPER CAUTION RED UPPER WARNING 2750 to 3500 RPM 0 to 75 F 75 to 220 F 220 to 24
114. S WHICH CAUSE CORROSION OR SCRATCHES SHOULD NEVER BE USED ON THE PAINTED ALUMINUM STRUCTURE To seal any minor surface chips or scratches and protect against corrosion the airplane should be waxed regularly with a good automotive wax 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 and on the cowl nose cap and propeller spinner will help reduce the abrasion encountered in these areas Reapplication of wax will generally be necessary after cleaning with soap solution or after chemical deicing operations When the airplane is parked outside in cold climates and it is necessary to remove ice before flight care should be taken to protect the painted surfaces during ice removal with chemical liquids Isopropyl alcohol will satisfactorily remove ice accumulations without damaging the paint However keep the isopropyl alcohol away from the windshield and cabin windows since it will attack the plastic and may cause it to craze Continued Next Page p162PHUS 01 U S 8 23 SECTION 8 CESSNA AIRPLANE HANDLING SERVICE MODEL 162 AND MAINTENANCE GARMIN G300 CLEANING AND CARE Continued PROPELLER CARE
115. SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 TAXIING Continued TAXIING DIAGRAM B10718 a d Use Up Aileron on Left Wing and A E Right Wing and 8 Neutral Elevator z Neutral Elevator 4 2 em EJES DE ma Use Down Aileron Use Down Aileron d on Left Wing and on Right Wing and Down Elevator Down Elevator e VR l Bg LEGEND WIND DIRECTION P 091011002 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 U S 7 29 SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 BEFORE TAKEOFF WARM UP If the engine idles with the throttle against the idle stop approximately 700 to 800 RPM and accelerates smoothly the engine is warm enough for takeoff Since the engine is closely cowled for efficient in flight engine cooling the airplane should be pointed into the wind to avoid overheating during prolonged engine operation on the ground Refer to Leaning For Ground Operations procedures to prevent spark plug fouling that can occur from long periods of idling and prolonged ground operations MAGNETO CHECK CAUTION MAKE SURE ENGINE OIL TEMPERATURE IS ABOVE 75 F AND OIL PRESSURE IS WITHIN THE GREEN BAND RANGE PRIOR TO PREFORMING A MAGNETO CHE
116. ST ISSUE OF TEM SPEC MHS 24 CESSNA DEALERS HAVE LIST OF APPROVED OILS Continued Next Page 2 18 U S 162PHUS 01 CESSNA SECTION 3 MODEL 162 OPERATING LIMITATIONS GARMIN G300 PLACARDS Continued 12 On firewall adjacent to battery box and second placard on external power receptacle door if external power receptacle option is installed B14616 CAUTION 12 VOLTS D C THIS AIRCRAFT IS EQUIPPED WITH ALTERNATOR AND NEGATIVE GROUND SYSTEM OBSERVE PROPER POLARITY REVERSE POLARITY WILL DAMAGE ELECTRICAL COMPONENTS 13 Located on both left and right fuel sight tubes B14537 E LVL FLT 3 4 G R N 1 2 D 1 2 1 4 MIN E TO O ka C 091471028 162PHUS 01 U S 3 19 3 20 E CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE GARMIN G300 EQUIPMENT LIST WEIGHT AND BALANCE EQUIPMENT LIST TABLE OF CONTENTS Page IntrOgGUc DON saaan TA LAAN DER EDE E SE QUI aoe ES 4 3 Comprehensive Equipment List ooccccccon 4 4 Airplane Weighing Procedures 0000 eee ee 4 8 Airplane Weighing Form 00 eee eee eee ees 4 9 Sample Weight and Balance Record 4 13 Weight And Balance ue ed eee ties ELI ETE S 4 15 Baggage MMedOWhic ix Kato Th EE Beate av ES 4 16 Sample Loading Problem 000 SE eee eee 4 17 Loading Graph case stor ete ARA AA AA ene eed 4 21 Loading Arrangements 000 cee eee eee ees 4 23
117. Sample Problem 2335 3 9 d aint OR oo Re o 5 4 diio EE a e a AE DE EE I 5 5 Qul P OR IE wine HEET OIE EO AA 5 6 F el Required Es oda NEE nC 9E dn EC Ed RA 5 7 LINO ost Oe as Ud 5 9 Demonstrated Operating Temperature 5 9 Airspeed Calibration o oooooooononorooooo o 5 10 Stall Speeds At 1320 Pounds 0 0 cece ees 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 22221 yep REALE NEP IRA 5 16 Temperature Conversion Chart 0 0000 cece eee 5 17 Crosswind Component 000 cece eet eee eee 5 18 162PHUS 00 U S 5 1 5 2 CESSNA SECTION 5 MODEL 162 PERFORMANCE GARMIN G300 INTRODUCTION Performance data charts on the following pages are presented so that you may know what to expect from the airplane under various conditions and to facilitate the planning of flights in detail with reasonable accuracy The data in the charts has been computed from actual flight tests with the airplane and engine in good condition and using average piloting techniques Fuel flow data for cruise is based on the recommended lean mixture setting at all altitudes Some indeterminate variables such as mixture leaning technique fuel metering characteristics engine and
118. Seas INTO THE WIND Light Winds Heavy Swells PARALLEL TO SWELLS ELT ACTIVATE Doors UNLATCH just prior to touchdown N 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 prohibited 9 Touchdown LEVEL ATTITUDE AT ESTABLISHED 300 FT MIN DESCENT 10 Face CUSHION AT TOUCHDOWN with folded coat 11 Airplane EVACUATE THROUGH CABIN DOORS 162PHUS 00 U S 6 11 SECTION 6 CESSNA EMERGENCY PROCEDURES MODEL 162 GARMIN G300 FIRES DURING START ON GROUND 1 MAGNETOS Switch START continue cranking to start the engine IF ENGINE STARTS 2 3 Power 1800 RPM for a few minutes Engine SHUTDOWN inspect for damage IF ENGINE FAILS TO START c EO D UU e CU P9 THROTTLE Control FULL push full in MIXTURE Control IDLE CUTOFF pull full out MAGNETOS Switch START continue cranking FUEL SHUTOFF Valve OFF pull full out MAGNETOS Switch OFF MASTER Switch ALT and BAT OFF Engine SECURE Parking Brake RELEASE Fire Extinguisher OBTAIN have ground attendants obtain if not installed Airplane EVACUATE Fire EXTINGUISH using fire extinguisher wool blanket or dirt Fire Damage INSPECT repair or replace damaged components and or wiring before conducting another flight ENGINE FIRE
119. TATIONS TABLE OF CONTENTS Page Ii OALUEUOI aa a od E CER 3 3 Airspeed Limitations 0 0 EE cece eee eee eee 3 4 Airspeed Indicator Markings 000 eee eee eee eee 3 5 Powerplant Limitations 4x e ede ee E fo ea x ee e S es 3 6 Powerplant and Electrical Instrument Markings 3 7 Weight LIM INS azo sa ER NG Spek SEER OL RT NA Re ee EE ese Re 3 8 Maximum Weight in Baggage Compartment 3 8 Center of Gravity Limits 2 0 0 ee ees 3 8 Servico Gelllhig 21927993 AA AA 3 8 ManeuverLimits pss DEE AA 3 9 Lead Faclefs AR AY 3 9 Flight Load Factor LiMitS o o oooooooooooo o 3 9 Kinds of Operations Limits momo 3 10 Kinds of Operations Equipment List 3 11 Fiel Limitations DE awa ioe Kagat aa kaa See e pe o 3 14 Flaps Limitations sass ko eene RE ds 3 14 System Limitations ees uto oco rada da NING 3 15 12V Power OUO vixero tata eid 0n Dos e e ol della ee 3 15 5300 Limitations ER RA 3 15 Placards iss EER REG SAD EED ARE ORE e dara RRS ater ie 3 16 162PHUS 01 U S 3 1 3 2 CESSNA SECTION 3 MODEL 162 OPERATING LIMITATIONS GARMIN G300 INTRODUCTION Section 3 includes operating limitations instrument markings and basic placards necessary for the safe operation of the airplane its engine standard systems and standard equipment The limitations included in this section and in Section 10 have been approved Observance of these operating l
120. TEM Continued FUEL INDICATING SYSTEM Fuel quantity is measured by two sight gages located in each wing root just forward and above the cabin door opening The sight gages are vented and include orifice fittings at the top and bottom of the sight tube The fuel levels are aided with floating aluminum 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 forward scale in level ground attitude which represents 3 gallons per side or 6 gallons total 1 4 tanks FUEL QUANTITY SIGHT GAGE B14537 eo LVL FLT 3 4 G R N 12 D 1 2 1 4 MIN E TO O Sa E 091471028 Figure 2 2 Continued Next Page 12 16 U S 162PHUS 01 CESSNA SECTION 2 MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION GARMIN G300 FUEL SYSTEM Continued FUEL INDICATING SYSTEM Continued An empty tank is shown on the fuel quantity indicator as a red line on the aft Level Flight scale along with the E indication When an indicator shows an empty tank approximately 0 73 gallons of unusable fuel remain in the tank The fuel gage shows the fuel available in the tank up to the limit
121. The white pointer indicates actual EGT temperature Red digits are shown for values less than O and more than 2000 F A red X is displayed when the instrument is invalid or out of the data range Continued Next Page 162PHUS 01 U S 2 11 SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 162 GARMIN G300 ENGINE Continued ENGINE INSTRUMENTS Continued CARBURETOR TEMPERATURE CARB F Carburetor temperature is provided as a reference to determine the potential for carburetor ice formation The CARB F indication is provided on vertical tape and in digital form on the right side of the EIS display atop the PFD and on the G300 ENGINE page The tape display range is from 20 to 80 F and the digital indication range is from 40 F to 100 F A yellow caution range is depicted from 5 F to 40 F A red X is displayed when the instrument is invalid or out of the 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 range of use It is recommended that cruising be accomplished at 75 power as much as practicable until a total of 50 hours has accumulated or oil consumption has stabilized
122. VITY MOMENT ENVELOPE U S B10726 1350 1320 1300 Maximum Takeoff Weight 1320 Pounds 1250 1200 1150 1100 1050 1000 Loaded Airplane Weight Pounds 950 900 850 800 105 115 125 135 145 155 165 175 185 Loaded Airplane Moment 1000 Pounds Inches Figure 4 8 Sheet 1 of 2 162PHUS 00 U S 4 27 SECTION 4 WEIGHT AND BALANCE EQUIPMENT LIST CENTER OF GRAVITY MOMENT ENVELOPE METRIC UNITS B13960 1210 CESSNA MODEL 162 GARMIN G300 Loaded Airplane Moment 1000 Kilograms Millimeters 1610 1310 141 1510 0 1710 1810 ue 2010 2110 620 Maxi mum Ta keoff Wei ght 598 74 Kilograms 600 580 560 540 C1 Nh O Kilograms 500 IN 00 O e Weigh E 460 3 N A o Loaded Airp IR NI o 400 380 4 28 U S Figure 4 8 Sheet 2 360 162PHUS 00 CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE GARMIN G300 EQUIPMENT LIST CENTER OF GRAVITY LIMITS U S UNITS B13958 Loaded Airplane Weight Pounds 1
123. X AUDIO INPUT entertainment audio input and Portable Electronic Device PED use is permitted only during the enroute phase of flight e Disconnect the cable from the AUX AUDIO INPUT jack when not in use e Use caution with audio cables in the cabin to avoid entangling occupants or cabin furnishings and to prevent damage to cables The PM3000 Pilot s Guide amp User Manual publication no 202 193 0001 or other PS Engineering publications can be obtained by contacting PS Engineering Inc 9800 Martel Road Lenoir City TN 37772 865 988 9800 or visit the PS Engineering website www ps engineering com for current updates and supplemental information S3 6 U S 162PHUS S3 00 CESSNA SECTION 10 SUPPLEMENTS MODEL 162 SUPPLEMENT 3 GARMIN G300 GENERAL Continued PS ENGINEERING PM3000 INTERCOM SYSTEM CONTROL PANEL B14689 1 9 2 4 N e Volume Push Squelch 0918G 1028 1 Power Volume Control Knob a Power ON OFF Pressing the VOLUME control knob will power on the unit ON and OFF b Volume Turn the VOLUME control knob clockwise to increase the volume level and counterclockwise to decrease the volume level The VOLUME control knob adjusts the volume level of the intercom and audio input only and does not affect the volume level of the SL40 Comm radio This feature allows the airplane radio and intercom volume to be balanced independently NOTE The PM3000 volume level affects the audio level for both t
124. Y SYSTEM MALFUNCTIONS LOSS OF ALL ELECTRICAL POWER EXCEPT PFD 1 MAIN CB RESET Switch PRESS MOMENTARILY IF ELECTRICAL POWER RESUMES NORMAL OPERATION 2 Continue flight and land as soon as practical IF ELECTRICAL POWER REMAINS INOPERATIVE EXCEPT PFD 2 Land 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 electrical power and PFD Refer to ABNORMAL LANDINGS LANDING WITH PARTIAL OR NO FLIGHT INSTRUMENT INFORMATION Continued Next Page 162PHUS 00 U S 6 19 SECTION 6 CESSNA EMERGENCY PROCEDURES MODEL 162 GARMIN G300 ELECTRICAL POWER SUPPLY SYSTEM MALFUNCTIONS Continued LOW VOLTS ANNUNCIATOR COMES ON OR VOLTS INDICATION BELOW GREEN BAND RANGE OR VOLTS LESS THAN 12 5 NOTE Volts indication below the green band range or less than 12 5 volts may occur during low RPM conditions with an electrical load on the system such as during a low RPM taxi Under these conditions the volts indication will increase into the green band range 12 5 15 0 volts at higher RPM The master switch need not be recycled since an overvoltage condition has not occurred to deactivate the
125. activating the mute control circuit Pressing the SQUELCH control knob once will activate this mode In this mode it is possible to have the music remain at a constant level regardless of any ICS or radio traffic When music is at a constant level both music and ICS intercom and radio communications will be heard at the same time Press the MUTE control knob again will restore the music auto muting function NOTE It is recommended that the MUTE mode uninterrupted music not be active when radio communications are being conducted or monitored with any air traffic control facility ground facility or other airplane 162PHUS S3 00 U S S3 9 SECTION 10 SUPPLEMENTS CESSNA SUPPLEMENT 3 MODEL 162 GARMIN G300 OPERATING LIMITATIONS Headsets are required for audio communications In the event of pilot and copilot simultaneously pressing the PTT the copilot will override If desired the pilot may regain priority by switching the intercom unit off EMERGENCY PROCEDURES If power is disrupted to the PM3000 intercom for any reason an internal relay will connect the pilot s headset directly to the intercom function of the SL40 Comm radio allowing uninterrupted radio communications to the pilot s headset only If there is a power failure of the PM3000 ICS or the power switch is selected to the off position the copilot will not hear radio communications If flight instruction is being given the instructor in the copilot s seat may desi
126. 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 the adjustments are made carefully and accurately Adjusting the mixture quickly is not recommended Continued Next Page 62PHUS 01 U S 7 37 SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 CRUISE Continued FUEL SAVINGS PROCEDURES FOR FLIGHT TRAINING OPERATIONS For best fuel economy during flight training operations the following procedures are recommended 1 After engine start and for all ground operations set the throttle to 1200 RPM and lean the mixture for maximum RPM After leaning set the throttle to the appropriate RPM for ground operations Leave the mixture at this setting until beginning the BEFORE TAKEOFF checklist If TAKEOFF is delayed after completing the BEFORE TAKEOFF checklist lean the mixture again as described above until ready to perform the TAKEOFF checklist 2 Lean the mixture for maximum RPM during 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 e When cruising or maneuvering at 75 power or less the mixture may be further leaned to best power cruis
127. age The numerical value for the EGT is located above the vertical scale Use the mixture control vernier adjustment to lean 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 of the engine at fuel flow rates mixture settings less than necessary to reach peak EGT Refer to Section 5 Figure 5 7 Cruise Performance for specific power settings and lean for best power cruise Continuous operation at mixture settings lean of peak EGT is prohibited Continued Next Page 17 36 U S 162PHUS 01 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 CRUISE Continued LEANING WITH EXHAUST GAS TEMPERATURE EGT INDICATOR if installed Continued CAUTION EXCESSIVE LEANING WILL INCREASE ENGINE TEMPERATURES AND MAY DAMAGE ENGINE WHEN INCREASING POWER ENRICHEN MIXTURE THEN ADVANCE THE THROTTLE TO INCREASE RPM WHEN REDUCING POWER RETARD THROTTLE THEN ADJUST THE MIXTURE CONTROL NOTE e Any change in altitude or power setting will require a change in the recommended lean mixture setting and a recheck of the EGT setting e The EGT indicator takes several seconds
128. 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 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 Continued Next Page 162PHUS 00 U S 7 7 SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 PREFLIGHT INSPECTION Continued LEFT WING Leading Edge N PAPAS Fuel Tank Vent Opening CHECK blockage Wing Tiedown DISCONNECT check security and condition Pitot Tube Cover REMOVE check for pitot blockage ee Light CHECK condition operation and cleanliness of cover Strobe Nav Light CHECK condition operation and cleanliness of cover LEFT WING Trailing Edge 1 2 3 Aileron CHECK freedom of movement and security NOTE Check for proper aileron movement by 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 Flap DEFLECT and CHECK flap aileron cables up spring tension and general condition Com Antenna and OAT Temp Probe CHECK se
