Cessna 208B Grand Caravan EX. Airplane Flight Manual (2012)

CESSNA

INTRODUCTION

MODEL 208B (867 SHP)

GARMIN G1000

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 Authorized Service Facility:

•

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 Program 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 Authorized Service Facility 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 current Cessna Authorized Service Facilities Directory accompanies

your new airplane. The Directory is revised annually, and a current

copy can be obtained from your nearest Cessna Authorized Service

Facility.

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

within the Cessna Organization.

208BPHCUS-00

U.S.

iii

INTRODUCTION

CESSNA

MODEL 208B (867 SHP)

GARMIN G1000

PERFORMANCE - SPECIFICATIONS

CARGO VERSION

SPEED (KTAS):

Maximum Cruise at 10,000 Feet

185 KNOTS

Maximum Cruise at 20,000 Feet

175 KNOTS

RANGE: With 2246 pounds usable fuel and fuel allowance for engine

start, taxi, takeoff, climb, descent and 45 minutes reserve.

Max Cruise at 10,000 Feet

Range - 792 NM

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Time - 4.4 HOURS

Max Cruise at 18,000 Feet

Range - 985 NM

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Time - 5.6 HOURS

Max Range at 10,000 Feet

Range - 918 NM

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Time - 6.0 HOURS

Max Range at 18,000 Feet

Range - 1052 NM

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Time - 6.6 HOURS

RATE OF CLIMB AT SEA LEVEL

1275 FPM

SERVICE CEILING

25,000 FEET

MAXIMUM OPERATING ALTITUDE

25,000 FEET

TAKEOFF PERFORMANCE:

Ground Roll

1399 FEET

Total Distance Over 50 Foot Obstacle

2160 FEET

LANDING PERFORMANCE:

Ground Roll

1004 FEET

Total Distance Over 50 Foot Obstacle

1836 FEET

STALL SPEED (KCAS):

Flaps UP, Power Idle

78 KNOTS

Flaps LAND, Power Idle

61 KNOTS

(Continued Next Page)

U.S.

208BPHCUS-00

CESSNA

INTRODUCTION

MODEL 208B (867 SHP)

GARMIN G1000

PERFORMANCE - SPECIFICATIONS

CARGO VERSION (Continued)

MAXIMUM WEIGHT:

Ramp

8842 POUNDS (4010.7 kg)

Takeoff

8807 POUNDS (3994.8 kg)

Landing

8500 POUNDS (3855.5 kg)

STANDARD EMPTY WEIGHT

4558 POUNDS (2067.5 kg)

MAXIMUM USEFUL LOAD

4284 POUNDS (1943.2 kg)

WING LOADING

31.5 lbs/sq. ft.

POWER LOADING

10.2 lbs/SHP

FUEL CAPACITY

335.6 GALLONS (1270.0 l)

OIL CAPACITY

14 QUARTS (13.2 l)

ENGINE: Pratt & Whitney Canada

PT6A-140

Free Turbine Flat Rated at 867 SHP

PROPELLER: Hartzell Propeller Systems

3-bladed, Constant Speed, Full Feathering, Reversible Propeller

Diameter

106 Inches (2.7 m)

The above performance figures are based on indicated weights,

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.

Performance for other operational conditions can be derived by

reference to operational data in other sections of this POH/AFM.

208BPHCUS-00

U.S.

INTRODUCTION

CESSNA

MODEL 208B (867 SHP)

GARMIN G1000

PERFORMANCE - SPECIFICATIONS

PASSENGER VERSION

SPEED (KTAS):

Maximum Cruise at 10,000 Feet

195 KNOTS

Maximum Cruise at 20,000 Feet

186 KNOTS

RANGE: With 2246 pounds usable fuel and fuel allowance for engine

start, taxi, takeoff, climb, descent and 45 minutes reserve.

Max Cruise at 10,000 Feet

Range - 832 NM

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Time - 4.4 HOURS

Max Cruise at 18,000 Feet

Range - 1040 NM

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Time - 5.7 HOURS

Max Range at 10,000 Feet

Range - 973 NM

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Time - 6.0 HOURS

Max Range at 18,000 Feet

Range - 1125 NM

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Time - 6.8 HOURS

RATE OF CLIMB AT SEA LEVEL

1330 FPM

SERVICE CEILING

25,000 FEET

MAXIMUM OPERATING ALTITUDE

25,000 FEET

TAKEOFF PERFORMANCE:

Ground Roll

1399 FEET

Total Distance Over 50 Foot Obstacle

2160 FEET

LANDING PERFORMANCE:

Ground Roll

1039 FEET

Total Distance Over 50 Foot Obstacle

1871 FEET

STALL SPEED (KCAS):

Flaps UP, Power Idle

78 KNOTS

Flaps LAND, Power Idle

61 KNOTS

(Continued Next Page)

U.S.

208BPHCUS-00

CESSNA

INTRODUCTION

MODEL 208B (867 SHP)

GARMIN G1000

PERFORMANCE - SPECIFICATIONS

PASSENGER VERSION (Continued)

MAXIMUM WEIGHT:

Ramp

8842 POUNDS (4010.7 kg)

Takeoff

8807 POUNDS (3994.8 kg)

Landing

8500 POUNDS (3855.5 kg)

STANDARD EMPTY WEIGHT

4805 POUNDS (2179.4 kg)

MAXIMUM USEFUL LOAD

4037 POUNDS (1831.4 kg)

WING LOADING

31.5 lbs/sq. ft.

POWER LOADING

10.2 lbs/SHP

FUEL CAPACITY

335.6 GALLONS (1270.0 l)

OIL CAPACITY

14 QUARTS (13.2 l)

ENGINE: Pratt & Whitney Canada

PT6A-140

Free Turbine Flat Rated at 867 SHP

PROPELLER: Hartzell Propeller Systems

3-bladed, Constant Speed, Full Feathering, Reversible Propeller

Diameter

106 INCHES (2.7 m)

The above performance figures are based on indicated weights,

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.

Performance for other operational conditions can be derived by

reference to operational data in other sections of this POH/AFM.

208BPHCUS-00

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vii

INTRODUCTION

CESSNA

MODEL 208B (867 SHP)

GARMIN G1000

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

208B (867 SHP) airplanes by serial number and

registration number shown on the Title Page. This POH is applicable to

Model 208B (867 SHP) airplanes, Serials 208B2197 and 208B5000

and On, equipped with the Garmin G1000. All information is based on

data available at the time of publication.

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

a standard equipped airplane. Section 9 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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208BPHCUS-00

CESSNA

INTRODUCTION

MODEL 208B (867 SHP)

GARMIN G1000

ORIGINAL ISSUE AND REVISIONS

This Pilot’s Operating Handbook and FAA Approved Airplane Flight

Manual 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:

208B PHCUS

-00

Revision Level (Original Issue)

Manual (Pilot’s Operating Handbook

867 SHP - Garmin G1000, U.S.)

(Serials 208B2197 and 208B5000 and

On)

Airplane Model - (208B)

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 Authorized Service Facility 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.

208BPHCUS-00

U.S.

INTRODUCTION

CESSNA

MODEL 208B (867 SHP)

GARMIN G1000

REVISION FILING INSTRUCTIONS

REGULAR REVISIONS

Pages to be removed or inserted in the Pilots’ Operating Handbook and

FAA Approved Airplane Flight Manual (POH/AFM) 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/AFM. As

revisions to the POH/AFM 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/AFM. 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/AFM 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/AFM 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/AFM 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/AFM and is

to be removed and discarded at the next revision to the POH. Removal

of temporary revision from the POH/AFM is accomplished per the

removal instructions on each temporary revision.

U.S.

208BPHCUS-00

CESSNA

INTRODUCTION

MODEL 208B (867 SHP)

GARMIN G1000

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

moved 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.

208BPHCUS-00

U.S.

INTRODUCTION

CESSNA

MODEL 208B (867 SHP)

GARMIN G1000

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

An operating procedure, technique, or maintenance

practice which may result in personal injury or loss

of life if not carefully obeyed.

CAUTION

An operating procedure, technique, or maintenance

practice which may result in damage to equipment if not

carefully obeyed.

NOTE

An operating procedure, technique, or maintenance

condition which is considered essential to emphasize.

LAND AS SOON AS POSSIBLE

Land at the nearest suitable airport. Unless otherwise specified, use

Normal Procedures for Approach, Before Landing, and Landing.

Extreme situations can require an off-airport landing. Primary

consideration is safety of occupants.

LAND AS SOON AS PRACTICAL

Land at a suitable airport. Unless otherwise specified, use Normal

Procedures for Approach, Before Landing, and Landing. The primary

consideration is the urgency of the emergency or abnormal situation.

Continuing to the destination or an alternate with appropriate service

facilities can be an option.

