Cessna 162 Skycatcher Aircraft Pilot. Operating Handbook (2009)

CESSNA

INTRODUCTION

MODEL 162

GARMIN G300

CONGRATULATIONS

Congratulations on your purchase and welcome to Cessna ownership!

Your Cessna has been designed and constructed to give you the most

in performance, value and comfort.

This Pilot’s Operating Handbook has been prepared as a guide to help

you get the most utility from your airplane. It contains information about

your airplane’s equipment, operating procedures, performance and

suggested service and care. Please study it carefully and use it as a

reference.

The worldwide Cessna Organization and Cessna Customer Service

are prepared to serve you. The following services are offered by each

Cessna Service Station:

• THE CESSNA AIRPLANE WARRANTIES, which provide coverage

for parts and labor, are upheld through Cessna Service Stations

worldwide. Warranty provisions and other important information are

contained in the Customer Care Handbook supplied with your

airplane. The Customer Care Card assigned to you at delivery will

establish your eligibility under warranty and should be presented to

your local Cessna Service Station at the time of warranty service.

• FACTORY TRAINED PERSONNEL to provide you with courteous,

expert service.

• FACTORY APPROVED SERVICE EQUIPMENT to provide you

efficient and accurate workmanship.

• A STOCK OF GENUINE CESSNA SERVICE PARTS are available

when you need them.

• THE LATEST AUTHORITATIVE INFORMATION FOR SERVICING

CESSNA AIRPLANES. Cessna Service Stations have all of the

current Maintenance Manuals, Illustrated Parts Catalogs and

various other support publications produced by Cessna Aircraft

Company.

Cessna

Service

Station

locator

available

www.cessnasupport.com.

We urge all Cessna owners/operators to utilize the benefits available

within the Cessna Organization.

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INTRODUCTION

CESSNA

MODEL 162

GARMIN G300

PERFORMANCE - SPECIFICATIONS

*SPEED:

Maximum at Sea Level

118 KNOTS (218.5 km/hr)

Cruise, 69% Power at 6000 Feet

109 KNOTS (201.9 km/hr)

CRUISE: Recommended lean mixture with fuel allowance for engine

start, taxi, takeoff, climb and 30 minutes reserve.

RANGE:

69% Power at 6000 Feet

Range - 336 NM

24 Gallons Usable Fuel

Time - 3.16 HOURS

RATE OF CLIMB AT SEA LEVEL

880 FPM (268.2 mpm)

SERVICE CEILING

14,625 FEET (4457.7 m)

TAKEOFF PERFORMANCE AT SEA LEVEL:

Ground Roll

640 FEET (195.1 m)

Total Distance Over 50 Foot Obstacle

1138 FEET (346.9 m)

LANDING PERFORMANCE AT SEA LEVEL:

Ground Roll

671 FEET (204.6 m)

Total Distance Over 50 Foot Obstacle

1369 FEET (417.3 m)

STALL SPEED:

Flaps UP, Power Idle

41 KIAS

Flaps FULL, Power Idle

37 KIAS

NOTE

* Speed performance is shown for airplanes not equipped

with the optional wheel fairings. Airplanes equipped with

optional wheel fairings will notice an increase in speeds by

approximately 2 knots. There is a corresponding difference

in range, while all other performance figures are

unchanged when speed fairings are installed.

The above performance figures are based on airplane weights at 1320

pounds (598.7 kg), standard atmospheric conditions, level, hard-

surfaced dry runways and no wind. They are calculated values derived

from flight tests conducted by Cessna Aircraft Company under carefully

documented conditions and will vary with individual airplanes and

numerous factors affecting flight performance.

(Continued Next Page)

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PERFORMANCE - SPECIFICATIONS (Continued)

MAXIMUM WEIGHT:

Ramp

1324 POUNDS (600.5 kg)

Takeoff

1320 POUNDS (598.7 kg)

Landing

1320 POUNDS (598.7 kg)

STANDARD EMPTY WEIGHT

834 POUNDS (378.3 kg)

MAXIMUM USEFUL LOAD

490 POUNDS (222.3 kg)

BAGGAGE ALLOWANCE

50 POUNDS (22.68 kg)

WING LOADING

11.0 lbs/sq. ft. (53.7 kg/sq m)

POWER LOADING

13.2 lbs/HP

FUEL CAPACITY (Usable)

24 GALLONS (90.8 l)

OIL CAPACITY (Sump)

5 QUARTS (4.73 I)

ENGINE: Teledyne Continental Motors

O-200D

100 BHP at 2750 RPM

PROPELLER:

Fixed Pitch, Diameter

67 INCHES (1.70 m)

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GARMIN G300

COVERAGE

The Pilot’s Operating Handbook (POH) in the airplane at the time of

delivery from Cessna Aircraft Company contains information applicable

to the Model 162 airplanes by serial number and registration number

shown on the Title Page. This POH is applicable to Model

162

airplanes, Serials 16200001 and On, equipped with Garmin G300

Integrated Cockpit System. All information is based on data available at

the time of publication.

This POH consists of ten sections that cover all operational aspects of

a standard equipped airplane. Section 10 contains the supplements

which provide amended operating limitations, operating procedures,

performance data and other necessary information for airplanes

conducting special operations for both standard and optional

equipment installed in the airplane.

Supplements are 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.

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ORIGINAL ISSUE AND REVISIONS

This Pilot’s Operating Handbook is comprised of the original issue and

any subsequent revisions. To make sure that information in this manual

is current, the revisions must be incorporated as they are issued. As

revisions are issued, they will be noted in the Log of Effective Pages.

The part number of this manual has also been designed to further aid

the owner/operator in determining the revision level of any POH. Refer

to the example below for a breakdown:

162

PHUS

-00

Revision Level (Original Issue)

Manual (Pilot’s Operating Handbook, U.S.)

(Serials 16200001 and On)

Airplane Model - (162)

It is the responsibility of the owner to maintain this POH in a current

status when it is being used for operational purposes. Owners should

contact a Cessna Service Station whenever the revision status of their

POH is in question.

Revisions are distributed to owners of U.S. Registered aircraft

according to FAA records at the time of revision issuance, and to

Internationally Registered aircraft according to Cessna Owner Advisory

records at the time of issuance. Revisions should be read carefully

upon receipt and incorporated in this POH.

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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.

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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.

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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.

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INTRODUCTION

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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.

Revision Level

Date of Issue

Original Issue

22 July 2009

Revision 2

26 April 2010

Revision 1

2 November 2009 Revision 3

28 September 2010

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SECTION 1

MODEL 162

GENERAL

GARMIN G300

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

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SECTION 1

MODEL 162

GENERAL

GARMIN G300

INTRODUCTION

This POH contains 10 sections, and includes the material required to

be furnished to the pilot by American Society for Testing and Materials

International (ASTM) standards F2245 for Light Sport Aircraft (LSA). It

also contains supplemental data supplied by Cessna Aircraft Company.

Section 1 provides basic 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:

Standard Composite Propeller - 1L100/LSA6754

Optional Aluminum Propeller - 1A162/TCD6754

Number of Blades: 2

Propeller Diameter: 67 inches (1.70 m)

Propeller Type: Fixed Pitch

(Continued Next Page)

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SECTION 1

CESSNA

GENERAL

MODEL 162

GARMIN G300

DESCRIPTIVE DATA (Continued)

FUEL

WARNING

USE OF UNAPPROVED FUELS MAY RESULT IN

DAMAGE TO THE ENGINE AND FUEL SYSTEM

COMPONENTS, RESULTING IN POSSIBLE ENGINE

FAILURE.

Approved Fuel Grades (and Colors):

100LL Grade Aviation Fuel (Blue)

100

Grade Aviation Fuel (Green)

NOTE

Isopropyl alcohol or Diethylene Glycol Monomethyl Ether

(DiEGME) may be added to the fuel supply in accordance

to TCM Service Information Letter (SIL99-2B). Refer to

Section 8 for additional information.

FUEL CAPACITY

Total Capacity

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)

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SECTION 1

MODEL 162

GENERAL

GARMIN G300

DESCRIPTIVE DATA (Continued)

OIL

OIL SPECIFICATION

SAE J1966 Aviation Grade Non-Dispersant Mineral Oil: Used when the

airplane was delivered from the factory and should be used to replenish

the supply during the first 25 hours. This oil should be drained and the

filter changed after the first 25 hours of operation. Refill the engine with

SAE J1966 Aviation Grade Non-Dispersant Mineral Oil and continue to

use until a total of 50 hours has accumulated or oil consumption has

stabilized.

SAE J1899 Aviation Grade Ashless Dispersant Oil: Oil conforming to

Teledyne Continental Motors (TCM) Service Information Letter SIL99-

2B, and all revisions and supplements thereto, must be used after first

50 hours or oil consumption has stabilized.

RECOMMENDED VISCOSITY FOR TEMPERATURE RANGE

Multiviscosity or straight grade oil may be used throughout the year for

engine lubrication. Refer to the following table for temperature versus

viscosity ranges.

SAE J1966

SAE J1899

Non-Dispersant

Ashless Dispersant Oil

Mineral Oil

SAE Grade

Temperature

SAE Grade

Above 4°C (40°F)

50 or 15W-50 or 25W-60

Below 4°C (40°F)

30 or 15W-50 or 25W-60

All Temperatures

M20W-50

15W-50, 20W- 50 or 25W-60

NOTE

When operating temperatures overlap, use the lighter

grade of oil.