129. al braking This permits very tight turning and maneuvering in confined spaces Full rudder deflection can assist directional control when taxiing Disc brakes located on the main gear wheels are hydraulically actuated by master cylinders on each rudder pedal A parking brake valve locks brake pressure to the disc calipers when the parking brake handle on the lower instrument is pulled with the brake pedals depressed The hydraulic brake system is connected in series running from the firewall mounted reservoir to the copilot s master cylinder then to the pilot s master cylinder then to the brake caliper through the parking brake valve 2 6 U S 162PHUS 01 CESSNA SECTION 2 MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION GARMIN G300 MISCELLANEOUS CABIN FEATURES The cabin is accessed through gas cylinder assisted doors hinged at the top In this manner the doors swing up and out of the way for ease of entry and loading of cargo Proper operation and care of the cabin doors will ensure years of flying enjoyment CAUTION THE CABIN DOORS SHOULD NOT BE SLAMMED THE DOORS DO NOT USE A PRE CATCH MECHANISM AND SHOULD NOT BE SLAMMED CLOSED AS THIS WILL ONLY ACCELERATE WEAR ON THE DOOR ASSEMBLY Doors should be latched from inside by pulling the door closed and while holding the door closed articulating the door latch handle as indicated by the placard Externally the door latch handle is operated through a vertical arc as indicated by the pla
130. 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 START ALT Circuit Breaker CHECK IN if open reset close circuit breaker If circuit breaker opens again do not reset MASTER Switch ALT Only OFF MASTER Switch ALT Only ON MAIN CB RESET Switch PRESS MOMENTARILY VOLTS CHECK 13 5 Volts minimum AMPS CHECK CHARGING positive AVN MASTER Switch ON only if VOLTS are 12 5 and AMPS are charging OO NO 6 20 U S 162PHUS 01 CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 ELECTRICAL POWER SUPPLY SYSTEM MALFUNCTIONS Continued IF VOLTS INDICATION REMAINS BELOW GREEN BAND RANGE OR LESS THAN 12 5 VOLTS 9 MASTER Switch ALT Only OFF 10 Electrical Load REDUCE as follows LDG Light Switch OFF use as required for landing NAV Light Switch OFF STROBE Light Switch OFF AVN MASTER Switch OFF ooopn 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 for 30 minutes Continued Next Page 162PHUS 00 U S 6 21 SECTION 6 CESSNA EMERGENCY PROCEDURES MODEL 162 GARMIN G300 ELECTRICAL
131. alues are for a standard temperature and are sufficiently accurate for most flight planning purposes However a further correction for the effect of temperature may be made as noted 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 16 C 10 C With this factor included the fuel estimate would be calculated as follows X 10 16 Increase Fuel to climb standard temperature 0 9 Gallons Increase due to non standard temperature 0 9 X 16 0 1 Gallons Corrected fuel to climb 1 0 Gallons Using a similar procedure for the distance to climb results in 7 nautical miles The resultant cruise distance is Total distance 260 Nautical Miles Climb distance 7 Nautical Miles Cruise distance 253 Nautical Miles Continued Next Page 162PHUS 01 U S 5 7 SECTION 5 CESSNA PERFORMANCE MODEL 162 GARMIN G300 SAMPLE PROBLEM Continued FUEL REQUIRED Continued With an expected 10 knot head wind the ground speed for cruise is predicted to be 108 Knots 10 Knots 98 Knots Therefore the time required for the cruise portion of the trip is 253 Nautical Miles 2 6 Hours 98 Knots The fuel required for cruise is 2 6 hours 6 0 gallons hour 15 6 Gallons A 30 minute reserve requires ok 6 0
132. and flight data update rates may require extended warm up The Garmin G300 EIS engine information is recommended for engine start due to possibility of engine damage resulting from inability to monitor engine upon start Takeoff is not recommended until displays are clearly legible and information updates as indicated by heading change during taxi RPM changes with throttle etc are shown in real time without hesitation The Garmin G300 display warm up is best accomplished by placing the airplane in a warm hangar and leaving the cabin doors open If a hangar is not available attach External Power if installed and set the MASTER Switch BAT and AVN MASTER Switch to the ON position Allow display units to warm internally until legible and display controls softkeys and knob function normally when operated Continued Next Page 7 42 U S 162PHUS 00 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 COLD WEATHER OPERATIONS Continued NOTE If external power is not available do not attempt the self warming procedure The battery will likely become depleted below the minimum voltage necessary for engine start External warm air preheat may be applied to the cabin area Use caution as excessively hot preheated air may damage interior or instrumentation Due to fuel lines routed through cabin area gas fired or exposed flame heaters should not be used to warm the cabin area STARTING When air temperatures are below 20
133. annot disarm or disable the ELT transmitter from the cockpit you can only deactivate the ELT after it has been activated The ELT can be energized by a lightning strike or hard landing If the RED light within the remote switch panel is illuminated and the aural warning is heard the ELT is energized Check for the emergency signal on a COM radio set to 121 5 MHz To stop the transmissions press the RESET button on the remote switch panel to de energize the ELT Tell the nearest Air Traffic Control facility about the accidental transmissions as soon as possible to hold search and rescue work to a minimum PERFORMANCE There is no change to the airplane performance when the Ameri King AK 450 ELT is installed S1 8 U S 162PHUS S1 00 MAMI EES Pilots Operating Handbook And Flight Training Supplement CESSNA MODEL 162 Serials 16200001 and On SUPPLEMENT 2 AMERI KING AK 451 EMERGENCY LOCATOR TRANSMITTER ELT SERIAL NO REGISTRATION NO This supplement must be inserted into Section 10 of the Pilots Operating Handbook and Airplane Flight Manual when the Ameri King AK 451 Emergency Locator Transmitter ELT is installed D Member of GAMA COPYRIGHT 2009 19 NOVEMBER 2009 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 162PHUS S2 00 U S S2 1 SECTION 10 SUPPLEMENTS CESSNA SUPPLEMENT 2 MODEL 162 GARMIN G300 SUPPLEMENT 2 AMERI KING AK 451 EMERGENCY LOCATOR TRANSMITTER ELT Use the Log of Eff
134. arburetor 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 priming should be required A cold engine with moderately warm room temperature ambient air will require 1 or 2 strokes of the throttle or primer A cold engine with cold ambient air temperatures above freezing will require up to 3 or 4 strokes of throttle or primer A cold engine should have the throttle open approximately 4 inch for start In extremely cold temperatures it may be necessary to continue priming while cranking the engine If the engine is under primed most likely in cold weather with a cold engine it will not fire at all and additional priming will be necessary As soon as the cylinders begin to fire open the throttle slightly to keep it running Continued Next Page 162PHUS 01 U S 7 25 SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 STARTING ENGINE Continued Weak intermittent firing followed by puffs of black smoke from the exhaust stack indicates over priming or flooding Excess fuel can be cleared from the combustion chambers by the following procedure set parking brake and hold brakes set the mixture control full lean idle cutoff and the place throttle control to full op
135. as 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 Dispose of the sampled fuel so that it does not cause a nuisance hazard or damage to the environment Continued Next Page 162PHUS 00 U S 7 11 SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 PREFLIGHT INSPECTION Continued NOSE Continued WARNING 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 Fuselage Fuel Sump Quick Drain Valve bottom center rear of engine cowling DRAIN 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 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 Dispose of the sampled fuel so that it does not cause a nuisance hazard or
136. at full throttle with carburetor heat off and mixture leaned to maximum RPM is 2375 2475 RPM For allowable variations in static RPM at non standard temperatures refer to the 162 Maintenance Manual Maximum Oil Temperature o o oo o 240 F 116 C Oil Pressure MINIMUM SS a 10 PSI Oil Pressure Maximum 0000 cc eee eens 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 Ashless Dispersant Oil Oil must comply with the latest revision and or supplement for Teledyne Continental Motors TCM Service Information Letter SIL99 2B or later revision must be used Propeller Manufacturer McCauley Propeller Systems Propeller Model Number 1A162 TCD6754 Propeller Diameter IGI oed 9o oen EE OON 67 INCHES 1 70 m MINIMUM ee RETE EN AA AA 66 INCHES 1 68 m 3 6 U S 162PHUS 01 CESSNA SECTION 3 MODEL 162 OPERATING LIMITATIONS GARMIN G300 POWERPLANT AND ELECTRICAL INSTRUMENT MARKINGS Powerplant and electrical instrument markings and their color code significance are shown in Figure 3 3 Operation with indications in the red range is prohibited Avoid operating with indicators in the
137. ation Grade Non Dispersant Mineral Oil and continue to use until a total of 50 hours has accumulated or oil consumption has stabilized SAE J1899 Aviation Grade Ashless 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 versus viscosity ranges SAE J1966 SAE J1899 Non Dispersant Ashless Dispersant Oil Mineral Oil SAE Grade Temperature SAE Grade Above 4 C 40 F 50 50 15W 50 20W 50 or 25W 60 Below 4 C 40 F 30 30 15W 50 20W 50 or 25W 60 All Temperatures M20W 50 15W 50 20W 50 or 25W 60 NOTE When operating temperatures overlap use the lighter grade of oil Continued Next Page 162PHUS 00 U S 8 15 SECTION 8 CESSNA AIRPLANE HANDLING SERVICE MODEL 162 AND MAINTENANCE GARMIN G300 OIL Continued CAPACITY OF ENGINE SUMP The engine has a total capacity of 5 5 U S quarts with the oil filter accounting for approximately 0 33 U S quarts of that total The engine must not be operated on less than 3 5 U S quarts as measured by the dipstick For extended flights the engine should be filled to capacity OIL AND OIL FILTER CHANGE After the first 25 hours o
138. aximum 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 e The fuel filler assembly is equipped with indicator tabs for 3 4 1 2 and 1 4 fuel quantities e Maximum full capacity is indicated when fuel reaches the upper hole of the indicator tab This fuel level allows for proper thermal expansion Filling the fuel tank above the upper hole eliminates expansion space resulting in fuel venting overboard through the fuel vent Continued Next Page 1 6 US 162PHUS 00 CESSNA SECTION 1 MODEL 162 GENERAL GARMIN G300 DESCRIPTIVE DATA Continued OIL OIL SPECIFICATION SAE J1966 Aviation Grade Non Dispersant Mineral Oil Used when the airplane was delivered from the factory and should be used to replenish the supply during the first 25 hours This oil should be drained and the filter changed after the first 25 hours of operation Refill the engine with SAE J1966 Aviation Grade Non Dispersant Mineral Oil and continue to use until a total of 50 hours has accumulated or oil consumption has stabilized SAE J1899 Aviation Grade Ashless 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 Multiviscosi
139. card 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 installed separating the baggage area from the aft tailcone The net is easily removed for maintenance access but it must be installed for flight to prevent any loose objects or baggage from migrating into the tailcone area causing control and or center of gravity issues Fire Extinguisher is installed for easy reach behind the cabin seats in the baggage area Extinguisher charge should be checked as part of each preflight inspection 162PHUS 01 U S 2 7 SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 162 GARMIN G300 ENGINE The airplane is powered by a normally aspirated direct drive air cooled horizontally opposed carbureted four cylinder engine with a wet sump lubrication system The engine is a Teledyne Continental O 200 D rated at 100 horsepower at 2750 RPM Major accessories include a starter gear driven alternator dual magnetos and a full flow oil filter mounted on the rear of the engine accessory case ENGINE CONTROLS Engine power is set using the throttle control The throttle control is a smooth black knob located at the center of the instrument panel The throttle control is configured so that the throttle is open in the forward position and closed i
140. ce Stations 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 e FACTORY APPROVED SERVICE EQUIPMENT to provide you efficient and accurate workmanship e A STOCK OF GENUINE CESSNA SERVICE PARTS are available when you need them THE LATEST AUTHORITATIVE INFORMATION FOR SERVICING CESSNA AIRPLANES Cessna Service Stations have all of the current Maintenance Manuals lllustrated Parts Catalogs and various other support publications produced by Cessna Aircraft Company A Cessna Service Station locator is available at www cessnasupport com We urge all Cessna owners operators to utilize the benefits available within the Cessna Organization 162PHUS 01 U S iii INTRODUCTION CESSNA MODEL 162 GARMIN G300 PERFORMANCE SPECIFICATIONS SPEED Maximum at Sea Level 118 KNOTS 218 5 km hr Cruise 69 Power at 6000 Feet 109 KNOTS 201 9 km hr CRUISE Recommended lean mixture with fuel allowance for engine start taxi takeoff climb and 30 minutes reserve RANGE 69 Power at 6000 Feet Range 360 NM 24 Gallons Usable Fuel Time
141. cedure 11 Clock 0 0 12 Magnetic Compass if installed 0 0 ENGINE INDICATING 1 Tachometer RPM 2 Carburetor Temperature Indicator 0 0 CARB F if installed 3 Oil Pressure Indicator 1 1 4 Oil Temperature Indicator 1 1 5 Exhaust Gas Temperature EGT 0 0 Indicator if installed ENGINE OIL 1 Engine Crankcase Dipstick 4 4 162PHUS 01 U S 3 13 SECTION 3 CESSNA OPERATING LIMITATIONS MODEL 162 GARMIN G300 FUEL LIMITATIONS Total RUS IER 25 46 U S GALLONS 12 73 GALLONS per tank Usable Fuel all flight conditions 24 0 U S GALLONS 12 GALLONS per tank Uhtusable PUB Sri a de te t naa 1 46 U S GALLONS 0 73 GALLONS per tank WARNING TAKEOFF IS PROHIBITED IF EITHER SIGHT GAGE INDICATES LESS THAN TANK OF FUEL OR FUEL LEVEL IS BELOW THE BOTTOM OF THE FUEL INDICATOR TAB MIN T O GRND MARKING ON FUEL INDICATOR 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 100 Grade Aviation Fuel Green FLAP LIMITATIONS Approved Takeoff Range o o o oooooomoomoo UP to 10 Approved Landing Range 00000e eee UP to FULL
142. could cause the problem Problems of this nature constitute an electrical emergency and should be dealt with immediately Electrical power malfunctions usually fall into two categories excessive rate of charge and insufficient rate of charge The following paragraphs describe the recommended remedy for each situation EXCESSIVE RATE OF CHARGE After engine starting and heavy electrical usage at low engine speeds such as extended taxiing 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 lf the charging current remains above this value on a long flight the battery electrolyte could overheat and evaporate Electronic components in the electrical system can be adversely affected by higher than normal voltage The built in overvoltage protection circuit will automatically disconnect the alternator if the charge voltage increases to more than 16 5 volts lf the overvoltage sensor circuit does not operate correctly as shown by voltage more than 16 5 volts on the electrical bus voltmeter the MASTER switch ALT section should be set to the OFF position Unnecessary electrical equipment should be de energized and the flight terminated as soon as practical If excessive rate of charge is indicated but the electrical bus voltmeter indicates less than 1
143. curity of attachment and general condition EMPENNAGE 1 2 3 4 17 8 Rudder Gust Lock if installed REMOVE Control Surfaces CHECK freedom of movement and security Elevator Trim Tab CHECK security verify tab is faired with elevator and trim indicator in T O position Tail Tiedown DISCONNECT Continued Next Page U S 162PHUS 01 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 PREFLIGHT INSPECTION Continued RIGHT WING Trailing Edge 1 ELT and GPS Antennas CHECK security of attachment and general condition 2 Flap DEFLECT and CHECK flap aileron cables up spring tension and general condition 3 Aileron CHECK freedom of movement and security NOTE Check for proper aileron movement by 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 RIGHT 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 the vent opening and apply suction a sound from the warning horn will confirm system operation 4 Fuel Quantity CHECK VISUALLY for desired level WARNING T
