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Cessna SKYCATCHER 162 Pilot's Operating Handbook And Flight Training Supplement

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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
ORIGINAL ISSUE - 22 JULY 2009
CESSNA AIRCRAFT COMPANY
WICHITA, KANSAS, USA
REVISION 2 - 26 APRIL 2010
162PHUS-02
U.S.

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Summary of Contents for Cessna SKYCATCHER 162

  • Page 1 REGISTRATION NUMBER This publication includes the material required to be furnished to the pilot by ASTM F2245. COPYRIGHT © 2009 ORIGINAL ISSUE - 22 JULY 2009 CESSNA AIRCRAFT COMPANY WICHITA, KANSAS, USA REVISION 2 - 26 APRIL 2010 162PHUS-02 U.S.
  • Page 3 CESSNA INTRODUCTION MODEL 162 GARMIN G300 PILOT’S OPERATING HANDBOOK FLIGHT TRAINING SUPPLEMENT CESSNA MODEL 162 SERIALS 16200001 AND ON ORIGINAL ISSUE - 22 JULY 2009 REVISION 2 - 26 APRIL 2010 PART NUMBER: 162PHUS-02 162PHUS-02 i/ii U.S.

  • Page 5: Cessna Model

    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.
  • Page 6 (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.
  • Page 7 CESSNA INTRODUCTION MODEL 162 GARMIN G300 PERFORMANCE - SPECIFICATIONS (Continued) MAXIMUM WEIGHT: Ramp......1324 POUNDS (600.5 kg) Takeoff.
  • Page 8 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.
  • Page 9 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.
  • Page 10 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.
  • Page 11 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.
  • Page 12 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...

  • Page 13: Thru

    CESSNA INTRODUCTION MODEL 162 GARMIN G300 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.
  • Page 14 INTRODUCTION CESSNA MODEL 162 GARMIN G300 LOG OF EFFECTIVE PAGES (Continued) Page Page Revision Number Status Number 3-8 thru 3-13 Revised 3-14 Original 3-15 Revised 3-16 Original * 3-17 Revised 3-18 thru 3-19/3-20 Revised 4-1/4-2 thru 4-4 Original Revised Original...
  • Page 15 CESSNA INTRODUCTION MODEL 162 GARMIN G300 LOG OF EFFECTIVE PAGES (Continued) Page Page Revision Number Status Number 6-20 Revised 6-21 thru 6-22 Original 6-23 thru 6-26 Revised 6-27 thru 6-30 Original 6-31 thru 6-33 Revised 6-34 thru 6-39 Original 6-40...

  • Page 16: Table Of Contents

    INTRODUCTION CESSNA MODEL 162 GARMIN G300 LOG OF EFFECTIVE PAGES (Continued) Page Page Revision Number Status Number 9-1/9-2 Original Revised 9-4 thru 9-5 Original * 9-6 Revised 9-7 thru 9-8 Revised 10-1/10-2 Original 162PHUS-02 U.S.
  • Page 17 CESSNA INTRODUCTION MODEL 162 GARMIN G300 TABLE OF CONTENTS SECTION GENERAL ........1 AIRPLANE AND SYSTEM DESCRIPTION .

  • Page 19: Model

    CESSNA SECTION 1 MODEL 162 GENERAL GARMIN G300 GENERAL TABLE OF CONTENTS Page Three View - Normal Ground Attitude ......1-3 Introduction .

  • Page 21: Three View - Normal Ground Attitude

    CESSNA SECTION 1 MODEL 162 GENERAL GARMIN G300 THREE VIEW - NORMAL GROUND ATTITUDE Figure 1-1* (Sheet 1 of 2) 162PHUS-01 U.S.
  • Page 22 SECTION 1 CESSNA GENERAL MODEL 162 GARMIN G300 THREE VIEW - NORMAL GROUND ATTITUDE NOTE • Wing span shown with standard strobe lights installed. • Wheel base length is 62.40 inches (1.58 m). • Propeller ground clearance is 8.50 inches (215.90 mm).

  • Page 23: Introduction

    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 data and information of general interest.

  • Page 24: Fuel

    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)

  • Page 25: Oil

    CESSNA SECTION 1 MODEL 162 GENERAL GARMIN G300 DESCRIPTIVE DATA (Continued) 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.

