Cessna T182 1982 Pilot Operating Handbook

.,-:~

.~

PILOT'S

OPERATING

HANDBOOK

I and

FAA

APPROVED

AIRPLANE

FLIGHT

MANUAL

o

CESSNA

AIRCRAFT COMPANY

I I1982 MODEL 1182

THIS DOCUMENT MUST

BE

Serial

No.

I

$')"

tog

lOy

CARRIED

IN

THE

AIRPLANE

AT

ALL

TIME~.

Registration

No:'J

'ret"

fP

t

THIS

HANDBOOK INCLUDES

THE

MATERIAL

REQUIRED TO

BE

FURNISHED TO

THE

PILOT

BY

CAR PART 3 AND CONSTITUTES

THE

FAA

APPROVED

AIRPLANE

FLIGHT

MANUAL.

1981

CESSNA

AIRCRAFT COMPANY

WICHITA,

KANSAS,

USA

f)

Member

of

GAMA

21

August

1981.

THIS

MANUAL

WAS

PROVIDED

FOR THE

AIRPLANE

IDENTIFIED

ON

THE TITLE

PAGE

ON

_

SUBSEQUENT

REVISIONS

SUPPLIED

BY

CESSNA

AIRCRAFT

COMPANY

MUST

BE

PROPERLY

IN-

SERTED.

CESSNA

AIRCRAFT

COMPANY,

PAWNEE

DIVISION

Cessna

Aircraft

CESSNA

CONG

RA

TULA

TIONS

MODEL

T182

CONGRATULATIONS

• • • •

Welcome

to

the

ranks

of

Cessna

owners!

Your

Cessna

has

been designed and

constructed

to

give

you

the

most

in

performance,

economy,

and

comfort.

It

is

our

desire

that

you

will

find

flying

it,

either

for

business

or

pleasure, a pleasant and

profitable

experience.

This Pilot's

Operating

Handbook

has

been

prepared

as a guide

to

help

you

get

the

most

pleasure and

utility

from

your

airplane.

It

contains

information

about

your

Cessna's

equipment,

operating

procedures,

and

performance;

and suggestions

for

its servicing and

care. We

urge

you

to

read it

from

cover

to

cover,

and

to

refer

to

it

frequently.

Our

interest

in

your

flying

pleasure

has

not

ceased

with

your

purchase

of

a Cessna.

Worldwide,

the Cessna

Dealer

organization

backed

by the Cessna

Customer

Services

Department

stands ready

to

serve you. The

following

services are

offered

by most Cessna

Dealers:

•

THE

CESSNA

WARRANTY,

which

provides

coverage

for

parts and

labor,

is

available at

Cessna Dealers

worldwide.

Specific

benefits

and

provisions

of

warranty,

plus

other

important

benefits

for

you,

are

contained

in

your

Customer

Care Program

book,

supplied

with

your

airplane.

Warranty

service

is

available

to

you

at

authorized

Cessna

Dealers

throughout

the

world

upon

presentation

of

your

Customer

Care Card

which

establishes

your

eligibility

under

the

warranty.

•

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

on

hand

when

you

need

them.

•

THE

LATEST

AUTHORITATIVE

INFORMATION

fOR

SERVICING CESSNA

AIR-

PLANES, since Cessna Dealers have all

of

the

Service

Manuals

and Parts Catalogs,

kept

current

by

Customer

Care Service

Information

Letters and

Customer

Care News

Letters,

published

by

Cessna

Aircraft

Company.

We

urge

all Cessna

owners

to

use

the

Cessna

Dealer

Organization

to

the fullest.

A

current

Worldwide

Customer

Care

Directory

one

of

your

cross-country

flight

planning

aids; a

warm

welcome

awaits

you

at

every

Cessna

Dealer.

21

August

1981

PERFORMANCE

-

CESSNA

SPECIFICA

TIONS

MODEL

T182

PERFORMANCE

-

SPECIFICATIONS

SPEED:

Maximum

at

20,000

Ft

168

KNOTS

Cruise,

75%

Power

at

20,000

Ft

158

KNOTS

Cruise,

75%

Power

at

10,000

Ft

145

KNOTS

CRUISE:

Recommended

lean

mixture

with

fuel

allowance

for

engine

start,

taxi,

takeoff,

climb

and

45

minutes

reserve.