144. d ee 6 26 Continued Next Page 6 2 U S 162PHUS 00 CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 TABLE OF CONTENTS Continued Page AMPLIFIED EMERGENCY PROCEDURES 6 27 Engine Fall tia t e d eR Wt aie Buona 6 27 Maximum Elder add rs 6 28 Forced Landings ss tepong EE EE pl dd ed 6 29 Landing Without Elevator Control ooocccocccoo o 6 30 BEE a A EES SO OE BANA ap DM a 6 30 Emergency Operation In Clouds 4 aa 6 31 Executing A 180 Turn In Clouds ADAHRS FAILED 6 31 Emergency 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 OPS Rm BIT Eo A ad 6 35 Rough Engine Operation Or Loss Of Power 6 36 Carburetor Icing uc sa ma EE EE EV ADA qu edo been pees 6 36 Spark Plug FOUlING s imde dpt Ped tete Pede 6 36 Magneto Malfunction eom ost RE EE la paaa KA ge EE Eer 6 36 Idle Power Engine Roughness 00002 eae 6 37 LOW OIDPIOSSUIB sa naaa eh ba AR BS eR ES 6 37 Electrical Power Supply System Malfunctions 6 38 Excessive Rate Of Charge 0 0 eee eee 6 38 Insufficient Rate Of Charge ooooooooomommm 6 39 Other Emergencies id uuu tad ed 6 40 Windshield Damage doe tex e ar 6 40 6300 Failures cast a ce pa o RC RE EURO 6 40 162PHUS 00 U S 6 3 6 4 CESSNA SECTION 6 MODEL 162 EMERGE
145. damage to the environment WARNING 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 10 Static Source Opening left side of fuselage CHECK verify 7 12 opening is clear U S 162PHUS 00 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 BEFORE STARTING ENGINE 1 Preflight Inspection COMPLETE Passenger Briefing COMPLETE Rudder Pedals ADJUST Seat Belts ADJUST and SECURE Cabin Doors AS DESIRED Brakes TEST and SET Circuit Breakers CHECK IN Electrical Equipment OFF AVN Master Switch OFF o CO S Or Or N CAUTION THE AVIONICS MASTER SWITCH MUST BE OFF DURING ENGINE START TO PREVENT POSSIBLE 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 Continued 2 CARB HEAT Control Knob OFF push full in 3 THROTTLE Control AS REQUIRED a Engine COLD OPEN 1 4 INCH b Engine WARM CLOSED 4 MIXTURE Control FULL RICH
146. der strong crosswind conditions normally are performed with the minimum flap setting necessary for the field length to minimize the drift angle immediately after takeoff Begin the takeoff with ailerons fully deflected into the wind As the airplane is accelerated reduce aileron deflection maintaining directional control down the runway Reaching a speed slightly higher than normal rotation speed apply gentle back pressure to the elevator control and quickly but carefully lift the airplane off the ground Do not over rotate but keep positive pitch angle and airspeed to prevent possible settling back to the runway When well clear of the 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 for increased power or to provide smoother engine operation If it is necessary to climb more rapidly to clear mountains or reach favorable winds at higher altitudes the best rate of climb speed is 62 KIAS and should be used with Maximum Continuous Power MCP If an obstruction dictates the use of a steep climb angle the best angle of climb speed is 57 KIAS and should be used with flaps UP and MCP This type
147. e This is especially applicable to cross country training flights but should be practiced during transition flight to and from the practice area as well e Using the above recommended procedures can provide fuel savings in excess of 5 when compared to typical training operations at full rich mixture In addition the above procedures will minimize spark plug fouling since the reduction in fuel consumption results in a proportional reduction in tetraethyl lead passing through the engine 7 38 U S 162PHUS 01 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 STALLS The stall characteristics are conventional for the flaps up and flaps down conditions and aural warning is provided by a stall warning horn which sounds between 5 and 10 knots above the stall in all configurations Power on stall recovery should be initiated by simultaneously lowering the nose while reducing power after which normal power off stall recovery techniques should be applied CAUTION INTENTIONAL POWER ON STALLS SHOULD BE LIMITED TO 30 DEGREES NOSE UP PITCH ANGLE EXCEEDING 30 DEGREES REQUIRES HIGH POWER AND ACCELERATED STALL ENTRY WHICH MAY RESULT IN DISORIENTATION WARNING INTENTIONAL SPINS ARE PROHIBITED REFER TO SECTION 6 EMERGENCY PROCEDURES SPINS IT IS RECOMMENDED THAT THESE EMERGENCY PROCEDURES BE MEMORIZED TO ENSURE PROMPT AND PROPER RECOVERY TECHNIQUES ARE USED IN THE EVENT AN INADVERTENT SPIN IS ENCOUNTERED Refer to Section 5 F
148. e ELT main control panel located in the tailcone S2 8 U S 162PHUS S2 00 CESSNA SECTION 10 SUPPLEMENTS MODEL 162 SUPPLEMENT 2 GARMIN G300 NORMAL PROCEDURES When operating in a remote area or over hazardous terrain it is recommended that the ELT be inspected by an approved technician more frequently than required by 14 CFR 91 207 NORMAL OPERATION Normal operation of the AK 451 ELT from the flight crew station is only to de energize the ELT after it has been accidentally energized no emergency For normal operation of the AK 451 ELT the main switch on the ELT main control panel must be set to the ARM position You cannot disarm or disable the ELT transmitter from the cockpit you can only deactivate the ELT after it has been activated The ELT can be energized by a lightning strike or hard landing If the GREEN ON light within the remote switch panel is flashing and the aural warning is heard the ELT is energized Check for the emergency signal on a COM radio set to 121 5 MHz To stop the transmissions press the RESET button on the remote switch panel to de energize the ELT Tell the nearest Air Traffic Control facility about the accidental transmissions as soon as possible to hold search and rescue work to a minimum PERFORMANCE There is no change to the airplane performance when the Ameri King AK 451 ELT is installed 162PHUS S2 00 U S S2 9 52 10 MAMI EES Pilots Operating Handbook And Flight Training Su
149. e ee 1 8 Maximum Weight In Baggage Compartment 1 8 Standard Airplane Weights 0000 eee eee eee 1 8 Cabin And Entry Dimensions llle 1 8 Baggage Space And Entry Dimensions 1 8 Specific LoadingS xssxbeesdvreers eii cee ER ORE EE OE nec 1 8 162PHUS 00 U S 1 1 1 2 CESSNA SECTION 1 MODEL 162 GENERAL GARMIN G300 THREE VIEW NORMAL GROUND ATTITUDE B8437 lt 9 10 3 0 m 30 4 62 9 26 m d A Y Y 0910T1002 0910T1002 Figure 1 1 Sheet 1 of 2 162PHUS 01 U S 1 3 SECTION 1 CESSNA GENERAL MODEL 162 GARMIN G300 THREE VIEW NORMAL GROUND ATTITUDE B8439 p 22 1 6 73 m 0910T1002 NOTE e Wing span shown with standard strobe lights installed e Wheel base length is 62 40 inches 1 58 m I Propeller ground clearance is 8 50 inches 215 90 mm e Wing area is 120 0 square feet 11 15 sq m Figure 1 1 Sheet 2 1 4 U S 162PHUS 01 CESSNA SECTION 1 MODEL 162 GENERAL GARMIN G300 INTRODUCTION This POH contains 10 sections and includes the material required to be furnished to the pilot by American Society for Testing and Materials International ASTM standards F2245 for Light Sport Aircraft LSA It also contains supplemental data supplied by Cessna Aircraft Company Section 1 provides basic
150. e 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 just forward of the horizontal stabilizer and allowing the tail to rest on the tail tiedown ring To assist in raising and holding the nosewheel off the ground ground anchors should be utilized at the tail tiedown point NOTE Ensure that the nose will be held off the ground under all conditions by means of suitable stands or supports under weight supporting bulkheads near the nose of the airplane or the engine truss mount Continued Next Page 8 12 U S 162PHUS 00 CESSNA SECTION 8 MODEL 162 AIRPLANE HANDLING SERVICE GARMIN G300 AND MAINTENANCE GROUND HANDLING Continuea LEVELING Longitudinal leveling of the airplane is accomplished by placing a level on leveling screws located on the left side of the tailcone Deflate the nose tire and raise the main landing gear to properly center the bubble in the level The fuselage wing carry through spar in the cabin may be used to level the airplane laterally FLYABLE STORAGE Engines in airplanes that are flown every 30 days or less may not achieve normal service life because of internal corrosion Corrosion occurs when moist
151. e while the 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 operation or sluggish engine acceleration is good cause for discontinuing the takeoff If this occurs you are justified in making a thorough full throttle static run up before another takeoff is attempted The engine should run smoothly and turn approximately 2375 2475 RPM with carburetor heat off and the mixture leaned to provide maximum RPM NOTE Carburetor heat should not be used during takeoff unless it is absolutely necessary to obtain smooth engine acceleration Continued Next Page 162PHUS 01 U S 7 31 SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 TAKEOFF Continued POWER CHECK Continued Full throttle run ups over loose gravel are especially harmful to propeller tips When takeoffs must be made over a gravel surface advance the throttle slowly This allows the airplane to start rolling before high RPM is developed and the gravel will be blown behind the propeller rather than pulled into it Prior to takeoff from fields above 5000 feet pressure altitude the mixture should be leaned
152. ective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number Supplement Status Date Original Issue 19 November 2009 LOG OF EFFECTIVE PAGES Page Page Revision Number Status Number S2 1 thru S2 9 S2 10 Original 0 S2 2 U S 162PHUS S2 00 CESSNA SECTION 10 SUPPLEMENTS MODEL 162 SUPPLEMENT 2 GARMIN G300 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that are currently active Airplane Serial Revision Incorporated Number Title Effectivity Incorporated in Airplane 162PHUS S2 00 U S S2 3 SECTION 10 SUPPLEMENTS CESSNA SUPPLEMENT 2 MODEL 162 GARMIN G300 AMERI KING AK 451 EMERGENCY LOCATOR TRANSMITTER ELT GENERAL The Ameri King AK 451 Emergency Locator Transmitter ELT installation uses a solid state 3 frequency transmitter 121 5 243 0 and 406 0 MHz powered by an internal lithium battery The AK 451 is also equipped with a panel mounted remote switch assembly and an external antenna mounted on the top of the tailcone The remote switch assembly is installed on the right instrument panel and receives power from a single lithium cell battery Duracell DL1 3 NB or manufactures approved equivalent CAUTION USE OF NON APPROVED
153. efer in resolution of a specific emergency This information should be reviewed in detail prior to flying the airplane as well as reviewed on a regular basis to keep pilot s knowledge of procedures fresh ENGINE FAILURE If an engine failure occurs during the takeoff roll stop the airplane on the remaining runway Those extra items on the checklist 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 exists to secure the fuel and ignition systems prior to touchdown After an engine failure in flight the most important task is to continue flying the airplane The best glide speed as shown in Figure 6 1 should be established as quickly as possible While gliding toward a suitable landing area an effort should be made to identify the cause of the failure If time permits an engine restart should be attempted as shown in the checklist If the engine cannot be restarted a forced landing without power must be completed 162PHUS 00 U S 6 27
154. en then crank the engine through several revolutions with the starter Be prepared to immediately reduce throttle control to idle once engine starts Repeat the starting procedure without any additional priming After starting if the oil pressure gage does not begin to show pressure within 30 seconds in the summertime and about twice that long in very cold weather stop the engine and investigate Lack of oil pressure can cause serious engine damage After starting 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 starter to remain engaged an excessively high charge indication full scale at 1000 RPM would be evident on the ammeter In this event immediately shut down engine and have electrical system inspected by qualified maintenance personnel prior to next flight RECOMMENDED STARTER DUTY CYCLE Operate the starter motor for 10 seconds followed by a 20 second cool down period This cycle can be repeated five additional times followed by a thirty minute cool down period before resuming cranking After cool down operate the starter motor again six cycles of 10 seconds followed by 20 seconds
155. en aie a 7 30 E Aiernater Check i iod ug tie beide d ER see d 7 31 Electric Elevator Trim is De stel VI siete eee AB DER 7 31 ME en EA oe ACERO ears wea Be ae NG 7 31 Power COCK sc rr buk do auo bra E e RAANG 7 31 Wing Flap Settings sd gee Had e RC ERR EE doce 7 32 Crosswind Takeoff becaria 7 33 Enroute Climb 2 9 4 eet Sc eu o EC eb coss add 7 33 NGUSO T UNI T PPM 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 SE mk Snack AE iudice SUR ga gra tot EE RE t alant ane 7 39 A oe epe dtp ed em tos dun ie de uera 7 39 LARIOS daa 7 40 Normal Landing adea RE EE HERDER dt 7 40 Shot Field Landing wi av atea 7 40 Crosswind Landings cd paa pa BAE kaa Is 7 41 Balked Landing porra ed 7 41 High Winds Operations 00 cee eee 7 41 Cold Weather Operations 000 cee eee eee 7 42 in PAA ee eae 7 43 Winterization Kit showers set BEER EI ees 7 45 7 46 Hot Weather Operations cece eee eee 7 45 7 46 7 2 U S 162PHUS 01 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 INTRODUCTION Section 7 provides procedures and amplified instructions for normal operations using standard and simply operated optional equipment Normal procedures associated with more complex optional equipment can be found in Section 10 Supplements AIRSPEEDS FOR NORMAL OPERAT
156. erating information 2 14 U S 162PHUS 01 CESSNA SECTION 2 MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION GARMIN G300 PROPELLER The airplane is equipped with a two bladed fixed pitch one piece forged aluminum alloy propeller which is anodized to retard corrosion The propeller is 67 inches in diameter FUEL SYSTEM The airplane fuel system Refer to Figure 2 6 consists of two vented integral fuel tanks one tank in each wing fuel shutoff valve and a fuel strainer The engine mounted portion of the system consists of the gravity fed updraft float carburetor WARNING 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 LEVEL TOTAL USABLE FUEL QUANTITY TOTAL TOTAL ALL FLIGHT TANKS EACH TANK FUEL UNUSABLE CONDITIONS Two Full 12 73 25 46 1 46 24 0 Figure 2 1 Fuel flows by gravity from the two wing tanks to a fuel shutoff valve the fuel strainer and to the carburetor The carburetor meters fuel flow in proportion to induction air flow and distributes to the cylinder intake manifold 162PHUS 01 Continued Next Page U S 2 15 SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 162 GARMIN G300 FUEL SYS
157. erational information 8 RCL Pressing the recall memory button will retrieve stored frequency Refer to the Garmin Pilots Guide for detailed description and operational information 9 MON Pressing of the frequency monitor button will allow monitoring of the standby frequency A small m will be displayed in front of the standby frequency When the active frequency receives a signal the unit will switch automatically to the active frequency An arrow lt or gt will point to the frequency that you are currently listening to 10 EC Pressing the emergency channel button automatically loads the Emergency Channel 121 500 MHz as the standby frequency The monitor function will be automatically enabled 11 Flip Flop Frequency Control Pressing the flip flop button will toggle the standby frequency over to the active frequency 12 Power Volume Squelch Control Knob a Power ON OFF Turning the POWER VOLUME control knob clockwise past the OFF detent will power on the unit b Volume Turn the POWER VOLUME control knob clockwise to increase the volume level and counterclockwise to decrease the volume level c Squelch Pull the POWER VOLUME control knob out to disable the automatic squelch function INTERCOM FUNCTION For airplanes not equipped with the optional PM3000 Intercom the Garmin SL40 VHF Comm Transceiver is configured to function as a voice activated intercom system when two headsets and microphones are properly c