  • Page 26: Maximum Certificated Weights

    SECTION 1 CESSNA GENERAL MODEL 162 GARMIN G300 DESCRIPTIVE DATA (Continued) MAXIMUM CERTIFICATED WEIGHTS Ramp Weight:......1324 POUNDS (600.6 kg) Takeoff Weight .
  • Page 27 CESSNA SECTION 2 MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION GARMIN G300 AIRPLANE AND SYSTEMS DESCRIPTION TABLE OF CONTENTS Page Introduction ..........2-3 Airframe .
  • Page 28 SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 162 GARMIN G300 TABLE OF CONTENTS Page Electrical System ........2-19 Master Switch .

  • Page 29: Introduction

    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.
  • Page 30 UP flaps position. The down- 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...

  • Page 31: Instrument Panel, Flight And System Instruments

    CESSNA SECTION 2 MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION GARMIN G300 INSTRUMENT PANEL, FLIGHT 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).

  • Page 32: Landing Gear And Brake System

    SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 162 GARMIN G300 INSTRUMENT PANEL, FLIGHT 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...

  • Page 33: Miscellaneous Cabin Features

    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.

  • Page 34: Engine

    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.

  • Page 35: Engine Instruments

    CESSNA SECTION 2 MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION GARMIN G300 ENGINE (Continued) ENGINE INSTRUMENTS The G300 Engine Indication System (EIS) provides the pilot graphical indicators and numerical values for Tachometer (RPM), Oil Pressure (OIL PSI), Oil Temperature (OIL ºF), Carburetor Temperature (CARB ºF), Battery Current (AMPS), and Elevator Trim Position (TRIM) along...

  • Page 36: Oil Pressure (Oil Psi)

    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 forward oil pressure port, provides a signal to the engine display that is processed and shown as oil pressure.

  • Page 37: Oil Temperature (Oil °F)

    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.

  • Page 38: Carburetor Temperature (Carb °F)

    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.

  • Page 39: Engine Lubrication System

    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.

  • Page 40: Air Induction System

    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 matter from the induction air.

  • Page 41: Propeller

    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.

  • Page 42: Fuel Indicating System

    SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 162 GARMIN G300 FUEL SYSTEM (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.

  • Page 43: Fuel Venting

    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...

  • Page 44: Reduced Tank Capacity

    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 the fuel filler indicator tab, thus giving a reduced fuel load of 3 gallons usable (minimum takeoff fuel) in each tank.

  • Page 45: Fuel Drain Valves

    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.
  • Page 46 SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 162 GARMIN G300 ELECTRICAL SYSTEM (Continued) Figure 2-4* 162PHUS-01 2-20 U.S.

  • Page 47: Master Switch

    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 two sides. The BAT side of the switch controls the electrical power to the airplane from both the main battery and secondary battery.

  • Page 48: Circuit Breakers

    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.

  • Page 49: 12V Power Outlet

    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.

  • Page 50: Lighting Systems

    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.

  • Page 51: Cabin Heating And Ventilating System

    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.
  • Page 53 CESSNA SECTION 3 MODEL 162 OPERATING LIMITATIONS GARMIN G300 OPERATING LIMITATIONS TABLE OF CONTENTS Page Introduction ..........3-3 Airspeed Limitations .

  • Page 55: Introduction

    • The airspeeds listed in Figure 3-1, Airspeed Limitations, are based on Airspeed Calibration data shown in Section The Cessna Model No. 162 is approved under ASTM standard F2245. 162PHUS-00 U.S.

  • Page 56: Airspeed Limitations

    SECTION 3 CESSNA OPERATING LIMITATIONS MODEL 162 GARMIN G300 AIRSPEED LIMITATIONS Airspeed limitations and their operational significance are shown in Figure 3-1. AIRSPEED LIMITATIONS SYMBOL SPEED KCAS KIAS REMARKS Stall Speed - Clean Stall speed flap up. Stall Speed - Landing...

  • Page 57: Airspeed Indicator Markings

    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 SIGNIFICANCE RANGE Red Band <37 Low airspeed warning.

  • Page 58: Powerplant Limitations

    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:......2750 RPM...

  • Page 59: Powerplant And Electrical Instrument Markings

    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 yellow range.

  • Page 60: Weight Limits

    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 .

  • Page 61: Maneuver Limits

    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.

  • Page 62: Kinds Of Operations Limits

    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 Operating Rules are defined by 14 CFR 91 and ASTM standard F2245, as applicable.

