Pilot’s Operating Handbook and Flight Training Supplement

a standard equipped airplane. Section 10 contains the supplements which provide amended operating limitations, operating procedures, performance data and other necessary information for airplanes conducting special operations for both standard and optional equipment installed in the airplane. Supplements are individual 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. 162PHUS-01 vi CESSNA INTRODUCTION MODEL 162 GARMIN G300 U.S. 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: 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 in this POH. 162 PHUS -00 Revision Level (Original Issue) Manual (Pilot’s Operating Handbook, U.S.) (Serials 16200001 and On) Airplane Model - (162) 162PHUS-00 vii INTRODUCTION CESSNA MODEL 162 GARMIN G300 U.S. 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 removed 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. 162PHUS-00 viii CESSNA INTRODUCTION MODEL 162 GARMIN G300 U.S. 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 3-4*). 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. ix 162PHUS-00 INTRODUCTION CESSNA MODEL 162 GARMIN G300 U.S. 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, TECHNIQUES, ETC., WHICH CAN RESULT IN PERSONAL INJURY OR LOSS OF LIFE IF NOT CAREFULLY FOLLOWED. CAUTION OPERATION PROCEDURES, TECHNIQUES, ETC., WHICH CAN RESULT IN DAMAGE TO EQUIPMENT IF NOT CAREFULLY FOLLOWED. NOTE An operating procedure, technique, etc., which is considered essential to emphasize. 162PHUS-00 x CESSNA INTRODUCTION MODEL 162 GARMIN G300 U.S. 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. (Continued Next Page) Revision Level Date of Issue Original Issue 22 July 2009 Revision 2 26 April 2010 Revision 1 2 November 2009 Page Number Page Status Revision Number * Title Revised 2 * i/ii Revised 2 iii thru vi Revised 1 vii thru x Original 0 * xi thru xiv Revised 2 xv/xvi Added 1 1-1/1-2 Original 0 1-3 thru 1-5 Revised 1 1-6 thru 1-7 Original 0 1-8 Revised 1 2-1 thru 2-8 Revised 1 2-9 thru 2-10 Original 0 2-11 thru 2-12 Revised 1 2-13 Original 0 2-14 thru 2-25/2-26 Revised 1 3-1/3-2 Revised 1 3-3 Original 0 * 3-4 Revised 2 3-5 thru 3-6 Revised 1 3-7 Original 0 162PHUS-02 xi INTRODUCTION CESSNA MODEL 162 GARMIN G300 U.S. LOG OF EFFECTIVE PAGES (Continued) (Continued Next Page) Page Number Page Status Revision Number 3-8 thru 3-13 Revised 1 3-14 Original 0 3-15 Revised 1 3-16 Original 0 * 3-17 Revised 2 3-18 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 162PHUS-02 xii CESSNA INTRODUCTION MODEL 162 GARMIN G300 U.S. LOG OF EFFECTIVE PAGES (Continued) (Continued Next Page) Page Number Page Status Revision Number 6-20 Revised 1 6-21 thru 6-22 Original 0 6-23 thru 6-26 Revised 1 6-27 thru 6-30 Original 0 6-31 thru 6-33 Revised 1 6-34 thru 6-39 Original 0 6-40 Revised 1 7-1 thru 7-2 Revised 1 * 7-3 Revised 2 7-4 Original 0 7-5 Revised 1 7-6 thru 7-7 Original 0 7-8 thru 7-10 Revised 1 7-11 thru 7-12 Original 0 7-13 thru 7-16 Revised 1 7-17 Original 0 7-18 thru 7-21 Revised 1 7-22 thru 7-24 Original 0 7-25 thru 7-26 Revised 1 7-27 thru 7-29 Original 0 7-30 thru 7-41 Revised 1 7-42 thru 7-43 Original 0 7-44 thru 7-45/7-46 Revised 1 8-1 Original 0 8-2 thru 8-10 Revised 1 8-11 thru 8-12 Original 0 8-13 Revised 1 8-14 thru 8-18 Original 0 8-19 thru 8-25/8-26 Revised 1 162PHUS-02 xiii INTRODUCTION CESSNA MODEL 162 GARMIN G300 U.S. LOG OF EFFECTIVE PAGES (Continued) Page Number Page Status Revision Number 9-1/9-2 Original 0 9-3 Revised 1 9-4 thru 9-5 Original 0 * 9-6 Revised 2 9-7 thru 9-8 Revised 1 10-1/10-2 Original 0 162PHUS-02 xiv CESSNA INTRODUCTION MODEL 162 GARMIN G300 U.S. TABLE OF CONTENTS SECTION GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 AIRPLANE AND SYSTEM DESCRIPTION . . . . . . . . .2 OPERATING LIMITATIONS . . . . . . . . . . . . . . . . . . . . .3 WEIGHT AND BALANCE/EQUIPMENT LIST . . . . . . .4 PERFORMANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 EMERGENCY PROCEDURES . . . . . . . . . . . . . . . . . .6 NORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . .7 AIRCRAFT HANDLING, SERVICE AND MAINTENANCE . . . . . . . . . . . . . . . . . . . . . . . . .8 PLACARDS AND MARKINGS . . . . . . . . . . . . . . . . . . .9 SUPPLEMENTARY INFORMATION . . . . . . . . . . . . .10 162PHUS-01 xv/xvi CESSNA SECTION 1 MODEL 162 GENERAL GARMIN G300 U.S. GENERAL TABLE OF CONTENTS Page Three View - Normal Ground Attitude . . . . . . . . . . . . . . . . . . . . . . . . 1-3 Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-5 Descriptive Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-5 Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-5 Propeller . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-5 Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-6 Fuel Capacity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-6 Oil . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-7 Oil Specification. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-7 Oil Capacity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-7 Maximum Certificated Weights . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-8 Maximum Weight In Baggage Compartment . . . . . . . . . . . . . . . . 1-8 Standard Airplane Weights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-8 Cabin And Entry Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-8 Baggage Space And Entry Dimensions . . . . . . . . . . . . . . . . . . . . 