158. f operation drain the engine oil sump and replace the filter Refill sump with non dispersant mineral oil and use until a total of 50 hours has accumulated or oil consumption has stabilized then change to ashless dispersant oil Ashless dispersant oil and oil filter should be changed 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 security proper routing and support and evidence of deterioration Inspect the intake and exhaust systems for cracks evidence of leakage and security of attachment Engine controls and linkages should be checked for freedom of movement through their full range security of attachment and evidence of wear Inspect wiring for security chafing burning defective insulation loose or broken terminals heat deterioration and corroded terminals A periodic check of these items during subsequent servicing operations is recommended 8 16 U S 162PHUS 00 CESSNA SECTION 8 MODEL 162 AIRPLANE HANDLING SERVICE GARMIN G300 AND MAINTENANCE FUEL APPROVED FUEL GRADES AND COLORS 100LL Grade Aviation Fuel Blue 100 Grade Aviation Fuel Green NOTE Isopropyl a
159. flection refer to Figure 7 2 Taxiing Diagram to aid in maintaining directional control This is particularly important in windy conditions Continued Next Page 162PHUS 00 U S 7 27 SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 TAXIING Continued NOTE Strong or gusty tail winds can over power the wing flap return springs causing the flaps to randomly blow down while taxiing Selecting flaps to FULL when taxing with a tailwind can prevent the blow down Use caution to prevent a build up of taxi speed due to blowing by strong tailwinds Flaps should be retracted when turning away from the tailwind condition and the BEFORE TAKEOFF Checklist should be used to insure flaps are properly 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 F Indicator will assist in amount of carb heat required to keep the carburetor temperature out of the yellow caution range and prevent engine roughness Taxiing over loose gravel or cinders should be done at the lowest engine RPM possible to avoid abrasion and stone damage to the propeller tips Continued Next Page 7 28 U S 162PHUS 00 CESSNA
160. flight operation SWITCH CIRCUIT BREAKER PANEL ASSEMBLY B14540 e ALTE SBAT AVN LIGHTS MASTER STROBE NAV LDG PANEL OFF OFF OFF OFF mmao z OFF OFF LIGHTS CAB MAIN CB START ALT STROBE NAV LDG PWR RESET 0000400 0600000 oe 2 Figure 2 5 2 22 U S 162PHUS 01 CESSNA SECTION 2 MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION GARMIN G300 ELECTRICAL SYSTEM Continued 12V POWER OUTLET A 12 volt power outlet connector POWER OUTLET 12V 7 5A is provided by an automotive style power outlet located on the center pedestal The power outlet receives electrical power from a dedicated 7 5 amp circuit breaker located in the switch circuit breaker panel CAUTION e CHARGING OF LITHIUM BATTERIES MAY CAUSE THE LITHIUM BATTERIES TO EXPLODE e TAKE CARE TO OBSERVE THE MANUFACTURER S POWER REQUIREMENTS PRIOR TO PLUGGING ANY DEVICE INTO THE 12 VOLT CABIN POWER SYSTEM CONNECTOR THIS SYSTEM IS LIMITED TO A MAXIMUM OF 7 5 AMPS e USE CAUTION WITH POWER ADAPTER CABLES IN THE CABIN TO AVOID ENTANGLING OCCUPANTS OR CABIN FURNISHINGS AND TO PREVENT DAMAGE TO CABLES SUPPLYING LIVE ELECTRIC CURRENT e 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 equipmen
161. gure 4 5 Sheet 2 162PHUS 00 U S 4 22 CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE GARMIN G300 EQUIPMENT LIST LOADING ARRANGEMENTS U S UNITS B13964 C G ARM FS 8 6 FS P Paso 142 FS Baggage FS FS FS 172 50 Area 190 00 155 00 100 00 155 190 0919020 Pilot and front seat passenger center of gravity for average occupant Arm measured to the center of the areas shown NOTE e 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 U S 4 23 SECTION 4 CESSNA WEIGHT AND BALANCE MODEL 162 EQUIPMENT LIST GARMIN G300 LOADING ARRANGEMENTS METRIC UNITS C G ARM FS 8 amp FS P Pass 3606 80 FS 4381 50 3937 4826 Baggage FS FS FS Area 4826 00 3937 00 SEG 09101001 Pilot and front seat passenger center of gravity for average occupant Arm measured to the center of the areas shown NOTE e All dimensions shown are in millimeters e The usable fuel C G arm is located at FS 3638 80 e The aft baggage wall approximate FS 4826 can be used as a convenient interior reference point for determining the location of baggage area fuselage
162. he 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 mE Full B14538 3 4 Full im Ful 1 4 Full 092611003 Figure 2 3 Continued Next Page 2 18 U S 162PHUS 01 CESSNA SECTION 2 MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION GARMIN G300 FUEL SYSTEM Continued FUEL DRAIN VALVES The fuel system is equipped with 6 drain valves 4 in the wings and 2 in the lower cowl to provide a means for the examination of fuel in the system for contamination and grade The system should be examined before each flight and after each refueling by using the sampler cup provided to drain fuel from each wing tank sump the lower cowl fuel shutoff valve drain and the fuel strainer sump lower cowl drain lf any evidence of fuel contamination is found it must be eliminated in accordance with the preflight inspection checklist and the discussion in Section 8 If takeoff weight limitations for the next flight permit the fuel tanks should be filled after each flight to prevent condensation ELECTRICAL SYSTEM The airplane is equipped with a 14 volt direct current DC electrical system powered by an engine driven alternator A 12
163. he pilot and copilot headsets and will not change with the number of headset connected 2 PWR XMT Indicator Light The fixed intensity LED indicator located above the mode selector switch will illuminate green when the unit is powered on The LED indicator will illuminate red during radio transmissions by either the pilot or copilot The LED indicator will also illuminate red during a stuck mic condition Continued Next Page 162PHUS S3 00 U S S3 7 SECTION 10 SUPPLEMENTS CESSNA SUPPLEMENT 3 MODEL 162 GARMIN G300 GENERAL Continued PS ENGINEERING PM3000 INTERCOM SYSTEM CONTROL PANEL Continued 3 ISO ALL Mode Selector Switch The mode selector switch allows the pilot to select the intercom function best suited for the current flight conditions Regardless of configuration the pilot will always hear radio communications through the SL40 Comm radio NOTE If power is disrupted to the PM3000 intercom for any reason an internal relay will connect the pilot s headset directly to the intercom function of the SL40 Comm radio allowing uninterrupted radio communications to the pilot s headset only a ISO Up Position The pilot is isolated from the intercom and is connected only to the SL40 Comm radios He will hear the airplane radio reception and sidetone during radio transmissions The copilot will hear himself and music but not the airplane radio traffic b ALL Down position Pilot and copilot will hear al
164. held microphone is required for all radio transmissions Transmitting radio communication utilizing the hand held microphone will require the operator to depress the push to talk button on the hand held microphone and the push to talk PTT button on the control stick at the same time while speaking directly into the hand held microphone EMERGENCY PROCEDURES Pressing the Emergency Channel EC button automatically loads the Emergency Channel 121 500 MHz as the standby frequency The monitor function will be automatically enabled Pressing the Flip Flop lt gt button will load the emergency channel into the active frequency for emergency communications In an emergency situation if the STUCK MIC annunciator message remains illuminated after you have stopped keying the microphone turn the power control knob to the off position and then turn back on Cycling the main power control knob will allow a 35 second transmission period prior to experiencing another STUCK MIC condition Cycling of the SL40 power will be required for all future transmission as long as the STUCK MIC annunciator is illuminated FAA APPROVED 162PHUS S7 00 U S S7 5 SECTION 10 SUPPLEMENTS CESSNA SUPPLEMENT 7 MODEL 162 GARMIN G300 NORMAL PROCEDURES GARMIN SL 40 VHF COMM TRANSCEIVER 814727 1 2 3 4 5 6 12 11 10 9 8 7 0918P1031 Figure S7 1 1 PHOTO SENSOR Sensor automatically adjusts display brightness for current lighting conditions The auto
165. herwise indicated true values not net change values for the weight and arm are shown Positive arms are distances aft of the airplane datum negative arms are distances forward of the datum Asterisks in the weight and arm column indicate complete assembly installations Some major components of the assembly are listed on the lines immediately following The sum of these major components does not necessarily equal the complete assembly installation 4 4 U S 162PHUS 00 CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE GARMIN G300 EQUIPMENT LIST REF WT ARM ITEM NO EQUIPMENT LIST DESCRIPTION DRAWING LBS INS 11 PAINT AND PLACARDS 11 01 S PAINT OVERALL WHITE WITH COLOR STRIPE 0900001 19 91 168 53 OVERALL WHITE COLOR 0900001 19 66 168 53 COLOR STRIPING 0919002 0 25 168 35 21 AIR CONDITIONING 21 01 S VENTILATORS ADJUSTABLE CABIN AIR 0914100 0 86 122 88 21 02 8 CABIN HEATER SYSTEM SHROUDED MUFFLER 0914100 1 01 99 15 TYPE 21 08 R AVIONICS COOLING FAN S4000 4 0918101 0 30 116 06 22 AUTO FLIGHT 22 01 O AUTOPILOT 0901120 7 14 111 41 23 COMMUNICATIONS 23 01 R NAV COM GPS 1 COMPUTER SL40 INTEGRATED AVIONICS UNIT 0918101 2 10 117 22 CI2480 201 VHF COMM GPS ANTENNA 0918123 0 56 164 78 CI420 10 XM ANTENNA AND CABLE ASSY 0918503 1 02 147 49 23 02 O AUDIO INTERCOM PM3000 AUDIO PANEL 0918504 1 04 1118 31 24 ELECTRICAL POWER 24 01 R ALTERN
166. hould be at idle as the main wheels touch the ground The main wheels must touch the ground before the nosewheel The nosewheel must be lowered to the runway carefully after the speed has diminished to avoid unnecessary nose gear loads This procedure is very important 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 obstacles are cleared smoothly reduce power and hold the approach speed by lowering the nose of the airplane The main wheels must touch the ground before the nosewheel with power at idle Immediately after the main wheels touch the ground carefully lower the nosewheel and apply heavy braking as required For maximum brake performance retract the flaps hold the control stick full back and apply maximum brake pressure without skidding the tires or loosing directional control Use of full rudder authority will assist directional control Continued Next Page 17 40 U S 162PHUS 01 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 LANDING Continued CROSSWIND LANDING When landing in a strong crosswind use the minimum flap setting required for the field length Sidesl
167. idual documents and may be issued or revised without regard to revision dates which apply to the POH itself These supplements contain a Log of Effective Pages which should be used to determine the status of each supplement vi U S 162PHUS 01 CESSNA INTRODUCTION MODEL 162 GARMIN G300 ORIGINAL ISSUE AND REVISIONS This Pilot s Operating Handbook is comprised of the original issue and any subsequent revisions To make sure that information in this manual is current the revisions must be incorporated as they are issued As revisions are issued they will be noted in the Log of Effective Pages The part number of this manual has also been designed to further aid the owner operator in determining the revision level of any POH Refer to the example below for a breakdown 162 PHUS 00 L Revision Level Original Issue Manual Pilot s Operating Handbook U S Serials 16200001 and On Airplane Model 162 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 Internationally Registered aircraft according to Cessna Owner Advisory records at the time of issuance Revisions should be read carefully upon receipt and incorporated
168. igure 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 useful to increase descent rates while allowing power to be kept above idle Carburetor heat should be used as needed for engine roughness and applied before reducing power to prevent carburetor ice from forming during low power descent Since heated air causes a richer fuel mixture readjust the mixture setting when carburetor heat is to be used for extended descent If a low power descent is made it is recommended that the throttle be cycled occasionally to check for engine roughness at higher power NOTE Extended low power descents should be avoided during the first 25 hours of operation of a new engine 162PHUS 01 U S 7 39 SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 LANDING NORMAL LANDING Normal landing approaches can be made with power on or power off with any flap setting within the flap airspeed limits Surface winds and air turbulence are usually the primary factors in determining the most comfortable approach speeds Slips to landing are very effective may be performed in all flap configurations Landing at slower speeds will result in shorter landing distances and minimum wear to tires and brakes Power s
169. imitations is required by Federal Aviation Regulations NOTE e 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 e The airspeeds listed in Figure 3 1 Airspeed Limitations are based on Airspeed Calibration data shown in Section 9 The Cessna Model No 162 is approved under ASTM standard F2245 162PHUS 00 U S 3 3 SECTION 3 OPERATING LIMITATIONS AIRSPEED LIMITATIONS Airspeed limitations and their operational significance are shown in Figure 3 1 CESSNA MODEL 162 GARMIN G300 AIRSPEED LIMITATIONS SYMBOL Stall Speed Clean REMARKS Stall speed flap up Configuration Stall Speed Landing Stall speed flaps full Maximum Flap Extended Speed FLAPS 10 FLAPS 25 FLAPS FULL Do not exceed this speed with flaps down Maximum Operating Maneuvering Speed 1320 Pounds 1200 Pounds 1100 Pounds Maximum speed at which the airplane may be stalled without exceeding structural limitations Design Maneuvering Speed Do not make full or abrupt control movements above this speed Does not provide protection from possible overstressing the airplane Never Exceed Speed Do not exceed this speed in any operation Maximum Structural Cruising Speed Figure 3 1 Do not exceed this speed exce
170. in this POH 162PHUS 00 U S vii INTRODUCTION CESSNA MODEL 162 GARMIN G300 REVISION FILING INSTRUCTIONS REGULAR REVISIONS Pages to be removed or inserted in the Pilots Operating Handbook are determined by the Log of Effective Pages located in this section This log contains the page number and revision level for each page within the POH As revisions to the POH occur the revision level on effected pages is updated When two pages display the same page number the page with the latest revision level shall be inserted into the POH The revision level on the Log Of Effective Pages shall also agree with the revision level of the page in question TEMPORARY REVISIONS Under limited circumstances temporary revisions to the POH may 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 issued with a current List of Temporary Revisions that is to be inserted opposite the first page of the Log of Effective Pages in the front of the POH and will supersede any previously issued List of Temporary Revisions This list is used to track the status of temporary revisions issued against this POH and is to be remo
171. ious ducting located in the cabin With the CABIN HEAT control knob in the off or full forward position preheated air is redirected into the engine compartment through the air control valve located on the firewall Fresh air ducts direct ram air from 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 stall warning horn will sound 5 8 knots prior to stall buffet to provide notice to the pilot of impending stall Horn activation will not prevent a stall from occurring When the horn sounds the pilot should react by initiating stall avoidance procedures decrease of angle of attack increase airspeed etc The stall warning system does not require electrical power for operation The stall warning system opening located in the right wing should be checked during Pen to make sure it is free of debris that might interfere with airflow and correct operation To check the system place a clean cloth over the vent opening and apply suction a sound from the warning horn will confirm system operation p162PHUS 01 U S 2 25 2 26 CESSNA SECTION 3 MODEL 162 OPERATING LIMITATIONS GARMIN G300 OPERATING LIMI
172. ips with full rudder deflection may be made in all flap configurations Although the crab or combination method of drift correction may be used the wing low method gives the best control After touchdown hold a straight course with the rudder and use up to full aileron deflection as required and differential braking as necessary The maximum allowable crosswind velocity is dependent upon pilot capability as well as airplane limitations Operation in direct crosswinds of 12 knots has been demonstrated not an operating limitation BALKED LANDING 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 accelerate to normal climb airspeed HIGH WIND OPERATIONS Takeoff and landings have been demonstrated in winds up to 22 knots and crosswinds up to 12 knots The pilot should be cautious of gusts and turbulence from terrain or buildings when in close proximity to ground during takeoff and landing Prompt and positive control inputs should be used to counter flight path deviations Proper taxi control techniques must be used at all times during ground operations Operations in wind conditions abo