  • Page 63: Kinds Of Operations Equipment List

    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 Recommended to be accessible to pilot in flight.
  • Page 64 SECTION 3 CESSNA OPERATING LIMITATIONS MODEL 162 GARMIN G300 KINDS OF OPERATIONS EQUIPMENT LIST (Continued) KIND OF OPERATION System, Instrument, Equipment and/ or Function COMMENTS FUEL SYSTEM 1 - Fuel Shutoff Control Valve 2 - Cockpit Fuel Quantity Indicator -...
  • Page 65 CESSNA SECTION 3 MODEL 162 OPERATING LIMITATIONS GARMIN G300 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 2 - G300 Altimeter 3 - G300 Vertical Speed Indicator...

  • Page 66: Fuel Limitations

    SECTION 3 CESSNA OPERATING LIMITATIONS MODEL 162 GARMIN G300 FUEL LIMITATIONS Total Fuel: ......25.46 U.S. GALLONS (12.73 GALLONS per tank)

  • Page 67: System Limitations

    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.

  • Page 68: Placards

    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.
  • Page 69 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...
  • Page 70 SECTION 3 CESSNA OPERATING LIMITATIONS MODEL 162 GARMIN G300 PLACARDS (Continued) 9. On the right side of the baggage compartment below the window: 10. Near both fuel tank filler cap: 11. On the engine oil access door: (Continued Next Page)
  • Page 71 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: 13. Located on both left and right fuel sight tubes.
  • Page 73 CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE/ GARMIN G300 EQUIPMENT LIST WEIGHT AND BALANCE/ EQUIPMENT LIST TABLE OF CONTENTS Page Introduction ..........4-3 Comprehensive Equipment List .

  • Page 75: Introduction

    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.

  • Page 76: Comprehensive 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 (Serials 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.
  • Page 77 CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE/ GARMIN G300 EQUIPMENT LIST ITEM NO EQUIPMENT LIST DESCRIPTION DRAWING 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...

  • Page 78: Equipment List

    SECTION 4 CESSNA WEIGHT AND BALANCE/ MODEL 162 EQUIPMENT LIST GARMIN G300 ITEM NO EQUIPMENT LIST DESCRIPTION DRAWING 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 CLAMP AND HARDWARE 0.24...
  • Page 79 CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE/ GARMIN G300 EQUIPMENT LIST ITEM NO EQUIPMENT LIST DESCRIPTION DRAWING INS. 34 - NAVIGATION 34-01-R PFD DISPLAY - GDU 370 DISPLAY 0918101 1.56 121.56 34-02-O MFD DISPLAY - GDU 375 DISPLAY 0918502 2.40...

  • Page 80: Airplane Weighing Procedures

    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).

  • Page 81: Airplane Weighing Form

    CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE/ GARMIN G300 EQUIPMENT LIST AIRPLANE WEIGHING FORM - U.S. UNITS Figure 4-2* (Sheet 1 of 4) 162PHUS-01 U.S.
  • Page 82 SECTION 4 CESSNA WEIGHT AND BALANCE/ MODEL 162 EQUIPMENT LIST GARMIN G300 AIRPLANE WEIGHING FORM - METRIC UNITS Figure 4-2* (Sheet 2) 162PHUS-01 4-10 U.S.
  • Page 83 CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE/ GARMIN G300 EQUIPMENT LIST AIRPLANE WEIGHING FORM - U.S. UNITS Figure 4-2 (Sheet 3) 162PHUS-00 4-11 U.S.
  • Page 84 SECTION 4 CESSNA WEIGHT AND BALANCE/ MODEL 162 EQUIPMENT LIST GARMIN G300 AIRPLANE WEIGHING FORM - METRIC UNITS Figure 4-2 (Sheet 4) 162PHUS-00 4-12 U.S.
  • Page 85 CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE/ GARMIN G300 EQUIPMENT LIST SAMPLE WEIGHT AND BALANCE RECORD - U.S. Figure 4-3 (Sheet 1 of 2) 162PHUS-00 4-13 U.S.

  • Page 86: Sample Weight And Balance Record

    SECTION 4 CESSNA WEIGHT AND BALANCE/ MODEL 162 EQUIPMENT LIST GARMIN G300 SAMPLE WEIGHT AND BALANCE RECORD METRIC Figure 4-3 (Sheet 2) 162PHUS-00 4-14 U.S.

  • Page 87: 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...

  • Page 88: Baggage Tiedown

    SECTION 4 CESSNA WEIGHT AND BALANCE/ 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.

