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

Model 162

SERIAL NUMBER

Serials 16200001 and On

This publication includes the material required to be furnished to the pilot by ASTM F2245.

COPYRIGHT © 2009

CESSNA AIRCRAFT COMPANY

WICHITA, KANSAS, USA

162PHUS-02

REGISTRATION NUMBER

ORIGINAL ISSUE - 22 JULY 2009

REVISION 2 - 26 APRIL 2010

U.S.

CESSNA INTRODUCTION
MODEL 162
GARMIN G300

PILOT’S OPERATING HANDBOOK

AND

FLIGHT TRAINING SUPPLEMENT

CESSNA MODEL 162

SERIALS

16200001 AND ON

ORIGINAL ISSUE - 22 JULY 2009

REVISION 2 - 26 APRIL 2010

162PHUS-02

PART NUMBER: 162PHUS-02

U.S.

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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.

A Cessna Service Station locator is available at
www.cessnasupport.com.

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

162PHUS-01

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iii

INTRODUCTION CESSNA

NOTE

MODEL 162

GARMIN G300

PERFORMANCE - SPECIFICATIONS

*SPEED:

Maximum at Sea Level . . . . . . . . . . . . . . 118 KNOTS (218.5 km/hr)

Cruise, 69% Power at 6000 Feet. . . . . . . 109 KNOTS (201.9 km/hr)

CRUISE: Recommended lean mixture with fuel allowance for engine

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

RANGE:

69% Power at 6000 Feet. . . . . . . . . . . . . . . . . . . . .Range - 360 NM

24 Gallons Usable Fuel . . . . . . . . . . . . . . . . . . . Time - 3.30 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 (19 5 .1 m)

Total Distance Over 50 Foot Obstacle. . . . . . .1138 FEET (346.9 m)

LANDING PERFORMANCE AT SEA LEVEL:

Ground Roll . . . . . . . . . . . . . . . . . . . . . . . . . . . .671 FEET (20 4 .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

* Speed performance is shown for airplanes not equipped

with the optional speed fairings. Airplanes equipped with
optional speed fairings will notice a increase in speeds by
approximately 2 knots. There is a corresponding difference
in range, while all other performance figures are
unchanged when speed fairings are installed.

The above performance figures are based on airplane weights at 1320
pounds (598.7 kg), standard atmospheric conditions, level, hard­surfaced dry runways and no wind. They are calculated values derived
from flight tests conduct ed 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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CESSNA INTRODUCTION
MODEL 162
GARMIN G300

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 (220.4 kg)

BAGGAGE ALLOWANCE . . . . . . . . . . . . . . . . 50 POUNDS (22.68 kg)

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

POWER LOADING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.2 lbs/HP

FUEL CAPACITY (Usable) . . . . . . . . . . . . . . . . . 24 GALLONS (90.8 l)

OIL CAPACITY (Sump) . . . . . . . . . . . . . . . . . . . . . . 5 QUARTS (4.73 I)

ENGINE: Teledyne Continental Motors . . . . . . . . . . . . . . . . . . . O-200D

100 BHP at 2750 RPM
PROPELLER:

Fixed Pitch, Diameter . . . . . . . . . . . . . . . . . . . .67 INCHES (1.70 m)

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INTRODUCTION CESSNA

MODEL 162

GARMIN G300

COVERAGE

The Pilot’s Operating Handbook (POH) in the airplane at the time of
delivery from Cessna Aircraft Company contains information applicable
to the Model 162 airplanes by serial number and registration number
shown on the Title Page. This POH is applicable to Model 162
airplanes, Serials 16200001 and On. All information is based on data
available at the time of publication.

This POH consists of ten sections that cover all operational aspects of
a standard equipped airplane. Section 10 contains the supplements
which provide amended operating limitations, operating procedures,
performance data and other necessary information for airplanes
conducting special operations for both standard and optional
equipment installed in the ai rplane.

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 o f Effective Pages, which should be used to
determine the status of each supplement.

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162PHUS-01

CESSNA INTRODUCTION
MODEL 162
GARMIN G300

ORIGINAL ISSUE AND REVISIONS

This Pilot’s Operating Handbook is comprised of the original issue and
any subsequent revisions. To make sure that information in this manual
is current, the revisions must be incorporated as they are issued. As
revisions are issued, they will be noted in the Log of Effective Pages.

The part number of this manual has also been designed to further aid
the owner/operator in determining the revision level of any POH. Refer
to the example below for a breakdown:

162 PHUS -00

Revision Level (Original Issue)
Manual (Pilot’s Operating Han dbook, 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.