75%

Power

at

20,000

Ft

.Range

745

NM

88

Gallons

Usable

Fuel

Time

4.9

HRS

75%

Power

at

to,OOO

Ft

.Range

725

NM

88

Gallons

Usable

Fuel

Time

5.1

HRS

Maximum

Range

at

20,000

Ft

.Range

885

NM

88

Gallons

Usable

Fuel

Time

7.3

HRS

Maximum

Range

at

10,000

Ft

.Range

920 NM..

88

Gallons

Usable

Fuel

Time

8.4

HRS

RATE

OF

CLIMB

AT

SEA

LEVEL

965

FPM

CERTIFICATED

MAXIMUM

OPERATING

ALTITUDE

20,000

FT

TAKEOFF

PERFORMANCE:

Ground

Roll

. . . . . . . . . .

790

FT

Total

Distance

Over

50-Ft

Obstacle

1475

IT

LANDING

PERFORMANCE:

Ground

Roll

. . . . . . . . . .

590

FT

Total

Distance

Over

50-Ft

Obstacle

1350

FT

STALL

SPEED

(KCAS):

Flaps

Up,

Power

Off

54

KNOTS

Flaps

Down,

Power

Off

49

KNOTS

MAXIMUM

WEIGHT:

Ramp

3112

LBS

Takeoff

3100

LBS

Landing

2950

LBS

STANDARD

EMPTY

WEIGHT:

Turbo

Skylane

1740

LBS

Turbo

Skylane

II

. . .

1793

LBS

MAXIMUM

USEFUL

LOAD:

Turbo

Skylane

. . . .

1372

LBS

Turbo

Sky

lane

II

. . .

1319

LBS

BAGGAGE

ALLOWANCE

200

LBS

WING

LOADING:

Pounds/

Sq

Ft

17.8

POWER

LOADING:

Pounds/

HP

13.2

FUEL

CAPACITY:

Total

92

GAL

OIL

CAPACITY

.....

9

QTS

ENGINE:

Turbocharged

Avco

Lycoming

0-540-L3C5D

235

BHP

at

2400

RPM

PROPELLER:

2-Bladed

Constant

Speed.

Diameter

82

IN

Performance

with

an

optiona.13-bladed

propeller

is

essentially

the

Same

as

shown

above.

The

above

performance

figures

are

based

on

the

indicated

weights,

standard

atInospheric

conditions,

level

hard-surface

dry

runways,

and

no

wind.

They

are

calculated

values

derived

from

flight

tests

conducted

by

the

Cessna

Aircraft

Company

under

carefully

documented

conditions

and

will

vary

with

individual

airplanes

and

numerous

factors

affecting

flight

performance.

ii

21

August

1981

I

CESSNA

COVERAGE/

REVISIONS/

MODELT182

LOG

OF

EFFECTIVE

PAGES

COVERAGE

The Pilot's

Operating

Handbook

in

the

airplane at

the

time

of

delivery

from

Cessna

Aircraft

Company

contains

information

applicable

to

the 1982

Model

T182

airplane designated by

the

serial

number

and registration

number

shown

on

the

Title

Page

of

this

handbook.

This

information

is

based

on data available at

the

time

of

publication.

REVISIONS

Changes

and/or

additions

to

this

handbook

will

be covered by revisions

published

by Cessna

Aircraft

Company. These revisions are

distributed

to

owners

of

U.

S.

Registered aircraft

according

to

FAA records at the

time

of

revision issuance.

Revisions should be

examined

immediately

upon

receipt and

incorporated

in this

handbook.

NOTE

It

is

the

responsibility

of

the

owner

to

maintain

this

handbook

in a current

status

when

it

is

being

used

for

operational

purposes.

Owners

should

contact

their

Cessna Dealer

whenever

the

revision status

of

their

handbook

is

in

question.

A revision bar

will

extend

the

full

length

of

new

or

revised text

and/or

illuSlrations added on

new

or

presently existing pages. This bar

will

be located adjacent to

the

applicable revised area on

the

outer

margin

of

the

page.

All revised pages

will

carry

the

revision

number

and date

on

the applicable page.

The

following

log

of

Effective

Pages

provides

the

dates

of

issue for

original

and revised pages, and

a listing

of

all pages in the

handbook.

Pages

affected

by

the

current

revision are

indicated

by an

asterisk

('j

preceding

the

pages listed.