  • Page 89: Sample Loading Problem

    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) (lb-ins/ (lbs) (lb-ins/ 1000) 1000) 1 - Basic Empty Weight (Use the data pertaining to your airplane as it is presently equipped.
  • Page 90 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.
  • Page 91 CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE/ GARMIN G300 EQUIPMENT LIST SAMPLE LOADING PROBLEM - U.S. UNITS NOTE When several loading configurations are representative of your operations, it may be useful to fill out one or more of the above columns so specific loadings are available at a glance.
  • Page 92 SECTION 4 CESSNA WEIGHT AND BALANCE/ MODEL 162 EQUIPMENT LIST GARMIN G300 SAMPLE LOADING PROBLEM - METRIC UNITS YOUR YOUR YOUR AIRPLANE AIRPLANE AIRPLANE Weight Moment Weight Moment Weight Moment (Kgs) (Kgs-mm/ (Kgs) (Kgs-mm/ (Kgs) (Kgs-mm/ 1000) 1000) 1000) NOTE...

  • Page 93: Loading Graph

    CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE/ GARMIN G300 EQUIPMENT LIST LOADING GRAPH - U.S. UNITS Figure 4-5 (Sheet 1 of 2) 162PHUS-00 4-21 U.S.
  • Page 94 SECTION 4 CESSNA WEIGHT AND BALANCE/ MODEL 162 EQUIPMENT LIST GARMIN G300 LOADING GRAPH - METRIC UNITS Figure 4-5 (Sheet 2) 162PHUS-00 4-22 U.S.
  • Page 95 CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE/ GARMIN G300 EQUIPMENT LIST LOADING ARRANGEMENTS - U.S. UNITS *Pilot and front seat passenger center of gravity for average occupant. **Arm measured to the center of the areas shown. NOTE • All dimensions shown are in inches.
  • Page 96 SECTION 4 CESSNA WEIGHT AND BALANCE/ MODEL 162 EQUIPMENT LIST GARMIN G300 LOADING ARRANGEMENTS - METRIC UNITS *Pilot and front seat passenger center of gravity for average occupant. **Arm measured to the center of the areas shown. NOTE • All dimensions shown are in millimeters.
  • Page 97 CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE/ GARMIN G300 EQUIPMENT LIST INTERNAL CABIN DIMENSIONS - U.S. UNITS NOTE • Maximum weight in the baggage compartment area is 50 pounds with a maximum floor loading of 8 pounds per square foot.
  • Page 98 SECTION 4 CESSNA WEIGHT AND BALANCE/ MODEL 162 EQUIPMENT LIST GARMIN G300 INTERNAL CABIN DIMENSIONS - METRIC UNITS NOTE • Maximum weight in the baggage compartment area is 22.68 kilograms with a maximum floor loading of 39.05 kilograms per square meter.

  • Page 99: Center Of Gravity Moment Envelope

    CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE/ GARMIN G300 EQUIPMENT LIST CENTER OF GRAVITY MOMENT ENVELOPE - U.S. Figure 4-8 (Sheet 1 of 2) 162PHUS-00 4-27 U.S.
  • Page 100 SECTION 4 CESSNA WEIGHT AND BALANCE/ MODEL 162 EQUIPMENT LIST GARMIN G300 CENTER OF GRAVITY MOMENT ENVELOPE METRIC UNITS Figure 4-8 (Sheet 2) 162PHUS-00 4-28 U.S.
  • Page 101 CESSNA SECTION 4 MODEL 162 WEIGHT AND BALANCE/ GARMIN G300 EQUIPMENT LIST CENTER OF GRAVITY LIMITS - U.S. UNITS Figure 4-9 (Sheet 1 of 2) 162PHUS-00 4-29 U.S.
  • Page 102 SECTION 4 CESSNA WEIGHT AND BALANCE/ MODEL 162 EQUIPMENT LIST GARMIN G300 CENTER OF GRAVITY LIMITS - METRIC UNITS Figure 4-9 (Sheet 2) 162PHUS-00 4-30 U.S.
  • Page 103 CESSNA SECTION 5 MODEL 162 PERFORMANCE GARMIN G300 PERFORMANCE TABLE OF CONTENTS Page Introduction ..........5-3 Use of Performance Charts .

  • Page 105: Introduction

    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.

  • Page 106: Sample Problem

    SECTION 5 CESSNA PERFORMANCE MODEL 162 GARMIN G300 SAMPLE PROBLEM 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:...

  • Page 107: Takeoff

    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.