OIL CAPACITY

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)

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SECTION 1

CESSNA

GENERAL

MODEL 162

GARMIN G300

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

490 POUNDS (222.3 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

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SECTION 2

MODEL 162

AIRPLANE AND SYSTEM DESCRIPTION

GARMIN G300

AIRPLANE AND SYSTEMS DESCRIPTION

TABLE OF CONTENTS

Page

Introduction

2-3

Airframe

2-3

Flight Controls and Trim System

2-4

Electric Trim System

2-9

Instrument Panel, Flight and System Instruments

2-10

Instrument Panel

2-12

Ground Control

2-14

Wing Flap System

2-15

Landing Gear

2-16

Baggage Area

2-17

Seats, Seat Belt and Shoulder Harness

2-18

Cabin Doors

2-21

Engine

2-24

Engine Controls

2-24

Engine Instruments

2-25

Tachometer (RPM)

2-25

Oil Pressure (OIL PSI)

2-26

Oil Temperature (OIL °F)

2-27

Exhaust Gas Temperature (EGT °F) (if installed)

2-27

Carburetor Temperature (CARB °F)

2-28

New Engine Break-In And Operation

2-28

Engine Lubrication System

2-29

Ignition And Starter System

2-29

Air Induction System

2-30

Exhaust System

2-30

Cooling System

2-30

Propeller

2-31

Fuel System

2-31

Fuel Distribution

2-31

Fuel Indicating System

2-33

Fuel Venting

2-34

Reduced Tank Capacity

2-35

Fuel Drain Valves

2-36

(Continued Next Page)

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AIRPLANE AND SYSTEM DESCRIPTION

MODEL 162

GARMIN G300

TABLE OF CONTENTS (Continued)

Page

Brake System

2-36

Electrical System

2-38

G300 Crew Alerting System (CAS)

2-40

Master Switch

2-40

Electrical System Monitoring

2-40

Main Battery Current (Amps)

2-40

System Voltage (Volts)

2-41

Circuit Breakers

2-41

12V Power Outlet

2-43

External Power Receptacle (if installed)

2-44

Lighting Systems

2-45

Exterior Lighting

2-45

Interior Lighting

2-45

Cabin Heating and Ventilating System

2-46

Pitot-Static System

2-48

Stall Warning System

2-48

Standard Avionics

2-49

Garmin Display Units (GDU)

2-49

Air Data, Attitude and Heading Reference System (ADAHRS)

and Magnetometer (GRS)

2-51

Garmin GTX 327 Transponder

2-52

Garmin SL 40 VHF Comm Transceiver

2-52

XM Weather and Radio Data Link (GDL) (if installed)

2-52

Avionics Support Equipment

2-53

Avionics Cooling Fans

2-53

Antennas

2-53

Microphone And Headset Installations

2-54

Auxiliary Audio Input Jack (if installed)

2-54

Cabin Features

2-55/2-56

Emergency Locator Transmitter (ELT)

2-55/2-56

Cabin Fire Extinguisher

2-55/2-56

2-2

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SECTION 2

MODEL 162

AIRPLANE AND SYSTEM DESCRIPTION

GARMIN G300

INTRODUCTION

This section provides description and operation of the airplane and its

systems. Some equipment described herein is optional and may not be

installed in the airplane. Refer to Section 10, Supplements, for details

of other optional systems and equipment.

AIRFRAME

The airplane is an all metal, two-place, high wing, single-engine

airplane equipped with tricycle landing gear and is designed for sport

flying and introductory training purposes.

The construction of the fuselage is a conventional formed sheet metal

bulkhead, stringer, and skin semi-monocoque construction. Wing struts

and main landing gear strut assemblies 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.

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AIRPLANE AND SYSTEM DESCRIPTION

MODEL 162

GARMIN G300

FLIGHT CONTROLS AND TRIM SYSTEM

The airplane's flight control system consists of conventional aileron,

rudder, and elevator control surfaces, refer to Figure 2-3. The control

surfaces are manually operated through cables and mechanical linkage

using a control stick for the ailerons and elevator, and rudder/brake

pedals for the rudder.

Dual under panel control sticks are used for aileron and elevator

control, refer to Figure 2-1. 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 armrest. The control lock provided with the airplane pins the

left control stick through a bracket attached to the instrument panel to

immobilize the ailerons and elevator. Rudder is held centered by the

springs used for increasing rudder pedal force.

CONTROL STICK

Figure 2-1*

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SECTION 2

MODEL 162

AIRPLANE AND SYSTEM DESCRIPTION

GARMIN G300

FLIGHT CONTROLS AND TRIM SYSTEM (Continued)

Rudder pedals, with toe brakes, provide rudder control through forward

and aft individually adjustable pilot and copilot pedal assemblies.

Rudder pedals should be adjusted before each flight, so that it is

possible to have full brake pedal deflection when the same side rudder

is fully deflected. Rotating the rudder pedal adjuster knob clockwise will

move the rudder pedals forward allowing more leg room for the pilot or

copilot. Rotating the knob counter-clockwise will move the pedals aft

bringing the pedals closer to the pilot.

RUDDER PEDALS

Figure 2-2*

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SECTION 2

CESSNA

AIRPLANE AND SYSTEM DESCRIPTION

MODEL 162

GARMIN G300

FLIGHT CONTROLS AND TRIM SYSTEM (Continued)

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 IS

NOT NORMAL AND SHOULD BE INSPECTED BY

MAINTENANCE PERSONNEL PRIOR TO FLIGHT.

2-8

U.S.

162PHUS-03

CESSNA

SECTION 2

MODEL 162

AIRPLANE AND SYSTEM DESCRIPTION

GARMIN G300

FLIGHT CONTROLS AND TRIM SYSTEM (Continued)

ELECTRIC TRIM 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 electric trim switch. Sliding the

trim switch up to the TRIM DN position will bring the nose of the

airplane down while sliding the trim switch down to the TRIM UP

position will trim the nose of the airplane up. Elevator trim tab position is

displayed on the Engine Indicating System (EIS) area of the Garmin

G300 display.

ELECTRIC TRIM SYSTEM

Figure 2-4*

162PHUS-03

U.S.

2-9

SECTION 2

CESSNA

AIRPLANE AND SYSTEM DESCRIPTION

MODEL 162

GARMIN G300

INSTRUMENT PANEL, FLIGHT AND SYSTEM

INSTRUMENTS

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 power switch (if installed) and below it is the

Ignition/Magneto key switch.

NOTE

Refer to the Garmin Pilot's Guide for details and operating

instructions of the G300 Avionics System.

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 GTX 327

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.

(Continued Next Page)

2-10

U.S.

162PHUS-03

CESSNA

SECTION 2

MODEL 162

AIRPLANE AND SYSTEM DESCRIPTION

GARMIN G300

INSTRUMENT PANEL, FLIGHT AND SYSTEM

INSTRUMENTS (Continued)

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 T-Handle, Fuel Shut-off Control

Knob and optional Fuel Primer Control Knob (if installed) are located

beneath the engine controls along the top of the vertical pedestal.

Headset Jacks, Auxiliary 12 Volt Cabin Power Outlet and Audio Input

Jack are positioned further down on the vertical pedestal.

Behind the instrument panel are the Autopilot Controller and Servo

Units for the Optional Autopilot System (if installed), 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 mounted in each wing root utilize floating balls for visual

indication of fuel quantity. Two fuel placards are used to differentiated

between level-flight (LVL FLT) and on-ground (GRND) fuel quantities.

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.

162PHUS-03

U.S.

2-11

CESSNA

SECTION 2

MODEL 162

AIRPLANE AND SYSTEM DESCRIPTION

GARMIN G300

INSTRUMENT PANEL

AUTOPILOT Power Switch (If installed)

Autopilot Controller Cover Plate - Autopilot controller located

behind instrument panel (If Installed).

Primary Flight Display (PFD)

MASTER Switch (ALT and BAT)

Switch Control Panel

Circuit Breaker Panel

PANEL LIGHTS Control Knob

Multifunction Display (MFD) (If installed)

ELT Remote Switch/Annunciator Panel (If installed)

10. PM3000 Intercom System Control Panel (If installed)

11.

CABIN HEAT Control Knob

12. MIXTURE Control Knob

13. FUEL SHUTOFF Valve Control Knob

14. Headset Jacks

15.

12V POWER OUTLET (7.5A)

16. AUX AUDIO INPUT Jack (If installed)

17. FUEL PRIMER Control Knob (If installed)

18. PARKING BRAKE Lock T-Handle

19. THROTTLE Control Knob (With Friction Lock)

20. CARB HEAT Control Knob

21. Garmin GTX 327 Transponder (If installed)

22. Garmin SL 40 VHF Comm Transceiver (If installed)

23. MAGNETOS/START Switch

162PHUS-03

U.S.

2-13

SECTION 2

CESSNA

AIRPLANE AND SYSTEM DESCRIPTION

MODEL 162

GARMIN G300

GROUND CONTROL

Effective ground control while taxiing is accomplished through a free-

castoring nosewheel by using the rudder pedals and differential

braking; left rudder pedal to steer left and right rudder pedal to steer

right. By applying either left or right brake, the degree of turn may be

increased up to 59° each side of center.

Moving the airplane by hand is most easily accomplished by attaching

a towbar to the nosewheel. If a towbar is not available, or pushing is

required, use the wing struts as push points. Do not use the vertical or

horizontal surfaces to move the airplane. If the airplane is to be towed

by vehicle, never turn the nosewheel more than 57.5° either side of

center or structural damage to the nose gear could result.