162PHUS-00

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vii

INTRODUCTION CESSNA

MODEL 162

GARMIN G300

REVISION FILING INSTRUCTIONS

REGULAR REVISIONS

Pages to be removed or inserted in the Pilots’ Operating Handbook are
determined by the Log of Effective Pages located in this section. This
log contains the page number and revision level for each page within
the POH. As revisions to the POH occur, the revision level on effected
pages is updated. When two pages display the same page number, the
page with the latest revision level shall be inserted into the POH. The
revision level on the Log Of Effective Pages shall also agree with the
revision level of the page in question.

TEMPORARY REVISIONS

Under limited circumstances, temporary revisions to the POH may be
issued. These temporary revisions are to be filed in the applicable
section in accordance with filing instructions appearing on the first p age
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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162PHUS-00

CESSNA INTRODUCTION
MODEL 162
GARMIN G300

IDENTIFYING REVISED MATERIAL

A bar will extend the full length of deleted, new, or revised text added
on new or previously existing pages. This bar will be located adjacent to
the applicable text in the margin on the left side of the page.

A bar in the footer will indicate a revision to the header/footer, a new
page, format or spelling/grammar changes and/or that information has
slipped to or from that page.

A bar located adjacent to the figure number in the margin on the left
side of the page will be used to indicate that the figure number only has
changed.

An asterisk located at the end of a figure number will be used to
indicate that an illustration has been revised or is all new material (Ex:
Figure 3-4*).

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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ix

INTRODUCTION CESSNA

WARNING

CAUTION

NOTE

MODEL 162

GARMIN G300

WARNINGS, CAUTIONS AND NOTES

Throughout the text, warnings, cautions and notes pertaining to
airplane handling and operatio ns are utilized. These a djunct s to the t ext
are used to highlight or emphasize important points.

OPERATING PROCEDURES, TECHNIQUES, ETC.,
WHICH CAN RESULT IN PERSONAL INJURY OR LOSS
OF LIFE IF NOT CAREFULLY FOLLOWED.

OPERATION PROCEDURES, TECHNIQUES, ETC.,
WHICH CAN RESULT IN DAMAGE TO EQUIPMENT IF
NOT CAREFULLY FOLLOWED.

An operating procedure, technique, etc., which is
considered essential to emphasize.

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CESSNA INTRODUCTION
MODEL 162
GARMIN G300

LOG OF EFFECTIVE PAGES

Use this page to determine the currency and applicability of your POH.

Pages affected by the current revision are indicated by an asterisk (*)
preceding the pages listed under the Page Number column.

Revision Level Date of Issue

Original Issue 22 July 2009 Revision 2 26 April 2010

Revision 1 2 November 2009

Page
Number

* Title Revised 2

* i/ii Revised 2

iii thru vi Revised 1
vii thru x Original 0

* xi thru xiv Revised 2

xv/xvi Added 1

1-1/1-2 Original 0
1-3 thru 1-5 Revised 1
1-6 thru 1-7 Original 0
1-8 Revised 1

2-1 thru 2-8 Revised 1
2-9 thru 2-10 Original 0
2-11 thru 2-12 Revised 1
2-13 Original 0
2-14 thru 2-25/2-26 Revised 1

Page

Status

Revision

Number

3-1/3-2 Revised 1
3-3 Original 0

* 3-4 Revised 2

3-5 thru 3-6 Revised 1
3-7 Original 0

(Continued Next Page)

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INTRODUCTION CESSNA

MODEL 162

GARMIN G300

LOG OF EFFECTIVE PAGES (Continued)

Page
Number

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* 3-17 Revised 2

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Number

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5-3 thru 5-9 Revised 1
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6-1 thru 6-4 Original 0

* 6-5 Revised 2

6-6 Original 0
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6-19 Original 0

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CESSNA INTRODUCTION
MODEL 162
GARMIN G300

LOG OF EFFECTIVE PAGES (Continued)

Page
Number

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* 7-3 Revised 2

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Number

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INTRODUCTION CESSNA

MODEL 162

GARMIN G300

LOG OF EFFECTIVE PAGES (Continued)

Page
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CESSNA INTRODUCTION
MODEL 162
GARMIN G300

TABLE OF CONTENTS

SECTION

GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1

AIRPLANE AND SYSTEM DESCRIPTION . . . . . . . . .2

OPERATING LIMITATIONS . . . . . . . . . . . . . . . . . . . . .3

WEIGHT AND BALANCE/EQUIPMENT LIST . . . . . . .4

PERFORMANCE. . . . . . . . . . . . . . . . . . . . . . . . . . . . .5

EMERGENCY PROCEDURES . . . . . . . . . . . . . . . . . .6

NORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . .7

AIRCRAFT HANDLING, SERVICE

AND MAINTENANCE . . . . . . . . . . . . . . . . . . . . . . . . .8

PLACARDS AND MARKINGS. . . . . . . . . . . . . . . . . . .9

SUPPLEMENTARY INFORMATION . . . . . . . . . . . . .10

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CESSNA 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 Ba ggage Compartment . . . . . . . . . . . . . . . .1-8

Standard Airplane W eights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-8

Cabin And Entry Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-8

Baggage Space And Entry Dimensions . . . . . . . . . . . . . . . . . . . .1-8

Specific Loadings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-8

U.S.