  • Page 108: Cruise

    SECTION 5 CESSNA PERFORMANCE MODEL 162 GARMIN G300 SAMPLE PROBLEM (Continued) 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.

  • Page 109: Fuel Required

    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.
  • Page 110 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...

  • Page 111: Landing

    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:...
  • Page 112 SECTION 5 CESSNA PERFORMANCE MODEL 162 GARMIN G300 Figure 5-1 162PHUS-00 5-10 U.S.
  • Page 113 CESSNA SECTION 5 MODEL 162 PERFORMANCE GARMIN G300 NOTE • Altitude loss during a stall recovery may be as much as 250 feet. • KIAS values are approximate. Figure 5-2 162PHUS-00 5-11 U.S.
  • Page 114 SECTION 5 CESSNA PERFORMANCE MODEL 162 GARMIN G300 Figure 5-3* 162PHUS-01 5-12 U.S.
  • Page 115 CESSNA SECTION 5 MODEL 162 PERFORMANCE GARMIN G300 Figure 5-4* 162PHUS-01 5-13 U.S.
  • Page 116 SECTION 5 CESSNA PERFORMANCE MODEL 162 GARMIN G300 Figure 5-5* 162PHUS-01 5-14 U.S.
  • Page 117 CESSNA SECTION 5 MODEL 162 PERFORMANCE GARMIN G300 Figure 5-6* 162PHUS-01 5-15 U.S.
  • Page 118 SECTION 5 CESSNA PERFORMANCE MODEL 162 GARMIN G300 Figure 5-7* 162PHUS-01 5-16 U.S.

  • Page 119: Temperature Conversion Chart

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

  • Page 120: Crosswind Component

    SECTION 5 CESSNA PERFORMANCE MODEL 162 GARMIN G300 CROSSWIND COMPONENT NOTE Maximum demonstrated crosswind velocity is 12 knots (not a limitation). Figure 5-9 162PHUS-00 5-18 U.S.
  • Page 121 CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 EMERGENCY PROCEDURES TABLE OF CONTENTS Page Introduction ..........6-5 Airspeeds For Emergency Operations.
  • Page 122 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.
  • Page 123 CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 TABLE OF CONTENTS (Continued) Page AMPLIFIED EMERGENCY PROCEDURES ....6-27 Engine Failure ......... 6-27 Maximum Glide .

  • Page 125: Introduction

    CESSNA SECTION 6 MODEL 162 EMERGENCY 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.

  • Page 126: Emergency Procedures

    SECTION 6 CESSNA EMERGENCY PROCEDURES 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 1.

  • Page 127: Engine Failure During Flight (Restart Procedures)

    CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 ENGINE FAILURES AND MALFUNCTIONS (Continued) ENGINE FAILURE DURING FLIGHT (Restart Procedures) 1. Airspeed - 70 KIAS (best glide speed) 2. THROTTLE Control - IDLE (pull full out) 3. CARB HEAT Control Knob - ON (pull full out) 4.
  • Page 128 SECTION 6 CESSNA EMERGENCY PROCEDURES MODEL 162 GARMIN G300 ENGINE FAILURES AND MALFUNCTIONS (Continued) CARB °F INDICATOR 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.

  • Page 129: Forced Landings

    CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 FORCED LANDINGS EMERGENCY LANDING WITHOUT ENGINE POWER 1. Seats and Seat Belts - SECURE 2. Airspeed -70 KIAS - Flaps UP 65 KIAS - Flaps 10° - FULL 3. MIXTURE Control - IDLE CUTOFF (pull full out) 4.

  • Page 130: Precautionary Landing With Engine Power

    SECTION 6 CESSNA 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.

  • Page 131: Ditching

    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) 2. Heavy Objects (in baggage area) - SECURE OR JETTISON (if possible) 3. Seats and Seat Belts - SECURE 4.

  • Page 132: Fires

    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. Power - 1800 RPM (for a few minutes) 3. Engine - SHUTDOWN (inspect for damage) IF ENGINE FAILS TO START 2.

  • Page 133: Electrical Fire Or Cabin Fire In Flight

    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.

  • Page 134: Wing Fire

    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 WARNING...

  • Page 135: Icing

    CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 ICING INADVERTENT ICING ENCOUNTER DURING FLIGHT 1. Turn back 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).
  • Page 136 SECTION 6 CESSNA EMERGENCY PROCEDURES MODEL 162 GARMIN G300 ICING (Continued) INADVERTENT ICING ENCOUNTER DURING FLIGHT (Continued) 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.