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208BPHCUS-00

CESSNA

INTRODUCTION

MODEL 208B (867 SHP)

GARMIN G1000

LOG OF EFFECTIVE PAGES

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

AFM.

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

Revision Level

Date of Issue

Original Issue

19 December 2012

Revision 1

22 May 2013

Page

Revision

Number

Status

Number

Title

Revised

Assignment Record

Original

Revised

ii thru xii

Original

xiii thru xviii

Revised

xix thru xx

Added

1-1 thru 1-5

Original

1-6

Revised

1-7

Original

1-8

Revised

1-9 thru 1-32

Original

2-1 thru 2-5

Original

2-6

Revised

2-7 thru 2-8

Original

2-9 thru 2-10

Revised

2-11 thru 2-13

Original

2-14

Revised

2-15

Original

2-16 thru 2-24

Revised

2-25 thru 2-26

Original

(Continued Next Page)

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xiii

INTRODUCTION

CESSNA

MODEL 208B (867 SHP)

GARMIN G1000

LOG OF EFFECTIVE PAGES (Continued)

Page

Revision

Number

Status

Number

2-27

Revised

2-28 thru 2-31

Original

2-32

Revised

2-33 thru 2-62

Original

3-1 thru 3-32

Original

3-33

Revised

3-34 thru 3-66

Original

3-67 thru 3-69

Revised

3-70 thru 3-102

Original

4-1 thru 4-56

Original

4-57 thru 4-58

Revised

4-59 thru 4-63

Original

4-64

Revised

4-65 thru 4-67

Original

4-68

Revised

4-69 thru 4-70

Original

5-1 thru 5-120

Original

6-1

Revised

6-2 thru 6-5

Original

6-6

Revised

6-7 thru 6-56

Original

7-1 thru 7-21

Original

7-22

Revised

7-23 thru 7-53

Original

7-54

Revised

7-55 thru 7-58

Original

7-59

Revised

(Continued Next Page)

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208BPHCUS-01

CESSNA

INTRODUCTION

MODEL 208B (867 SHP)

GARMIN G1000

LOG OF EFFECTIVE PAGES (Continued)

Page

Revision

Number

Status

Number

7-60

Original

7-61

Revised

7-62 thru 7-75

Original

7-76 thru 7-78

Revised

7-79 thru 7-126

Original

8-1 thru 8-16

Original

8-17 thru 8-18

Revised

8-19 thru 8-20

Original

8-21 thru 8-22

Revised

8-23 thru 8-58

Original

9-1 thru 9-2

Original

208BPHCUS-01

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CESSNA

SECTION 1

MODEL 208B (867 SHP)

GENERAL

GARMIN G1000

GENERAL

TABLE OF CONTENTS

Page

Three View - Normal Ground Attitude

1-3

Introduction

1-5

Descriptive Data

1-6

Engine

1-6

Propeller

1-6

Fuel

1-7

Oil

1-10

Maximum Certificated Weights

1-11

Cabin And Entry Dimensions

1-11

Baggage/Cargo Compartment and

Cargo Door and Entry Dimensions

1-11

Specific Loadings

1-11

Symbols, Abbreviations and Terminology

1-12

General Airspeed Terminology And Symbols

1-12

Meteorological Terminology

1-13

Engine Power Terminology

1-13

Airplane Performance And Flight Planning Terminology

1-15

Autopilot/Flight Director and AFCS Terminology

1-16

Weight And Balance Terminology

1-17

Metric/Imperial/U.S. Conversion Charts

1-19

Weight Conversions

1-20

Length Conversions

1-22

Distance Conversions

1-26

Volume Conversions

1-27

Temperature Conversions

1-30

Pressure Conversion

1-31

208BPHCUS-00

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1-1

SECTION 1

CESSNA

GENERAL

MODEL 208B (867 SHP)

GARMIN G1000

THREE VIEW - NORMAL GROUND ATTITUDE

NOTE

•

Normal ground attitude shown is based on standard

empty weight, proper inflation of nosewheel and main

gear tires and wings level.

•

Wing span shown with position/strobe lights installed.

•

Maximum height shown with nose gear strut depressed

as far as possible.

•

Wheel base length is 13 feet - 3.5 inches (4.05 m).

•

Wing area is 279.4 square feet (25.9 sq. m).

•

Minimum turning radius (*pivot point to outboard wing tip

strobe light) is 33 feet - 8 inches (10.3 m).

•

Propeller ground clearance varies between 2.5 inches

(63 mm) and 14.75 inches (375 mm) depending upon

configuration and installed options. Refer to Descriptive

Data, Propeller, in this section for complete listing of

propeller ground clearances.

Figure 1-1 (Sheet 2)

1-4

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208BPHCUS-00

CESSNA

SECTION 1

MODEL 208B (867 SHP)

GENERAL

GARMIN G1000

INTRODUCTION

This POH/AFM contains 9 sections, and includes the material required

to be furnished to the pilot by 14 CFR 23. It also contains supplemental

data supplied by Cessna Aircraft Company. This POH/AFM constitutes

the FAA Approved Airplane Flight Manual.

WARNING

• This POH/AFM is not intended to be a guide for

basic flight instruction or a training manual and

should not be used as one. It is not a substitute

for adequate and competent flight instruction,

pilot skill, and pilot knowledge of current

Airworthiness Directives, applicable Federal

Aviation Regulations and/or Advisory Circulars.

• Assuring the airworthiness of the airplane is the

responsibility of the airplane owner or operator.

Determining if the airplane is safe for flight is the

responsibility of the pilot in command. The pilot

is also responsible for adhering to the operating

limitations set forth by instrument markings,

placards, and this POH/AFM.

Generally, information in this POH/AFM is applicable to both the cargo

version and the passenger version of the Model

208B. Some

equipment differences exist between these versions. Specific versions

are identified through use of the terms “Cargo Version” and “Passenger

Version”. When one of these terms appears in text or on an illustration,

the information applies only to that group of airplanes. If no term

appears, the information applies to all airplanes.

Section 1 provides basic data and information of general interest. It

also contains definitions or explanations of symbols, abbreviations, and

terminology commonly used.

208BPHCUS-00

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1-5

SECTION 1

CESSNA

GENERAL

MODEL 208B (867 SHP)

GARMIN G1000

DESCRIPTIVE DATA

ENGINE

Number of Engines

Engine Manufacturer

Pratt & Whitney Canada, Inc.

Engine Model Number

PT6A-140

Engine Type:

Free turbine, two-shaft engine utilizing a compressor section having

three axial stages and one centrifugal stage, an annular reverse-flow

combustion chamber, a one-stage compressor turbine, a one-stage

power turbine, and a single exhaust. The power turbine drives the

propeller through a two-stage planetary gearbox at the front of the

engine.

Horsepower

Flat rated at 867 SHP

PROPELLER

HARTZELL

Propeller Manufacturer

Hartzell Propeller Inc.

Propeller Model Number

HC-B3TN-3AF/T10890CN-2

Number of Blades

Propeller Diameter

Maximum 106 Inches (2.7 m)

Minimum 104 Inches (2.6 m)

Propeller Type:

Constant-speed, full-feathering, reversible, hydraulically-

actuated aluminum propeller, with a feathered blade angle of

78.0°

+1.0°, a low pitch blade angle of

8.5°

+0.2°, and a

maximum reverse blade angle of -21° +0.5° at FS 42.00.

Propeller ground clearance with standard tires and standard length

nose gear fork:

With nose tire inflated and strut barrel extended 3.625

inches (92 mm), propeller ground clearance is 11.25

inches (285 mm).

With nose tire deflated and nose strut fully compressed,

propeller ground clearance is 2.5 inches (63 mm).

Propeller ground clearance with standard tires and extended length

nose gear fork:

With nose tire inflated and strut barrel extended 3.625

inches (92 mm), propeller ground clearance is 14.75

inches (375 mm).

With nose tire deflated and nose strut fully compressed,

propeller ground clearance is 5.875 inches (149 mm).

1-6

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208BPHCUS-01

CESSNA

SECTION 1

MODEL 208B (867 SHP)

GENERAL

GARMIN G1000

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:

JET A (ASTM-D1655)

JP-8+100 (MIL-DTL-83133)

JET A-1 (ASTM-D1655)

AN8 (MIL-DTL-83133)

JET No. 3 (GB 6537)

RT (GOST 10227)

JP-5 (MIL-DTL-5624)

RT (GSTU 320.00149943.007)

JP-8 (MIL-DTL-83133)

TS-1 (GOST 10227)

NOTE

Refer to Section 2, Limitations, Fuel Limitations, for more

information on Approved Fuels.