The minimum turning radius of the airplane, using differential braking

during taxi, is approximately 38 feet. To obtain a minimum radius turn

during ground handling, the airplane may be rotated around either main

landing gear by pressing down on a tailcone bulkhead just forward of

the horizontal stabilizer to raise the nosewheel off the ground. Care

should be exercised to ensure that pressure is exerted only on the

bulkhead area and not on skin between the bulkheads. Pressing down

on the horizontal stabilizer to raise the nosewheel off the ground is not

recommended.

2-14

U.S.

162PHUS-03

CESSNA

SECTION 2

MODEL 162

AIRPLANE AND SYSTEM DESCRIPTION

GARMIN G300

WING FLAP SYSTEM

The single slot type wing flaps, refer to Figure 2-6, are manually

operated down by a flap control handle located between the seats and

returned to the faired UP position by air load and return spring assist.

Flap control handle can be repositioned to the following detent

positions only after depressing the release button in the end of the flap

control handle.

Flaps UP

Fully Stowed (Flush Position)

Flaps 10º

First Notch

Flaps 25º

Second Notch

Flaps FULL

Last Notch (Full up Position)

Figure 2-6*

162PHUS-03

U.S.

2-15

SECTION 2

CESSNA

AIRPLANE AND SYSTEM DESCRIPTION

MODEL 162

GARMIN G300

LANDING GEAR

The tricycle type landing gear on the Model 162 features tapered spring

steel main gear strut assemblies and a spring steel nose gear with a

urethane spring for shock absorption, refer to Figure 2-7. The nose

wheel is free-castoring with directional control done via differential

braking. This permits very tight turning and maneuvering in confined

spaces. Full rudder deflection can assist directional control when

taxiing.

Figure 2-7*

2-16

U.S.

162PHUS-03

CESSNA

SECTION 2

MODEL 162

AIRPLANE AND SYSTEM DESCRIPTION

GARMIN G300

BAGGAGE AREA

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 in the baggage area. A aft bulkhead close-out net is

installed separating the baggage area from the aft tailcone. The net is

easily removed for maintenance access, but 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.

Figure 2-8*

162PHUS-03

U.S.

2-17

SECTION 2

CESSNA

AIRPLANE AND SYSTEM DESCRIPTION

MODEL 162

GARMIN G300

SEATS, SEAT BELT AND SHOULDER HARNESS

SEATS

The seating arrangement consists of two forward pivoting crew seats

for the pilot and copilot, which allow easy access to the baggage area.

Both seat positions are equipped with manually adjustable seat and

shoulder belts, refer to Figure 2-9.

SEAT BELTS

The seat belts are attached to airplane structure on the floorboard. The

buckle portion of the seat belt is located inboard of each seat, while the

link portion is located outboard of each seat location, refer to Figure 2-

To use the seat belts, lengthen the link portion of the lap belt as needed

by grasping the sides of the link and pulling outward against the belt.

Insert and lock the belt link into the buckle. Positive locking has

occurred when a distinctive “snap” sound is heard. Tighten belt as

needed to achieve proper fit. Proper installation of the lap belt can be

verified by ensuring that the lap belt is snug and low on the waist as

worn normally during flight.

To release the seat belts, grasp the top of the buckle opposite the link

and pull outward.

CAUTION

IF IT BECOMES NECESSARY TO REMOVE SEAT BEAT

OR SHOULDER HARNESS DURING FLIGHT USE CARE

TO MAKE SURE THAT SEAT BELT OR SHOULDER

HARNESS DOES NOT FALL UNDER THE SEAT WHERE

IT MAY NOT BE RETRIEVABLE WHILE SEATED IN THE

AIRPLANE.

(Continued Next Page)

2-18

U.S.

162PHUS-03

CESSNA

SECTION 2

MODEL 162

AIRPLANE AND SYSTEM DESCRIPTION

GARMIN G300

SEATS, SEAT BELT AND SHOULDER HARNESS

(Continued)

SHOULDER HARNESSES

Each shoulder harness, refer to Figure 2-9, is attached to the airplane

structure at the aft bulkhead.

To use a seat shoulder harness fasten and adjust the seat lap belt first.

Lengthen the shoulder harness as required by pulling on the

connecting link on the end of the harness and the narrow release strap.

Snap the connecting link firmly onto the retaining stud on the seat belt

link. Then adjust shoulder harness to proper length. A properly

adjusted harness will permit the occupant to lean forward enough to sit

completely erect, but prevent excessive forward movement and contact

with objects during sudden deceleration. Also, the pilot will want the

freedom to reach all controls easily.

Removing the shoulder harness is accomplished by pulling upward on

the narrow release strap, and removing the harness connecting link

from the stud on the seat belt link. In an emergency, the shoulder

harness may be removed by releasing the seat belt first, and allowing

the harness, still attached to the link portion of the seat belt, to drop to

the side of the seat.

CAUTION

MAKE SURE THAT THE SEAT BELTS ARE PROPERLY

STOWED PRIOR TO CLOSING CABIN DOOR. THE

DOOR SEAL AND/OR DOOR STRUCTURE CAN BE

DAMAGED IF DOOR COMES IN CONTACT WITH SEAT

BELT OR SHOULDER HARNESS BELT LINK WHILE

CLOSING.

162PHUS-03

U.S.

2-19

CESSNA

SECTION 2

MODEL 162

AIRPLANE AND SYSTEM DESCRIPTION

GARMIN G300

CABIN DOORS

Entry to and exit from the airplane is accomplished through either of

two upward opening cabin doors, one on each side of the cabin, refer to

Section 4 for cabin and cabin door dimensions. The cabin doors

incorporate a gas strut to assist in opening and holding the door in the

full up position, refer to Figure 2-10. Each door assembly is equipped

with a recessed exterior door handle/latch, interior door latch, fabric-

cover door strap/handle, key operated door lock and zippered cabin

door storage pocket.

WARNING

MAKE SURE BOTH EXTERIOR CABIN DOOR LOCK

ASSEMBLIES ARE UNLOCKED PRIOR TO FLIGHT.

CABIN DOORS CANNOT BE OPENED FROM INSIDE

THE AIRPLANE IF EXTERIOR CABIN DOOR LOCK IS

ENGAGED.

To open the cabin doors from outside the airplane, insert key and

unlock the cabin door lock by rotating the lock assembly

counterclockwise to the unlocked position. Rotate the door handle

downward to the OPEN position as indicated on the placard and gently

pull outward on the door. Allow the gas strut to raise door to the fully

open position and verify gas strut will support the door assembly and

that the door does not come in contact with the wing lower skin.

CAUTION

PULLING OUT HORIZONTALLY ON THE EXTERNAL

DOOR HANDLE/LATCH ASSEMBLY WILL DAMAGE THE

DOOR HANDLE MECHANISM AND OUTER DOOR SKIN.

To close cabin doors from outside the airplane, lower the cabin door

partially down to verify the exterior door handle/latch assembly is in the

OPEN position prior to pushing door closed. Make sure that both the

forward and aft latch mechanisms are fully seated prior to rotating the

exterior door handle/latch assembly to the closed or full up position.

Rotate cabin door lock clockwise to secure cabin door. Make sure door

is locked by carefully trying to rotate the exterior door handle/latch

assembly.

(Continued Next Page)

162PHUS-03

U.S.

2-21

SECTION 2

CESSNA

AIRPLANE AND SYSTEM DESCRIPTION

MODEL 162

GARMIN G300

CABIN DOORS (Continued)

CAUTION

THE CABIN DOOR ASSEMBLY SHOULD NOT BE

SLAMMED SHUT. THE DOORS DO NOT USE A PRE-

CATCH MECHANISM AND SHOULD NOT BE SLAMMED

CLOSED AS THIS CAN DAMAGE THE DOOR AND/OR

DOOR LATCH ASSEMBLY.

To close the cabin doors from inside the airplane, first secure seat belts

and make sure door openings are clear of obstructions. Then from a

seated position, reach out and grab the cabin door strap and carefully

pull the door to the fully closed position. Make sure that both the

forward and aft latch mechanisms are fully seated prior to sliding the

interior door latch assembly to the LATCHED full forward position. On

later models the interior door latch assembly will not move to the

LATCHED or full forward position if the forward latch mechanism is not

fully engaged. Lightly push on the front and rear lower areas of the door

to make sure the door is properly latched and secured for flight.

To open the cabin doors from inside the airplane, first hold the cabin

door strap and carefully pull in on the strap while sliding the interior

door latch assembly to the OPEN full aft position. Carefully push out on

the inside of door while holding onto the cabin door strap and slowly

allow door to raise to the full up position.

CAUTION

DURING HIGH WIND CONDITIONS EXTREME CARE

SHOULD BE TAKEN TO PREVENT THE CABIN DOOR

FROM BLOWING OPEN UPON OPENING, WHICH

COULD DAMAGE THE DOOR AND/OR LOWER WING

SKIN.

If cabin door should accidently come open during flight, leave cabin

door open and do not attempt to close, refer to Section 6, Emergency

Procedures, DOOR OPEN IN FLIGHT.

WARNING

INTENTIONAL FLIGHT WITH DOOR(S) OPEN IS

PROHIBITED.

2-22

U.S.

162PHUS-03

SECTION 2

CESSNA

AIRPLANE AND SYSTEM DESCRIPTION

MODEL 162

GARMIN G300

ENGINE

The airplane is powered by a normally aspirated, direct drive, air-

cooled, horizontally opposed, carbureted four cylinder engine with a

wet sump lubrication system. The engine is a Teledyne Continental O-

200-D rated at 100 horsepower at 2750 RPM. Major accessories

include a starter, gear-driven alternator, dual magnetos and a full flow

oil filter mounted on the rear of the engine accessory case.