1-8 Specific Loadings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-8 1-1/1-2 162PHUS-00 CESSNA SECTION 1 MODEL 162 GENERAL GARMIN G300 U.S. THREE VIEW - NORMAL GROUND ATTITUDE Figure 1-1* (Sheet 1 of 2) 1-3 162PHUS-01 SECTION 1 CESSNA GENERAL MODEL 162 GARMIN G300 U.S. 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). • Wing area is 120.0 square feet (11.15 sq. m). Figure 1-1* (Sheet 2) 162PHUS-01 1-4 CESSNA SECTION 1 MODEL 162 GENERAL GARMIN G300 U.S. 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 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) 1-5 162PHUS-01 SECTION 1 CESSNA GENERAL MODEL 162 GARMIN G300 U.S. 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 . . . . . . . . . . . . . . . . . 25.46 U.S. GALLONS (96.34 l) Total Usable . . . . . . . . . . . . . . . . . . . 24.00 U.S. GALLONS (90.82 l) Total Capacity Each Tank . . . . . . . . 12.73 U.S. GALLONS (48.17 l) Total Usable Each Tank . . . . . . . . . . 12.00 U.S. GALLONS (45.41 l) NOTE • To ensure maximum fuel capacity and minimize crossfeeding when refueling, always park the airplane in a wings level, normal ground attitude. Refer to Figure 1- 1 for normal ground attitude dimensions. • The fuel filler assembly is equipped with indicator tabs for 3/4, 1/2 and 1/4 fuel quantities. • 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 1-6 CESSNA SECTION 1 MODEL 162 GENERAL GARMIN G300 U.S. 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 Multiviscosity or straight grade oil may be used throughout the year for engine lubrication. Refer to the following table for temperature versus viscosity ranges. NOTE When operating temperatures overlap, use the lighter grade of oil. OIL CAPACITY Sump. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.0 U.S. QUARTS (4.73 l) Total. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.5 U.S. QUARTS (5.20 l) Minimum Operating Quantity . . . . . . . . . . 3.5 U.S. QUARTS (3.31 l) (Continued Next Page) Temperature SAE J1966 Non-Dispersant Mineral Oil SAE Grade SAE J1899 Ashless Dispersant Oil 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 1-7 162PHUS-00 SECTION 1 CESSNA GENERAL MODEL 162 GARMIN G300 U.S. DESCRIPTIVE DATA (Continued) MAXIMUM CERTIFICATED WEIGHTS Ramp Weight:. . . . . . . . . . . . . . . . . . . . . . . . 1324 POUNDS (600.6 kg) Takeoff Weight . . . . . . . . . . . . . . . . . . . . . . . 1320 POUNDS (598.8 kg) Landing Weight . . . . . . . . . . . . . . . . . . . . . . 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 . . . . . . . . . . . . . . . . . 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 . . . . . . . . . . . . . . . . . . . . . 11.0 lbs/sq. ft. (53.7 kg/sq. m) Power Loading . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.2 lbs/HP 162PHUS-01 1-8 CESSNA SECTION 2 MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION GARMIN G300 U.S. AIRPLANE AND SYSTEMS DESCRIPTION TABLE OF CONTENTS Page Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 Airframe . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 Instrument Panel, Flight and System Instruments . . . . . . . . . . . . . . . 2-5 Landing Gear and Brake System. . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6 Miscellaneous Cabin Features . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-7 Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8 Engine Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8 Engine Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9 Tachometer (RPM) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9 Oil Pressure (OIL PSI) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-10 Oil Temperature (OIL °F) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11 Exhaust Gas Temperature (EGT °F) (if installed) . . . . . . . . . . . . . 2-11 Carburetor Temperature (CARB °F) . . . . . . . . . . . . . . . . . . . . . . 2-12 New Engine Break-In And Operation . . . . . . . . . . . . . . . . . . . . . . 2-12 Engine Lubrication System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-13 Ignition And Starter System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-13 Air Induction System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14 Exhaust System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14 Cooling System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14 Propeller . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15 Fuel System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-15 Fuel Distribution . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15 Fuel Indicating System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-16 Fuel Venting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-17 Reduced Tank Capacity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-18 Fuel Drain Valves . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-19 162PHUS-01 2-1 SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 162 GARMIN G300 U.S. TABLE OF CONTENTS Page Electrical System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-19 Master Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-21 Electrical System Monitoring . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-21 Main Battery Current (Amps). . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-21 System Voltage (Volts) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-21 Circuit Breakers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-22 12V Power Outlet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-23 External Power Receptacle (if installed) . . . . . . . . . . . . . . . . . . . 