  • Page 137: Abnormal Landings

    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.

  • Page 138: Landing With A Flat Nose Tire

    SECTION 6 CESSNA EMERGENCY PROCEDURES MODEL 162 GARMIN G300 ABNORMAL LANDINGS (Continued) LANDING WITH A FLAT NOSE TIRE 1. Approach - NORMAL (choose longest runway if possible) 2. Wing Flaps - AS REQUIRED a. 65 to 70 KIAS - Flaps UP - 10°...

  • Page 139: Electrical Power Supply System Malfunctions

    CESSNA SECTION 6 MODEL 162 EMERGENCY PROCEDURES GARMIN G300 ELECTRICAL POWER SUPPLY 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.

  • Page 140: Low Volts Annunciator Comes On Or Volts Indication Below

    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...
  • Page 141 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: a.

  • Page 142: Volts Indication Above Green Band Range Or

    SECTION 6 CESSNA EMERGENCY PROCEDURES MODEL 162 GARMIN G300 ELECTRICAL 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.

  • Page 143: Air Data, Attitude And Heading Reference System (Adahrs) Failure

    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)) 1. ADAHRS Circuit Breaker - CHECK IN a.

  • Page 144: Pfd/Mfd Display Malfunction Or Failure

    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.

  • Page 145: Pfd Or Mfd Display Information Not Updating

    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.

  • Page 146: Electric Pitch Trim Failure

    SECTION 6 CESSNA EMERGENCY PROCEDURES MODEL 162 GARMIN G300 ELECTRIC PITCH TRIM FAILURE 1. AVN MASTER Switch - VERIFY ON 2. TRIM/AP Circuit Breaker - CHECK IN a. If open, reset (close) circuit breaker. If circuit breaker opens again, do not reset.

  • Page 147: Amplified Emergency Procedures

    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 refer in resolution of a specific emergency.

  • Page 148: Maximum Glide

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

  • Page 149: Forced Landings

    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...

  • Page 150: Landing Without Elevator Control

    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.

  • Page 151: Emergency Operation In Clouds

    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.

  • Page 152: Emergency Descent Through Clouds (Adahrs Failed)

    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.

  • Page 153: Recovery From Spiral Dive In The Clouds (Adahrs Failed)

    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.

  • Page 154: Inadvertent Flight Into Icing Conditions

    SECTION 6 CESSNA EMERGENCY PROCEDURES MODEL 162 GARMIN G300 INADVERTENT FLIGHT 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.

  • Page 155: Spins

    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.

  • Page 156: Rough Engine Operation Or Loss Of Power

    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;...

  • Page 157: Idle Power Engine Roughness

    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...

  • Page 158: Electrical Power Supply System Malfunctions

    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.

  • Page 159: Insufficient Rate Of Charge

    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.

  • Page 160: Other Emergencies

    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.
  • Page 161 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 NORMAL PROCEDURES TABLE OF CONTENTS Page Introduction ..........7-3 Airspeeds For Normal Operation .
  • Page 162 SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 TABLE OF CONTENTS (Continued) Page AMPLIFIED NORMAL PROCEDURES..... 7-23 Preflight Inspection........7-23 Before Starting Engine .

  • Page 163: Introduction

    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.

  • Page 164: Normal Procedures

    SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 NORMAL PROCEDURES PREFLIGHT INSPECTION NOTE Visually check airplane for general condition during walk- around inspection. Airplane should be parked in a normal ground attitude (refer to Figure 1-1) to make sure that fuel drain valves allow for accurate sampling.

  • Page 165: 6. Wing Flaps - Up

    CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 PREFLIGHT INSPECTION (Continued) CABIN 1. Pilot's Operating Handbook - AS REQUIRED 2. Garmin G300 Pilot’s Guide - AS REQUIRED 3. Pilot’s Checklist - AS REQUIRED 4. Parking Brake - SET 5. Control Stick Lock - REMOVE 6.

  • Page 166: Left Wing

    SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 PREFLIGHT INSPECTION (Continued) 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.
  • Page 167 CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 PREFLIGHT INSPECTION (Continued) 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.

  • Page 168: Left Wing Leading Edge

    SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 PREFLIGHT INSPECTION (Continued) LEFT WING Leading Edge 1. Fuel Tank Vent Opening - CHECK (blockage) 2. Wing Tiedown - DISCONNECT (check security and condition) 3. Pitot Tube Cover - REMOVE (check for pitot blockage) 4.