(Continued Next Page)

208BPHCUS-00

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1-7

SECTION 1

CESSNA

GENERAL

MODEL 208B (867 SHP)

GARMIN G1000

DESCRIPTIVE DATA (Continued)

FUEL (Continued)

APPROVED FUEL ADDITIVES

One of the following fuel system anti-ice additives must be added to the

fuel as noted at the following concentrations. Use of fuel anti-ice

additives is required if freezing temperatures are expect during any part

of the flight. Use of static dissipater or biocide additives is optional.

NOTE

•

MIL-DTL-27686 (EGME) or MIL-DTL-85470 (DiEGME),

Type: Anti-Ice Additive, in a concentration of 0.10 to 0.15

percent by volume.

•

MIL-DTL-27686 (EGME) or MIL-DTL-85470 (DiEGME),

Type: Anti-Ice Additive, in a concentration of 0.10 to 0.20

percent by volume.

•

GOST 8313 (Fluid I), Type: Anti-Ice Additive, in a

concentration of 0.10 to 0.30 percent by volume.

•

CIS TU6-10-1458 (Fluid I-M), Type: Anti-Ice Additive, in

a concentration of 0.10 to 0.30 percent by volume.

•

T1301

(SH0396-92), Type: Anti-Ice Additive, in a

concentration of 0.10 to 0.15 percent by volume.

•

DuPont Stadis

450, Type: Static Dissipator, in a

concentration as required to bring fuel up to 300

conductive units, not to exceed 1 Parts Per Million

(PPM).

•

SOHIO Biobor JF, Type: Biocide, at a concentration not

to exceed 20 PPM of elemental boron (270 PPM of total

additive).

•

Kathon FP, Type: Biocide, at a concentration not to

exceed 100 PPM of total additive.

•

Refer to Section

8, Airplane Handling, Service and

Maintenance, Servicing, Fuel, for additional information

and recommended blending instructions for approved

fuel additives.

1-8

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208BPHCUS-01

CESSNA

SECTION 1

MODEL 208B (867 SHP)

GENERAL

GARMIN G1000

DESCRIPTIVE DATA (Continued)

FUEL (Continued)

FUEL CAPACITY

TOTAL FUEL

Both Tanks and Reservoir:

339.1 U.S. Gallons (1283 l)

Both Tanks:

335.6 U.S. Gallons (1270 l)

Each Tank:

167.8 U.S. Gallons (635 l)

TOTAL USABLE FUEL

Both Tanks ON and Reservoir:

335.3 U.S. Gallons (1268 l)

Both Tanks ON:

332.0 U.S. Gallons (1256 l)

Single Tank ON:

165.0 U.S. Gallons (624 l)

TOTAL UNUSABLE FUEL

Both Tanks ON:

3.6 U.S. Gallons (13 l)

Single Tank ON:

2.8 U.S. Gallons (10 l)

208BPHCUS-00

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1-9

SECTION 1

CESSNA

GENERAL

MODEL 208B (867 SHP)

GARMIN G1000

DESCRIPTIVE DATA (Continued)

OIL

OIL SPECIFICATION

Oil conforming to Pratt & Whitney Engine Service Bulletin No. 1001,

and all revisions or supplements thereto, must be used. Refer to

Section 8, Airplane Handling, Service and Maintenance, Servicing,

Oil, for a listing of approved oils.

OIL CAPACITY

Total:

14 U.S. QUARTS (13.2 I)

(including filter, cooler, and hoses)

Drain and Refill Quantity:

9.5 U.S. QUARTS (9.0 l)

(approximately)

OIL QUANTITY OPERATING RANGE

Fill to within 1.5 quarts of MAX HOT or MAX COLD (as appropriate)

on dipstick. Quart marking indicate U.S. quarts low if oil is hot. For

example, a dipstick reading of 3 indicates the system is within 2

quarts of MAX if the oil is cold and within 3 quarts of MAX if the oil is

hot.

WARNING

Make sure oil dipstick cap is securely latched

down. Operating the engine with less than the

recommended oil level and with the dipstick cap

unlatched will result in excessive oil loss and

eventual engine stoppage.

NOTE

To obtain an accurate oil level reading, it is recommended

the oil level be checked within 10 minutes after engine

shutdown while the oil is hot (MAX HOT marking) or prior to

the first flight of the day while the oil is cold (MAX COLD

marking). If more than

10 minutes has elapsed since

engine shutdown and engine oil is still warm, perform an

engine dry motoring run before checking oil level.

1-10

U.S.

208BPHCUS-00

CESSNA

SECTION 1

MODEL 208B (867 SHP)

GENERAL

GARMIN G1000

DESCRIPTIVE DATA (Continued)

MAXIMUM CERTIFICATED WEIGHTS

Ramp Weight

8842 POUNDS (4010 kg)

Takeoff Weight

8807 POUNDS (3994 kg)

Landing Weight

8500 POUNDS (3855 kg)

CABIN AND ENTRY DIMENSIONS

Refer to Section 6, Weight and Balance, Cabin Internal Dimensions, for

detailed dimensions of the cabin interior and entry door openings.

BAGGAGE/CARGO COMPARTMENT AND CARGO DOOR

AND ENTRY DIMENSIONS

Refer to Section 6, Weight and Balance, Cabin Internal Dimensions, for

detailed dimensions of the baggage/cargo area and cargo door

openings.

SPECIFIC LOADINGS

Wing Loading

31.5 lbs./sq. ft.

Power Loading

10.2 lbs./SHP

208BPHCUS-00

U.S.

1-11

SECTION 1

CESSNA

GENERAL

MODEL 208B (867 SHP)

GARMIN G1000

SYMBOLS, ABBREVIATIONS AND TERMINOLOGY

GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS

KCAS

Knots Calibrated Airspeed is indicated airspeed

corrected for position and instrument error and expressed

in knots. Knots calibrated airspeed is equal to KTAS in

standard atmosphere at sea level.

KIAS

Knots Indicated Airspeed is the speed shown on the

airspeed indicator and expressed in knots.

KTAS

Knots True Airspeed is the airspeed expressed in knots

relative to undisturbed air which is KCAS corrected for

altitude and temperature.

Maneuvering Speed is the maximum speed at which full

or abrupt control movements may be used without

overstressing the airframe.

V_FE

Maximum Flap Extended Speed is the highest speed

permissible with wing flaps in a prescribed extended

position.

V_MO

Maximum Operating Speed is the speed that may not

be deliberately exceeded at any time.

V_S

Stalling Speed or the minimum steady flight speed is

the minimum speed at which the airplane is controllable.

V_SO

Stalling Speed or the minimum steady flight speed is

the minimum speed at which the airplane is controllable in

the landing configuration at the most forward center of

gravity.

V_x

Best Angle of Climb Speed is the speed which results in

the greatest gain of altitude in a given horizontal distance.

V_Y

Best Rate of Climb Speed is the speed which results in

the greatest gain in altitude in a given time.

1-12

U.S.

208BPHCUS-00

CESSNA

SECTION 1

MODEL 208B (867 SHP)

GENERAL

GARMIN G1000

SYMBOLS, ABBREVIATIONS AND TERMINOLOGY

(Continued)

METEOROLOGICAL TERMINOLOGY

OAT

Outside Air Temperature is the free air static

temperature. It may be expressed in either degrees

Celsius (°C) or degrees Fahrenheit (°F).

ISA

International Standard Atmosphere is an atmosphere

in which:

1. The air is a perfect dry gas.

2. The temperature at sea level is 15°C.

3. The pressure at sea level is

29.92 inches of

mercury (in.hg.) (1013.2 mb).

The temperature gradient from sea level to the altitude

at which the temperature is -56.5°C is -1.98°C per 1000

feet.

Standard

Standard Temperature is 15°C at sea level pressure

Temperature

altitude and decreases by 2°C for each 1000 feet of

altitude.

Pressure

Pressure Altitude is the altitude read from an altimeter

Altitude

when the altimeter's barometric scale has been set to

29.92 inches of mercury (1013 mb).

ENGINE POWER TERMINOLOGY

Beta Mode Beta Mode is the engine operational mode in which

propeller blade pitch is controlled by the power lever.

The beta mode may be used during ground operations

only.

Flameout

Flameout is the unintentional loss of combustion

chamber flame during operation.

Flat Rated Flat Rated denotes constant horsepower over a specific

altitude and/or temperature.

Gas

Gas Generator RPM indicates the percent of gas

Generator

generator RPM based on a figure of 100% being 37,468

RPM (N_g)

RPM.

GCU

Generator Control Unit

(Continued Next Page)

208BPHCUS-00

U.S.

1-13

SECTION 1

CESSNA

GENERAL

MODEL 208B (867 SHP)

GARMIN G1000

SYMBOLS, ABBREVIATIONS AND TERMINOLOGY

(Continued)

ENGINE POWER TERMINOLOGY (Continued)

Hot Start

Hot Start is an engine start, or attempted start, which

results in an ITT exceeding 1090°C.

