Beechcraft C23 SUNDOWNER 180 Pilot Operating Handbook

PILOT'S OPERATING

HANDBOOK

AND

FAA

APPROVED

AIRPLANE

FLIGHT

MANUAL

for

the

eecheraft

Sunclowner

180

C23

FAA

APPROVED INNORMAL

AND UTILITY

CATEGORY

BASED

ON

CAR 3. THIS

DOCUMENT

MUST BE CARRIED IN

THE

AIRPLANE AT

ALL TIMES AND

BE

KEPT WITHIN REACH OF

THE

PILOT DURING

ALL

FLIGHT

OPERATIONS.

THIS

HANDBOOK INCLUDES

THE

MATERIAL REQUIRED TO

BE FURNISHED

TO THE PILOT

BY FAR PART 23.

Mfr's

Serial No.

Registration No.

FAA Approved by:

THIS HANDBOOK

SUPERSEDES

ALL BEECH PUBLISHED

OWNERS

MANUALS AND CHECK LISTS ISSUED

FOR THIS

AIRPLANE WITH

THE

EXCEPTION OF

FAA APPROVED

AIRPLANE

FLIGHT MANUALS.

P/N

169-590008-23

P/N

169-590008-23A4

Issued: February, 1979 Revised: January, 1982

PUBLISHED

BY

COMMERCIAL PUBLICATIONS

BEECH

AIRCRAFT CORPORATION

WICHITA,

KANSAS

67201

U. S. A.

Geechcraft

-­General Avtation

A RilyNieert

Company

Manufacturers Associalion

C23

Sundowner

180

Pilot's Operating

Handbook

and

FAA Approved

Airplane

Flight

Manual

INTRODUCTION

This Pilot's

Operating

Handbook

and

FAA Approved

Air-

plane

Flight

Manual is

in the format and

contains data

recommended in the GAMA (General

Aviation

Manu-

facturers Association)

Handbook Specification

Number

1.

Use

of

this

specification

by

all

manufacturers

will provide

the pilot the same type data

in

the

same

place in

all of the

handbooks.

In recent

years

BEECHCRAFT handbooks

contained most

of the data

now provided,

however,

the new

handbooks

contain

more

detailed data

and

some

entirely

new

data.

For example,

attention is

called

to Section X

SAFETY IN¾

FORMATION.

While

little of the

information

is

new

and

every

pilot

has been

exposed

to the basic

fundamentals,

BEECHCRAFT feels it is highly important to have

SAFETY

INFORMATION

in a

condensed form

in

the hands

of the

pilots.

The

SAFETY

INFORMATION

should

be

read

and

studied.

Periodic

review will

serve as a

reminder of

good

piloting

techniques.

February

1979

a

Sundowner 180 C23

PILOT'S

OPERATING

HANDBOOK

and

FAA

APPROVED AIRPLANE FLIGHT MANUAL

TABLE

OF

CONTENTS

SECTION 1 ................................. General

SECTION 2

..............................

Limitations

SECTION

3

...................

Emergency

Procedures

SECTION

4

...................... Normal Procedures

SECTION 5

............................. Performance

SECTION 6 ....... Weight

and Balance/Equipment List

SECTION

7

..................... Systems Description

SECTION

8 .

. . . .

Handling, Servicing

and Maintenance

SECTION 9 ...............

............ Supplements

SECTION

10

......................

Safety

Information

b

February

1979

SUNDOWNER

180

C23

Pilot's

Operating Handbook

and

FAA

Approved Airplane

Flight Manual

A4....................................................................January,

1982

LOG OF

REVISIONS

Page Description

Title Page

Added

Revision

Date

Logo Page

Added

Page A (A4)

Updated

5-1

Revised "Table

of

Contents"

5-3

thru

5-6

Revised

"Introduction to

Performance

and Flight

Planning"

5-18

Revised

"Cruise

Performance"

chart

5-19

Shifted Material

and Added

"Notes"

5-20

Shifted Material

5-21

Added New

Page

and Shifted

Material

5-22

Added

New Page

7-1

Revised

"Table

of

Contents"

7-3

Revised "Table of Contents"

7-5

Shifted

Material

7-6

Shifted

Material

7-11

Shifted

Material

and Revised "Flight

Instruments"

7-25

Shifted Material

and

Revised

"Alternator"

7-26

and Shifted

Material

and Revised

7-27

"External

Power

Receptacle"

7-28

Shifted

Material and Revised

"Interior

Lighting"

7-30

Shifted

Material

7-31

Shifted

Material

1

of

2

Page

A

LOG OF

REVISIONS

Page

Description

7-32

Shifted

Material

8-1

Revised

"Table of

Contents"

8-10

and

Shifted

Material and

Revised

8-11

"External

Power Receptacle"

2

of 2 Page A

SUNDOWNER

180 C23

Pilot's

Operating

Handbook

and

FAA Approved

Airplane Flight

Manual

A3......................................................................