  • Page 169: Right Wing Trailing Edge

    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.
  • Page 170 SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 PREFLIGHT INSPECTION (Continued) RIGHT WING (Continued) 5. Fuel Filler Cap - SECURE and VENT CLEAR 6. Main Wheel Tire - CHECK (proper inflation and general condition (weather checks, tread depth and wear, etc.)) 7.

  • Page 171: Nose

    CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 PREFLIGHT INSPECTION (Continued) NOSE 1. Engine Cooling Air Inlets - CHECK (clear of obstructions) 2. Propeller and Spinner - CHECK (for nicks and security) 3. Air Filter - CHECK (for condition and blockage by dust or other foreign matter) 4.

  • Page 172: Garmin G300

    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...

  • Page 173: Before Starting Engine

    CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 BEFORE STARTING ENGINE 1. Preflight Inspection - COMPLETE 2. Passenger Briefing - COMPLETE 3. Rudder Pedals - ADJUST 4. Seat Belts - ADJUST and SECURE 5. Cabin Doors - AS DESIRED 6.

  • Page 174: Garmin G300

    SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 STARTING ENGINE (With Battery) (Continued) 5. AVN MASTER Switch - OFF 6. MASTER Switch (ALT and BAT) - ON 7. Engine Indicating System - CHECK PARAMETERS (verify no red X's through indicators) 8.

  • Page 175: Garmin G300

    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.

  • Page 176: Garmin G300

    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 red X's through indicators) 14. VOLTS - CHECK EIS ENGINE PAGE (verify 12.5 to 15.0 volts indication and LOW VOLTS annunciation is not shown) 15.

  • Page 177: Starting Engine (With External Power)

    CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 STARTING ENGINE (With External Power) (if installed) (Continued) 26. Internal Power - CHECK a. MASTER Switch (ALT) - OFF b. LDG Light Switch - ON c. NAV Light Switch - ON d.

  • Page 178: Before Takeoff

    SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 BEFORE TAKEOFF 1. Parking Brake - SET a. Brakes - Apply b. PARKING BRAKE Control Knob - ON (pull full out) 2. Seats and Seat Belts - CHECK SECURE 3. Cabin Doors - CLOSED and LOCKED 4.

  • Page 179: Takeoff

    CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 BEFORE TAKEOFF (Continued) 14. Annunciators - CHECK (verify no annunciators are shown) 15. THROTTLE Control - CHECK IDLE (900 RPM or LESS) 16. THROTTLE Control Friction Lock - ADJUST 17. COM Frequency - SET 18.

  • Page 180: Enroute Climb

    SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 ENROUTE CLIMB 1. Airspeed - 65 - 75 KIAS 2. THROTTLE Control - FULL (push full in) 3. MIXTURE Control - RICH (above 5000 feet pressure altitude, lean for maximum RPM)

  • Page 181: Wing Flaps 10° - Full

    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) 3.

  • Page 182: After Landing

    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.

  • Page 183: Amplified Normal Procedures

    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.

  • Page 184: Garmin G300

    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.

  • Page 185: Before Starting Engine

    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.

  • Page 186: Recommended Starter Duty Cycle

    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 open;...

  • Page 187: Leaning For Ground Operations

    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.

  • Page 188: Garmin G300

    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.

  • Page 189: Garmin G300

    CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 TAXIING (Continued) TAXIING DIAGRAM NOTE Strong quartering tail winds require caution. Avoid sudden bursts of the throttle and sharp braking when the airplane is in this attitude. Use differential braking and rudder to maintain direction.

  • Page 190: Before Takeoff

    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.

  • Page 191: Alternator Check

    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 MAGNETO check (1700 RPM) by setting all electrical equipment required for the flight to the ON position.

  • Page 192: Wing Flap Settings

    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.

  • Page 193: Crosswind Takeoff

    CESSNA SECTION 7 MODEL 162 NORMAL PROCEDURES GARMIN G300 TAKEOFF (Continued) CROSSWIND TAKEOFF Takeoffs under 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.

  • Page 194: Cruise

    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...

  • Page 195: Leaning Without Exhaust Gas Temperature (Egt) Indicator

    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 ºF display) to prevent ice from forming.

  • Page 196: Leaning With Exhaust Gas Temperature (Egt) Indicator

    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.

  • Page 197: Garmin G300

    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...

  • Page 198: Fuel Savings Procedures For Flight Training Operations

    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.

  • Page 199: Stalls

    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.