ITT

Interstage Turbine Temperature

Maximum

Maximum Climb Power is the maximum power

Climb Power approved for normal climb. Use of this power setting is

limited to climb operations. This power corresponds to

that developed at the maximum torque limit, ITT of

825°C or Ng limit, whichever is less. This power

corresponds to that shown in Section 5, Performance,

Maximum Engine Torque for Climb.

Maximum

Maximum Rated Power is the maximum power rating

Rated Power

not limited by time. Use of this power should be limited to

those abnormal circumstances which require maximum

airplane performance (i.e., severe icing conditions or

windshear downdrafts). This power corresponds to that

developed at the maximum torque limit, ITT of 825°C or

N_g limit, whichever is less.

N_g

N_g signifies gas generator RPM.

Propeller

Propeller RPM indicates propeller speed in RPM.

RPM

Reverse

Reverse Thrust is the thrust produced when the

Thrust

propeller blades are rotated past flat pitch into the

reverse range.

SHP

SHP is shaft horsepower and is the power delivered at

the propeller shaft.

SHP = Propeller RPM x Torque (foot-pounds)

5252

Takeoff

Takeoff Power is the maximum power rating and is

Power

limited to a maximum of 5 minutes whenever ITT is

greater than 825°C, under normal operation. Use of this

power should be limited to normal takeoff operations.

This power corresponds to that shown in Section 5,

Performance, Maximum Engine Torque For Takeoff.

Torque

Torque is a measurement of rotational force exerted by

the engine on the propeller.

Windmill

Windmill is propeller rotation from airstream inputs.

1-14

U.S.

208BPHCUS-00

CESSNA

SECTION 1

MODEL 208B (867 SHP)

GENERAL

GARMIN G1000

SYMBOLS, ABBREVIATIONS AND TERMINOLOGY

(Continued)

AIRPLANE PERFORMANCE AND FLIGHT PLANNING

TERMINOLOGY

Demonstrated

Demonstrated Crosswind Velocity is the velocity of

Crosswind

the crosswind component for which adequate control

Velocity

of the airplane during takeoff and landing was actually

demonstrated during certification tests. The value

shown is not considered to be limiting.

Usable Fuel

Usable Fuel is the fuel available for flight planning.

Unusable Fuel Unusable Fuel is the quantity of fuel that cannot be

safely used in flight.

PPH

Pounds Per Hour is the amount of fuel consumed per

hour.

NM/1000 lbs

Nautical Miles Per Thousand Pounds of Fuel is the

distance which can be expected per 1000 pounds of

fuel consumed at a specific engine power setting and/

or flight configuration.

g is acceleration due to gravity.

Course Datum Course Datum is the compass reference used by the

autopilot, along with course deviation, to provide lateral

control when tracking a navigation signal.

Land As Soon Land at the nearest suitable airport. Unless

As Possible

otherwise specified, use Normal Procedures for

Approach, Before Landing, and Landing. Extreme

situations can require an off airport landing. Primary

consideration is safety of occupants.

Land As Soon Land at a suitable airport. Unless otherwise

As Practical

specified, use Normal Procedures for Approach,

Before Landing, and Landing. The primary

consideration is the urgency of the emergency or

abnormal situation. Continuing to the destination or an

alternate with appropriate service facilities can be an

option.

208BPHCUS-00

U.S.

1-15

SECTION 1

CESSNA

GENERAL

MODEL 208B (867 SHP)

GARMIN G1000

SYMBOLS, ABBREVIATIONS AND TERMINOLOGY

(Continued)

AUTOPILOT/FLIGHT

DIRECTOR

AND

AFCS

TERMINOLOGY

CAUTION

A thorough understanding of the difference between an

autopilot, a flight director, and an AFCS is required

before operating any of the components of the Garmin

G1000/GFC

700 Flight Control System. Refer to

Garmin Cockpit Resource Guide (CRG) for complete

operating details.

Autopilot

Autopilot is a system which automatically controls

attitude and/or flight path of the airplane as directed by

the pilot through the system's computer.

Flight

Flight Director is a system which provides visual

Director

recommendations to the pilot to allow him to manually

control the airplane attitude and/or flight path in response

to his desires as selected through the system's computer.

Automated

AFCS applies to the union of autopilot and flight director

Flight

systems which allows the pilot to manage his flight by

Control

observing computed visual recommendations while the

System

autopilot automatically follows these recommendations as

(AFCS)

selected by the pilot using the system's controls.

1-16

U.S.

208BPHCUS-00

CESSNA

SECTION 1

MODEL 208B (867 SHP)

GENERAL

GARMIN G1000

SYMBOLS, ABBREVIATIONS AND TERMINOLOGY

(Continued)

WEIGHT AND BALANCE TERMINOLOGY

Reference

Reference Datum is an imaginary vertical plane from

Datum

which all horizontal distances are measured for

balance purposes.

Station

Station is a location along the airplane fuselage given

in terms of the distance from the reference datum.

Arm

Arm is the horizontal distance from the reference

datum to the center of gravity (C.G.) of an item.

Moment

Moment is the product of the weight of an item

multiplied by its arm. (Moment divided by the constant

1000 is used in this POH/AFM to simplify balance

calculations by reducing the number of digits.)

Center of

Center of Gravity is the point at which an airplane, or

Gravity (C.G.)

equipment, would balance if suspended. Its distance

from the reference datum is found by dividing the total

moment by the total weight of the airplane.

C.G. Arm

Center of Gravity Arm is the arm obtained by adding

the airplane's individual moments and dividing the sum

by the total weight.

C.G. Limits

Center of Gravity Limits are the extreme center of

gravity locations within which the airplane must be

operated at a given weight.

Standard

Standard Empty Weight is the weight of a standard

Empty Weight

airplane, including unusable fuel, full operating fluids

and full engine oil.

Basic Empty

Basic Empty Weight is the standard empty weight

Weight

plus the weight of optional equipment.

Useful Load

Useful Load is the difference between ramp weight

and the basic empty weight.

(Continued Next Page)

208BPHCUS-00

U.S.

1-17

SECTION 1

CESSNA

GENERAL

MODEL 208B (867 SHP)

GARMIN G1000

SYMBOLS, ABBREVIATIONS AND TERMINOLOGY

(Continued)

WEIGHT AND BALANCE TERMINOLOGY (Continued)

MAC

Mean Aerodynamic Chord is a chord of an imaginary

rectangular airfoil having the same pitching moments

throughout the flight range as that of the actual wing.

Maximum

Maximum Ramp Weight is the maximum weight

Ramp Weight

approved for ground maneuver, and includes the

weight of fuel used for start, taxi and runup.

Maximum

Maximum Takeoff Weight is the maximum weight

Takeoff Weight approved for the start of the takeoff roll.

Maximum

Maximum Landing Weight is the maximum weight

Landing

approved for the landing touchdown.

Weight

Tare

Tare is the weight of chocks, blocks, stands, etc. used

when weighing an airplane, and is included in the

scale readings. Tare is deducted from the scale

reading to obtain the actual (net) airplane weight.

1-18

U.S.

208BPHCUS-00

CESSNA

SECTION 1

MODEL 208B (867 SHP)

GENERAL

GARMIN G1000

METRIC/IMPERIAL/U.S. CONVERSION CHARTS

The following charts have been provided to help international operators

convert U.S. measurement supplied with the POH/AFM into metric and

imperial measurements.

The standard followed for measurement units shown is the National

Institute of Standards Technology (NIST), Publication 811, "Guide for

the Use of the International System of Units (SI)."

Please refer to the following pages for these charts.

208BPHCUS-00

U.S.

1-19

CESSNA

SECTION 2

MODEL 208B (867 SHP)

OPERATING LIMITATIONS

GARMIN G1000

OPERATING LIMITATIONS

TABLE OF CONTENTS

Page

Introduction

2-3

Airspeed Limitations

2-4

Airspeed Indicator Markings

2-5

Powerplant Limitations

2-6

Powerplant Instrument Markings

2-10

Miscellaneous Instrument Markings

. 2-11

Preflight

2-12

Visual and Tactile Check

2-12

Weight Limits

2-13

Center of Gravity Limits

2-13

Maneuver Limits

2-14

Flight Load Factor Limits

2-14

Flight Crew Limits

2-14

Kinds Of Operations Limits

2-15

Kinds of Operations Equipment List

.2-16

Fuel Limitations

2-25

Maximum Operating Altitude Limit

2-28

Outside Air Temperature Limits

2-28

Maximum Passenger Seating Limits

2-28

System and Equipment Limitations

2-29

Flap Limitations

2-29

Standby Electric System

2-29

Aux Audio System

2-29

12V Power System

2-29

Generator Limitations

2-30

G1000 Limitations

2-31

Operational Approvals

2-33

Garmin GFC-700 Automated Flight Control System (AFCS) . . . 2-34

L3 Communications WX 500 Stormscope

2-35

Sirius XM Weather

2-35

Traffic Advisory System (TAS)

2-35

Terrain Awareness and Warning System (TAWS-B)

2-36

(Continued Next Page)

FAA APPROVED

208BPHCUS-00

U.S.