ENGINE CONTROLS

Engine power is set using the throttle control. The throttle control is a

smooth black knob located at the center of the instrument panel. The

throttle control is configured so that the throttle is open in the forward

position and closed 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 the idle cutoff position is full aft. 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)

2-24

U.S.

162PHUS-03

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

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-03

U.S.

2-25

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.

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)

2-26

U.S.

162PHUS-03

CESSNA

SECTION 2

MODEL 162

AIRPLANE AND SYSTEM DESCRIPTION

GARMIN G300

ENGINE (Continued)

ENGINE INSTRUMENTS (Continued)

OIL TEMPERATURE (OIL °F)

The oil temperature sensor is installed in the engine oil filter adapter

and provides a signal to the engine display that is processed and

shown as oil temperature.

Engine oil temperature is shown on all 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-03

U.S.

2-27

SECTION 2

CESSNA

AIRPLANE AND SYSTEM DESCRIPTION

MODEL 162

GARMIN G300

ENGINE (Continued)

ENGINE INSTRUMENTS (Continued)

CARBURETOR TEMPERATURE (CARB °F)

Carburetor temperature is provided as a reference to determine the

potential for carburetor ice formation. The CARB °F indication is

provided on vertical tape and in digital form on the right side of the EIS

display atop the PFD and on the G300 ENGINE page. The tape display

range is from 20 to 80°F and the digital indication range is from -40°F to

100°F. A yellow caution range is depicted from 5°F to 40°F. A red-X is

displayed when the instrument is invalid or out of the data range.

NOTE

Although carburetor ice is more likely to form at

temperatures within the yellow band range, it can form at

temperatures outside the yellow caution range. If engine

roughness or unexplained RPM loss is encountered, full

carburetor heat should be immediately applied.

NEW ENGINE BREAK-IN AND OPERATION

The initial engine run-in was accomplished at the factory and is ready

for the full range of use. It is recommended that cruising be

accomplished at 75% power as much as practicable until a total of 50

hours has accumulated or oil consumption has stabilized. This will

ensure proper seating of the piston rings. Low cruise power settings

should be used for extended descents during the first 25 hours of new

engine operations. Avoid extended descents with reduced power

settings.

(Continued Next Page)

2-28

U.S.

162PHUS-03

CESSNA

SECTION 2

MODEL 162

AIRPLANE AND SYSTEM DESCRIPTION

GARMIN G300

ENGINE (Continued)

ENGINE LUBRICATION SYSTEM

The engine utilizes a full pressure, wet sump type lubrication system

with aviation grade oil as the lubricant. The capacity of the engine

sump, located on the bottom of the engine, along with the engine oil

filter and oil cooler is 5.5 quarts. Oil is drawn from the sump through a

filter screen on the end of a pickup tube to the engine driven oil pump.

Oil from the pump then passes through a full-flow oil filter, a pressure

relief valve at the rear of the right oil gallery, and an oil cooler before

lubricating engine parts. The oil returns to the sump by gravity. The filter

adapter in the full-flow filter is equipped with a bypass valve which will

cause lubricating oil to bypass the filter in the event the filter becomes

plugged, or the oil temperature is extremely cold.

An oil dipstick/filler tube is located at the left rear of the engine case.

The oil dipstick/filler tube is accessed through a door located on the left

side of the engine cowling. The engine should not be operated on less

than 3.5 quarts of oil. For extended flight, fill to 5.0 quarts (dipstick

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-03

U.S.

2-29

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. 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.

2-30

U.S.

162PHUS-03

CESSNA

SECTION 2

MODEL 162

AIRPLANE AND SYSTEM DESCRIPTION

GARMIN G300

PROPELLER

The airplane is equipped with a 67 inches diameter, two bladed, fixed

pitch, one-piece composite propeller incorporating a nickle leading

edge cap. An optional two bladed, fixed pitch, one-piece forged

aluminum alloy propeller, which is anodized to retard corrosion is also

available.

FUEL SYSTEM

The airplane fuel system, refer to Figure 2-12, consists of two vented

integral fuel tanks (one tank in each wing), fuel shutoff valve, and a fuel

strainer. The engine-mounted portion of the system consists of the

gravity-fed updraft float carburetor.

WARNING

UNUSABLE FUEL LEVELS FOR THIS AIRPLANE WERE

DETERMINED IN ACCORDANCE WITH ASTM

INTERNATIONAL

COMPLIANCE

STANDARDS.

FAILURE TO OPERATE THE AIRPLANE IN

COMPLIANCE WITH FUEL LIMITATIONS SPECIFIED IN

SECTION 3 MAY FURTHER REDUCE THE AMOUNT OF

FUEL AVAILABLE IN FLIGHT.

FUEL QUANTITY DATA IN U.S. GALLONS

FUEL LEVEL

TOTAL USABLE

FUEL

(QUANTITY

TOTAL

ALL FLIGHT

TANKS

EACH TANK)

FUEL

UNUSABLE

CONDITIONS

Two

Full (12.73)

25.46

1.46

24.0

Figure 2-11

FUEL DISTRIBUTION

Fuel flows by gravity from the two wing tanks to a fuel shutoff valve, the

fuel strainer, and to the carburetor. The carburetor meters fuel flow in

proportion to induction air flow and distributes to the cylinder intake

manifold.

162PHUS-03

U.S.

2-31

CESSNA

SECTION 2

MODEL 162

AIRPLANE AND SYSTEM DESCRIPTION

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. The fuel levels are aided with floating balls for increased

readability. There are two scales displayed on each fuel sight gage.

The aft scale shows fuel levels to be read in level flight. The markings

should not be relied upon for accurate readings during skids, slips or

unusual attitudes. The forward scale shows fuel levels as read on level

ground. Minimum takeoff is indicated when the center of the ball is at

the "MIN/TO" line on the forward scale in level ground attitude which

represents 3 gallons per side or 6 gallons total (1/4 tanks).

FUEL QUANTITY SIGHT GAGE

Figure 2-13

(Continued Next Page)

162PHUS-03

U.S.

2-33

SECTION 2

CESSNA

AIRPLANE AND SYSTEM DESCRIPTION

MODEL 162

GARMIN G300

FUEL SYSTEM (Continued)

FUEL INDICATING SYSTEM (Continued)

An empty tank is shown on the fuel quantity indicator as a red line on

the aft (Level Flight) scale along with the “E” indication. When an

indicator shows an empty tank, approximately 0.73 gallons of unusable

fuel remain in the tank. The fuel gage shows the fuel available in the

tank up to the limit of the gage measurement range of approximately ¾

tank. At this level, additional fuel may be available, but no additional

indication of the fuel will be visible. A visual check of each wing tank

fuel level must be performed prior to each flight. Compare the visual

fuel level and indicated fuel quantity to accurately estimate usable fuel.

WARNING

TAKEOFF IS PROHIBITED IF EITHER FUEL SIGHT

GAGE INDICATES BELOW THE MIN/TO INDICATION

(LESS THAN 1/4 TANK) OR BELOW THE BOTTOM OF

THE IN-TANK FUEL FILLER INDICATOR TAB.

FUEL VENTING

Fuel system venting is essential to system operation. Complete

blockage of the fuel venting system will result in decreasing fuel flow

and eventual engine stoppage. The fuel venting system consists of an

interconnecting vent line between the fuel tanks and a check valve

equipped overboard vent in the left fuel tank assembly. The overboard

vent protrudes from the bottom surface of the left wing, just inboard of

the wing strut upper attachment point. The fuel filler caps are vacuum

vented; the fuel filler cap vents will open and allow air to enter the fuel

tanks in case the overboard vents become blocked.

(Continued Next Page)

2-34

U.S.

162PHUS-03

CESSNA

SECTION 2

MODEL 162

AIRPLANE AND SYSTEM DESCRIPTION

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. Continued filling to

each subsequent hole in the indicator tab will add an additional 3

gallons usable fuel per tank. Do not fuel above top hole as fuel

expansion may cause overflow from fuel vent.

IN-TANK FUEL FILLER INDICATOR TAB

Figure 2-14

(Continued Next Page)

162PHUS-03

U.S.

2-35

SECTION 2

CESSNA

AIRPLANE AND SYSTEM DESCRIPTION

MODEL 162

GARMIN G300

FUEL SYSTEM (Continued)

FUEL DRAIN VALVES

The fuel system is equipped with 6 drain valves (4 in the wings and 2 in

the lower cowl) to provide a means for the examination of fuel in the

system for contamination and grade. The system should be examined

before each flight and after each refueling, by using the sampler cup

provided to drain fuel from each wing tank sump, the lower cowl fuel

shutoff valve drain and the fuel strainer sump lower cowl drain. If any

evidence of fuel contamination is found, it must be eliminated in

accordance with the preflight inspection checklist and the discussion in

Section 8. If takeoff weight limitations for the next flight permit, the fuel

tanks should be filled after each flight to prevent condensation.

BRAKE SYSTEM

Disc brakes located on the main gear wheels are hydraulically actuated

by master cylinders on each rudder pedal, refer to Figure 2-15. A

parking brake valve locks brake pressure to the disc calipers when the

parking brake handle on the lower instrument is pulled with the brake

pedals depressed. The hydraulic brake system is connected in series

running from the firewall mounted reservoir to the copilot's master

cylinder then to the pilot's master cylinder then to the brake caliper

through the parking brake valve.