LOG

OF

EFFECTIVE PAGES

Dates

of

issue

for

original

and revised pages are:

,

Original

21

August

1981

Revision 1 4

December

1981

Revision 2 4 February

1982

Page

Date

Title

21

August

1981

Assignment Record

21

August

1981

i

thru

ii

21

August

1981

'iii

thru

iv 4 February

1982

v

21

August

1981

vi

Blank

21

August

1981

1-1

thru

1-9

...•......

21

August

1981

1-10 Blank

21

August

1981

2-1

...........•......

21

August

1981

2-2

Blank

21

August

1981

2-3

21

August

1981

2-4 4

December

1981

2-5

thru

2-8

21

August

1981

2-9

4

December

1981

Page

2-10

thru

2-11 2-12 Blank 3-1

thru

3-3

3-4

thru

3-5

3-6

thru

3-14

'3-15

thru

3-16

3-17

thru

3-18

4-1

thru

4-2

4-3

4-4

thru

4-10 4-11 4-12

thru

4-20 4-21 4-22

thru

4-24

Date

21

August

1981

21

August

1981

21

August

1981

4

December

1981

21

August

1981

4 February

1982

21

August

1981

21

August

1981

4

December

1981

21

August

1981

4

December

1981

21

August

1981

4

December

1981

21

August

1981

21

August

1981

Revision

2 - 4

February

1982/

D1216R2-13PH-CES-400-2/B2

iii

LOG

OF

EFFECTIVE

PAGES

CESSNA

MODEL

T182

LOG OF

EFFECTIVE

PAGES

(Continued)

Page

Date

5-1

21

August

1981

5-2 Blank

21

August

1981

5-3

thru

5-7

21

August

1981

5-8 Blank. . . . .

21

August

1981

5-9

thru

5-10 4

December

1981

5-11

21

August

1981

5-12 4

December

1981

5-13

thru

5-32

21

August

1981

5-33 4

December

1981

5-34 Blank

21

August

1981

6-1

21

August

1981

6-2 Blank

21

August

1981

6-3

lhru

6-29

21

August

1981

Page

Date

6-30 Blank 7-1

thru

7-42 8-1 8-2 Blank 8-3

thru

8-19 8-20 Blank 9-1

thru

9-3 9-4 Blank

21

August

1981

21

August

1981

21

August 1981

21

August

1981

21

August

1981

21

August

1981

21

August

1981

21

August

1981

NOTE

Refer

to

Section 9 Table

of

Contents

for

supplements

applicable

to

optional

sys-

tems.

'-

21

August

1981

Revision

2 - 4

February

1982

iv

TABLE

OF

CONTENTS

CESSNA MODEL

T182

TABLE

OF

CONTENTS

SECTION

GENERAL 1

LIMITATIONS

2

EMERGENCY PROCEDURES 3

NORMAL

PROCEDURES 4

\

PERFORMANCE. 5

WEIGHT & BALANCE/

EQUIPMENT

LIST

6

AIRPLANE

&

SYSTEMS

DESCRIPTIONS 7

AIRPLANE

HANDLING,

SERVICE &

MAINTENANCE

8

SU

PPLEMENTS

(Optional

Systems

Description

&

Operating

Procedures)

I (

n1

2

6'

flz('s

-

11}1J4

\1\:,

"i.~

tjr

IJ

G

'36

ttl"'·

.;.;

v/(vi

blank)

21

August

1981

9

CESSNA

SECTION

1

MODELT182

GENERAL

SECTION 1

GENERAL

TABLE OF

CONTENTS

Page

Three

View

..

1-2

Introduction

. . 1-3

Descriptive

Data

1-3

Engine

..

1-3

Propeller

(2-Bladed)

1-3

Propeller

(3-Bladed)

1-3

Fuel

. . . . . . . . 1-3

Oil

1-4

Maximum

Certificated

Weights

1-5

Standard

Airplane

Weights

. . 1-5

Cabin

And

Entry

Dimensions

. 1-5

Baggage

Space

And

Entry

Dimensions

1-5

Specific

Loadings

1-5

Symbols,

Abbreviations

And

Terminology

1-6

General

Airspeed

Terminology

And

Symbols

1-6

Meteorological

Terminology

1-6

Engine

Power

Terminology

. . . . . . . . 1-7

Airplane

Performance

And

Flight

Planning

Terminology

1-7

Weight

And

Balance

Terminology

. . . . . . . . . . . 1-7

WARNING

PITOT

HEATER

MUST

BE

ON

WHEN

OPERATING

BelOW

40°F

IN

INSTRUMENT

METEOROLOGICAL

CONDITIONS.