1-1/1-2162PHUS-00

CESSNA SECTION 1
MODEL 162 GENERAL
GARMIN G300

THREE VIEW - NORMAL GROUND ATTITUDE

Figure 1-1* (Sheet 1 of 2)

U.S.

1-3162PHUS-01

SECTION 1 CESSNA

NOTE

GENERAL MODEL 162

GARMIN G300

THREE VIEW - NORMAL GROUND ATTITUDE

• Wing span shown with standard strobe lights installed.

• Wheel base length is 62.40 inches (1.58 m).

• Propeller ground clearance is 8.50 inches (215.90 mm).

• Wing area is 120.0 square feet (11.15 sq. m).

Figure 1-1* (Sheet 2)

1-4

U.S.

162PHUS-01

CESSNA SECTION 1
MODEL 162 GENERAL
GARMIN G300

INTRODUCTION

This POH contains 10 sections, and includes the material required to
be furnished to the pilot by American Society for Testing and Materials
International (ASTM) standards F2245 for Light Sport Aircraft (LSA). It
also contains supplement al data supplied by Cessna Aircraft Company.

Section 1 provides basic data and information of general interest.

DESCRIPTIVE DATA

ENGINE

Number of Engines: 1
Engine Manufacturer: Teledyne Continental Motors
Engine Model Number: O-200-D

Engine Type: Normally aspirated, direct drive, air-cooled, horizontally

opposed, carburetor equipped, four cylinder engine with

201.0 cu. in. displacement.

Horsepower Rating and Engine Speed: 100 rated BHP at 2750 RPM

PROPELLER

Propeller Manufacturer: McCauley Propeller Systems
Propeller Model Number: 1A162/TCD6754
Number of Blades: 2
Propeller Diameter: 67 inches (1.70 m)
Propeller Type: Fixed Pitch

(Continued Next Page)

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1-5162PHUS-01

SECTION 1 CESSNA

WARNING

NOTE

NOTE

GENERAL MODEL 162

GARMIN G300

DESCRIPTIVE DATA (Continued)

FUEL

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)

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 CAPAC ITY

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)

• To ensure maximum fuel capacity and minimize

crossfeeding when refueling, always park the airplane in
a wings level, normal ground attitude. Refer to Figure 1­1 for normal ground attitude dimensions.

• The fuel filler assembly is equipped with indicator tabs

for 3/4, 1/2 and 1/4 fuel quantitie s.

1-6

• 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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162PHUS-00

CESSNA SECTION 1

NOTE

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 use d to replen ish
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 SIL99­2B, 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

Non-Dispersant

Mineral Oil

Temperature

Above 4°C (40°F) 50 50 or 15W-50 or 25W-60
Below 4°C (40°F) 30 30 or 15W-50 or 25W-60
All Temperatures M20W-50 15W-50, 20W- 50 or 25W-60

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)

SAE Grade

Ashless Dispersant Oil

SAE J1899

SAE Grade

(Continued Next Page)

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1-7162PHUS-00

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 k g)

Landing Weight . . . . . . . . . . . . . . . . . . . . . . 1320 POUNDS (598.8 kg)

MAXIMUM WEIGHT IN BAGGAGE COMPARTMENT

Baggage Area (Station 155 to 190). . . . . . . 50 POUNDS (22.68 kg)

STANDARD AIRPLANE WEIGHTS

Standard Empty Weight . . . . . . . . . . . . . . . . . 834 POUNDS (378.3 kg)

Maximum Useful Load . . . . . . . . . . . . . . . . . . 486 POUNDS (220.4 kg)

CABIN AND ENTRY DIMENSIONS

Detailed dimensions of the cabin interior and entry door openings are
illustrated in Section 4.

BAGGAGE SPACE AND ENTRY DIMENSIONS

Dimensions of the baggage area are illustrated in detail in Section 4.