August,1980

LOG

OF

REVISIONS

Page

Description

Title

Page Added Revision

Date

Page A (A3) Updated
1-4

and

1-5

Revised "Use

of Handbook"

1-6

Shifted

Material

1-15

Revised

"Engine

Controls

and

Instruments"

2-5

Revised

"Power

Plant

Limitations"

2-12

Revised

"Electrical

Power"

2-27

Revised "Fuel

Selector Panel" Placard

2-28

Shifted

Material

3-1

Revised

"Table

of

Contents"

3-3

Revised

"Emergency

Airspeeds"

and

Added

Note

3-7

Revised "Emergency

Descent"

3-8

and

3-9

Added

"Starter Engaged Warning

Light

Illuminated"

and Revised

"Alternator

Out

Procedure"

3-10

and

3-11

Shifted

Material

4-1

Revised "Table

of

Contents"

4-5

Shifted

Material

4-6

Revised "Before

Starting"

4-7

Shifted Material

4-8

Revised

"Starting"

4-9

Revised "Before

Take-off"

4-10

thru

4-12

Shifted

Material

6-5

Revised "Weighing

Instructions"

6-11

Revised "Weight and

Balance

Responsibilities"

7-2

Revised

"Table of

Contents"

7-15

Revised "Shoulder

Harnesses"

7-18

and

7-19

Shifted

Material

A3

1

of 2

Page A

LOG

OF

REVISIONS

Page

Description

7-20

Revised

"Starter"

7-21

and

7-23

Revised

"Fuel

System"

8-15

Revised

"Tires"

8-34

and

8-35

Revised

"Consumable

Materials"

8-41

Revised

"Power Plant"

10-1

Thru

10-67

Bevised

Safety

Section

Dated

March

1981.

2 of 2 Page

A

Sundowner 180

C23

PILOT'S OPERATING HANDBOOK

and

FAA

APPROVED

AIRPLANE

FLIGHT MANUAL

LOG OF

REVISIONS

A2-----------.................

October1979

PAGE

DESCRIPTION

Title

Page

Update

Page A (A2)

New

2-1

Update

Table

of

Contents

2-5

Add

"Fuel

Additives"

2-6

Shift Material

2-7

Revise "Weight

Limits" and "Center

of

Gravity Limits"

2-8

Revise "Maneuver Limits"

4-1

Update Table

of Contents

4-8

Revise "After

Starting

and

Before

Taxi"

4-10

Shift

Material

4-11

Revise

"Descent"

4-15

Add "Noise Characteristics"

8-8

Revise

"Jacking"

8-35

Revise

"Consumable

Materials"

Page A

Sundowner

180 C23

PILOT'S OPERATING HANDBOOK

and

FAA APPROVED AIRPLANE FLIGHT

MANUAL

LOG OF REVISIONS

A1

.............

........

............ APRIL

1979

PAGES

DESCRIPTION

Title

Page Update

A1

New

1-9

Add

NOTE

34

Revise

material

34

Revise

material

3-7

Revise

switch designation

3-8

Revise

switch

designation

4-6

Revise

switch

designation

4-7

Add

28-volt

system

information

4-8

&

4-9

Shift material

4-12

Revise

switch

designation

7-2&7-3

Update

Table

of

Contents

7-11

Revise

"Switches"

7-24

&

7-25

Revise

switch

designation

Revise

"Battery"

7-25

Revise

"Alternator"

7-26

&

7-27

Shift material and

add

revised

"External

Power

Receptacle"

7-32

Revise

switch

designation

8-2

Update

Table

of

Contents

8-11

Revise "External

Power"

8-14

&

8-15

Revise

"Battery"

8-34

Revise "Consumable

Materials"

8-38

Revise

"Bulb Replacement Guide"

Page A

Sundowner 180 C23

PILOT'S

OPERATING HANDBOOK

and

FAA APPROVED

AIRPLANE

FLIGHT

MANUAL

LOG

OF REVISIONS

Original

.......................February,1979

PAGES

DESCRIPTION

Title

Page

Original

"A"

Page

Original

a and

b

Original

1-1

thru

1-18

Original

2-1

thru

2-32

Original

3-1

thru

3-12

Original

4-1

thru

4-14

Original

5-1

thru

5-20

Original

6-1

thru

6-20

Original

7-1

thru

7-32

Original

8-1

thru

8-46

Original

Section

9

See Log

of

Supplements

10-1

thru

10-30

Original

A

Page A

BEECH

CRAFT Sundowner

180

C23(An-1285anelAfter)

SECTION I

GENERAL

TABLE

OF CONTENTS

SUBJECT PAGE

Thank

You

......................................