2-36

U.S.

162PHUS-03

SECTION 2

CESSNA

AIRPLANE AND SYSTEM DESCRIPTION

MODEL 162

GARMIN G300

ELECTRICAL SYSTEM

The airplane is equipped with a 14-volt direct current (DC) electrical

system powered by an engine driven alternator, refer to Figure 2-16. A

12-volt main storage battery is located on the right forward side of the

firewall. The alternator and main battery are controlled by the MASTER

switch found on the switch/circuit breaker panel.

The alternator and main battery power is supplied to a relay panel

located on the left forward side of the firewall. Power for all electrical

circuits, except the secondary power circuit, is supplied from the relay

panel to the electrical bus located in the switch/circuit breaker panel.

The electrical bus is supplied with power anytime the MASTER switch

is turned on. The electrical bus provides power to the avionics bus

through the AVN MASTER switch. The avionics bus is supplied with

power anytime the MASTER switch and AVN MASTER switch are

turned on.

The optional autopilot system (if installed) is powered through the

avionics electrical bus via the AVN MASTER switch and is protected by

the TRIM/AP circuit breaker. An autopilot power switch is located to the

left of the PFD and supplies power to the autopilot system components

when selected to the AUTOPILOT position.

The electrical system is equipped with a secondary battery located

between the firewall and the instrument panel. This secondary battery

supplies power to the secondary power circuit for PANEL LIGHTS

dimming as well as stable power to the G300 avionics and displays

during engine start. This prevents undesired panel light dimming and

loss of G300 information resulting from voltage drop during the engine

start. The secondary battery is also controlled by the MASTER switch

found on the switch/circuit breaker panel. Power is supplied to

equipment on the secondary power circuit anytime the MASTER switch

is turned on.

(Continued Next Page)

2-38

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162PHUS-03

SECTION 2

CESSNA

AIRPLANE AND SYSTEM DESCRIPTION

MODEL 162

GARMIN G300

ELECTRICAL SYSTEM (Continued)

G300 CREW ALERTING SYSTEM (CAS)

All system alerts, cautions and warnings are shown on the PFD screen.

The following annunciations are supported:

LOW VOLTS

TRIM UP or TRIM DOWN (if installed)

TERRAIN

SET BARO

Refer to the Garmin G300 Pilot’s Guide for more information on CAS

system annunciations.

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. The ALT side of the switch

controls the alternator system.

In normal operation, both sides of the switch (ALT and BAT) are

operated simultaneously. However, the BAT side of the switch may be

selected separately as necessary. The ALT side of the switch cannot be

set to ON without the BAT side of the switch also being set to ON.

ELECTRICAL SYSTEM MONITORING

Main battery current, and system voltage indications are available on

the PFD during single display operation and on the MFD when a

second display is available.

MAIN BATTERY CURRENT (AMPS)

The main battery current indication is shown on all G300 EIS pages. A

positive number indicates a charging battery while a negative number

indicates a discharging battery. The tape display range is -35 to 35

amps with digital information range from -50 to 50 amps. A red-X is

displayed when the instrument is invalid or out of the data range. A

white pointer indicates actual current value.

(Continued Next Page)

2-40

U.S.

162PHUS-03

CESSNA

SECTION 2

MODEL 162

AIRPLANE AND SYSTEM DESCRIPTION

GARMIN G300

ELECTRICAL SYSTEM (Continued)

SYSTEM VOLTAGE (VOLTS)

Electrical system voltage is shown on the G300 ENGINE page. The

tape display is 8 to 18 volts with digital information range from -30 to 30

volts. The tape has a red band from 8 volts to less then 12.5 volts (low

warning), a green band from 12.5 to 15.0 volts (normal operating

range), a yellow band from 15.0 to 16.0 volts (high caution) and another

red band from greater than 16.0 volts to 18.0 volts (high warning). A

red-X is displayed when the instrument is invalid or out of the data

range. A white pointer indicates actual system voltage.

When the system voltage is less than 12.5 volts, a red LOW VOLTS

CAS message is displayed on the bottom left side of G300 PFD attitude

indicator.

CIRCUIT BREAKERS

Individual system circuit breakers are found on the switch/circuit

breaker panel, refer to Figure 2-17. All circuit breakers on this panel are

capable of being opened, or disengaged from the electrical system, by

pulling straight out on the outer ring for emergency electrical load

management. Using the circuit breaker as a switch is discouraged

since the practice will decrease the life of the circuit breaker.

The relay panel, located forward of the firewall, contains three circuit

breakers associated with the alternator, main power feeder, and

secondary power feeder. The alternator and main power circuit

breakers are capable of being reset in flight by momentarily pushing the

MAIN CB RESET switch located on the switch/circuit breaker panel.

Pushing the MAIN CB RESET switch activates the reset solenoids

contained in the relay panel.

CAUTION

EXCESSIVE ACTIVATION OF THE MAIN CB RESET

SWITCH WILL DECREASE SOLENOID LIFE.

Activation of the MAIN CB RESET switch is not required during normal

preflight operation.

(Continued Next Page)

162PHUS-03

U.S.

2-41

CESSNA

SECTION 2

MODEL 162

AIRPLANE AND SYSTEM DESCRIPTION

GARMIN G300

ELECTRICAL SYSTEM (Continued)

12V POWER OUTLET

A 12 volt power outlet connector (POWER OUTLET 12V - 7.5A) is

provided by an automotive style power outlet located on the center

pedestal. The power outlet receives electrical power from a dedicated

7.5 amp circuit breaker located in the switch/circuit breaker panel.

CAUTION

• CHARGING OF LITHIUM BATTERIES MAY CAUSE

THE LITHIUM BATTERIES TO EXPLODE.

• TAKE CARE TO OBSERVE THE MANUFACTURER'S

POWER REQUIREMENTS PRIOR TO PLUGGING

ANY DEVICE INTO THE 12 VOLT CABIN POWER

SYSTEM CONNECTOR. THIS SYSTEM IS LIMITED TO

A MAXIMUM OF 7.5 AMPS.

• USE CAUTION WITH POWER/ADAPTER CABLES IN

THE CABIN TO AVOID ENTANGLING OCCUPANTS

OR CABIN FURNISHINGS AND TO PREVENT

DAMAGE TO CABLES SUPPLYING LIVE ELECTRIC

CURRENT.

• DISCONNECT POWER/ADAPTER CABLES WHEN

NOT IN USE.

162PHUS-03

U.S.

2-43

SECTION 2

CESSNA

AIRPLANE AND SYSTEM DESCRIPTION

MODEL 162

GARMIN G300

ELECTRICAL SYSTEM (Continued)

EXTERNAL POWER RECEPTACLE (if installed)

The External Power Receptacle, if installed, allows the use of an

external power source for cold weather starting or for lengthy

maintenance work on electrical equipment. The receptacle is located

on the forward left side of the firewall and is accessed through a hinged

door in the engine cowling.

Anytime an external power source of correct voltage, 12.0 - 14.0 volts,

and polarity is connected to the external power receptacle, the power

will be connected to the main battery regardless of MASTER switch

position. In order to power onboard equipment with the external power

source, the MASTER switch must be turned to the ON position.

Figure 2-18*

2-44

U.S.

162PHUS-03

CESSNA

SECTION 2

MODEL 162

AIRPLANE AND SYSTEM DESCRIPTION

GARMIN G300

LIGHTING SYSTEMS

EXTERIOR LIGHTING

Exterior lighting consists of navigation/strobe lights located on the wing

tips and a landing/taxi light located on the outboard left wing leading

edge.

All exterior lights are operated by switches found on the switch circuit

breaker panel assembly to the right of the PFD. Exterior lights are

grouped together in the LIGHTS section of the switch panel. To activate

the LDG (landing/taxi light), NAV, and STROBE light(s), place the

switch in the up position. Circuit breakers for the lights are found on the

lower portion of the switch circuit breaker panel assembly.

INTERIOR LIGHTING

Instrument panel, pedestal and interior lighting is provided by an

integral LED matrix light assembly mounted on the overhead cabin

structure. Individual LEDs are directed at various instrument panel

locations and both fuel quantity indicators for night and low-light

illumination. Airplanes equipped with the BRS parachute option will

also have a LED light directed at the parachute deployment handle.

The PANEL LIGHTS dimming knob, located on the right side of the

electrical system switch/CB panel, controls intensity of the overhead

LED matrix lighting, non-stabilized magnetic compass internal lighting

(if installed) and Garmin G300 displays when the G300 display setup

backlight intensity is configured in the AUTO mode. Refer to the

Garmin Pilot’s Guide for detailed information on manually adjusting the

internal lighting on G300 displays.

Rotating the PANEL LIGHTS dimming knob full clockwise provides

maximum brightness while rotating the dimmer control knob

counterclockwise decreases light intensity from the highest level to off.

Power for the PANEL LIGHTS dimmer control is provided by the

secondary power circuit and protected by the SEC PWR circuit breaker.

162PHUS-03

U.S.

2-45

SECTION 2

CESSNA

AIRPLANE AND SYSTEM DESCRIPTION

MODEL 162

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, refer to Figure

2-19.

Cabin heat is controlled by a push-pull cable from the CABIN HEAT

control knob located on the lower instrument panel. When the CABIN

HEAT control knob is placed in the ON or full aft position, air is heated

as it is directed around the exhaust heat shroud and ducted to a air

control valve located on the firewall. With the air control valve in the on

position, warm air is directed towards the pilot's and front passenger’s

feet through various ducting located in the cabin. With the CABIN HEAT

control knob in the OFF or full forward position, preheated air is

redirected into the engine compartment through the air control valve

located on the firewall.