173. key at any time will cancel the entry and restore the previous code Continued Next Page FAA APPROVED U S 162PHUS S6 00 CESSNA SECTION 10 SUPPLEMENTS MODEL 162 SUPPLEMENT 6 GARMIN G300 NORMAL PROCEDURES Continued 11 IDENT Pressing the IDENT key activates the Special Position Identification SPI pulse for 18 seconds identifying the transponder return from others on the air traffic controller s screen The word IDENT will appear in the upper left corner of the display when IDENT mode is active 12 VFR Sets the transponder code to 1200 unless configured otherwise Pressing the VFR key again will restore the previous identification code ALTITUDE TREND INDICATOR When the PRESSURE ALT page is displayed an arrow may be displayed to the right of the altitude indicating that the altitude is increasing or decreasing Two sizes of arrows may be displayed depending on rate of climb descent AUTOMATIC ALT STBY MODE SWITCHING The GTX 327 automatically switches to ALT mode when ground speed exceeds approximately 30 knots GPS ground speed The unit automatically returns to STBY mode when the airplane slows below 30 knots NOTE The ON Mode A ALT Mode C and STBY keys can be used at any time to manually override the automatic ALT STBY mode switching PERFORMANCE There is no change to the airplane performance when the Garmin GTX 327 Transponder is installed FAA APPROVED 162PHUS S6 00 U S S6 7 S6 8
174. l radio communications intercom and music However during any ICS conversation the music volume automatically mutes The music volume increases gradually back to the original level after radio communications have been completed Continued Next Page S3 8 U S 162PHUS S3 00 CESSNA SECTION 10 SUPPLEMENTS MODEL 162 SUPPLEMENT 3 GARMIN G300 GENERAL Continued PS ENGINEERING PM3000 INTERCOM SYSTEM CONTROL PANEL Continued 4 SQUELCH Control Knob Separate squelch circuits for the pilot and copilot are controlled by the single Squelch control knob Normal speech levels should open the channel when the microphone is positioned properly near the lips This VOX operated intercom keeps the microphone channels off silent when the pilot or copilot is not speaking to reduce the background noise coming from the airplane When talking is stopped a delay of about one half second occurs before the channel closes Proper setting of the squelch level prevents squelch closure between words to eliminate choppy intercom conversations a SQUELCH Control Set the squelch level with the engine running by slowly rotating the SQUELCH control knob clockwise until you no longer hear background noise in the headsets b MUTE Control Normally any radio traffic or intercom conversations will automatically mute the audio signal with the mode selector switch in ALL position However the PM3000 can be placed in an uninterrupted music mode by
175. lcohol or Diethylene Glycol Monomethyl Ether DIEGME may be added to the fuel supply in quantities not to exceed 1 alcohol or 0 15 DIEGME of total volume Refer to Fuel Additives in later paragraphs for additional information FUEL CAPACITY Total Capacity uat ane ool areas 25 46 U S GALLONS 96 34 1 Total Usable 24 00 U S GALLONS 90 82 1 Total Capacity Each Tank 12 73 U S GALLONS 48 17 I Total Usable Each Tank 12 00 U S GALLONS 45 41 I NOTE e 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 e The fuel filler assembly is equipped with indicator tabs for 3 4 1 2 and 1 4 fuel quantities e Maximum full capacity is indicated when fuel reaches the upper hole of the indicator tab This fuel level allows for proper thermal expansion Filling the fuel tank above the upper hole eliminates expansion space resulting in fuel venting overboard through the fuel vent Continued Next Page 162PHUS 00 U S 8 17 SECTION 8 CESSNA AIRPLANE HANDLING SERVICE MODEL 162 AND MAINTENANCE GARMIN G300 FUEL Continued FUEL ADDITIVES Strict adherence to recommended preflight draining instructions as called for in Section 7 will eliminate any free water accumulations from the tank sumps While small amounts of water may still remain in solutio
176. le pages Left of the PFD on the upper panel is the optional autopilot controller unit if installed and below it is the Ignition Magneto key switch he electrical system switch circuit breaker panel located to the right of the PFD has switches in the 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 installed takes over the moving map and engine instrument functions from the PFD as well as other display page functions On the far right side of the panel is the remote ELT switch and optional intercom control panel Engine controls are located below the radio stack and MFD display if installed along the bottom center of the instrument panel The controls are left to right Carb Heat Throttle Control Mixture Control and Cabin Heat Control The parking brake and fuel shut off control knobs are located beneath the engine controls on the top of the vertical pedestal Headset jacks and auxiliary 12 volt cabin power outlet are positioned further down on the vertical pedestal Continued Next Page 162PHUS 01 U S 2 5 SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 162 GARM
177. lve ON push full in MIXTURE Control RICH if restart has not occurred PRIMER IN and LOCKED if installed BAUL Oh NOTE If the propeller is windmilling engine 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 MAGNETOS Switch BOTH or START if propeller is stopped 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 POWER IMMEDIATELY 3 Airspeed 70 KIAS best glide speed 4 Land as soon as possible refer to EMERGENCY LANDING WITHOUT ENGINE POWER IF OIL F WITHIN GREEN BAND RANGE 2 OIL F MONITOR 3 OIL PSI MONITOR 4 Land as soon as practical nearest suitable airport recommended Continued Next Page 162PHUS 01 U S 6 7 SECTION 6 CESSNA EMERGENCY PROCEDURES MODEL 162 GARMIN G300 ENGINE FAILURES AND MALFUNCTIONS Continued CARB F INDICATOR IN YELLOW BAND RANGE YELLOW DIGITS 1 ENGINE MONITOR FOR ROUGHNESS AND OR RPM LOSS NOTE Carb F indicator in yellow band range indicates temperatures may support carb icing formation IF ENGINE ROUGHNESS AND OR RPM LOSS IS DETECTED CARB F IN YELLOW BAND RANGE 2 CARB HEAT Control Knob ON pull full out 3
178. ly activates the transmitter for testing or emergency situations The RED warning light comes on to indicate that the transmitter is transmitting a distress signal 2 ON Light Transmitter warning light comes on RED to indicate the transmitter is transmitting a distress signal 3 RESET Reset button deactivates or de energizes the transmitter 0918T1029 OPERATING LIMITATIONS There are no additional airplane operating limitations when the Ameri King AK 450 ELT is installed Refer to 14 CFR 91 207 for ELT inspection requirements The AK 450 must be inspected and tested by an approved technician using the correct test equipment under the appropriate civil aviation authorities approved conditions S1 6 U S 162PHUS S1 00 CESSNA SECTION 10 SUPPLEMENTS MODEL 162 SUPPLEMENT 1 GARMIN G300 EMERGENCY PROCEDURES If a forced landing is necessary press the ON switch within the remote switch panel before landing This is very important in remote or mountainous terrain The RED warning light will illuminate and the aural warning will be heard After a landing when search and rescue aid is needed use the ELT as follows NOTE The ELT remote switch assembly could be inoperative if damaged during a forced landing If inoperative the inertia G switch will activate automatically However to turn the ELT OFF and ON again requires manual switching of the ELT main control panel switch which is located on the ELT
179. m Instrument Equipment and or Function FUEL SYSTEM COMMENTS 1 Fuel Shutoff Control Valve 2 Cockpit Fuel Quantity Indicator L Tank 3 Cockpit Fuel Quantity Indicator R Tank INDICATING RECORDING SYSTEM 1 Stall Warning System 2 G300 System Annunciator and Warning Displays LANDING GEAR 1 Wheel Fairings Removable LIGHTING 1 PFD Bezel Lighting 2 PFD Display Backlighting 3 MFD Bezel Lighting 4 MFD Display Backlighting 5 Cockpit Overhead Panel Lighting 6 Aircraft Position NAV Lights 7 STROBE Light System 8 LAND Landing Light 9 Non stabilized Magnetic Compass Internal Lightin it installed bu O O O O 0 o O AA HA a nr O sm O Continued Next Page 162PHUS 01 CESSNA MODEL 162 GARMIN G300 SECTION 3 OPERATING LIMITATIONS KINDS OF OPERATIONS EQUIPMENT LIST continued KIND OF OPERATION System Instrument Equipment and or Function COMMENTS NAVIGATION AND PITOT STATIC SYSTEM 1 G300 Airspeed Indicator 1 1 2 G300 Altimeter 1 1 3 G300 Vertical Speed Indicator 0 0 4 G300 Attitude Indicator 0 0 5 G300 Directional Indicator HSI 0 0 6 G300 Turn Coordinator 0 0 7 G300 Magnetic Heading 1 1 Indicator 8 GPS Receiver Navigator A R AR As Required Per Procedure 9 GTX 327 Mode C Transponder A R AR As Required Per Procedure 10 Blind Altitude Encoder A R AR As Required Per Pro
180. n H 1 q Sa SSS S 1 LLP DE al EER ums Load Weight Pounds Fuel 6 Ibs gal KA AA y se EE ee post ern e o SRS AI I A RE EE las sp e recen E 3 DOTA spo te no sd N OE AG ee kaa L 6 Gal Min Takeoff Fuel Baggage E Um An A A A i aa SE 0 10 20 30 40 50 60 Load Moment 1000 Pounds Inches Figure 4 5 Sheet 1 of 2 162PHUS 00 U S 4 21 CESSNA MODEL 162 GARMIN G300 LOADING GRAPH METRIC UNITS WEIGHT AND BALANCE EQUIPMENT LIST SECTION 4 B10723 Load Moment 1000 Kilogram Millimeters o o 00 co XM eper EE le Ka maan D WII E T PA PAKANA AMO APAN TA AE PNE i En 7 BANA CS AS seso T 4 a ss FA H 4 4 ds 4 E So n H H O ase aa i CECI ae i 300 i i me TT ON oan EE 3 1 3 E i a HN E f a PA i 1 e i n kana i E i 1 3 E ass juris send eon fi 4 EE DE d m dd AE SEE ae 1 l A ERROR mee mS 2 o N EE er EI E EE eg o i s suJeJBo y 106186 M peo S o o o co press a en spe rt sens i RER gt sa a E a a e ME REDE AG en SERE Re NGA a los BES id Q in Takeoff Fuel 3 E DAT S asas i E ded H i x i E sence A PARE SARNE ARAE alo Ra Fi
181. n deflected aileron may appear to be stuck or difficult to move up This is normal characteristic of the Cessna 162 ailerons system that only occurs when the ailerons are moved down from outside the airplane It is recommended that the aileron movement be checked by moving the ailerons up from the flaps UP faired position then returned to this position However if an aileron is externally moved down and becomes over centered simply re center the cockpit control stick and continue the walk around inspection CAUTION AILERON OVER CENTERING ONLY OCCURS WHEN AILERONS ARE MOVED FROM OUTSIDE THE AIRPLANE CONTROL STICK STIFFNESS OR STICKING IN ANY DIRECTION OF ANY CONTROL SURFACE THIS IS NOT NORMAL AND SHOULD BE INSPECTED BY MAINTENANCE PERSONNEL PRIOR TO FLIGHT 12 4 U S 162PHUS 01 CESSNA SECTION 2 MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION GARMIN G300 INSTRUMENT PANEL FLIGHT AND SYSTEM INSTRUMENTS NOTE Refer to the Garmin Pilot s Guide for details and operating instructions of the G300 Avionics System The Model 162 Skycatcher instrument panel is oriented around the Garmin G300 Flight and Engine Instrumentation Display s Directly in front of the pilot is the G300 Primary Flight Display PFD which has all flight navigation and engine instruments depicted in an electronic format on a liquid crystal display A vast amount of additional flight and navigational information is accessible through the G300 system s various selectab
182. n in the gasoline it will normally be consumed and go unnoticed in the operation of the engine One exception to this can be encountered when operating under the combined effect of 1 use of certain fuels with 2 high humidity conditions on the ground 3 followed by flight at high altitude and low temperature Under these unusual conditions small amounts of water in solution can precipitate from the fuel stream and freeze in sufficient quantities to induce partial icing of the engine fuel system While these conditions 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 isopropy alcohol or Diethylene Glycol Monomethyl Ether DIEGME compound to the fuel supply The introduction of alcohol or DIEGME compound into the fuel provides two distinct effects 1 it absorbs the dissolved water from the gasoline and 2 alcohol has a freezing temperature depressant effect NOTE When using fuel additives it must be remembered that the final goal is to obtain a correct fuel to additive ratio in the tank and not just with fuel coming out of the refueling nozzle For example adding 15 gallons of correctly proportioned fuel to a tank which contains 20 gallons of untreated fuel will result in a lo
183. n 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 throttle control and is equipped with a lock button in the end of the knob The rich position is full forward and full aft is the idle cutoff 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 mixture control knob and then positioning the control as desired Continued Next Page 42 8 U S 162PHUS 01 CESSNA SECTION 2 MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION GARMIN G300 ENGINE Continued ENGINE INSTRUMENTS The G300 Engine Indication System ElS provides the pilot graphical indicators and numerical values for Tachometer RPM Oil Pressure OIL PSI Oil Temperature OIL F Carburetor Temperature CARB F Battery Current AMPS and Elevator Trim Position TRIM along the top of the appropriate G300 Display Additional indicators and numerical values for Exhaust Gas Temperature EGT F Electrical Bus Voltage VOLTS and Engine Hours ENG HRS are
184. nes 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 switch CB panel controls intensity of the overhead LED matrix lighting non stabilized magnetic compass internal lighting if installed and Garmin G300 displays when the G300 display setup backlight intensity is configured in the AUTO mode Rotating the PANEL LIGHTS dimming knob full clockwise provides maximum brightness while rotating the dimmer control knob counterclockwise decreases light intensity from the highest level to off Power for the PANEL LIGHTS dimmer control is provided by the secondary power circuit and protected by the SEC PWR circuit breaker 12 24 U S 162PHUS 01 CESSNA SECTION 2 MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION GARMIN G300 CABIN HEATING AND VENTILATING SYSTEM The cabin heating and ventilating system consists of a cabin heat system and fresh air from wing leading edge openings Cabin heat is controlled by a push pull cable from the CABIN HEAT control knob located on the lower instrument panel When the CABIN HEAT control knob is placed in the ON or full aft position air is heated as it is directed around the exhaust heat shroud and ducted to a air control valve located on the firewall With the air control valve in the on position warm air is directed towards the pilot s and front passenger s feet through var
185. ng maneuvering Continued Next Page 162PHUS 01 U S 6 31 SECTION 6 CESSNA EMERGENCY PROCEDURES MODEL 162 GARMIN G300 EMERGENCY OPERATION IN CLOUDS Continued EMERGENCY DESCENT THROUGH CLOUDS ADAHRS FAILED When returning to VFR flight after a 180 turn is not practical a descent through the clouds to VFR conditions below may be appropriate If possible obtain an ATC assistance and clearance for an emergency descent through the clouds Po descending into the clouds prepare for a stabilized descent as ollows 1 Reference optional magnetic compass if installed or select G300 map with COMPASS ARC from MAP SET UP menu for GPS derived approximate heading information on moving map display 2 If MFD is installed select 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 wind vector information will allow approximation of airspeed MIXTURE Control RICH push full in CARB HEAT Control Knob ON pull full out THROTTLE Control REDUCE 1700 1800 RPM Approximate Airspeed 70 75 Knots estimate airspeed from GS and wind vector data Elevator Trim ADJUST