2-1

SECTION 2

CESSNA

OPERATING LIMITATIONS

MODEL 208B (867 SHP)

GARMIN G1000

TABLE OF CONTENTS (Continued)

Page

Other Limitations

2-37

Optional Equipment User’s Guide

2-37

Type II, Type III or Type IV Anti-ice Fluid Takeoff Limitations . . 2-37

Flight in Known Icing Visual Cues

2-38

Placards

2-39

Interior Placards

2-39

Flight Crew Area

2-39

Passenger Area

2-46

Cargo Area

2-48

Exterior Placards

2-51

Wings

2-54

Engine Compartment

2-56

Forward Fuselage

2-59

Aft Fuselage

2-61

FAA APPROVED

2-2

208BPHCUS-00

U.S.

CESSNA

SECTION 2

MODEL 208B (867 SHP)

OPERATING LIMITATIONS

GARMIN G1000

INTRODUCTION

Section

2 includes operating limitations, instrument markings, and

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

engine, standard/non-standard systems and standard/non-standard

equipment.

WARNING

The limitations included in this section and in

Section

9 have been approved by the Federal

Aviation Administration. Observance of these

operating limitations is required by Federal

Aviation Regulations.

NOTE

• Operation in countries other than the United States may

require observance of other limitations, procedures or

performance data.

• Refer to Section 9, Supplements, of this POH/AFM for

amended operating limitations, operating procedures,

performance data and other necessary information for

airplanes equipped with specific options.

• The airspeeds listed in Figure 2-1, Airspeed Limitations,

and Figure 2-2, Airspeed Indicator Markings, are based

on Airspeed Calibration data shown in Section 5 with the

normal static source. If the alternate static source is

being used, ample margins should be observed to allow

for the airspeed calibration variations between the

normal and alternate static sources as shown in Section

The Cessna Model No. 208B is certificated under FAA Type Certificate

No. A37CE.

FAA APPROVED

208BPHCUS-00

U.S.

2-3

CESSNA

SECTION 2

MODEL 208B (867 SHP)

OPERATING LIMITATIONS

GARMIN G1000

AIRSPEED INDICATOR MARKINGS

The airspeed on both the PFD and standby airspeed indicator is

indicated with an airspeed tape with colored bands, refer to Section 7,

Flight Instruments, for more information on airspeed indication. The

indicator markings and their color code significance are shown in

Figure 2-2.

AIRSPEED INDICATOR MARKINGS

* G1000 airspeed indicator only.

Figure 2-2

FAA APPROVED

208BPHCUS-00

U.S.

2-5

SECTION 2

CESSNA

OPERATING LIMITATIONS

MODEL 208B (867 SHP)

GARMIN G1000

POWERPLANT LIMITATIONS

ENGINE

Engine Manufacturer

Pratt & Whitney Canada Inc.

Engine Model Number

PT6A-140

Engine Operating Limits

Refer to Figure 2-3

Fuel Grade and Approved Fuel Additives . .Refer to Fuel Limitations

OIL SPECIFICATION

Oil conforming to Pratt & Whitney Engine Service Bulletin No. 1001,

and all revisions or supplements thereto, must be used. Refer to

Section 8, Airplane Handling, Service and Maintenance, Servicing,

Oil, for a listing of approved oils.

When adding oil, service the engine with the type and viscosity

which is currently being used in the engine.

PROPELLER

Propeller Manufacturer

Hartzell Propeller Inc.

Propeller Model Number

HC-B3TN-3AF/T10890CN-2

Propeller Diameter

Maximum

106 Inches (2.7 m)

Minimum

104 Inches (2.6 m)

Hartzell Propeller Blade Angle at 42-inch Station:

Feathered

78.0 + 1.0°

Low Pitch

8.5 + 0.2°

Maximum Reverse

-21 + 0.5°

(Continued Next Page)

FAA APPROVED

2-6

208BPHCUS-01

U.S.

CESSNA

SECTION 2

MODEL 208B (867 SHP)

OPERATING LIMITATIONS

GARMIN G1000

POWERPLANT LIMITATIONS (Continued)

PROPELLER SYSTEM OPERATING LIMITS

An overspeed governor check shall be performed before the first

flight of the day, after engine control system maintenance, or if

adjustment has been made.

Propeller RPM must be set at

1900 during all instrument

approaches.

ENGINE CONTROL OPERATING LIMITS

Flight operation with the POWER Lever set below the IDLE position

is prohibited. Such positioning may lead to loss of airplane control or

may result in an engine overspeed condition and consequent loss of

engine power.

Operation of the EMERGENCY POWER Lever is prohibited with the

POWER Lever out of the IDLE position.

ENGINE STARTING CYCLE LIMITS

Using the airplane battery, the starting cycle shall be limited to the

following intervals and sequence:

30 seconds ON - 60 seconds OFF,

30 seconds ON - 30 minutes OFF.

Repeat the above cycle as required.

Using external power, the starting cycle shall be limited to the

following intervals and sequence:

20 seconds ON - 120 seconds OFF,

20 seconds ON - 60 minutes OFF.

Repeat the above cycle as required.

(Continued Next Page)

FAA APPROVED

208BPHCUS-00

U.S.

2-7

CESSNA

SECTION 2

MODEL 208B (867 SHP)

OPERATING LIMITATIONS

GARMIN G1000

POWER PLANT LIMITATIONS (Continued)

ENGINE OPERATING LIMITS (Continued)

NOTE

Per Section 5, Performance, Figure 5-8, Maximum Engine

Torque for Takeoff. Anytime ITT exceeds 825°C, this power

setting is limited to 5 minutes.

For every

10°C

(18°F) below

-30°C

(-22°F) ambient

temperature, reduce maximum allowable Ng by 2.2%.

Normal oil pressure is 85 to 105 PSI at Ng speeds above 72%

with oil temperature between 60° and 70°C (140° and 158°F).

Oil pressures below 80 PSI are undesirable and should be

tolerated only for the completion of the flight, preferably at a

reduced power setting. Oil pressures below normal should be

reported as an engine discrepancy and should be corrected

prior to next flight. Oil pressures below 40 PSI are unsafe and

require that either the engine be shut down or a landing be

made as soon as possible using the minimum power required

to maintain flight.

2090 PROP RPM may be used in an emergency condition,

to complete a flight, and may be utilized at all engine ratings.

Use of Maximum Rated Power Setting is intended for

abnormal situations (e.g., maintain altitude or climb out of

severe icing or windshear conditions).

Maximum transient oil temperature is 104°C for a maximum of

10 minutes.

Per Section 5, Performance, Figures 5-9, Maximum Engine

Torque for Climb.

Per Section 5, Performance, Figure 5-20, Cruise Maximum

Torque with Cargo Pod Installed or Figure

5-37, Cruise

Maximum Torque without Cargo Pod.

Increase Ng to keep idle ITT within limit.

10. Torque must not exceed 2397 foot-pounds. Full 867 SHP

rating is available only at propeller RPM settings of 1900.

11. A transient fluctuation of up to +40 PROP RPM is permitted to

account for power setting accuracy and steady state

fluctuations. Note: Steady state Max N

p setting is 1900 RPM.

Figure 2-3 (Sheet 2)

FAA APPROVED

208BPHCUS-01

U.S.

2-9

SECTION 2

CESSNA

OPERATING LIMITATIONS

MODEL 208B (867 SHP)

GARMIN G1000

POWERPLANT INSTRUMENT MARKINGS

Powerplant instrument markings and their color code significance are

shown in Figure 2-3. Operation with indications in the red range is

prohibited. Avoid operating with indicators in the yellow range.

NOTE

1. Incorporates dynamic redline that moves to display

maximum allowable torque as a function of OAT and

pressure altitude. Takeoff torque is displayed up to 16,000 feet

MSL, while maximum rated torque is displayed at 16,000 feet

MSL and above.

2. Incorporates blue torque bug that moves to compensate for

OAT, pressure altitude and propeller RPM variation.

3. Incorporates red line that moves to compensate for OAT.

100% Ng is 37,468 RPM.

4. Start mode values also valid for OFF mode (red triangle at

1090°C not shown in OFF mode).

5. Start mode is defined as the period between starter

engagement and the point where idle Ng RPM reaches 55%.

6. Run mode is defined as anytime idle Ng RPM is above 55%.

Figure 2-4

FAA APPROVED

2-10

208BPHCUS-01

U.S.