Cabin heat air volume will be reduced anytime you are operating with

the CARB HEAT in the on position. This is done to allow maximum heat

directed to the carburetor to prevent or alleviate carburetor ice. Always

use maximum CARB HEAT when carburetor icing is suspected.

Fresh air ducts direct ram air from the wing root openings to fresh air

valves located overhead at the outboard corners of the windshield.

These fresh air valves are equipped with directional control as well as

variable flow adjustment settings.

2-46

U.S.

162PHUS-03

SECTION 2

CESSNA

AIRPLANE AND SYSTEM DESCRIPTION

MODEL 162

GARMIN G300

PITOT-STATIC SYSTEM

The pitot-static system uses a total pressure (pitot) head mounted on

the lower surface of the left wing, external static port mounted on the

left side of the forward fuselage and associated plumbing to connect

the G300 ADAHRS unit and the optional autopilot control unit (if

installed).

STALL WARNING SYSTEM

Stall warning is a pneumatically operated by localized pressure

differential created by low pressure airflow around the wing and higher

static pressure internally. The stall warning horn will sound 5-8 knots

prior to stall buffet to provide notice to the pilot of impending stall. Horn

activation will not prevent a stall from occurring. When the horn sounds,

the pilot should react by initiating stall avoidance procedures (decrease

of angle of attack, increase airspeed, etc.). The stall warning system

does not require electrical power for operation. The stall warning

system opening located in the right wing should be checked during

preflight to make sure it is free of debris that might interfere with airflow

and correct operation. To check the system, place a clean cloth over

the vent opening and apply suction; a sound from the warning horn will

confirm system operation.

2-48

U.S.

162PHUS-03

CESSNA

SECTION 2

MODEL 162

AIRPLANE AND SYSTEM DESCRIPTION

GARMIN G300

STANDARD AVIONICS

The Garmin G300 Avionics System is an integrated flight control and

navigation system. The system combines primary flight instruments,

navigational, engine and electrical system information displayed on

color Liquid Crystal Display(s) (LCD). The G300 system consists of the

following pieces of equipment:

GARMIN DISPLAY UNITS (GDU)

The Cessna 162 can be configured with the standard single Garmin

Display Unit or the optional dual display installation.

SINGLE DISPLAY (Standard)

The primary flight instrument information and engine system

information will always be shown on the upper portion of the GDU and

the navigational or other menu selected information will be displayed

on the lower portion when configured in the split screen mode. Refer to

the Garmin Pilot’s Guide for system information and operating

instructions.

The upper portion of the GDU displays roll and pitch information,

heading and course navigation information, plus altitude, airspeed and

vertical speed information to the pilot. Engine and electrical information

are also displayed in the EIS strip as well as displaying warning/status

annunciations of airplane systems. Autopilot system information will be

displayed along the upper portion of the GDU if the optional autopilot

system is installed.

The lower portion of the GDU displays navigation information. The

navigation information can be configured with the Horizontal Situation

Indicator (HSI) display as default or one of the other menu driven map

displays including a large scalable, moving map that corresponds to the

airplane's current location. Data from other components of the system

can be overlaid on this map. Lightning and weather information can all

be displayed on the lower portion of the GDU display.

(Continued Next Page)

162PHUS-03

U.S.

2-49

SECTION 2

CESSNA

AIRPLANE AND SYSTEM DESCRIPTION

MODEL 162

GARMIN G300

STANDARD AVIONICS (Continued)

GARMIN DISPLAY UNITS (GDU) (Continued)

DUAL DISPLAYS (Optional)

When the dual display option is installed, the GDU located in front of

the pilot is automatically configured as a PFD and the second GDU

located to the right, is automatically configured as a MFD. Refer to the

Garmin Pilot’s Guide for system information and operating instructions.

The top or upper portion of the PFD displays roll and pitch information,

heading and course navigation information, plus altitude, airspeed and

vertical speed information to the pilot as well as displaying warning/

status annunciations of airplane systems. Autopilot system information

will be displayed along the upper portion of the PFD attitude display if

the optional autopilot system is installed. The lower portion of the PFD

will display the HSI and navigation information. All other map functions,

engine and electrical information move over to the MFD.

The MFD displays a large scalable, moving map that corresponds to

the airplane's current location. Data from other components of the

system can be overlaid on this map. Lightning and weather information

can also be displayed on the MFD. The dual display MFD becomes the

principle display for all of the engine, fuel, and electrical system

parameters on the EIS strip along the top portion of the MFD and MFD

engine pages.

During a single display failure, the Garmin G300 installation will

automatically revert into backup mode and display all flight information

and basic engine information on the remaining display. This feature

allows the pilot full access to all necessary information should either of

the display screens malfunction. XM radio and WX weather systems

information will continue to operate during a PFD display failure, but will

become inoperative during a MFD display failure due to system

components being integrated into the MFD display unit.

(Continued Next Page)

2-50

U.S.

162PHUS-03

CESSNA

SECTION 2

MODEL 162

AIRPLANE AND SYSTEM DESCRIPTION

GARMIN G300

STANDARD AVIONICS (Continued)

AIR DATA, ATTITUDE AND HEADING REFERENCE

SYSTEM (ADAHRS) AND MAGNETOMETER (GRS)

The ADAHRS provides airplane attitude and flight characteristics

information to the G300 displays integrated avionics units. The

ADAHRS unit, located behind the instrument panel, contains

accelerometers, tilt sensors and rate sensors that replace spinning

mass gyros used in other airplanes. The magnetometer, located in the

tailcone, interfaces with the ADAHRS to provide heading information.

The air data portion of the ADAHARS compiles information from the

airplane's pitot-static system to calculate pressure altitude, airspeed,

true airspeed, vertical speed and outside air temperature. An outside

air temperature probe, mounted on top of the cabin, is connected to the

ADAHRS.

The engine monitor portion of the ADAHARS is responsible for

receiving and processing the signals from all of the engine and airframe

sensors. It is connected to engine RPM, CARB TEMP and EGT

sensors along with receiving information from the electrical system

components. This unit transmits this information to the engine display

computers.

(Continued Next Page)

162PHUS-03

U.S.

2-51

SECTION 2

CESSNA

AIRPLANE AND SYSTEM DESCRIPTION

MODEL 162

GARMIN G300

STANDARD AVIONICS (Continued)

GARMIN GTX 327 TRANSPONDER

Refer to Section

10, Supplement

6 for appropriate transponder

operating information.

GARMIN SL 40 VHF COMM TRANSCEIVER

Refer to Section

10, Supplement

7 for appropriate transceiver

operating information.

XM WEATHER AND RADIO DATA LINK (GDL) (if installed)

The optional XM weather and radio data link provides weather

information and digital audio entertainment in the cockpit. The XM

receiver unit is part of the optional MFD second display. XM weather

and XM radio operate in the S-band frequency range to provide

continuous uplink capabilities at any altitude throughout North America.

A subscription to the XM satellite radio service is required for the XM

weather and radio data link to be used. Refer to the Garmin Pilot’s

Guide for system information and operating instructions.

2-52

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162PHUS-03

CESSNA

SECTION 2

MODEL 162

AIRPLANE AND SYSTEM DESCRIPTION

GARMIN G300

AVIONICS SUPPORT EQUIPMENT

Avionics cooling fan, antennas, and provisions for aviation-style

headsets support the operation of the avionics equipment installations.

AVIONICS COOLING FAN

A single DC electric fan provides forced air and ambient air circulation

cooling for the G300 avionics equipment. The fan is located forward of

the instrument panel and removes air from between the firewall

bulkhead and instrument panel, directing the warm air up at the inside

of the windshield.

Power is provided to the cooling fan when the MASTER (BAT) switch

and the AVN MASTER switch are both ON.

ANTENNAS

A single combination VHF COM/GPS antenna is mounted on the top of

the cabin. The dual-mode COM/GPS antenna is mounted on the left

side. It connects to the VHF communication transceiver and the GPS

receiver in the PFD and GDL.

The transponder antenna is mounted on the bottom of the cabin and is

connected to the Mode S transponder by a coaxial transmission cable.

The optional XM antenna (if installed) is mounted on the top right side

of the cabin. It provides a signal to the GDL-69A XM Data Link receiver.

(Continued Next Page)

162PHUS-03

U.S.

2-53

SECTION 2

CESSNA

AIRPLANE AND SYSTEM DESCRIPTION

MODEL 162

GARMIN G300

AVIONICS SUPPORT EQUIPMENT (Continued)

MICROPHONE AND HEADSET INSTALLATIONS

Standard equipment for the airplane includes two push-to-talk (PTT)

microphone buttons on the control sticks and provisions for aviation-

style headsets at each pilot station.

For airplanes not equipped with the PM3000 Intercom System all radio

communications are transmitted through the Garmin SL40 Comm

radio.

For airplanes equipped with the PS Engineering PM3000 Intercom

System, all radio communications are transmitted through the PM3000

Intercom System when the system is selected to the ON position,

otherwise all radio communications are transmitted through the Garmin

SL40 Comm radio. For more information on system description and

operation, refer to Section 10, Supplement 3.

AUXILIARY AUDIO INPUT JACK (if installed)

An auxiliary audio input jack (AUX AUDIO INPUT) is located on the

center pedestal when the PS Engineering Intercom System is installed,

refer to Section 10, Supplement 3 for additional operating information.