186. ng Flaps RETRACT to 25 Climb Speed 50 KIAS until obstacle is cleared Climb Speed 60 KIAS after obstacle is cleared Wing Flaps 10 then UP after reaching a safe altitude and 60 KIAS OV qeu 162PHUS 01 U S 7 21 SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 AFTER LANDING 1 CARB HEAT Control Knob OFF push full in 2 Wing Flaps UP 3 STROBE Light Switch OFF 4 Transponder STBY SECURING AIRPLANE 1 Parking Brake SET a Brakes APPLY b PARKING BRAKE Control Knob ON pull full out THROTTLE Control IDLE pull full out Electrical Equipment OFF AVN MASTER Switch OFF MIXTURE Control IDLE CUTOFF pull full out MAGNETOS Switch OFF MASTER Switch ALT and BAT OFF Control Lock INSTALL 9o OD OV coo a 7 22 U S 162PHUS 00 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 AMPLIFIED NORMAL PROCEDURES PREFLIGHT INSPECTION The preflight inspection described in Figure 7 1 and adjacent checklist is required prior to each flight If the airplane has been in extended storage has had recent major maintenance or has been operated from rough runways a more extensive exterior inspection is recommended Before every flight check the condition of main and nose landing gear tires Keep tires inflated to the pressure specified in Section 8 Airplane Handling Service And Maintenance Examine tire sidewalls for patterns of shallow cracks called weather checks These cracks
187. nt installed in the airplane Operators should refer to each supplement to ensure that all limitations and procedures appropriate for their airplane are observed A Cessna Approved Log Of Approved Supplements is provided for convenience only This log is a numerical list of all Cessna Approved supplements applicable to this airplane by name supplement number and revision level This log should be used 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 This log lists the page number and revision level of every page in the supplement The log also lists the dates on which revisions to the supplement occurred Supplement page numbers will include an S and the supplement number preceding the page number The part number of the supplement provides information on the revision level Refer to the following example 162PHUS S1 00 L Revision Level of Supplement Supplement Number Cessna 162 U S Pilot s Operating Handbook Serials 16200001 and On 162PHUS 00 U S 10 1 10 2 CESSNA SECTION 10 MODEL 162 SUPPLEMENTS GARMIN G300 LOG OF APPROVED SUPPLEMENTS NOTE It is the airplane owner
188. nutes If the fire is not extinguished a rapid descent should be initiated and the electrical system turned back on This may provide airspeed and altitude data in preparation for a forced landing 6 30 U S 162PHUS 00 CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 EMERGENCY OPERATION IN CLOUDS The Model 162 Skycatcher is not equipped or certified for IFR flight The following instructions assume that the pilot is not very proficient at instrument flying and is flying the airplane without the autopilot engaged EXECUTING A 180 TURN IN CLOUDS ADAHRS FAILED Upon inadvertently entering the clouds an immediate turn to reverse course and return to VFR conditions should be made With ADAHRS FAILED magnetometer magnetic heading information 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 etc are also available with a functioning G300 system Refer to the G300 Pilot s Guide If the optional magnetic compass is installed the magnetic compass maybe used in place of the G300 compass arc The magnetic compass will be subject to normal magnetic compass A N D S variations duri
189. o the Preflight Inspection covered in Section 7 of this POH complete servicing inspection and test requirements for your airplane are detailed in the Maintenance Manual The Maintenance Manual outlines all items which require attention at specific intervals plus those items which require servicing inspection and or testing at special intervals Since Cessna 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 inspections or tests For these regulatory requirements owners should check with local aviation officials where the airplane is being operated For quick and ready reference quantities materials and specifications for frequently used service items are as follows 8 14 U S 162PHUS 00 CESSNA SECTION 8 MODEL 162 AIRPLANE HANDLING SERVICE GARMIN G300 AND MAINTENANCE OIL OIL SPECIFICATION SAE J1966 Aviation Grade Non Dispersant Mineral Oil Used when the airplane was delivered from the factory and should be used to replenish the supply during the first 25 hours This oil should be drained and the filter changed after the first 25 hours of operation Refill the engine with SAE J1966 Avi
190. of climb should be of the minimum duration and engine temperatures should be carefully monitored due to the low climb speed 162PHUS 01 U S 7 33 SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 CRUISE Normal cruise is performed between 40 and 75 power The engine RPM and corresponding fuel consumption for various altitudes can be determined by using the data in Section 5 NOTE Cruise flight should use 75 power as much as possible until the engine has operated for a total of 50 hours or oil consumption has stabilized Operation at this higher power will ensure proper seating of the piston 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 charts in Section 5 provide the pilot with flight planning information for the Model 162 in still air at maximum gross weight without speed fairings installed Cruise performance may differ slightly due to differences in weight and center of gravity location 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 consumption Proper leaning
191. of the gage measurement range of approximately Y tank At this level additional fuel may be available but no additional indication of the fuel will be visible A visual check of each wing tank fuel level must be performed prior to each flight Compare the visual fuel level 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 engine stoppage The fuel venting system consists of an interconnecting vent line between the fuel tanks and a check valve equipped overboard vent in the left fuel tank assembly The overboard vent protrudes from the bottom surface of the left wing just inboard of the wing strut upper attachment point The fuel filler caps are vacuum vented the fuel filler cap vents will open and allow air to enter the fuel tanks in case the overboard vents become blocked Continued Next Page 162PHUS 01 U S 2 17 SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 162 GARMIN G300 FUEL SYSTEM Continued REDUCED TANK CAPACITY The airplane may be serviced to a reduced capacity to permit heavier cabin loadings This is accomplished by filling each tank to the bottom edge of t
192. ol FULL push full in MIXTURE Control RICH above 5000 feet pressure altitude lean for maximum RPM Directional Control MAINTAIN use differential braking until rudder control becomes effective Elevator Control LIFT NOSEWHEEL AT 50 KIAS Climb Airspeed 65 75 KIAS Wing Flaps RETRACT at safe altitude SHORT FIELD TAKEOFF ED RA OO NE Wing Flaps 10 CARB HEAT Control Knob OFF push full in Brakes APPLY THROTTLE Control FULL push full in MIXTURE Control RICH above 5000 feet pressure altitude lean for maximum RPM Brakes RELEASE Elevator Control SLIGHTLY TAIL LOW Directional Control MAINTAIN use differential braking until rudder control becomes effective Climb Airspeed 55 KIAS until all obstacles are cleared Wing Flaps RETRACT SLOWLY when airspeed is more than 60 KIAS 162PHUS 01 U S 7 19 SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 ENROUTE CLIMB 1 2 3 Airspeed 65 75 KIAS THROTTLE Control FULL push full in MIXTURE Control RICH above 5000 feet pressure altitude lean for maximum RPM NOTE For maximum performance climb speeds refer to Section 5 Figure 5 5 Maximum Rate of Climb at 1320 Pounds CRUISE 1 2 3 Power 2400 2750 RPM 75 recommended Elevator Trim Control Switch ADJUST MIXTURE Control LEAN for best power setting DESCENT 1 2 3 4 5 Power AS DESIRED 2750 RPM maximum
193. onnected STUCK MICROPHONE The Garmin SL40 helps protect the pilot from a situation where the microphone may become stuck in the ON or transmit position If the microphone is keyed or activated for longer than 35 seconds the SL40 will return to the receive mode on the selected frequency A flashing STUCK MIC message will be displayed until the transmit key is released FAA APPROVED 162PHUS S7 00 U S S7 7 SECTION 10 SUPPLEMENTS CESSNA SUPPLEMENT 7 MODEL 162 GARMIN G300 PERFORMANCE There is no change to the airplane performance when the Garmin SL 40 VHF Comm Transceiver is installed FAA APPROVED S7 8 U S 162PHUS S7 00
194. ons 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 date mailing information to Cessna If you require a duplicate Owner Advisory to be sent to an address different from the aircraft registration address on file at Cessna please complete and return an Owner Advisory Application otherwise no action is required on your part INTERNATIONAL AIRPLANE OWNERS To receive Cessna Owner Advisories please complete and return an Owner Advisory Application 8 4 U S 162PHUS 01 CESSNA SECTION 8 MODEL 162 AIRPLANE HANDLING SERVICE GARMIN G300 AND MAINTENANCE PUBLICATIONS Various publications and flight operation aids are furnished in the airplane when delivered from the factory These items are listed below e Pilots Operating Handbook and Flight Training Supplement e Pilots Checklist e Garmin G300 Pilots Guide 190 00921 00 latest revision e Garmin G300 Cockpit Reference Guide CRG latest revision e Passenger Briefing Card e Customer Care Handbook To obtain additional publications or owner advisory information you may contact Cessna Customer Service at 316 517 5800 Fax 316 517 7271 or write to Cessna Aircraf
195. or change altitude to exit icing conditions Consider lateral or vertical flight path reversal to return to last known good flight conditions to obtain an outside air temperature that is less conducive to icing Maintain VER flight WARNING FAILURE TO ACT QUICKLY MAY RESULT IN AN UNRECOVERABLE ICING ENCOUNTER 2 CABIN HEAT Control Knob ON pull full out 3 A P DISC PRESS if installed verify autopilot disengages and aural alert is heard WARNING DO NOT ENGAGE AUTOPILOT WITH VISIBLE ICE ON AIRFRAME OR AFTER ENCOUNTERING 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 used continuously 5 Watch for ice accretion on pitot tube and signs of pitot static icing Airspeed and altimeter indications may become unreliable a Attitude and Heading information will remain reliable in event of airspeed and altimeter failure Use attitude indicator to monitor pitch and bank b Reference GS ground speed in conjunction with GPS derived wind information to determine an approximate airspeed Continued Next Page 162PHUS 01 U S 6 15 SECTION 6 CESSNA EMERGENCY PROCEDURES MO
196. or smoothest operation 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 until a slight drop in engine RPM is indicated This is the Best Power Cruise setting CAUTION EXCESSIVE LEANING WILL INCREASE ENGINE TEMPERATURES AND MAY DAMAGE ENGINE WHEN INCREASING POWER ENRICHEN MIXTURE THEN ADVANCE THE THROTTLE TO INCREASE RPM WHEN REDUCING POWER RETARD THROTTLE THEN ADJUST THE MIXTURE CONTROL Lean the mixture for maximum RPM during all operations at any altitude including those below 3000 feet when using 75 or less power Above 5000 feet mixture may be leaned for maximum RPM during full throttle climbs after engine has accumulated 50 hours Continued Next Page 162PHUS 01 U S 7 35 SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 CRUISE Continued LEANING WITH EXHAUST GAS TEMPERATURE EGT INDICATOR if installed The cruise performance data in this POH is based on the recommended lean mixture setting determined from the maximum or peak EGT at power settings of 75 MCP and lower EGT F is displayed with a vertical scale and pointer on the EIS ENGINE p
197. ositive STROBE Light Switch OFF AVN MASTER Switch ON MIXTURE Control LEAN as required U S 162PHUS 01 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 STARTING ENGINE With External Power if installed 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 External Power Continued 2 CARB HEAT Control Knob OFF push full in 3 THROTTLE Control AS REQUIRED a Engine COLD OPEN 1 4 INCH b Engine WARM CLOSED MIXTURE Control FULL RICH push full in AVN MASTER Switch OFF MASTER Switch ALT and BAT ON Engine Indicating System CHECK PARAMETERS verify no red X s through indicators VOLTS CHECK EIS ENGINE PAGE EDE 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 eventually unreadable If the G300 display becomes unreadable connect external power per the following procedure The battery may require servicing 9 AMPS CHECK verify discharge shown negative 10 MASTER Switch ALT and BAT OFF 11 EXTERNAL POWER CONNECT to external power receptacle 12 MASTER Switch
198. panel and receives power from a single lithium cell battery Duracell DL1 3 NB or manufactures approved equivalent CAUTION USE OF NON APPROVED BATTERIES WILL VOID MANUFACTURERS TSO 91A AND PRODUCT WARRANTIES The remote switch controls ELT operating modes from the flight crew station When the ELT main unit control switch is set to the ARM position the transmitter is energized only when the internal G switch senses longitudinal inertia forces per TSO C91a TSO C126 In emergency situations the transmitter can also be immediately energized by pressing the ON switch located within the remote switch assembly The AK 450 transmitter unit is located in the tailcone behind the baggage area On the ELT transmitter unit is a panel containing an ON OFF ARM switch and a transmitter warning light The ELT installation uses two different warnings to tell the pilot when the ELT is energized The aural warning is an unusual sound that is easily heard by the pilot The visual warning is a steady RED light located within the panel mounted remote switch that shows the pilot that the ELT has been activated When the AK 450 is energized the ELT transmits the standard swept tone signal on the international VHF frequency of 121 5 MHz and UHF frequency of 243 0 MHz until battery power is gone The 121 5 MHz signal is mainly used to pinpoint the beacon during search and rescue operations and is monitored by general aviation commercial aircraft
199. pplement CESSNA MODEL 162 Serials 16200001 and On SUPPLEMENT 3 PS ENGINEERING PM3000 INTERCOM SYSTEM SERIAL NO REGISTRATION NO This supplement must be inserted into Section 10 of the Pilot s Operating Handbook and Airplane Flight Manual when the PS Engineering PM3000 Intercom System is installed D Member of GAMA COPYRIGHT 2009 19 NOVEMBER 2009 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 162PHUS S3 00 U S S3 1 SECTION 10 SUPPLEMENTS CESSNA SUPPLEMENT 3 MODEL 162 GARMIN G300 SUPPLEMENT 3 PS ENGINEERING PM3000 INTERCOM SYSTEM Use the Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number Supplement Status Date Original Issue 19 November 2009 LOG OF EFFECTIVE PAGES Page Page Revision Number Status Number S3 1 thru S3 10 Original 0 S3 2 U S 162PHUS S3 00 CESSNA SECTION 10 SUPPLEMENTS MODEL 162 SUPPLEMENT 3 GARMIN G300 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that are currently active Airplane Serial Revision Incorporated Number Title Effectivity Incorporated in Airplane 162PHUS S3 00 U S S3 3 SECTION 10 SUPPLEMENTS CESSNA SUPPLEMENT 3 MODEL 162 GARMIN G30
200. 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 PERFORMANCE CHARTS Performance data is presented in tabular form to illustrate the effect of different variables Sufficiently detailed information is provided in the tables so that conservative values can be selected and used to determine the particular performance figure with reasonable accuracy 162PHUS 01 U S 5 3 SECTION 5 PERFORMANCE SAMPLE PROBLEM CESSNA MODEL 162 GARMIN G300 The following sample flight problem utilizes information from the various charts to determine the predicted performance data for a typical flight Assume the following information has already been determined AIRPLANE CONFIGURATION Takeoff weight Usable fuel TAKEOFF CONDITIONS Field pressure altitude Temperature Wind component along runway Field length CRUISE CONDITIONS Total distance Pressure altitude Temperature Expected wind enroute LANDING CONDITIONS Field pressure altitude Temperature Field length 1320 Pounds 24 0 Gallons 1500 Feet 28 C 16 C Above Standard 14 Knot Head Wind 3500 Feet 260 Nautical Miles 5500 Feet 20 C 16 C Above Standard 10 Knot Head Wind 2000 Feet 25 C 3000 Feet Continued Next Page 5 4 U S 1
201. pt in smooth air and then only with caution 162PHUS 02 CESSNA SECTION 3 MODEL 162 OPERATING LIMITATIONS GARMIN G300 AIRSPEED INDICATOR MARKINGS Airspeed indicator markings and their color code significance are shown in Figure 3 2 AIRSPEED INDICATOR MARKINGS KIAS VALUE OR MARKING RANGE SIGNIFICANCE Red Band Low airspeed warning White Band Full Flap Operating Range Lower limit is maximum weight Vso in landing configuration Upper limit is maximum speed permissible with flaps extended J Green Band Normal Operating Range Lower limit is maximum weight Vs at most forward C G with flaps retracted Upper limit is maximum structural cruising speed Yellow 124 148 Operations must be conducted with caution Band and only in smooth air Red Line gt 149 Maximum speed for all operations Flaps 25 85 Maximum Flaps 25 Operation Tick Mark Flaps 10 100 Maximum Flaps 10 Operation Tick Mark Vx Tick 57 Best Angle of Climb Air Speed Mark Vy Tick 62 Best Rate of Climb Air Speed Mark Figure 3 2 162PHUS 01 U S 3 5 SECTION 3 CESSNA OPERATING LIMITATIONS MODEL 162 GARMIN G300 POWERPLANT LIMITATIONS Engine Manufacturer Teledyne Continental Motors Engine Model Number O 200 D Maximum Power 100 BHP Rating Engine Operating Limits for Takeoff and Continuous Operations Maximum Engine Speed is SS ES se ooo 2750 RPM NOTE The static RPM range