SECTION 2

CESSNA

OPERATING LIMITATIONS

MODEL 208B (867 SHP)

GARMIN G1000

PREFLIGHT

Takeoff is prohibited with any frost, ice, snow, or slush adhering to the

wings, horizontal stabilizer, vertical stabilizer, control surfaces, propeller

blades, and/or engine air inlets.

WARNING

Even small amounts of frost, ice, snow or slush on

the wing may adversely change lift and drag.

Failure to remove these contaminants will degrade

airplane performance and will prevent a safe takeoff

and climb.

VISUAL AND TACTILE CHECK

To assure the absence of frost, a tactile check of the wing leading edge

and upper surface, as specified in Section 4, Normal Procedures, is

required in addition to a visual inspection if the OAT is below 10°C

(50°F). During ground icing conditions, takeoff must be accomplished

within 5 minutes of completing the tactile check unless the airplane is

operated per 14 CFR 135.227(b)(3).

Ground icing conditions are defined as:

1. The OAT is 2°C (36°F) or below and visible moisture is present

(i.e. rain, drizzle, sleet, snow, fog, water is present on the wing,

etc.), or,

2. The OAT is 5°C (41°F) or below and conditions are conducive to

active frost formation

(e.g. clear night with a dew point

temperature/OAT difference of 3°C (5°F) or less).

Takeoff is prohibited if frost, ice or snow may reasonably be expected to

adhere to the airplane between the tactile check and takeoff (e.g. snow

near freezing temperature with no deicing/anti-ice fluid application).

FAA APPROVED

2-12

208BPHCUS-00

U.S.

CESSNA

SECTION 2

MODEL 208B (867 SHP)

OPERATING LIMITATIONS

GARMIN G1000

WEIGHT LIMITS

Maximum Ramp Weight

8842 Pounds (4010 kg)

Maximum Takeoff Weight

8807 Pounds (3994 kg)

Maximum Landing Weight

8500 Pounds (3855 kg)

NOTE

Refer to Section 6, Weight and Balance, Figure 6-11, Cabin

Internal Loading Arrangements, for recommended loading

arrangements.

CENTER OF GRAVITY LIMITS

CENTER OF GRAVITY RANGE

FORWARD WITH OR WITHOUT CARGO POD

185.00 inches (4699 mm) (11.19% MAC) aft of datum at 6500

pounds (2948 kg) or less, with straight line variation to 193.37 inches

(4912 mm) (23.80% MAC) aft of datum at 8000 pounds (3628 kg)

and straight line variation to 199.15 inches (5059 mm) (32.50%

MAC) aft of datum at 8807 pounds (3994 kg).

AFT WITH OR WITHOUT CARGO POD

204.35 inches (5190 mm) (40.33% MAC) aft of datum at all weights

up to 8807 pounds (3994 kg).

REFERENCE DATUM

100 inches (2540 mm) forward of front face of firewall.

MEAN AERODYNAMIC CHORD (MAC)

The leading edge of the MAC is 177.57 inches (4510 mm) aft of the

datum. The MAC length is 66.40 inches (1686 mm).

FAA APPROVED

208BPHCUS-00

U.S.

2-13

SECTION 2

CESSNA

OPERATING LIMITATIONS

MODEL 208B (867 SHP)

GARMIN G1000

MANEUVER LIMITS

This airplane is certificated in the normal category. The normal category

is applicable to aircraft intended for non-aerobatic operations. These

include any maneuvers incidental to normal flying, stalls (except whip

stalls), lazy eights, chandelles, and turns in which the angle of bank is

not more than 60°.

Aerobatic maneuvers, including spins, are not approved.

FLIGHT LOAD FACTOR LIMITS

Maximum Takeoff Weight

8807 Pounds (3994 kg)

*Flaps UP

+3.8g, -1.52g

*Flaps LAND (All Settings)

+2.4g

*The design load factors are 150% of the above, and in all cases,

the structure meets or exceeds design loads.

FLIGHT CREW LIMITS

One pilot required in left seat.

FAA APPROVED

2-14

208BPHCUS-01

U.S.

CESSNA

SECTION 2

MODEL 208B (867 SHP)

OPERATING LIMITATIONS

GARMIN G1000

KINDS OF OPERATIONS LIMITS

The Cessna 208B (867 SHP) equipped with the Garmin G1000 is

approved for day and night, VFR and IFR operations. The airplane may

be approved for flight into known icing conditions when appropriate

equipment is installed. The operating limitation placard reflects the

limits applicable at the time of Airworthiness Certificate issuance.

The minimum equipment for approved operations required under the

Operating Rules are defined by 14 CFR 91 and 14 CFR 135, as

applicable.

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

systems and equipment upon which type certification for each kind of

operation was predicated.

These systems and equipment items must be installed and operable

unless:

1. The airplane is approved to be operated in accordance with a

current Minimum Equipment List (MEL) issued by the FAA.

Or;

2. An alternate procedure is provided in the basic FAA Approved

Airplane Flight Manual for the inoperative state of the listed

equipment and all limitations are complied with.

NOTE

The following systems and equipment list does not included

all equipment required by the 14 CFR Parts 91 and 135

Operating Requirements. It also does not include

components obviously required for the airplane to be

airworthy such as wings, primary flight controls,

empennage, engine, etc.

(Continued Next Page)

FAA APPROVED

208BPHCUS-00

U.S.

2-15

CESSNA

SECTION 2

MODEL 208B (867 SHP)

OPERATING LIMITATIONS

GARMIN G1000

FUEL LIMITATIONS

FUEL CAPACITY

TOTAL FUEL

Both Tanks and Reservoir:

339.1 U.S. Gallons (1283 l)

Both Tanks:

335.6 U.S. Gallons (1270 l)

Each Tank:

167.8 U.S. Gallons (635 l)

TOTAL USABLE FUEL

Both Tanks ON and Reservoir:

335.3 U.S. Gallons (1268 l)

Both Tanks ON:

332.0 U.S. Gallons (1256 l)

Single Tank ON:

165.0 U.S. Gallons (624 l)

TOTAL UNUSABLE FUEL

Both Tanks ON:

3.6 U.S. Gallons (13 l)

Single Tank ON:

2.8 U.S. Gallons (10 l)

Maximum Fuel Imbalance:

200 Pounds (90 kg)

NOTE

To achieve full fuel capacity, fill fuel tank to the top of the

filler neck. Filling fuel tanks to the bottom of the fuel filler

collar

(level with flapper valve) allows space for thermal

expansion and results in a decrease in fuel capacity of 4.0

U.S. gallons (15 l) per side (8.0 U.S. gallons (30 l) total).

The fuel quantity, fuel used and fuel remaining functions of the G1000

are supplemental information only and must be verified by the pilot.

Continuous uncoordinated flight is prohibited if L FUEL LOW, R FUEL

LOW or L-R FUEL LOW annunciator is shown on PFD.

Unusable fuel quantity will continue to increase the longer a significant

sideslip is maintained.

Due to possible fuel starvation, maximum full rudder sideslip duration is

limited to a maximum of three minutes.

FAA APPROVED

208BPHCUS-00

U.S.

2-25

CESSNA

SECTION 2

MODEL 208B (867 SHP)

OPERATING LIMITATIONS

GARMIN G1000

FUEL LIMITATIONS (Continued)

FUEL GRADE (SPECIFICATION) AND FUEL ADDITIVES

(Continued)

APPROVED FUEL ADDITIVES

One of the following fuel system anti-ice additives must be added to the

fuel as noted at the following concentrations. Use of fuel anti-ice

additives is required if freezing temperatures are expected during any

part of the flight. Refer to Section 8, Airplane Handling, Service and

Maintenance, Servicing, Fuel, for additional information and

recommended blending instructions for approved fuel additives.

NOTE

MIL-DTL-27686 (EGME) or MIL-DTL-85470 (DiEGME), Type:

Anti-Ice Additive, in a concentration of 0.10 to 0.15 percent by

volume.

MIL-DTL-27686 (EGME) or MIL-DTL-85470 (DiEGME), Type:

Anti-Ice Additive, in a concentration of 0.10 to 0.20 percent by

volume.

GOST

8313

(Fluid I), Type: Anti-Ice Additive, in a

concentration of 0.10 to 0.30 percent by volume.

CIS TU6-10-1458 (Fluid I-M), Type: Anti-Ice Additive, in a

concentration of 0.10 to 0.30 percent by volume.

T1301

(SH0396-92), Type: Anti-Ice Additive, in a

concentration of 0.10 to 0.15 percent by volume.

DuPont Stadis 450, Type: Static Dissipator, in a concentration

as required to bring fuel up to 300 conductive units, not to

exceed 1 Parts Per Million (PPM).

SOHIO Biobor JF, Type: Biocide, at a concentration not to

exceed

20 PPM of elemental boron

(270 PPM of total

additive).

Kathon FP, Type: Biocide, at a concentration not to exceed

100 PPM of total additive.

Figure 2-6 (Sheet 2)

FAA APPROVED

208BPHCUS-01

U.S.