2-54

U.S.

162PHUS-03

CESSNA

SECTION 2

MODEL 162

AIRPLANE AND SYSTEM DESCRIPTION

GARMIN G300

CABIN FEATURES

EMERGENCY LOCATOR TRANSMITTER (ELT)

Refer to Section 10, Supplements 1 or 2 for appropriate ELT operating

information.

CABIN FIRE EXTINGUISHER (if installed)

A portable Halon 1211 (Bromochlorodifluoromethane) fire extinguisher

is installed on the baggage area floorboard to be accessible in case of

fire. The extinguisher is classified 5B:C by Underwriters Laboratories.

The extinguisher should be checked prior to each flight to ensure that

the pressure of the contents, as indicated by the gage at the top of the

extinguisher, is within the green arc (approximately 125 psi) and the

operating lever lock pin is securely in place.

To operate the fire extinguisher:

1. Loosen retaining clamp(s) and remove extinguisher from bracket.

2. Hold extinguisher upright, pull operating ring pin, and press lever

while directing the liquid at the base of the fire at the near edge.

Progress toward the back of the fire by moving the nozzle rapidly

with a side-to-side sweeping motion.

WARNING

VENTILATE

THE

CABIN

PROMPTLY

AFTER

SUCCESSFULLY EXTINGUISHING THE FIRE TO

REDUCE THE GASES PRODUCED BY THERMAL

DECOMPOSITION.

3. The contents of the cabin fire extinguisher will empty in

approximately eight seconds of continuous use.

Fire extinguishers should be recharged by a qualified fire extinguisher

agency after each use. After recharging, secure the extinguisher to its

mounting bracket.

162PHUS-03

U.S.

2-55/2-56

CESSNA

SECTION 3

MODEL 162

OPERATING LIMITATIONS

GARMIN G300

OPERATING LIMITATIONS

TABLE OF CONTENTS

Page

Introduction

3-3

Airspeed Limitations

3-4

Airspeed Indicator Markings

3-5

Powerplant Limitations

3-6

Powerplant and Electrical Instrument Markings

3-7

Weight Limits

3-8

Maximum Weight in Baggage Compartment

3-8

Center of Gravity Limits

3-8

Service Ceiling

3-8

Maneuver Limits

3-9

Load Factors

3-9

Flight Load Factor Limits

3-9

Kinds of Operations Limits

3-10

Kinds of Operations Equipment List

3-11

Fuel Limitations

3-14

Flaps Limitations

3-14

System Limitations

3-15

12V Power Outlet

3-15

G300 Limitations

3-15

Placards

3-16

162PHUS-01

U.S.

3-1/3-2

CESSNA

SECTION 3

MODEL 162

OPERATING LIMITATIONS

GARMIN G300

INTRODUCTION

Section 3 includes operating limitations, instrument markings, and

basic placards necessary for the safe operation of the airplane, its

engine, standard systems and standard equipment. The limitations

included in this section and in Section 10 have been approved.

Observance of these operating limitations is required by Federal

Aviation Regulations.

NOTE

• Refer to Section 10, Supplements, of this Pilot's

Operating Handbook for amended operating limitations,

operating procedures, performance data and other

necessary information for airplanes equipped with

specific options.

• The airspeeds listed in Figure 3-1, Airspeed Limitations,

are based on Airspeed Calibration data shown in Section

The Cessna Model No. 162 is approved under ASTM standard F2245.

162PHUS-00

U.S.

3-3

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

V_S

Stall Speed - Clean

Stall speed flap up.

V_SO

Stall Speed - Landing

Stall speed flaps full

Configuration

V_FE

Maximum Flap

Do not exceed this speed

Extended Speed:

with flaps down.

FLAPS 10°

100

FLAPS 25°

FLAPS FULL

V_O

Maximum Operating

Maximum speed at which

Maneuvering Speed

the airplane may be

stalled without exceeding

1320 Pounds

structural limitations.

1200 Pounds

1100 Pounds

Design Maneuvering

Do not make full or abrupt

control movements above

Speed:

100

102

this speed.

Does

not

provide

protection from possible

overstressing the airplane.

V_NE

Never Exceed Speed

143

148

Do not exceed this speed

in any operation.

V_NO

Maximum Structural

120

124

Do not exceed this speed

Cruising Speed

except in smooth air, and

then only with caution.

Figure 3-1

3-4

U.S.

162PHUS-02

CESSNA

SECTION 3

MODEL 162

OPERATING LIMITATIONS

GARMIN G300

AIRSPEED INDICATOR MARKINGS

Airspeed indicator markings and their color code significance are

shown in Figure 3-2.

AIRSPEED INDICATOR MARKINGS

KIAS VALUE OR

MARKING

SIGNIFICANCE

RANGE

Red Band

<37

Low airspeed warning.

White Band

37 - 70

Full Flap Operating Range. Lower limit is

maximum weight V_SO in landing configuration.

Upper limit is maximum speed permissible with

flaps extended.

Green Band

41 - 124

Normal Operating Range. Lower limit is

maximum weight V_S1 at most forward C.G.

with flaps retracted. Upper limit is maximum

structural cruising speed.

Yellow

124 - 148

Operations must be conducted with caution

Band

and only in smooth air.

Red Line

>149

Maximum speed for all operations.

Flaps 25°

Maximum Flaps 25° Operation

Tick Mark

Flaps 10°

100

Maximum Flaps 10° Operation

Tick Mark

Vx Tick

Best Angle of Climb Air Speed

Mark

Vy Tick

Best Rate of Climb Air Speed

Mark

Figure 3-2

162PHUS-01

U.S.

3-5

SECTION 3

CESSNA

OPERATING LIMITATIONS

MODEL 162

GARMIN G300

POWERPLANT LIMITATIONS

Engine Manufacturer: Teledyne Continental Motors

Engine Model Number: O-200-D

Maximum Power: 100 BHP Rating

Engine Operating Limits for Takeoff and Continuous Operations:

Maximum Engine Speed:

2750 RPM

NOTE

The static RPM range at full throttle with carburetor heat off

and mixture leaned to maximum RPM is 2375 - 2475 RPM.

For allowable variations in static RPM at non-standard

temperatures, refer to the 162 Maintenance Manual.

Maximum Oil Temperature:

240°F (116°C)

Oil Pressure, Minimum:

10 PSI

Oil Pressure, Maximum:

100 PSI

CAUTION

ENGINE OPERATION WITH INDICATED OIL PRESSURE

BELOW THE GREEN BAND RANGE WHILE IN CRUISE

OR CLIMB CONFIGURATION IS CONSIDERED

ABNORMAL. REFER TO SECTION

3, AMPLIFIED

EMERGENCY PROCEDURES, "LOW OIL PRESSURE".

Fuel Grade: Refer to Fuel Limitations

Oil Grade (Specification):

SAE J1966 Aviation Grade Non-Dispersant Mineral Oil or SAE

J1899 Aviation Grade Ashless Dispersant Oil. Oil must comply with

the latest revision and/or supplement for Teledyne Continental

Motors (TCM) Service Information Letter SIL99-2B or later revision,

must be used.

Propeller Manufacturer: McCauley Propeller Systems

Standard Composite Propeller Model Number

1L100/LSA6754

Maximum Propeller Diameter

67.0 INCHES (1.70 m)

Minimum Propeller Diameter

66.5 INCHES (1.69 m)

Optional Aluminum Propeller Model Number

1A162/TCD6754

Maximum Propeller Diameter

67.0 INCHES (1.70 m)

Minimum Propeller Diameter

66.0 INCHES (1.68 m)

3-6

U.S.

162PHUS-03

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.

POWERPLANT AND ELECTRICAL INSTRUMENT MARKINGS

GREEN

RED

YELLOW

RED

(NORMAL

INSTRUMENT

(LOWER

(UPPER

OPERATING

WARNING)

CAUTION)

WARNING)

RANGE)

Tachometer

----

2000 to 2750

2750* to 3500

(RPM)

RPM

Oil

----

0 to 75°F

75 to 220°F

220 to 240°F

240* to 265°F

Temperature

(OIL °F)

Oil Pressure

0 to 10 PSI

10 to 30 PSI

30 to 60 PSI

60 to 100 PSI

100* to 140 PSI

(OIL PSI)

Exhaust Gas

----

1000 to 1600°F

Temperature

White Advisory

(if installed)

(EGT °F)

Carburetor

5 to 40°F

Temperature

(CARB °F)

Battery

-35 to 35

Current

White Advisory

(AMPS)

Bus Voltage

-30 to 12.5

12.5 to 15

15 to 16

16 to 30

(VOLTS)

*Maximum operating limit is lower end of red.

Figure 3-3

162PHUS-00

U.S.

3-7

SECTION 3

CESSNA

OPERATING LIMITATIONS

MODEL 162

GARMIN G300

WEIGHT LIMITS

Maximum Ramp Weight:

1324 POUNDS (600.6 kg)

Maximum Takeoff Weight

1320 POUNDS (598.8 kg)

Maximum Landing Weight

1320 POUNDS (598.8 kg)

MAXIMUM WEIGHT IN BAGGAGE COMPARTMENT

Baggage Area (Station 155 to 190)

50 POUNDS (22.68 kg)

WARNING

AFT BULKHEAD CLOSEOUT NET REQUIRED FOR

FLIGHT.

NOTE

Maximum baggage compartment loading must not exceed

8 pounds per square foot.

CENTER OF GRAVITY LIMITS

Center Of Gravity Range:

Forward: 134.5 inches aft of datum at 1320 pounds or less, with

straight line variation to 132.0 inches aft of datum at

1050 pounds.