202. quired 162PHUS 01 U S 6 17 SECTION 6 CESSNA EMERGENCY PROCEDURES MODEL 162 GARMIN G300 ABNORMAL LANDINGS Continued LANDING WITH A FLAT NOSE TIRE 1 2 EN vo Ok pede Approach NORMAL choose longest runway if possible Wing Flaps AS REQUIRED a 65 to 70 KIAS Flaps UP 10 b Below 65 KIAS Flaps 10 FULL Touchdown ON MAINS tail slightly low Elevator continue stick to full aft as airplane slows hold nosewheel off the ground as long as possible When nosewheel touches down maintain full up elevator as airplane slows to stop Directional Control MAINTAIN using full rudder control Attempt to limit differential braking Braking Use brakes only as needed to lessen chance of prop RU Rolling drag of the flat nose tire will increase braking effect DOOR OPEN IN FLIGHT DOE NIE WARNING INTENTIONAL FLIGHT WITH DOOR S OPEN IS PROHIBITED CABIN DOOR LEAVE OPEN do not attempt to close THROTTLE Control REDUCE as necessary Airspeed 80 KIAS or less Seat Belts CHECK verify secure and tight Cabin CHECK stow loose materials Land as soon as practical pipi WITH DOOR OPEN NEN QT 6 18 Wing Flaps AS REQUIRED a 65 to 70 KIAS Flaps UP 10 b Below 65 KIAS Flaps 10 FULL Landing Approach NORMAL limit sideslip angle if possible Touchdown NORMAL U S 162PHUS 01 CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 ELECTRICAL POWER SUPPL
203. r 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 Navigate using pilotage and GPS moving map if available Land as soon as possible 3 EIS Engine Indicating System RED X STILL DISPLAYED a If only the EIS is RED X no other PFD or MFD RED X is present continue monitoring Non emergency full throttle operation should be limited to prevent engine overspeed or exceeding temperatures Descents should be made at idle with carburetor heat applied b Land as soon as possible 4 Affected Indicator RED X HAS CLEARED indicator normal 5 Land as soon as practical 162PHUS 01 U S 6 23 SECTION 6 CESSNA EMERGENCY PROCEDURES MODEL 162 GARMIN G300 PFD MFD DISPLAY MALFUNCTION OR FAILURE PFD OR MFD DISPLAY BLACK NO INFORMATION WARNING DO NOT SELECT G300 MANUAL INTENSITY MODE BACKLIGHT INTENSITY SHOULD REMAIN IN THE AUTOMATIC MODE TO PREVENT AN UNREADABLE DISPLAY CONDITION 1 PANEL LIGHTS Control Knob FULL BRIGHT full clockwise rotation 2 PFD MFD Circuit Breaker CHECK IN a If open reset close circuit breaker If circuit breaker opens again do 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 BLAC
204. r to have the Cessna Service Station from whom you purchased the airplane accomplish this work 8 8 U S 162PHUS 01 CESSNA SECTION 8 MODEL 162 AIRPLANE HANDLING SERVICE GARMIN G300 AND MAINTENANCE PILOT CONDUCTED PREVENTIVE MAINTENANCE A certified pilot who owns or operates an airplane not used as an air carrier is authorized by 14 CFR 43 to perform limited maintenance on his her airplane Refer to 14 CFR 43 for a list of the specific maintenance operations which are allowed NOTE Pilots operating airplanes of other than U S registry should refer to the regulations of the country of certification for information on preventive maintenance that may be performed by pilots A current 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 alterations on the airplane to ensure that airworthiness of the airplane is not violated Alterations or repairs to the airplane must be accomplished by licensed personnel utilizing only Cessna Aircraft Company Approved components and Cessna Approved data such as Cessna Service Bulletins Cessna Approved Modification Kits and or Cessna Approved Maintenance Manuals 162
205. rakes or when the 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 wheel lock 2 Install a surface control lock over the fin and rudder 3 Tie sufficiently strong ropes or chains 700 pounds tensile strength to the wing tail and nose tiedown fittings and secure each rope or chain to a ramp tiedown 4 Install a pitot tube cover Continued Next Page 162PHUS 00 U S 8 11 SECTION 8 CESSNA AIRPLANE HANDLING SERVICE MODEL 162 AND MAINTENANCE GARMIN G300 GROUND HANDLING Continued JACKING When a requirement exists to jack the entire airplane off the ground or when wing jack points are used in the jacking operation refer to the Maintenance Manual for specific procedures and equipment required Individual main gear may be jacked by using the jack pad which is incorporated in the main landing gear strut When using the individual gear strut jack pad flexibility of the gear strut may cause the main wheel to slide inboard as the wheel is raised tilting the jack The jack must then be lowered for a second jacking operation Do not jack both main wheels simultaneously using th
206. re 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 airplane by serial number should be accomplished and the airplane should receive repetitive and required inspections Modifications not approved by Cessna may void warranties on the airplane since Cessna has no way of knowing the full effect on the overall airplane Operation of an airplane that has been modified may be a risk to the occupants and operating procedures and performance data set forth in the POH may no longer be considered accurate for the modified airplane 162PHUS 01 U S 8 3 SECTION 8 CESSNA AIRPLANE HANDLING SERVICE MODEL 162 AND MAINTENANCE GARMIN G300 IDENTIFICATION PLATE All correspondence regarding your airplane should include the Serial Number The Serial Number Model Number and ASTM Standard Number can be found on the Identification Plate located on the aft left tailcone CESSNA OWNER ADVISORIES Cessna Owner Advisories are sent to Cessna Aircraft FAA Registered owners of record at no charge to inform them about Safety Alerts mandatory Notice of Corrective Actions and or beneficial airplane service requirements and product changes Copies of the actual bulletins are available from Cessna Service Stati
207. re to retain radio communications This emergency situation will require the pilot and copilot to swap headsets or switch headset jacks The pilot s control stick PTT switch will still control all radio transmissions NORMAL PROCEDURES There is no change to the airplane normal procedures when the PS Engineering PM3000 Intercom System is installed PERFORMANCE There is no change to the airplane performance when the PS Engineering PM3000 Intercom System is installed S3 10 U S 162PHUS S3 00 E SS Pilot s Opera ing Handbook And Flight Training Supplement CESSNA MODEL 162 Serials 16200001 and On SUPPLEMENT 6 GARMIN GTX 327 TRANSPONDER SERIAL NO REGISTRATION NO This supplement must be inserted into Section 10 of the Pilot s Operating Handbook and Airplane Flight Manual when the Garmin GTX 327 Transponder is installed D Member of GAMA COPYRIGHT 2009 2 NOVEMBER 2009 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 162PHUS S6 00 U S S6 1 SECTION 10 SUPPLEMENTS CESSNA SUPPLEMENT 6 MODEL 162 GARMIN G300 SUPPLEMENT 6 GARMIN GTX 327 TRANSPONDER Use the Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number Supplement Status Date Original Issue 2 November 2009 LOG OF EFFECTIVE PAGES Page Page Revision Number Status Number S6 1 thru S6 7 S6 8 Original 0 FAA APPR
208. reater than 16 0 volts to 18 0 volts high warning A red X is displayed when the instrument is invalid or out of the data range A white pointer indicates actual system voltage When the system voltage is less than 12 5 volts a red LOW VOLTS CAS message is displayed on the bottom left side of G300 PFD attitude indicator 162PHUS 01 U S 2 21 SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 162 GARMIN G300 ELECTRICAL SYSTEM Continued CIRCUIT BREAKERS Individual system circuit breakers are found on the switch circuit breaker panel All circuit breakers on this panel are capable of being opened or disengaged from the electrical system by pulling straight out on the outer ring for emergency electrical load management Using the circuit breaker as a switch is discouraged since the practice will decrease the life of the circuit breaker he 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 the reset solenoids contained in the relay panel CAUTION EXCESSIVE ACTIVATION OF THE MAIN CB RESET SWITCH WILL DECREASE SOLENOID LIFE Activation of the MAIN CB RESET switch is not required during normal pre
209. rm the BEFORE TAKEOFF checklist if outside air temperatures are very cold After a suitable warm up period of 2 to 5 minutes at 1000 RPM slowly accelerate the engine to higher engine RPM The engine should not exceed 1700 RPM until oil temperature indicates more than 75 F 24 C and oil pressure is within the green band range 30 to 60 PSI Once engine oil pressure and oil temperature reach normal operating range perform the BEFORE TAKEOFF checklist followed 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 operations are conducted Refer to Section 10 Supplement 4 for installation and operational details HOT WEATHER OPERATIONS Refer to the general warm engine starting information under Starting Engine in this section Cabin doors may be left open for engine start and taxi if desired to aid cabin cooling Face the airplane into the wind when possible for additional cooling airflow and avoid prolonged engine operation on the ground Cabin doors must be closed for flight p162PHUS 01 U S 7 45 7 46 CESSNA SECTION 8 MODEL 162 AIRPLANE HANDLING SERVICE GARMIN G300 AND MAINTENANCE AIRPLANE HANDLIN
210. roughly familiar with the G300 operation page and information location and methods of accessing the GPS flight data before beginning any flight in the Model 162 Skycatcher It is recommended that the pilot step through each of the G300 emergency procedures in the Emergency Procedures Checklist for familiarization before operating the aircraft Failure of the G300 PFD display will cause an automatic reversion of the PFD display to the MFD display if installed Failure of the PFD without an installed MFD display will leave the pilot to rely largely on external cues for pilotage and navigation The Emergency Procedures Checklist contains suggestions for managing a successful PFD failure and landing It is recommended that the pilot become familiar with this checklist before operating the airplane 6 40 U S 162PHUS 01 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 NORMAL PROCEDURES TABLE OF CONTENTS Page Ma Le ne NA dd 7 3 Airspeeds For Normal Operation aa 7 3 NORMAL PROCEDURES 7 4 Preflight Inspection uoc SLEE SEE BOERE SEER EE SERES DLE 7 4 CAM cee APA eS 7 5 Left WING Scars a de RE Roa 7 6 Left Wing Leading Edge ee ee Es see ees 7 8 Left Wing Trailing EOOO EES BEE DES LEDE RE Ed 7 8 Empernriage ss sube etes ee RE te BERE EE RE Phim 7 8 Right Wing Trailing Edge ei ee ese ss ee es 7 9 RIAL aa a aio ii E pitch ht GAIA 7 9 NOSE nia cee IE dvi at can A
211. s 16200001 and On This comprehensive equipment list provides the following information in column form In the ITEM NO column each item is assigned a coded number The first two digits of the code represent the identification of the item within Air Transport Association Specification 100 11 for Paint and Placards 24 for Electrical Power 77 for Engine Indicating etc These assignments also correspond to the Maintenance Manual chapter for the airplane After the first two digits items receive a unique sequence number 01 02 03 etc After the sequence number a suffix letter is assigned to identify equipment as a required item a standard item or an optional item Suffix letters are as follows R Required items or equipment for ASTM certification S Standard equipment items O Optional equipment items replacing required or standard items A Optional equipment items which are in addition to required or standard items In the 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 provided on the weight in pounds and arm in inches of the equipment item NOTE Unless ot
212. s may be cleaned with 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 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 ABRASIVE SOAPS OR DETERGENTS WHICH CAUSE CORROSION OR SCRATCHES SHOULD NEVER BE USED ON THE PAINTED ALUMINUM STRUCTURE For complete information related to interior cleaning refer to the Maintenance Manual AVIONICS CARE The Garmin G300 and avionics displays have an anti reflective coating that is very sensitive to skin oils waxes ammonia and abrasive cleaners Clean the displays as described in the G300 Pilot s Guide 162PHUS 01 U S 8 25 8 26 CESSNA SECTION 9 MODEL 162 PLACARDS AND MARKINGS GARMIN G300 PLACARDS AND MARKINGS TABLE OF CONTENTS Page Airspeed Indicator Markings ooo 9 3 Powerplant Instrument Markings eee eee 9 4 mico pama Re REDE AA 9 5 162PHUS 00 U S 9 1 9 2 CESSNA SECTION 9 MODEL 162 PLACARDS AND MARKINGS GARMIN G300 AIRSPEED INDICATOR MARKINGS Airspeed indicator markings and their color code significance are shown in Figure 9 2 AIRSPEED INDICATOR MA
213. ssenger and baggage Forward pivoting seats allow access to the baggage area Wing struts and main landing gear legs attach to an I beam structure under the baggage area behind the seats Nose gear and engine mount assembly attach to the firewall separating the cabin from engine compartment The aft 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 through spars the wing is attached by forward spar to fuselage struts The wing empennage and flight control surfaces are also made of sheet metal spars ribs and skin semi monocoque construction with balance weights incorporated into the rudder elevators and ailerons FLIGHT CONTROLS The airplane s flight control system consists of conventional aileron rudder and elevator control surfaces manually operated through a cable system An elevator trim tab is located on the right elevator Trim tab operation is by direct linkage to a elevator mounted electric servo motor controlled by a control stick mounted trim switch Elevator trim tab position is displayed on the Engine Indicating System area of the G300 display Continued Next Page
214. ssential electrical equipment and avionics consider exterior lights and radio equipment because the battery can supply the electrical system for only a short time Reduce electrical load as soon as possible to extend the life of the battery for landing Land as soon as practical 162PHUS 00 U S 6 39 SECTION 6 CESSNA EMERGENCY PROCEDURES MODEL 162 GARMIN G300 OTHER EMERGENCIES WINDSHIELD DAMAGE If a bird strike or other incident should damage the windshield in flight to the point of creating an opening a significant loss in performance may be expected Decrease airspeed and set power as necessary to maintain best glide speed 70 KIAS to minimize stress on windshield and airframe structure If airplane performance or other adverse conditions prevent landing at an airport prepare for an off airport landing in accordance with the PRECAUTIONARY LANDING WITH ENGINE POWER or DITCHING checklists G300 FAILURES The Garmin G300 system provides all flight and engine instrument information via the Air Data Attitude and Heading Reference System ADAHRS unit Individual sensors within the ADAHRS unit provide air and flight data information as well as serve as the central gateway 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 tho
215. t The receptacle is located on the forward left side of the firewall and is accessed through a hinged door in the engine cowling Anytime an external power source of correct voltage and polarity is connected to the external power receptacle the power will be connected to the main battery regardless of MASTER switch position In order to power onboard equipment with the external power source the MASTER switch must be turned to the ON position 162PHUS 01 U S 2 93 SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 162 GARMIN G300 LIGHTING SYSTEMS EXTERIOR LIGHTING Exterior lighting consists of navigation strobe lights located on the wing tips and a landing taxi light located on the outboard left wing leading edge All exterior lights are operated by switches found on the switch circuit breaker panel assembly to the right of the PFD Exterior lights are grouped together in the LIGHTS section of the switch panel To activate the LDG landing taxi light NAV and STROBE light s place the switch in the up position Circuit breakers for the lights are found on the lower portion of the switch circuit breaker panel assembly INTERIOR LIGHTING Instrument panel pedestal and interior lighting is provided by an integral LED matrix 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 Airpla