0890018.2

21

August

1981

1-1

SECTION

1

CESSNA

GENERAL

MODEL

T182

r

9'-3"

MAX.

o

I

28'-5"--------

I

11

'-8"

'1

NOTES,

1.

Dimensions shown are based on standard

a

empty

weight

and

proper

nose

gear

and

tire

inflation.

2. Wing

span

shown

with

strObe

lights

installed.

3.

Maximum

height shown

with

nose gear

depressed as far

as

possible

and

flashing

beacon installed.

4. Wheel base length

is

66

1/2"

5.

Propeller ground clearance

is

103/4"

6. Wing

area

is

174

square

feet.

7.

Minimum

tuming

radius

I *

pivot

point

to

outboard

wing

tip)

is

27'-7"

umJiIITITl~1llII"'TIJJI!iIITIlm

PIVOT

POINT

__

PIVOT

POINT

*

1------------36'-0"------------

<.r:=..::=::=

_

Figure

1-1.

Three

View

21

August

1981 1-2

CESSNA

SECTION

1

MODEL

T182

GENERAL

INTRODUCTION

(

This

handbook

contains 9 sections,

and

includes

the

material

required

to

be

furnished

to

the

pilot

by

CAR

Part

3.

It

also

contains

supplemental

data

supplied

by

Cessna

Aircraft

Company.

Section 1 provides

basic

data

and

information

of

general

interest.

It

also

contains

definitions

or

explanations

of

symbols,

abbreviations,

and

terminology

commonly

used.

DESCRIPTIVE

DATA

ENGINE

Number

of

Engines:

1.

Engine

Manufacturer:

A

vco

Lycoming.

Engine

Model

Number:

0-540-L3C5D.

Engine

Type:

Turbocharged,

direct-drive,

air-cooled,

horizon

tally-

opposed,

carburetor

equipped,

six-cylinder

engine

with

541.5

cu.

in.

displacement.

Horsepower

Rating

and

Engine

Speed:

235

rated

BHP

at

31

inches

Hg

and

2400

RPM.

.<k

PROPELLER

(2-BLADED)

Propeller

Manufacturer:

McCauley

Accessory

Division.

Propeller

Model

Number:

B2D34C219/90DHB-8.

Number

of

Blades:

2.

Propeller

Diameter,

Maximum:

82

inches.

Minimum:

80.5

inches.

Propeller

Type:

Constant

speed

and

hydraulically

actuated,

with a low

pitch

setting

of

15.80 and a high

pitch

setting

of

31.90 (30

inch

station).

PROPELLER

(3-BLADED)

Propeller

Manufacturer:

McCauley

Accessory

Division.

Propeller

Model

Number:

B3D32C407/82NDA-3.

Number

of

Blades:

3.

Propeller

Diameter,

Maximum:

79

inches.

Minimum:

78

inches.

Propeller

Type:

Constant

speed

and

hydraulically

actuated,

with a low

pitch

setting

of

16.00 and a high

pitch

setting

of

31.70 (30

inch

station).

FUEL

Approved

Fuel

Grades

(and

Colors):

100LL

Grade

Aviation

Fuel

(Blue).

100

(Formerly

100/130)

Grade

Aviation

Fuel

(Green).

21

August

1981

1-3

SECTION

1

CESSNA

GENERAL

MODEL

T182

NOTE

Isopropyl

alcohol

or

ethylene

glycol

monomethyl

ether

(

1

may

be

added

to

the

fuel

supply.

Additive

concentrations

shall

not

exceed

1%

for

isopropyl

alcohol

or

.15%

for

I

ethylene

glycol

monomethyl

ether.

Refer

to

Section 8 for

additional

information.

Total

Capacity:

92

gallons.

Total

Capacity

Each

Tank:

46

gallons.

Total

Usable:

88

gallons.

NOTE

To

ensure

maximum

fuel

capacity

when

refueling

and

minimize

cross-feeding

when

parked

on a sloping

surface,

place

the

fuel

selector

valve

in

either

LEFT

or

RIGHT

position.

OIL

Oil

Grade

(Specification):

(

MIL-L-6082

Aviation

Grade

Straight

Mineral

Oil:

Use

to

replenish

supply

during

first

25

hours

and

at

the

first

25-hour

oil

change.