1-3

Important Notice

................................

1-3

Use of

the Handbook ............................

1-4

Revising

the Handbook

..........................

1-5

Supplernents Revision

Record

.

. . . .

. ... . ..... . . . . .

1-6

Vendor-Issued

STC

Supplements

.................

1-6

Airplane Three View

............................

1-7

Ground

Turning

Clearance .......................

1-8

Descriptive

Data

Engine

......................................

1-9

Propeller

....................................

1-9

Fuel ........................................

1-9

Oil Capacity ................................

1-10

February

1979

1-1

Section

I BE

ECHCRAFT

Sundowner

180

General

C23

(M-1285

ánd

After)

TABLE

OF

CONTENTS

(Continued)

SUBJECT PAGE

Approved

Oil

Types

.........................

1-10

Maximum

Certificated

Weights

..................

1-11

Cabin

and

Entry

Dimensions

....................

1-11

Baggage Space

and

Entry

Dimensions

...........

1-11

Specific

Loadings

..............................

1-11

Symbols, Abreviations and

Terminology

General

Airspeed

...........................

1-12

Meteorological

.............................

1-14

Power

.....................................

1-15

Engine Controls and

Instruments

............

1-15

Airplane Performance

and Flight

Planning

...

1-16

Weight

and Balance

........................

1-16

1-2

February

1979

BEECHCRAFT Sundowner 180 Section I
C23

(M-1285

and

After)

General

THANK

YOU

. . .

for

displaying

confidence

in

us by

selecting

a BEECHCRAFT

airplane. Our design enginee<s,

assemblers and inspectors

have

utilized

their

skills

and

years

of experience

to ensure

that

the

BEECHCRAFT

meets

the

high

standards of

quality and performance

for

which

BEECHCRAFT

airplanes have become famous

throughout the

world.

IMPORTANT

NOTICE

This handbook must

be

read

carefully by

the owner

and

operator

in

order

to become

familiar

with

the

operation

of

the

airplane. Suggestione

and recommendations

have

been made

within

it to aid

in obtaining

ma×imum

per-

formance without

sacrificing

economy. Be

familiar

with,

and operate the

airplane in accordance

with the Pilot's

Operating

Handbook

and

FAA Approved Airplane Flight

Manual,

ancVorplacards which are located in the

airplane.

As

a

further

reminder,

the

owner

and operator of

this

airplane

should also be

familiar with the

Federal Aviation

Regulations applicable

to

the operation

and

maintenance

of the airplane and

FAR Part 91 General

Operating and

Flight

Rules.

Further,

the

airplane

must

be operated and

maintained in accordance with FAA

Airworthiness

Directives which

may be

issued

against

it.

The

Federal

Aviation

Regulations place

the

responsibility

for the

maintenance of this

airplane

on the owner and

the

operator

who should ensure

that all

maintenance

is

done

by

qualified mechanics

in

conformity

with

all

airworthiness requirements

established for this airplane.

All

limits,

procedures,

safety

practices, time

limits,

servicing,

and

maintenance

requirements contained in

February

1979

1-3

Section I

BEECHCRAFT

Sundowner

180

General C23

(M-1285

and

After)

this

handbook are

considered

mandatory

for the continued

airworthiness

of

this

airplane, inacondition

equal to that

of its

original

manufacture.

Authorized

BEECHCRAFT

Aero or

Aviation Centers

and

International Distributors

or

Dealers can

provide

recommended

modification, service,

and

operating

procedures issued

by

both

FAA

and Beech

Aircraft

Corporation,

which

are designed

to get

maximum

utility

and

safety

from this airplane.

USE OF

THE HANDBOOK

The Pilot's Operating Handbook

is

designed

so that

nec-

essary documents

may

be maintained

for

the

safe and

efficient operation

of the

airplane. The

handbook

has

been

prepared in

loose leaf

form

for

ease

in

maintenance and

in

a

convenient

size for storage.

The

handbook

has

been

arranged

with

quick

reference tabs imprinted with thetitle

of each

section and

contains

ten basic

divisions:

Section

.I General

Section II

Limitations

Section

III Emergency

Procedures

Section

IV

Normal

Procedures

Section

V

Performance

Section VI Weight

and

Balance/Equipment

List
Section Vil Systems Description
Section Vill

Handling,

Servicing

and

Maintenance

Section

IX

Supplements

Section

X Safety

Information

NOTES

Except

as

noted,

all

airspeeds quoted in this

handbook

are

Indicated Airspeeds (IAS)and

as-

sume zero

instrument

error.

1-4

August,

1980

BEECHCRAFT Sundowner

180

Section I

C23

(M-1285

and

After)

General

Due to

the large

variety of

airplane

configura-

tions available

through optional

equipment,

it

should

be

noted that in

describing

and

illustrating

the

handbook,

optional

equipment

may

not be designated as such in every case.