2-27

SECTION 2

CESSNA

OPERATING LIMITATIONS

MODEL 208B (867 SHP)

GARMIN G1000

MAXIMUM OPERATING ALTITUDE LIMIT

Non-Icing Conditions

25,000 Feet

Icing Conditions (if equipped)

20,000 Feet

Any conditions with any ice on the airplane

20,000 Feet

OUTSIDE AIR TEMPERATURE LIMITS

Cold Day

-54°C from Sea Level to 25,000 Feet

Hot Day:

Ground Operations

+42°C from Sea Level to 5000 Feet

ISA +37°C above 5000 Feet

Flight Operations

ISA +37°C from Sea Level to 25,000 Feet

Refer to Section 5, Performance, Figure 5-5, ISA Conversion and

Operating Temperature Limits Chart, for a graphical presentation of the

operating air temperature limits.

NOTE

• With both deck skin fans inoperative, ground operations

are limited to +42°C for 30 minutes.

• Ground operations up to +38°C are not time limited with

both deck skin fans inoperative.

MAXIMUM PASSENGER SEATING LIMITS

In the passenger version, up to 11 seats may be installed. The right

front seat may be occupied by either a second crew member or a

passenger. When the right front seat is occupied by a passenger, only

eight seats in the aft cabin can be occupied.

In the cargo version, a maximum of one seat may be installed to the

right of the pilot’s seat for a second crew member or a passenger.

Refer to Section 6, Weight and Balance, Figure 6-11, Cabin Internal

Loading Arrangements, for approved seat locations.

FAA APPROVED

2-28

208BPHCUS-00

U.S.

CESSNA

SECTION 2

MODEL 208B (867 SHP)

OPERATING LIMITATIONS

GARMIN G1000

SYSTEM AND EQUIPMENT LIMITATIONS

FLAP LIMITATIONS

Approved Takeoff Range

UP to TO/APR

Approved Landing Range

UP to LAND

Approved Landing Range in Icing Conditions

UP to TO/APR

STANDBY ELECTRIC SYSTEM

When operating the standby electrical system, the maximum electrical

load is 75 amps from Sea Level to 21,000 feet. To ensure adequate

alternator cooling at higher altitudes, reduce maximum standby

electrical system load 5 amps per 1000 feet above 21,000 feet.

AUX AUDIO SYSTEM

Use of the AUX AUDIO entertainment input is prohibited during takeoff

and landing.

Use of the AUX AUDIO entertainment audio input and Portable

Electronic Devices

(PED), such as cellular telephones, games,

cassette, CD or MP3 players, is prohibited under IFR unless the

operator of the airplane has determined that the use of the Aux Audio

System and the connected PED(s) will not cause interference with the

navigation or communication system of the airplane.

12V POWER SYSTEM

The 12 Volt Power System is limited to a maximum combined current

draw of 10 Amps (120 watts) all locations.

The 12 Volt Power System (12V POWER OUTLET) is not certified for

supplying power to flight-critical communications or navigation devices.

Use of the 12 Volt Power System is prohibited during takeoff and

landing.

Use of the 12 Volt Power System is prohibited under IFR unless the

operator of the airplane has determined that the use of the 12 VDC

power supply and connected PED(s) will not cause interference with

the navigation or communication systems of the airplane.

FAA APPROVED

208BPHCUS-00

U.S.

2-29

SECTION 2

CESSNA

OPERATING LIMITATIONS

MODEL 208B (867 SHP)

GARMIN G1000

SYSTEM AND EQUIPMENT LIMITATIONS (Continued)

GENERATOR LIMITATIONS

Maximum generator load limit is a function of Ng, air conditioning and

bleed air heat position.

ON GROUND

MAXIMUM GENERATOR LOAD - GROUND OPERATIONS

AIR CONDITIONING - OFF,

AIR CONDITIONING - ON,

BLEED AIR HEAT - ON or OFF

BLEED AIR HEAT - OFF

AMPS

55%

60%

100

60%

65%

135

65%

155

IN FLIGHT

MAXIMUM GENERATOR LOAD - FLIGHT OPERATIONS

AIR CONDITIONING - OFF,

AIR CONDITIONING - ON,

BLEED AIR HEAT - ON or OFF

BLEED AIR HEAT - OFF

AMPS

65%

125

65%

125

72%

140

72%

170

>80%

200

>80%

200

FAA APPROVED

2-30

208BPHCUS-00

U.S.

CESSNA

SECTION 2

MODEL 208B (867 SHP)

OPERATING LIMITATIONS

GARMIN G1000

SYSTEM AND EQUIPMENT LIMITATIONS (Continued)

G1000 LIMITATIONS

The current Garmin G1000 Cockpit Reference Guide (CRG) Part

Number and System Software Version that must be available to the

pilot during flight are displayed on the MFD AUX group, SYSTEM

STATUS page.

GPS based IFR enroute, oceanic and terminal navigation is prohibited

unless the pilot verifies the currency of the database or verifies each

selected waypoint for accuracy by reference to current approved data.

RNAV/GPS instrument approaches must be accomplished in

accordance with approved instrument approach procedures that are

retrieved from the G1000 navigation database. The G1000 database

must incorporate the current update cycle.

Use of the NAVIGATION 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.

Navigation using the G1000 is not authorized North of 72° 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 regions:

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

(Northern Canada).

2. North of 70° North latitude between longitude 70° W and 128° W

(Northern Canada).

3. North of 70° North latitude between longitude 85° E and 114° E

(Northern Russia).

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

E (region south of Australia and New Zealand).

(Continued Next Page)

FAA APPROVED

208BPHCUS-00

U.S.

2-31

SECTION 2

CESSNA

OPERATING LIMITATIONS

MODEL 208B (867 SHP)

GARMIN G1000

SYSTEM AND EQUIPMENT LIMITATIONS (Continued)

G1000 LIMITATIONS (Continued)

Use of the TERRAIN PROXIMITY information for primary terrain

avoidance is prohibited. The Terrain Proximity map is intended only to

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

terrain clearance at all times. In addition, Terrain Proximity information

is not available in locations north of 75° North latitude or South of 60°

South latitude due to the absence of terrain data in these geographical

areas.

The COM 1/2 (split COM) function of the Audio Panel is not approved

for use. During COM 1/2 operation, transmission by one crew member

inhibits reception by the other crew member.

Dispatch with GIA1, GIA2, PFD, or MFD cooling advisory message is

prohibited.

Verify the torque gage dynamic redline agrees with the values listed in

Figure 5-8, Maximum Engine Torque For Takeoff, for current altitude

and temperature.

The dynamic redline is a graphical representation of takeoff power

below 16,000 feet MSL and Maximum Rated Power above 16,000 feet

MSL as depicted in Section 5, Performance, Figure 5-8, Maximum

Engine Torque For Takeoff chart and Figure 5-9 Maximum Engine

Torque For Climb. The dynamic redline automatically compensates for

altitude and temperature changes and adjusts displayed takeoff torque

for inertial separator deployment and bleed air heat switch position.

Failure to comply with the dynamic redline indication can result in

accelerated engine wear, unscheduled engine maintenance and

increased operating costs even though no other published engine

limitation has been exceeded.

The maximum cruise torque bug functions of the G1000 engine torque

indicator is advisory information only.

All power settings must be verified by the pilot, refer to Section 5,

Performance, Figure 5-8, Maximum Engine Torque For Takeoff, Figure

5-9, Maximum Engine Torque For Climb and Figure 5-19, Cruise

Performance (with Cargo Pod) or Figure 5-36, Cruise Performance

(without Cargo Pod) for the approved engine power settings.

FAA APPROVED

2-32

208BPHCUS-01

U.S.

CESSNA

SECTION 2

MODEL 208B (867 SHP)

OPERATING LIMITATIONS

GARMIN G1000

SYSTEM AND EQUIPMENT LIMITATIONS (Continued)

G1000 LIMITATIONS (Continued)

OPERATIONAL APPROVALS

The Garmin G1000 GPS receivers are approved under TSO C145c

Class 3. The Garmin G1000 system has been demonstrated capable

of, and has been shown to meet the accuracy requirements for, the

following operations provided it is receiving usable navigation data.

These do not constitute operational approvals.

1. Enroute, terminal, non-precision instrument approach

operations using GPS and WAAS (including GPS, or GPS, and

RNAV approaches), and approach procedures with vertical

guidance (including LNAV/VNAV, LNAV + V, and LPV) within the

U.S. National Airspace System in accordance with AC 20-138C.