Continue

to

use

until a total

of

50

hours

has

accumulated

or

oil

consumption

has

stabilized.

MIL-L-22851

Ashless

Dispersant

Oil:

This

oil

must

be

used

after

first

50

hours

or

oil

consumption

has

stabilized.

Recommended

Viscosity

For

Temperature

Range:

MIL-L-6082

Aviation

Grade

Straight

Mineral

Oil:

All

temperatures,

use

SAE

20W-50

or

Above

16°C

(60°F),

use

SAE

50

-1°C

(30°F)

to

32°C

(90°

F),

use

SAE

40

-18°C

(O°F)

to

21°C

(70°F),

use

SAE

30

Below

-12°C

(10°F),

use

SAE

20

MIL-L-22851

Ashless

Dispersant

Oil:

All

temperatures,

use

SAE

20W-50

or

Above

16°C

(60°F),

use

SAE

40

or

SAE

50

-1°C

(30°F)

to

32°C

(90°F),

use

SAE

40

-18°C

(O°F)

to

21°C

(70°F),

use

SAE

40

or

SAE

30

Below

-12°C

(10°F),

use

SAE

30

J \

Oil

Capacity:

Sump: 8 Quarts. Total: 9 Quarts.

21

August

1981

1-4

CESSNA

SECTION

1

MODEL

T182

GENERAL

MAXIMUM

CERTIFICATED

WEIGHTS

Ramp:

3112

lbs.

Takeoff:

3100

lbs.

Landing:

2950

lbs.

Weight

in

Baggage

Compartment:

Baggage

Area"

A"

(or

passenger

on

child's

seat) -Station

82

to

109: 120

lbs.

See

note

below.

.

Baggage

Area

"B" -Station

109

to

124: 80

lbs.

See

note

below.

Baggage

Area

"C" -Station

124

to

134: 80

lbs.

See

note

below.

NOTE

The

maximum

allowable

combined

weight

capacity

for

baggage

in

areas

A,

Band

C

is

200

lbs.

The

maximum

allowable

weight

capacity

for

baggage

in

areas

Band

Cis

80

lbs.

STANDARD

AIRPLANE

WEIGHTS

Standard

Empty

Weight,

Turbo

Skylane:

1740

lbs.

Turbo

Sky

lane

II: 1793

lbs.

Maximum

Useful

Load,

Turbo

Skylane:

1372

lbs.

Turbo

Skylane

II: 1319

lbs.

CABIN

AND

ENTRY

DIMENSIONS

Detailed

dimensions

of

the

cabin

interior

and

entry

door

openings

are

illustrated

in

Section

6.

BAGGAGE

SPACE

AND

ENTRY

DIMENSIONS

Dimensions

of

the

baggage

area

and

baggage

door

opening

are

illustrated

in

detail

in

Section

6.

SPECIFIC

LOADINGS

Wing

Loading:

17.8

lbs.!

sq.

ft.

Power

Loading:

13.2

lbs./

hp.

21

August

1981

1-5

SECTION

1

CESSNA

GENERAL

MODEL

T182

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

KT

AS

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.

VA

Maneuvering

Speed

is

the

maximum

speed

at

which

full

or

abrupt

control

movements

may

be

used.

V

Maximum

Flap

Extended

Speed

is

the

highest

speed

FE

permissible

with

wing

flaps

in a prescribed

extended

position.

V

Maximum

Structural

Cruising

Speed

is

the

speed

that

NO

should

not

be

exceeded

except

in

smooth

air.

then

only

with

caution.

V

Never

Exceed

Speed

is

the

speed

limit

that

may

not

be

NE

exceeded

at

any

time.

V

Stalling

Speed

or

the

minimum

steady

flight

speed

at

s

which

the

airplane

is

controllable.

V

Stalling

Speed

or

the

minimum

steady

flight

speed

at

So

which

the

airplane

is

controllable

in

the

landing

configu-

ration

at

the

most

forward

center

of

gravity.

V

Best

Angle-of-Climb

Speed

is

the

speed

which

results

in

x

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.

METEOROLOGICAL

TERMINOLOGY

OAT

Outside

Air

Temperature

is

the

free

air

static

temperature.

21

August

1981

1-6

CESSNA MODEL

T182

Standard

Temperature

Pressure

Altitude

SECTION

1

GENERAL

It

is

expressed

in

either

degrees

Celsius

or

degrees

Fah-

renheit.