SPECIFIC LOADINGS

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

Power Loading . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .13.2 lbs/HP

1-8

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162PHUS-01

CESSNA 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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-3

Instrument Panel, Flight and System Instruments. . . . . . . . . . . . . . .2-5

Landing Gear and Brake System. . . . . . . . . . . . . . . . . . . . . . . . . . . .2-6

Miscellaneous Cabin Features . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-7

Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8

Engine Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-8

Engine Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-9

Tachometer (RPM). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-9

Oil Pressure (OIL PSI) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-10

Oil Temperature (OIL °F) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-11

Exhaust Gas Temperature (EGT °F) (if installed). . . . . . . . . . . . .2-11

Carburetor Temperature (CARB °F) . . . . . . . . . . . . . . . . . . . . . .2-12

New Engine Break-In And Operation . . . . . . . . . . . . . . . . . . . . . .2-12

Engine Lubrication System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-13

Ignition And Starter System . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-13

Air Induction System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-14

Exhaust System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-14

Cooling System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-14

Propeller . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-15

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

Fuel Distribution . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-15

Fuel Indicating System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-16

Fuel Venting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-17

Reduced Tank Capacity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-18

Fuel Drain Valves . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-19

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SECTION 2 CESSNA
AIRPLANE AND SYSTEM DESCRIPTION MODEL 162

GARMIN G300

TABLE OF CONTENTS

Page

Electrical System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-19

Master Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-21

Electrical System Monitoring. . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-21

Main Battery Current (Amps). . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-21

System Voltage (Volts) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-21

Circuit Breakers. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-22

12V Power Outlet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-23

External Power Receptac le ( i f installed) . . . . . . . . . . . . . . . . . . . 2-23

Lighting Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-24

Exterior Lighting. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-24

Interior Lighting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-24

Cabin Heating and Ventilating System. . . . . . . . . . . . . . . . . . 2-25/2-26

Stall Warning System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-25/2-26

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162PHUS-01

CESSNA SECTION 2
MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION
GARMIN G300

INTRODUCTION

This section provides description and operation of the airplane and its
systems. Some equipment described herein is optional and may not be
installed in the airplane. Refer to Section 10, Supplements, for details
of other optional systems and equipment.

AIRFRAME

The airplane is an all metal, two-place, high wing, single-engine
airplane equipped with tricycle landing gear and is designed for sport
flying and introductory training purposes.

The sheet metal fuselage bulkhead, stringer, and skin semi­monocoque construction provide safe and comfortable environment for
pilot, passenger, and baggage. Forward pivoting seats allow access to
the baggage area. Wing struts and main landing gear legs attach to an
I-beam structure under the baggage area behind the seats. Nose gear
and engine mount assembly attach to the firewall separating the cabin
from engine compartment.

The aft fuselage empennage (tail assembly) consists of horizontal and
vertical stabilizers, the rudder, a left elevator, and a right elevator with
elevator trim tab. Att aching on either side the fuselage above t he ca bin,
the wing contains fuel tanks at the wing root between the forward and
aft spars. Aft of the rear wing spar are mounted the flaps (inboard) and
ailerons (outboard). In addition to the fuselage carry-through spars, the
wing is attached by forward-spar-to-fuselage struts. The wing,
empennage, and flight control surfaces are also made of sheet metal
spars, ribs, and skin semi-monocoque construction with balance
weights incorporated into the rudder, elevators, and ailerons.

FLIGHT CONTROLS

The airplane's flight control system consists of conventional aileron,
rudder, and elevator control surfaces manually operated through a
cable system. An elevator trim tab is located on the right elevator. Trim
tab operation is by direct linkage to a elevator mounted electric servo
motor controlled by a control stick mounted trim switch. Elevator trim
tab position is displayed on the Engine Indicating System area of the
G300 display.

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SECTION 2 CESSNA

CAUTION

AIRPLANE AND SYSTEM DESCRIPTION MODEL 162

GARMIN G300

FLIGHT CONTROLS (Continued)

Dual under panel control sticks are used for aileron and elevator
control. The under panel control sticks mimic th e contro l movement of a
floor mounted control stick while providing ease of entry to the cabin.
The control stick location is designed so that the pilot's hand naturally
falls on the control stick with the outboard arm on the door arm rest.

Rudder pedals with toe brakes provide rudder control through forward
and aft individually adjustable pilot and copilot pedal assemblies.
Rudder pedals should be adjusted so that it is possible to have full
brake pedal deflection when the same side rudder is fully deflected.

Wing flaps are manually operated down by a flap handle located
between the seats and returned to faired UP position by air load and
return spring assist. Flap detent position UP, 10º, 25º, or FULL may be
selected only after depressing the release button in the end of the flap
handle.

A control gust lock is provided. The control lock pins the left control
stick through a bracket to immobilize the ailerons and elevator. Rudder
is held centered by the springs used for increasing rudder pedal force.

During the preflight walk-around inspection it is possible to move the
ailerons into an over-centered position by moving the aileron down
from the centered or faired with the flaps UP flaps position. The down­deflected 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.

AILERON OVER CENTERING ONLY OCCURS WHEN
AILERONS ARE MOVED FROM OUTSIDE THE
AIRPLANE. CONTROL STICK STIFFNESS OR STICKING
IN ANY DIRECTION OF ANY CONTROL SURFACE THIS
IS NOT NORMAL AND SHOULD BE INSPECTED BY
MAINTENANCE PERSONNEL PRIOR TO FLIGHT.

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