Aft:

136.9 inches aft of datum at all weights.

Reference Datum: Lower portion of front face of firewall.

SERVICE CEILING:

14,625 Feet (4457.7 m)

3-8

U.S.

162PHUS-03

CESSNA

SECTION 3

MODEL 162

OPERATING LIMITATIONS

GARMIN G300

MANEUVER LIMITS

This airplane is approved under ASTM standard F2245 and is intended

for recreational and instructional flight operations. In the acquisition of

various pilot certificates certain maneuvers are required and these

maneuvers are permitted in this airplane.

MANEUVERS AND RECOMMENDED ENTRY SPEED*

Chandelles

102 KIAS

Lazy Eights

102 KIAS

Steep Turns

102 KIAS

Stalls (Except Whip Stalls)

Slow Deceleration

Power On Stalls

Slow Deceleration

(limit pitch to 30° nose up attitude)

* Abrupt use of the controls is prohibited above 102 KIAS.

WARNING

• AEROBATIC MANEUVERS, INCLUDING SPINS, ARE

PROHIBITED.

• INTENTIONAL FLIGHT WITH CABIN DOORS OPEN

IS PROHIBITED.

LOAD FACTORS

FLIGHT LOAD FACTOR LIMITS

Flight Load Factors (Maximum Takeoff Weight - 1320 POUNDS):

Flaps UP:

+4.0g, -2.0g

Flaps FULL:

+2.0g

162PHUS-03

U.S.

3-9

SECTION 3

CESSNA

OPERATING LIMITATIONS

MODEL 162

GARMIN G300

KINDS OF OPERATIONS LIMITS

The Cessna 162 airplane is approved for DAY - NIGHT - VFR

operations only. Flight into known icing conditions is prohibited.

The minimum equipment for approved operations required under the

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

as applicable.

The following Kinds of Operations Equipment List (KOEL) identifies the

equipment required to be operational for airplane airworthiness in the

listed kind of operations.

3-10

U.S.

162PHUS-01

CESSNA

SECTION 3

MODEL 162

OPERATING LIMITATIONS

GARMIN G300

KINDS OF OPERATIONS EQUIPMENT LIST

KIND OF

OPERATION

System, Instrument, Equipment

and/or Function

COMMENTS

PLACARDS AND MARKINGS

1 - 162 POH/FTS - Garmin G300

Recommended to be

accessible to pilot in

flight.

2 - 162 Pilot’s Checklist

Required

accessible to pilot in

flight.

3 - Garmin G300 Pilot’s Guide

Recommended to be

accessible to pilot in

flight.

AIR CONDITIONING

1 - Avionics Fan

COMMUNICATIONS

1 - VHF COM

ELECTRICAL POWER

1 - 12V Main Battery

2 - 14V Alternator

3 - Standby Battery

4 - Ammeter

EQUIPMENT AND FURNISHINGS

1 - Seat Belt Assembly

Each Seat Occupant

2 - Shoulder Harness

Each Seat Occupants

3 - Aft Bulkhead Closeout Net

FLIGHT CONTROLS

1 - Elevator Trim System

2 - Elevator Trim Indicator

(Continued Next Page)

162PHUS-03

U.S.

3-11

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 -

L Tank

3 - Cockpit Fuel Quantity Indicator -

R Tank

INDICATING/RECORDING

SYSTEM

1 - Stall Warning System

2 - G300 System Annunciator and

Warning Displays

LANDING GEAR

1 - Wheel Fairings

Removable

LIGHTING

1 - PFD Bezel Lighting

2 - PFD Display Backlighting

3 - MFD Bezel Lighting (if installed)

4 - MFD Display Backlighting

(if installed)

5 - Cockpit Overhead Panel Lighting

6 - Aircraft Position (NAV) Lights

7 - STROBE Light System

8 - LAND (Landing) Light

9 - Non-stabilized Magnetic

Compass Internal Lighting

(if installed)

(Continued Next Page)

3-12

U.S.

162PHUS-03

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

4 - G300 Attitude Indicator

5 - G300 Directional Indicator (HSI)

6 - G300 Turn Coordinator

7 - G300 Magnetic Heading

Indicator

8 - GPS Receiver/Navigator

A/R

As Required Per

Procedure.

9 - GTX 327 Mode C Transponder

A/R

As Required Per

Procedure.

10 - Blind Altitude Encoder

A/R

As Required Per

Procedure.

11 - G300 Clock

12 - Magnetic Compass (if installed)

13 - Autopilot System

ENGINE INDICATING

1 - Tachometer (RPM)

2 - Carburetor Temperature Indicator

(CARB °F)

3 - Oil Pressure Indicator

4 - Oil Temperature Indicator

5 - Exhaust Gas Temperature (EGT)

Indicator (if installed)

ENGINE OIL

1 - Engine Crankcase Dipstick

162PHUS-03

U.S.

3-13

SECTION 3

CESSNA

OPERATING LIMITATIONS

MODEL 162

GARMIN G300

FUEL LIMITATIONS

Total Fuel:

25.46 U.S. GALLONS

(12.73 GALLONS per tank)

Usable Fuel (all flight conditions):

24.0 U.S. GALLONS

(12 GALLONS per tank)

Unusable Fuel:

1.46 U.S. GALLONS

(0.73 GALLONS per tank)

WARNING

TAKEOFF IS PROHIBITED IF EITHER SIGHT GAGE

INDICATES LESS THAN ¼ TANK OF FUEL OR FUEL

LEVEL IS BELOW THE BOTTOM OF THE FUEL

INDICATOR TAB.

MIN

GRND

MARKING ON FUEL INDICATOR

T.O.

NOTE

To ensure maximum fuel capacity and minimize

crossfeeding when refueling, always park the airplane in a

wings level, normal ground attitude. Refer to Figure 1-1 for

normal ground attitude definition.

Fuel remaining in the tank after the fuel quantity indicator reads “E”

cannot be safely used in flight.

Approved Fuel Grades (And Colors):

100LL Grade Aviation Fuel (Blue)

100

Grade Aviation Fuel (Green)

FLAP LIMITATIONS

Approved Takeoff Range:

UP to 10°

Approved Landing Range:

UP to FULL

3-14

U.S.

162PHUS-00

CESSNA

SECTION 3

MODEL 162

OPERATING LIMITATIONS

GARMIN G300

SYSTEM LIMITATIONS

12V POWER OUTLET

The 12 Volt Power Outlet (POWER OUTLET 12V - 7.5A) is not certified

for supplying power to flight-critical communications or navigation

devices.

Use of the 12 Volt Power Outlet is prohibited during takeoff and landing.

G300 LIMITATIONS

NOTE

It is recommended that a current Garmin G300 Pilot’s

Guide be available to the pilot during flight.

Use of the MAP page for pilotage navigation is prohibited. The

navigation map is intended only to enhance situational awareness.

Navigation is to be conducted using only current charts, data and

authorized navigation facilities.

Use of the TERRAIN information for primary terrain and obstacle

avoidance is prohibited. The terrain map is intended only to enhance

situational awareness. It is the pilot’s responsibility to provide terrain

clearance at all times.

Navigation using the G300 is not authorized north of 70° North latitude

or south of 70° South latitude due to unsuitability of the magnetic fields

near the Earth's poles. In addition, operations are not authorized in the

following two regions:

1. North of 65° North latitude between longitude 75° W and 120° W

(Northern Canada).

2. South of 55° South latitude between longitude 120° E and 165° E

(region south of Australia and New Zealand).

162PHUS-03

U.S.

3-15

SECTION 3

CESSNA

OPERATING LIMITATIONS

MODEL 162

GARMIN G300

PLACARDS

The following information must be displayed in the form of composite or

individual placards.

1. In full view of the pilot: (The DAY-NIGHT-VFR entry, shown on

the example below, will vary with installed equipment):

The markings and placards installed in this airplane contain operating

limitations which must be complied with when operating this airplane.

Other operating limitations which must be complied with when

operating this airplane in this category are contained in the Pilot’s

Operating Handbook.

No acrobatic maneuvers, including spins, are approved.

Flight into known icing conditions prohibited.

This airplane is approved for the following flight operations as of the

date of original airworthiness certificate:

DAY - NIGHT - VFR

2. On control lock:

3. On left instrument panel above magnetos switch:

MIN

TAKEOFF PROHIBITED WITH LESS THAN 1/4 FUEL

(Continued Next Page)

3-16

U.S.

162PHUS-03

CESSNA

SECTION 3

MODEL 162

OPERATING LIMITATIONS

GARMIN G300

PLACARDS (Continued)

4. On the lower left instrument panel:

WARNING

Assure that all contaminants,

including water, are removed

from fuel and fuel systems

before flight. Failure to assure

contaminant free fuel and heed

all safety instructions and

owner advisories prior to flight

can result in bodily injury or death.

5. On the upper left instrument panel:

NO INTENTIONAL SPINS

6. On the instrument panel directly above the PFD:

MAXIMUM OPERATING MANEUVERING SPEED: 89 KIAS

DESIGN MANEUVERING SPEED: 102 KIAS

7. On the upper right instrument panel:

8. On the right instrument panel:

This aircraft was

manufactured in

accordance with Light

Sport Aircraft airworthiness

standards and does not conform

to standard category airworthiness

requirements.

(Continued Next Page)

162PHUS-03

U.S.

3-17

Cessna 162 Skycatcher Aircraft Pilot. Operating Handbook (2009) - page 1