2. As a required Long Range Navigation (LRN) system for use in

the following types of airspace when used in conjunction with

Garmin WAAS Fault Detection/Exclusion Prediction Program,

part number 006-A0154-01 or later approved version:

a. Oceanic/Remote - RNP-10 (per FAA AC 20-138C, FAA

Order

8400-12C, and FAA Order

8900.1). Both GPS

receivers are required to be operating and receiving usable

signals except for routes requiring only one Long Range

Navigation (LRN) sensor.

NOTE

Each display computes an independent navigation solution

based on the on-side GPS sensor. However, either display

will automatically revert to the cross-side sensor if the on-

side sensor fails or if the cross-side sensor is determined to

be more accurate. A BOTH ON GPS1 or BOTH ON GPS2

message does not necessarily mean that one GPS has

failed. Refer to the MFD AUX-GPS STATUS page to

determine the status of the unused GPS.

b. North Atlantic

(NAT) Minimum Navigational Performance

Specifications (MNPS) Airspace per AC 91-49 Chg 1 and

AC 120-33. Both GPS receivers are required to be operating

and receiving usable signals except for routes requiring only

one Long Range Navigation sensor.

c. Enroute and Terminal including RNP5/BRNAV and PRNAV

(RNP-1) - In accordance with JAA TGL-10, ACJ 20X4, AC

90-96A, and AC 90-100A, provided the FMS is receiving

usable navigation information from one or more GPS

receivers.

FAA APPROVED

208BPHCUS-00

U.S.

2-33

SECTION 2

CESSNA

OPERATING LIMITATIONS

MODEL 208B (867 SHP)

GARMIN G1000

SYSTEM AND EQUIPMENT LIMITATIONS (Continued)

G1000 LIMITATIONS (Continued)

GARMIN GFC 700 AUTOMATED FLIGHT CONTROL SYSTEM

(AFCS)

The GFC

700 AFCS preflight test must be successfully

completed prior to use of the autopilot, flight director or manual

electric trim.

A pilot, with the seat belt fastened, must occupy the left pilot’s

seat during all autopilot operations.

The autopilot and yaw damper must be off during all takeoff and

landings.

Autopilot maximum engagement speed

175 KIAS

Autopilot minimum engagement speed

80 KIAS

Electric Trim maximum operating speed

175 KIAS

The autopilot must be disengaged below 200 feet AGL during

approach operations and below 800 feet AGL during all other

operations.

ILS approaches using the autopilot/flight director are limited to

Category I approaches only.

Raw data ILS approaches below 400 feet AGL are prohibited.

Use of the autopilot is prohibited when the audio panel is

inoperative, since the aural alert will not be provided when

autopilot is disengaged.

When conducting a missed approach, use of the autopilot is

prohibited until a rate of climb is established that will meet all

altitude requirements of the missed approach procedure.

FAA APPROVED

2-34

208BPHCUS-00

U.S.

CESSNA

SECTION 2

MODEL 208B (867 SHP)

OPERATING LIMITATIONS

GARMIN G1000

SYSTEM AND EQUIPMENT LIMITATIONS (Continued)

G1000 LIMITATIONS (Continued)

L3 COMMUNICATIONS WX 500 STORMSCOPE (if installed)

Use of the WEATHER MAP (WX-500 Stormscope) for hazardous

weather (thunderstorm) penetration is prohibited. LTNG information on

the NAVIGATION MAP or WEATHER MAP is approved only as an aid

to hazardous weather avoidance, not penetration. The WX-500

Stormscope user’s guide should be available to the pilot during flight.

SIRIUS XM WEATHER (if installed)

Use of the XM data link weather information for maneuvering in, near or

around areas of hazardous weather is prohibited. Information

contained within XM data link weather products may not accurately

depict current weather conditions.

Do not use the indicated XM data link weather product age to

determine the age of the weather information shown by the XM data

link weather product. Due to time delays inherent in gathering and

processing weather data for XM data link transmission, the weather

information shown by the XM data link weather product may be

significantly older than the indicated weather product age.

TRAFFIC ADVISORY SYSTEM (TAS) (if installed)

Use of the TRAFFIC MAP to maneuver the airplane to avoid traffic is

prohibited. The Traffic Advisory System (TAS) is intended for advisory

use only. TAS is intended only to help the pilot to visually locate traffic.

It is the responsibility of the pilot to see and maneuver to avoid traffic.

TAS is unable to detect any intruding aircraft without an operating

transponder. TAS can detect and track aircraft with either an ATCRBS

(operating in Mode A or C) or Mode S transponders.

ATC procedures and the “see and avoid concept” will continue to be the

primary means of aircraft separation. However, if communication is lost

with ATC, TAS adds a significant backup for collision avoidance.

FAA APPROVED

208BPHCUS-00

U.S.

2-35

SECTION 2

CESSNA

OPERATING LIMITATIONS

MODEL 208B (867 SHP)

GARMIN G1000

SYSTEM AND EQUIPMENT LIMITATIONS (Continued)

G1000 LIMITATIONS (Continued)

TERRAIN AWARENESS AND WARNING SYSTEM (TAWS-B) (if

installed)

Use of the Terrain Awareness and Warning System (TAWS-B) to

navigate to avoid terrain or obstacles is prohibited. TAWS-B is only

approved as an aid to help the pilot to see-and-avoid terrain or

obstacles.

TAWS-B must be inhibited when landing at a location not included in

the airport database.

Use of TAWS-B is prohibited when operating using the QFE altimeter

setting (altimeter indicates 0 feet altitude when the airplane is on the

runway).

The pilot is authorized to deviate from the current ATC clearance only

to the extent necessary to comply with TAWS-B warnings.

The geographic area of the TAWS-B database must match the

geographic area in which the airplane is being operated.

TAWS-B is not available in locations north of 75° North latitude or south

60° South latitude due to the absence of terrain data in these

geographical areas.

FAA APPROVED

2-36

208BPHCUS-00

U.S.

CESSNA

SECTION 2

MODEL 208B (867 SHP)

OPERATING LIMITATIONS

GARMIN G1000

OTHER LIMITATIONS

OPTIONAL EQUIPMENT USER’S GUIDE

The pilot is responsible for ensuring the appropriate user’s guide(s) for

all optional equipment installed in the airplane is accessible to the pilot

in flight.

TYPE II, TYPE III OR TYPE IV ANTI-ICE FLUID TAKEOFF

LIMITATIONS

FLAP LIMITATIONS

Takeoff Flaps Setting

AIRSPEED LIMITATIONS

Takeoff Rotation Speed

83 KIAS

FAA APPROVED

208BPHCUS-00

U.S.

2-37

SECTION 2

CESSNA

OPERATING LIMITATIONS

MODEL 208B (867 SHP)

GARMIN G1000

OTHER LIMITATIONS (Continued)

FLIGHT IN KNOWN ICING VISUAL CUES

As Required by AD 96-09-15, Paragraph (a) (1)

WARNING

Severe icing may result from environmental

conditions outside of those for which the airplane

is certificated. Flight in freezing rain, freezing

drizzle, or mixed icing conditions

(supercooled

liquid water and ice crystals) may result in ice

build-up on protected surfaces exceeding the

capability of the ice protection system, or may

result in ice forming aft of the protected surfaces.

This ice may not be shed using the ice protection

systems, and may seriously degrade the

performance and controllability of the airplane.

During flight, severe icing conditions that exceed those for which the

airplane is certificated shall be determined by the following visual cues.

If one or more of these visual cues exists, immediately request priority

handling from Air Traffic Control to facilitate a route or an altitude

change to exit the icing conditions.

1. Unusually extensive ice is accreted on the airframe in areas not

normally observed to collect ice.

2. Accumulation of ice on the upper or lower surface of the wing aft

of the protected area.

3. Heavy ice accumulations on the windshield, or when ice forms aft

of the curved sections on the windshield.

4. Ice forms aft of the protected surfaces of the wing struts.

Since the autopilot may mask tactile cues that indicate adverse

changes in handling characteristics, use of the autopilot is prohibited

when any of the visual cues specified above exist, or when unusual

lateral trim requirements or autopilot trim warnings are encountered

while the airplane is in icing conditions.

FAA APPROVED

2-38

208BPHCUS-00

U.S.

CESSNA

SECTION 2

MODEL 208B (867 SHP)

OPERATING LIMITATIONS

GARMIN G1000

PLACARDS

WARNING

The following information must be displayed in the

form of composite or individual placards. As a

minimum, the exact wording of these placards is

required as specified in this section. Placard

wording can be from part numbered placards

obtained from Cessna Aircraft Company or

equivalent placards installed by an approved repair

station in accordance with normal maintenance

practices/procedures.

INTERIOR PLACARDS

FLIGHT CREW AREA

In full view of the pilot on the sunvisor or windshield trim on airplanes

not equipped for flight into known icing:

(Continued Next Page)

FAA APPROVED

208BPHCUS-00

U.S.

2-39

Cessna 208B Grand Caravan EX. Airplane Flight Manual (2012) - page 1