Standard

Temperature

is

15°C

at

sea

level

pressure

alti-

tude

and

decreases

by

2°C

for

each

1000

feet

of

altitude.

Pressure

Altitude

is

the

altitude

read

from

an

altimeter

when

the

altimeter's

barometric

scale

has

been

set

to

29.92

inches

of

mercury

(1013

mb).

ENGINE

POWER

TERMINOLOGY

BHP

Brake

Horsepower

is

the

power

developed

by

the

engine.

RPM

Revolutions

Per

Minute

is

engine

speed.

MP

Manifold

Pressure

is a pressure

measured

in

the

engine's

induction

system

and

is

expressed

in

inches

of

mercury

(Hg).

AIRPLANE

PERFORMANCE

AND

FLIGHT

PLANNING

TERMINOLOGY

Demonstrated Crosswind Velocity

Usable

Fuel

Unusable Fuel

GPH NMPG

g

Demonstrated

Crosswind

Velocity

is

the

velocity

of

the

crosswind

component

for

which

adequate

control

of

the

airplane

during

takeoff

and

landing

was

actually

demon-

strated

during

certification

tests.

The

value

shown

is

not

considered

to

be

limiting.

Usable

Fuel

is

the

fuel

available

for

flight

planning.

Unusable

Fuel

is

the

quantity

of

fuel

that

can

not

be

safely

used

in

flight.

Gallons

Per

Hour

is

the

amount

of

fuel

consumed

per

hour.

Nautical

Miles

Per

Gallon

is

the

distance

which

can

be

expected

per

gallon

of

fuel

consumed

at a specific

engine

power

setting

and/

or

flight

configuration.

g

is

acceleration

due

to

gravity.

WEIGHT

AND

BALANCE

TERMINOLOGY

deference

Reference

Datum

is

an

imaginary

vertical

plane

from

Datum

which

all

horizontal

distances

are

measured

for

balance

purposes.

21

August

1981

1-7

SECTION

1

GENERAL

Station

Arm

Moment

Center

of Gravity (C.G.)

C.G. Arm

C.G. Limits

Standard

Empty Weight

Basic

Empty

Weight Useful

Load

Maximum Ramp Weight

Maximum Takeoff Weight

Maximum Landing Weight

Tare

CESSNA

MODEL

T182

Station

is a location

along

the

airplane

fuselage

given

in

terms

of

the

distance

from

the

reference

datum.

Arm

is

the

horizontal

distance

from

the

reference

datum

to

the

center

of

gravity

(C.G.)

of

an

item.

Moment

is

the

product

of

the

weight

of

an

item

multiplied

by

its

arm.

(Moment

divided

by

the

constant

1000

is

used

in

this

handbook

to

simplify

balance

calculations

by

reduc-

ing

the

number

of

digits.)

Center

of

Gravity

is

the

point

at

which

an

airplane,

or

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.

Center

of

Gravity

Arm

is

the

arm

obtained

by

adding

the

airplane's

individual

moments

and

dividing

the

sum

by

the

total

weight.

Center

of

Gravity

Limits

are

the

extreme

center

of

gravity

locations

within

which

the

airplane

must

be

operated

at

a

given

weight.

Standard

Empty

Weight

is

the

weight

of a standard

air-

plane,

including

unusable

fuel,

full

operating

fluids

and

full

engine

oil.

Basic

Empty

Weight

is

the

standard

empty

weight

plus

the

weight

of

optional

equipment.

Useful

Load

is

the

difference

between

ramp

weight

and

the

basic

empty

weight.

Maximum

Ramp

Weight

is

the

maximum

weight

approved

for

ground

maneuver.

(It

includes

the

weight

of

start,

taxi

and

runup

fuel.)

Maximum

Takeoff

Weight

is

the

maximum

weight

approved

for

the

start

of

the

takeoff

roll.

Maximum

Landing

Weight

is

the

maximum

weight

approved

for

the

landing

tOUChdown.

Tare

is

the

weight

of

chocks,

blocks,

stands,

etc.

used

when

21

August

1981

(

/

1-8

CESSNA MODEL

T182

SECTION

1

GENERAL

(

weighing

an

airplane.

and

is

included

in

the

scale

read-

ings.

Tare

is

deducted

from

the

scale

reading

to

obtain

the

actual

(net)

airplane

weight.