  • Page 200: Landing

    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.

  • Page 201: Crosswind Landing

    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. Sideslips 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.

  • Page 202: Cold Weather Operations

    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.

  • Page 203: Starting

    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.

  • Page 204: Garmin G300

    SECTION 7 CESSNA NORMAL PROCEDURES MODEL 162 GARMIN G300 COLD WEATHER OPERATION (Continued) STARTING (Continued) Cold weather starting procedures 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.

  • Page 205: Winterization Kit

    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 perform 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.

  • Page 207: Garmin G300

    Identification Plate ........8-4 Cessna Owner Advisories ....... . . 8-4 United States Airplane Owners .

  • Page 208: Garmin G300

    SECTION 8 CESSNA AIRPLANE HANDLING, SERVICE MODEL 162 AND MAINTENANCE GARMIN G300 TABLE OF CONTENTS (Continued) Page Fuel ..........8-17 Approved Fuel Grades (And Colors) .

  • Page 209: Introduction

    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 are necessary, as well as other seasonal and periodic services.

  • Page 210: Identification Plate

    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...

  • Page 211: Publications

    • 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 Aircraft Company, P.O. Box 7706, Wichita, KS 67277, Dept 569C. To obtain additional Garmin publications, you may contact Garmin...

  • Page 212: Garmin G300

    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.

  • Page 213: Airplane File

    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.

  • Page 214: Airplane Inspection Periods

    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...

  • Page 215: Pilot Conducted Preventive Maintenance

    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...

  • Page 216: Ground Handling

    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°...

  • Page 217: Parking

    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.

  • Page 218: Jacking

    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.

  • Page 219: Leveling

    CESSNA SECTION 8 MODEL 162 AIRPLANE HANDLING, SERVICE GARMIN G300 AND MAINTENANCE GROUND HANDLING (Continued) 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.

  • Page 220: Servicing

    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.

  • Page 221: Oil

    CESSNA SECTION 8 MODEL 162 AIRPLANE HANDLING, SERVICE GARMIN G300 AND MAINTENANCE 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.

  • Page 222: Capacity Of Engine Sump

    SECTION 8 CESSNA AIRPLANE HANDLING, SERVICE MODEL 162 AND MAINTENANCE GARMIN G300 (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.

  • Page 223: Fuel

    CESSNA SECTION 8 MODEL 162 AIRPLANE HANDLING, SERVICE GARMIN G300 AND MAINTENANCE FUEL APPROVED FUEL GRADES (AND COLORS) 100LL Grade Aviation Fuel (Blue) Grade Aviation Fuel (Green) NOTE Isopropyl alcohol 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.

  • Page 224: Fuel Additives

    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 solution in the gasoline, it will normally be consumed and go unnoticed in the operation of the engine.

  • Page 225: Garmin G300

    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.

  • Page 226: Garmin G300

    SECTION 8 CESSNA AIRPLANE HANDLING, SERVICE MODEL 162 AND MAINTENANCE GARMIN G300 FUEL (Continued) FUEL ADDITIVES (Continued) FUEL MIXING RATIO 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.

  • Page 227: Fuel Contamination

    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. 162PHUS-01 8-21 U.S.

  • Page 228: Landing Gear

    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...

  • Page 229: Painted Surfaces

    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.

  • Page 230: Propeller Care

    SECTION 8 CESSNA AIRPLANE HANDLING, SERVICE MODEL 162 AND MAINTENANCE GARMIN G300 CLEANING AND CARE (Continued) PROPELLER CARE 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.

  • Page 231: Interior Care

    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;...

  • Page 233: Garmin G300

    CESSNA SECTION 9 MODEL 162 PLACARDS AND MARKINGS GARMIN G300 PLACARDS AND MARKINGS TABLE OF CONTENTS Page Airspeed Indicator Markings ....... 9-3 Powerplant Instrument Markings .

  • Page 235: Garmin G300

    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 MARKINGS KIAS VALUE OR MARKING SIGNIFICANCE RANGE Red Band <37 Low airspeed warning.

  • Page 236: Garmin G300

    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.

  • Page 237: Garmin G300

    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.

  • Page 238: Garmin G300

    SECTION 9 CESSNA PLACARDS AND MARKINGS MODEL 162 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...

  • Page 239: Garmin G300

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

  • Page 240: Garmin G300

    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: 13. Located on both left and right fuel sight tubes: 162PHUS-01 U.S.

  • Page 241: Garmin G300

    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).

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