216. t 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 supplemental information The following additional publications plus many other supplies that are applicable to your airplane are available from a Cessna Service Station e Information Manual contains Pilots Operating Handbook Information e Maintenance Manual Wiring Diagram Manual and Illustrated Parts Catalog Continued Next Page 162PHUS 01 U S 8 5 SECTION 8 CESSNA AIRPLANE HANDLING SERVICE MODEL 162 AND MAINTENANCE GARMIN G300 PUBLICATIONS Continued Cessna Service Stations have 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 8 6 U S 162PHUS 01 CESSNA SECTION 8 MODEL 162 AIRPLANE HANDLING SERVICE GARMIN G300 AND MAINTENANCE AIRPLANE FILE There are miscellaneous data information and licenses that are a part of the airplane file The following is a checklist for that file In addition a periodic check should be made
217. t X on left side of tailcone pe A 0 O 1270 2540 3810 5080 6350 7620 8890 10 160 Fuselage Station FS Millimeters NOTE It is the responsibility of the pilot to make sure that the airplane is loaded properly 091071002 Figure 4 2 Sheet 2 4 10 U S 162PHUS 01 CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE GARMIN G300 EQUIPMENT LIST AIRPLANE WEIGHING FORM U S UNITS B10721 Locating CG with Airplane on Landing Gear Nosewheel Weight xB 100 Inches Total Weight Jj Nose L R Wheel Weights X Inches Aft of Datum A Locating Percent MAC CG Arm of Airplane 121 50 Inches CG Percent MAC 0 480 Inches Measuring A and B Leveling Provisions Measure A and B per pilot s 3 operating handbook Longitudinal Left side of tailcone instructions to assist in locating at FS 218 61 Inches and 250 61 Inches CG with airplane weighed on landing gear Airplane as Weighed Table Position Scale reading Scale drift Tare Net weight Left Wheel Right Wheel Nose Wheel Airplane total as weighed Basic Empty Weight and Center of Gravity Table Moment Item Weg CaA Inch Pounds Pounds Inches 1000 f H Airplane calculated or as weighed includes all undrainable fluids and full oil Drainable unusable fuel at 6 0 pounds per 8 76 143 26 1 25 gallon 1 46 gallons
218. ted reset button c ARM ARMS transmitter for automatic activation if G switch senses a predetermined deceleration level EA N S2 6 U S 162PHUS S2 00 CESSNA SECTION 10 SUPPLEMENTS MODEL 162 SUPPLEMENT 2 GARMIN G300 GENERAL Continued AMERI KING AK 451 ELT REMOTE SWITCH PANEL B14688 1 2 3 O ELT Q O56 O ON ON RESET O 0918T1029 1 ON Button Remotely activates the transmitter for testing or emergency situations The GREEN ON light flashes to indicate the ELT transmitter is transmitting a distress signal 2 ON Light Transmitter ON light flashes GREEN to indicate the transmitter is transmitting a distress signal 3 RESET Reset button deactivates or de energizes the transmitter OPERATING LIMITATIONS There are no additional airplane operating limitations when the Ameri King AK 451 ELT is installed The airplane owner or operator must register the AK 451 ELT with the applicable civil aviation authority before use to make sure that the identification code transmitted by the ELT is in the COSPAS SARSAT database Refer to www cospas sarsat org for registration information Refer to 14 CFR 91 207 for ELT inspection requirements The AK 451 must be inspected and tested by an approved technician using the correct test equipment under the appropriate civil aviation authorities approved conditions 162PHUS S2 00 U S S2 7 SECTION 10 SUPPLEMENTS CESSNA SUPPLEMENT
219. tempt to clear ice from the windshield GPS moving map navigation may assist if ice creates a loss of visibility If available select G300 TERRAIN ON for additional altitude and obstacle awareness during reduced visibility Use of a forward slip can improve forward and over the nose landing visibility inhibited by windshield ice FLAPS should NOT be used for landing if airframe ice is present The autopilot if installed should be disconnected at first indication of airframe icing and remain disconnected after any icing encounter due to the possibility of unseen residual ice on the airframe 6 34 U S 162PHUS 00 CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 SPINS Should an inadvertent spin occur the following recovery procedure should be used 1 IMMEDIATELY RETARD THROTTLE TO IDLE POSITION 2 PLACE AILERONS IN NEUTRAL POSITION 3 APPLY AND HOLD FULL RUDDER OPPOSITE TO THE DIRECTION OF ROTATION AND MOVE CONTROL STICK BRISKLY FORWARD FAR ENOUGH TO BREAK THE STALL Full down elevator may be required at aft center of gravity loadings to assure optimum recoveries 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
220. ter from the induction air Airflow passing through the filter enters an air box which is equipped with a cable operated air door for cold air or pre heated air from a shroud around the exhaust for carburetor heat The pre heated air is also the source for alternate air if the air induction filter should become blocked The pre heated air is unfiltered and drawn through a scat tube in the cylinder baffles Use of full carburetor heat at full throttle will result in a loss of approximately 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 Ja single exhaust outlet Outside air is supplied to a shroud constructed around the outside of the muffler to form a heating chamber The air heated by the shroud is then supplied to the cabin COOLING SYSTEM Ram air for engine cooling enters through two intake openings in the front of the engine cowling The cooling air is directed from above the engine around the cylinders and other areas of the engine by baffling and then exits through an opening at the bottom aft edge of the engine cowling A winterization kit is available for the airplane Refer to Section 10 Supplement 4 for description and op
221. the vernier mixture control to lean of fuel mixture You may also have to lean the fuel mixture if this low engine speed results in power 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 sending unit or relief valve is malfunctioning Land at the nearest airport to determine the source of the problem If a total loss of oil pressure and a rise in oil temperature occur at about the same time it could mean that the engine is about to fail Reduce power immediately and select a field suitable for a forced landing Use only the minimum power necessary to reach the landing site 162PHUS 00 U S 6 37 SECTION 6 CESSNA EMERGENCY PROCEDURES MODEL 162 GARMIN G300 ELECTRICAL POWER SUPPLY SYSTEM MALFUNCTIONS Malfunctions in the electrical power supply system can be detected through regular monitoring of the main battery ammeter AMPS and the electrical bus voltmeter VOLTS however the cause of these malfunctions is usually difficult to determine A broken alternator shaft excessive brush wear or an internal wiring issue is most likely the cause of alternator failures although other factors
222. to give maximum RPM at full throttle with the airplane not moving After full throttle is applied adjust the throttle friction lock clockwise to prevent the throttle from moving back from a maximum power position Similar friction lock adjustments should be made as required in other flight conditions to 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 flap retraction speed of 60 KIAS is reached For a short field 10 wing flaps and an obstacle clearance speed of 55 KIAS should be used Soft or rough field takeoffs are performed with 10 flaps by lifting the airplane off the ground as soon as practical in a slightly tail low attitude If no obstacles are ahead the airplane should be leveled off immediately to accelerate to a higher climb speed When departing a soft field with an aft C G loading the elevator trim control should be adjusted towards the nose down direction to give comfortable control wheel forces during the initial climb 17 32 U S 162PHUS 01 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 TAKEOPFF Continued CROSSWIND TAKEOFF Takeoffs un
223. transmitter unit located in the tailcone 1 MAKE SURE THE ELT IS ENERGIZED a If the RED warning light in the remote switch panel is not illuminated press the ON switch within the remote switch panel to energize the ELT transmitter b Listen for the aural warning If the COM radio s operate and can be energized safely no threat of fire or explosion energize a COM radio and set the frequency to 121 5 MHz The ELT tone should be heard on the COM radio if the ELT is working correctly When done de energize the COM radio s to conserve the airplane battery power c Make sure that nothing is touching or blocking the ELT antenna 2 AFTER RESCUE Press the RESET button in the remote switch panel to de energize the ELT If the remote switch does not de energize the ELT press the RESET button on the ELT main control panel located in the tailcone 162PHUS S1 00 U S S1 7 SECTION 10 SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 162 GARMIN G300 NORMAL PROCEDURES When operating in a remote area or over hazardous terrain it is recommended that the ELT be inspected by an approved technician more frequently than required by 14 CFR 91 207 NORMAL OPERATION Normal operation of the AK 450 ELT from the flight crew station is only to de energize and arm the ELT after it has been accidentally energized no emergency For normal operation of the AK 450ELT the main switch on the ELT main control panel must be set to the ARM position You c
224. two sides The BAT side of the switch controls the electrical power to the airplane from both the main battery and secondary battery The ALT side of the switch controls the alternator system In normal operation both sides of the switch ALT and BAT are operated simultaneously However the BAT side of the switch may be selected separately as necessary The ALT side of the switch cannot be set to ON without the BAT side of the switch also being set to ON ELECTRICAL SYSTEM MONITORING Main battery current and system voltage indications are available on the PFD during single display operation and on the MFD when a second display is available MAIN BATTERY CURRENT AMPS The main battery current indication is shown on all G300 ElS 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 is shown on the G300 ENGINE page The tape display is 8 to 18 volts with digital information range from 30 to 30 volts The tape has a red band from 8 volts to less then 12 5 volts low warning a green band from 12 5 to 15 0 volts normal operating range a yellow band from 15 0 to 16 0 volts high caution and another red band from g
225. ty or straight grade oil may be used throughout the year for engine lubrication Refer to the following table for temperature versus viscosity ranges SAE J1966 SAE J1899 Non Dispersant Ashless Dispersant Oil Mineral Oil SAE Grade Temperature SAE Grade Above 4 C 40 F 50 50 or 15W 50 or 25W 60 Below 4 C 40 F 30 30 or 15W 50 or 25W 60 All Temperatures M20W 50 15W 50 20W 50 or 25W 60 NOTE When operating temperatures overlap use the lighter grade of oil OIL CAPACITY E 5 0 U S QUARTS 4 73 I MO PR ae QT UO EE SE EE 5 5 U S QUARTS 5 20 Minimum Operating Quantity 3 5 U S QUARTS 3 31 Continued Next Page 162PHUS 00 U S 1 7 SECTION 1 CESSNA GENERAL MODEL 162 GARMIN G300 DESCRIPTIVE DATA Continued MAXIMUM CERTIFICATED WEIGHTS Ramp Weight 2208s BERE a 1324 POUNDS 600 6 kg Takeoff Welght os vor ie 1320 POUNDS 598 8 kg Landing Weight aida 1320 POUNDS 598 8 kg MAXIMUM WEIGHT IN BAGGAGE COMPARTMENT Baggage Area Station 155 to 190 50 POUNDS 22 68 kg STANDARD AIRPLANE WEIGHTS Standard Empty Weight iese 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 si
226. ure from the air and the products of combustion combine to attack cylinder walls and bearing surfaces during periods when the airplane is not flown The minimum recommended operating frequency for the engine is one continuous flight hour not counting taxi 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 present environmental conditions and the frequency of airplane activity NOTE The engine manufacturer does not recommend pulling the engine through by hand during storage periods If the airplane is to remain inactive for more than 30 days consult the latest revision of Teledyne Continental Motors TCM Service Information Letter SIL99 1 or later revision www tcmlink com It is recommended when storing the airplane for any period of time to keep fuel tanks full to minimize condensation in tanks Keep the battery fully charged to prevent the electrolyte from freezing in cold weather Refer to the Maintenance Manual for proper airplane storage procedures 162PHUS 01 U S 8 13 SECTION 8 CESSNA AIRPLANE HANDLING SERVICE MODEL 162 AND MAINTENANCE GARMIN G300 SERVICING In addition t
227. ve 22 knots are not recommended 162PHUS 01 U S 7 41 SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 COLD WEATHER OPERATIONS Special consideration should be given to the operation of the airplane fuel system during the winter season or prior to any flight in cold temperatures Proper preflight draining of the fuel system is especially important and will eliminate any free water accumulation The use of additives such as isopropyl alcohol or Diethylene Glycol Monomethyl Ether DIEGME may also be desirable Refer to Section 8 Fuel Additives for more information on the proper use of fuel additives Cold weather often causes conditions that require special care during airplane operations Even small accumulations of frost ice or snow must be removed particularly from wing tail and all control surfaces to assure satisfactory flight performance and handling Also control surfaces must be free of any internal accumulations of ice or snow If snow or slush covers the takeoff surface allowance must be made for takeoff distances which will be increasingly 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
228. ved and discarded at the next revision to the POH Removal of temporary revisions from the POH is accomplished per the removal instructions on each temporary revision viii U S 162PHUS 00 CESSNA INTRODUCTION MODEL 162 GARMIN G300 IDENTIFYING REVISED MATERIAL A bar will extend the full length of deleted new or revised text added on new or previously existing pages This bar will be located adjacent to the applicable text in the margin on the left side of the page A bar in the footer will indicate a revision to the header footer a new page format or spelling 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 47 All revised pages will carry the revision number opposite the page number on the applicable page A list of revisions is located at the beginning of the Log Of Effective Pages 162PHUS 00 U S IX INTRODUCTION CESSNA MODEL 162 GARMIN G300 WARNINGS CAUTIONS AND NOTES Throughout the text warnings cautions and notes pertaining to airplane handling and operations are utilized These adjuncts to the text are used to highlight or emphasize important points WARNING OPERATING PROCEDURES
229. ward oil pressure port provides a signal to the engine display that is processed and shown as oil pressure Engine oil pressure is shown on all ElS pages The analog instrument range is O to 110 PSI with digital information range from O to 140 PSI The instrument has a red band from 0 to 10 PSI low warning a yellow band from 10 to 30 PSI low caution a green band from 30 to 60 PSI normal operating range a yellow band from 60 to 100 PSI high caution and a red band from 100 to 110 PSI high warning A white pointer indicates actual oil pressure When oil pressure is 0 to 10 PSI 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 green band adjust the engine speed to maintain adequate oil pressure When engine speed is at idle or near idle the oil pressure indication must be above the lower red band With the engine at normal operating oil temperature and engine speed at or close to idle oil pressure below the green band but above the lower red band is acceptable In cold weather the oil pressure will initially be high close to the upper red band when the engine is started As
230. wer than acceptable concentration level to the 35 gallons of fuel which now reside in the tank Continued Next Page 8 18 U S 162PHUS 00 CESSNA SECTION 8 MODEL 162 AIRPLANE HANDLING SERVICE GARMIN G300 AND MAINTENANCE FUEL Continued FUEL ADDITIVES Continued 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 is recommended 1 For best results the alcohol should be added during the fueling operation by pouring the alcohol directly on the fuel stream issuing from the fueling nozzle 2 An alternate method that may be used is to premix the complete alcohol dosage with some fuel in 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 HEALTH WHEN BREATHED AND OR ABSORBED INTO THE SKIN CAUTION MIXING OF DIEGME WITH FUEL IS EXTREMELY IMPORTANT

Model 162 - Cessna Flight Training

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