{

(

21

August

1981

1-9/(1-10

blank)

CESSNA

SECTION

2

MODEL

T182

LIMITATIONS

SECTION 2

LIMITATIONS

TABLE OF

CONTENTS

Page

Introduction

. . . . . . . .

2-3

Airspeed

Limitations

2-4

Airspeed

Indicator

Markings

2-5

Power

Plant

Limitations

2-5

Power

Plant

Instrument

Markings

2-6

Weight

Limits

. . . . .

2-7

Center

Of

Gravity

Limits

2-7

Maneuver

Limits

2-7

Flight

Load

Factor

Limits

2-8

Kinds

Of

Operation

Limits

2-8

Fuel

Limitations

. . . . . 2-8

Maximum

Operating

Altitude

Limit

2-9

Other

Limitations

2-9

Flap

Limitations

2-9

Placards

.....

2-9

21

August

1981

2-1/(2-2

blank)

CESSNA

SECTION

2

MODELT182

LIMIT

ATIONS

INTRODUCTION

Section 2 includes

operating

limitations.

instrument

markings,

and

~,

basic

placards

necessary

for

the

safe

operation

of

the

airplane,

its

engine,

standard

systems

and

standard

equipment.

The

limitations

included

in

this

section

and

in

Section 9 have

been

approved

by

the

Federal

Aviation

Administration.

Observance

of

these

operating

limitations

is

required

by

Federal

Aviation

Regulations.

NOTE

Refer

to

Section 9 of

this

Pilot's

Operating

Handbook

for

amended

operating

limitations,

operating

procedures,

performance

data

and

other

necessary

information

for

airplanes

equipped

with

specific

options.

NOTE

The

airspeeds

listed

in

the

Airspeed

Limitations

chart

(figure

2-1)

and

the

Airspeed

Indicator

Markings

chart

(figure

2-2)

are

based

on

Airspeed

Calibration

data

shown

in

Section

5

with

the

normal

static

source,

with

the

exception

of

the

bottom

of

the

green

and

white

arcs

on

the

airspeed

indicator.

These

are

based

on a power-off

air-

speed

calibration.

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

5.

Your

Cessna

is

certificated

under

FAA

Type

Certificate

No.

3A13

as

Cessna

Model

No.

T182.

21

August

1981

2-3

I

SECTION

2

CESSNA

LIMITATIONS

MODEL

T182

AIRSPEED

LIMITATIONS

Airspeed

limitations

and

their

operational

significance

are

shown

in

figure

2-1.

~

1\

SPEED KCAS

KIAS

REMARKS

VNE

Never Exceed Speed 175 178 Do

not

exceed this

speed

in

any operation.

VNO

Maximum

Structural

Cruising Speed

138 140

Do

not

exceed this

speed

except in smooth air, and

then

only

with

caution.

VA

Maneuvering Speed:

3100 Pounds

2600 Pounds 2100 Pounds

110 100

90

111 101

90

Do

not

make

full

or

abrupt

control

movements above

this speed.

VFE

Maximum

Flap Extended

Speed:

To 10

0

Flaps

10

0

-

FULL

Flaps

138

95

140

95

Do

not

exceed these speeds

with

the given flap settings.

Maximum

Window

Open

Speed

175

178

Do

not

exceed this

speed

with

windows open.

Figure

2-1.

Airspeed

Limitations

j

21

August

1981

Revision

1 - 4

Elecember

1981

2-4

CESSNA

SECTION

2

MODELT182

LIMITATIONS

AIRSPEED

INDICATOR

MARKINGS

Airspeed

indicator

markings

and

their

color

code

significance

are

shown

in

figure

2-2.

MARKING

KIAS

VALUE

OR

RANGE

SIGNIFICANCE

White

Arc

40 -95

Full

Flap Operating Range.

Lower

limit

is

maximum

weight

V

So

in

landing

configuration.

Upper

limit

is

maximum

speed permissible

with

flaps extended.

Green

Arc

48 - 140

Normal Operating Range. Lower

limit

is

maximum

weight Vs at most

forward

C.G.

with

flaps retracted. Upper

limit

is

maximum

structural

cruising speed.

Yellow

Arc

140-178

Operations

must

be conducted

with

caution and

only

in

smooth

air.

Red

Line

178

Maximum

speed

for

all operations.

Figure

2-2.

Airspeed

Indicator

Markings

POWER

PLANT

LIMITATIONS

Engine

Manufacturer:

Avco

Lycoming.