2-23 Lighting Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-24 Exterior Lighting. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-24 Interior Lighting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-24 Cabin Heating and Ventilating System . . . . . . . . . . . . . . . . . . 2-25/2-26 Stall Warning System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-25/2-26 162PHUS-01 2-2 CESSNA SECTION 2 MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION GARMIN G300 U.S. 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, passenger, 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) 162PHUS-01 2-3 SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 162 GARMIN G300 U.S. 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, 10º, 25º, or FULL may be selected only after depressing the release button in the end of the flap handle. A control gust lock is provided. The control lock pins the left control stick through a bracket to immobilize the ailerons and elevator. Rudder is held centered by the springs used for increasing rudder pedal force. During the preflight walk-around inspection it is possible to move the ailerons into an over-centered position by moving the aileron down from the centered or faired with the flaps 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 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. 162PHUS-01 2-4 CESSNA SECTION 2 MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION GARMIN G300 U.S. 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 selectable 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. The 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 2-5 SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 162 GARMIN G300 U.S. 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 ¼ fuel requirement for take-off. In-tank fuel tabs are equipped with indicator holes for full, ¾, ½, and the bottom of the tab indicates ¼ (minimum takeoff). See Fuel System description section for more information. The optional magnetic compass (if installed) is mounted to the airplane structure above the center of the windshield. LANDING GEAR AND BRAKE SYSTEM The tricycle type landing gear on the Model 162 features tapered spring steel main gear legs and a spring steel nose gear with elastimetric pucks for shock absorption. The nose gear is free-castoring and directional control is done via differential 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. 162PHUS-01 2-6 CESSNA SECTION 2 MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION GARMIN G300 U.S. 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 placard. Pulling the external handle horizontally may damage the mechanism and door. The baggage area is accessed by tilting the seats forward and can accommodate up to 50 pounds of cargo. Tie-down rings are supplied to secure cargo. A tailcone close-out net is 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 2-7 SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 162 GARMIN G300 U.S. 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 in the full aft position. A friction lock, located at the base of the throttle control knob, is operated by rotating the lock clockwise to increase friction or counterclockwise to decrease friction. Engine fuel mixture is controlled by the mixture control. The mixture control is a red knob, with raised points around the circumference, located immediately to the right of the 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) 162PHUS-01 2-8 CESSNA SECTION 2 MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION GARMIN G300 U.S. 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 the top of the appropriate G300 Display. Additional indicators and numerical values for Exhaust Gas Temperature (EGT ºF), Electrical Bus Voltage (VOLTS), and Engine Hours (ENG HRS) are 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 2-9 SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 162 GARMIN G300 U.S. 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. Engine oil pressure is shown on all EIS pages. The analog instrument range is 0 to 110 PSI with digital information range from 0 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 the engine and oil warm up, the oil pressure will come down into the green band range. (Continued Next Page) 162PHUS-00 2-10 CESSNA SECTION 2 MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION GARMIN G300 U.S. 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 EIS 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°F (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. The white pointer indicates actual EGT temperature. Red digits are shown for values less than 0°F 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 2-11 SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 162 GARMIN G300 U.S. 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. 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) 162PHUS-01 2-12 CESSNA SECTION 2 MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION GARMIN G300 U.S. 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 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 2-13 SECTION 2 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 162 GARMIN G300 U.S. 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. 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 a 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 operating information. 162PHUS-01 2-14