Engine

Model

Number:

0-540-L3C5D.

Maximum

Power:

235

BHP

rating.

Engine

Operating

Limits

for

Takeoff

and

Continuous

Operations:

Maximum

Engine

Speed:

2400

RPM.

Maximum

Manifold

Pressure:

31

in.

Hg.

Maximum

Cylinder

Head

Temperature:

500°F

(260°C).

Maximum

Oil

Temperature:

245°F

(118°C).

Oil

Pressure,

Minimum:

25

psi.

Maximum:

115

psi.

Fuel

Pressure,

Minimu'm:

3.0

psi.

Maximum:

30.0

psi.

'uel

Grade:

See

Fuel

Limitations.

Oil

Grade

(Specification):

MIL-L-6082

Aviation

Grade

Straight

Mineral

Oil

or

MIL-L-22851

Ashless

Dispersant

Oil.

21

August

1981 2-5

- - -

- -

-

- - -

-

--

- - -

- -

-

--

- - -

SECTION

2

CESSNA

LIMIT

ATIONS

MODEL

T182

Propeller

Manufacturer:

McCauley

Accessory

Division.

Propeller

Model

Number,

2-Bladed:

B2D34C219/90DHB-8

3-Bladed:

B3D32C407/82NDA-3.

Propeller

Diameter,

2-Bladed

Maximum:

82

inches.

2-Bladed

Minimum:

80.5

inches.

3-Bladed

Maximum:

79

inches.

3-Bladed

Minimum:

78

inches.

Propeller

Blade

Angle

at

30

Inch

Station,

2-Bladed

Low:

15.8

0

•

2-Bladed

High:

31.9

0

•

3-Bladed

Low:

16.0

0

•

3-Bladed

High:

31.7

0

•

POWER PLANT

INSTRUMENT

MARKINGS

Power

plant

instrument

markings

and

their

color

code

significance

are

shown

in

figure

2-3.

INSTRUMENT

RED

LINE

GREEN

ARC

RED LINE

MINIMUM

NORMAL

MAXIMUM

LIMIT

OPERATING

LIMIT

Tachometer

2100 -

2400

RPM

2400

RPM

Manifold

Pressure

17-25

31

in.Hg

Oil Temperature

100°-245°F

245°F

Cylinder

Head

200° -500°F

500°F

Temperature

Fuel

Pressure

3.0

psi

3.0 - 30.0 psi

30.0

psi

Oil

Pressure

25

psi

60-90

psi

115

psi

Suction

4.5

- 5.4

in.

Hg

Fuel Quantity

E

(2

Gal. Unusable

Each Tank)

)

J

j

I

Figure

2-3.

Power

Plant

Instrument

Markings

21

August

1981

2-6

CESSNA

SECTION

2

MODEL

T182

LIMITATIONS

WEIGHT

LIMITS

Maximum

Ramp

Weight:

3112

lbs.

Maximum

Takeoff

Weight:

3100

lbs.

Maximum

Landing

Weight:

2950

lbs.

Maximum

Weight

in

Baggage

Compartment:

Baggage

Area"

A"

(or

passenger

on

child's

seat) -Station

82

to

109: 120

lbs.

See

following

note.

Baggage

Area

"B" -Station

109

to

124: 80

lbs.

See

following

note.

Baggage

Area

"C" -Station

124

to

134: 80

lbs.

See

following

note.

NOTE

The

maximum

allowable

combined

weight

capacity

for

baggage

in

areas

A,

Band

C

is

200

lbs.

The

maximum

allowable

weight

capacity

for

baggage

in

areas

Band C is

801bs.

CENTER

OF

GRAVITY

LIMITS

Center

of

Gravity

Range:

Forward:

33.0

inches

aft

of

datum

at

2250

lbs.

or

less,

with

straight

line

variation

to

35.5

inches

aft

of

datum

at

2700

lbs.,

with

straight

line

variation

to

38.9

inches

aft

of

datum

at

2950

lbs.

(landing),

with

straight

line

variation

to

40.9

inches

aft

of

datum

at

3100

lbs.

(takeoff).

Aft: 46.0

inches

aft

of

datum

at

all

weights.

Reference

Datum:

Front

face

of

firewall.

MANEUVER

LIMITS

This

airplane

is

certificated

in

the

normal

category.

The

normal

Cessna T182 1982 Pilot Operating Handbook

Specifications and Main Features

Frequently Asked Questions

User Manual