Through variations

provided by

custom

designing, the

illustrations in this handbook

will not be

typical

of every

airplane.

Neither Service

Publications, Reissues,

nor

Revisions

are

automatically

provided to the

holder of this handbook. For

information on

how

to

obtain "Revision Service" applicable

to

this

handbook,

consult

any

BEECHCRAFT

Aero or Aviation Center or

Internationat

Distributor or Dealer

or

refer

to the latest

revision of BEECHCRAFT Service Instructions
No.

0250-010.

Beech

Aircraft

Corporation expressly reserves

the

right

to supersede, cancel and/or declare

obsolete

any

part, part

numbers,

kits

or

publication that

may be

referenced in this

handbook

without

prior

notice.

The

ownerloperator

should

always

refer to

all

supplements, whether STC Supplements or

Beech Supplements,

for

possible placards,

limitations, normal,

emergency and

other

operational procedures

for

proper

operation of

the airplane with optional

equipment

installed.

REVISING THE HANDBOOK

Immediately following

the

title

page is the

"Log

of

Revisions"

page(s).

The

Log

of Revisions

pages

are used

for

maintaining a

listing of

all effective

pages

in

the

hand-

book

(except the

SUPPLEMENTS

section),

and

as

a

record

of

revisions

to these pages. In the

lower

right corner

of

the

August, 1980

1-5

SectionI

BEECHCRAFTSundowner180

General

C23

(M-1285

and

After)

outlined portion

of

the

Log of

Revisions

is

a

box

containing

a

capital letter

which

denotes

the

issue or

reissue

of

the

handbook.

This

letter

may

be suffixed

by

a

number which

indicates

the numerical revision.

When

a

revision to

any

information in

the

handbook

is

made,

a

new

Log of

Re-

visions will

be issued.

All

Logs of Revisions must be

re-

tained

in

the

handbook

to

provide a current

record

of

ma-

terial

status

until

a

reissue

is made.

WARNING

When

this

handbook is

used

for

airplane

operational

purpose

it is

the pilot's

respon-

sibility to

maintain

it

in current status.

SUPPLEMENTS REVISION RECORD
Section

IX

contains supplements and

a

Log

of

Supple-

ments

page.

On

the

"Log"

page is a

listing of

the

supple-

mental equipment

available

for

installation

on

the

BEECH-

CRAFT airplane.
Upon

receipt of

a

new

or

revised supplement,

compare

the

"Log"

page just

received with

the

existing "Log"

page

in

the

manual.

Retain the

"Log"

page

with the

latest

date

on

the

bottom

of the

page (this

log

will

usually

have

the

greater

number of

entries)

and

discard

the

other

log.

VENDOR-ISSUED

STC

SUPPLEMENTS

When

a

new airplane

is delivered

from

the

factory,

the

handbook

delivered

with

it

contains

either

an

STC

(Supplemental

Type Certificate)

Supplement

or

a Beech

Flight Manual Supplement for

every

installed item

requiring a

supplement.

Ifa

new

handbook for

operation

of

the airplane

is

obtained at

a

later

date, it

is the

responsi-

bility

of the

owner/operator

to

ensure

that

all required STC

Supplements

(as

well

as

weight and

balance

and other

pertinent

data)

are transferred

into

the new handbook.

1-6

August,

1980

BEECHCRAFT Sundowner

180

Section I

C23

(M-1285

and

After)

General

25' 9"

S'3"

14"

6'

4"

32'

9"

10'

8"

76"

DIA.

O

r

11 10"

THREE

VIEW

c29-oor-io

February

1979 1-7

Sectioni

BEECHCRAFTSundowner180

General

C23

(M-1285

and

After)

GROUND TURNING CLEARANCE

Radius for Wing Tip

.................

23

ft.

11 in.

®

Radius for

Nose Wheel

..............

9

ft. 10

in.

©

Radius for

inside

Gear ................ 2 ft.

O

in.

©

Radius for

Outside

Gear .............. 13 ft.

O in.

TURNING

RADII

ARE

CALCULATED

USING FULL

STEER-

ING, ONE

BRAKE

AND

PARTIAL POWER.

1-8

February

1979

BEECHCRAFTSundowner180

Sectioni

C23

(M-1285

and

After)

General

14

"

6'

4"

32'

9"

10' 8"

76"

DIA.

11'

10"

i

THREE

VIEW

C23-607-10

February

1979

1-7

Section i

BEECH

CRAFT

Sundowner

180

General

C23(M-1285

and

After)

GROUND

TURNING CLEARANCE

Radius for Wing Tip

................. 23 ft.

11 in.

®

Radius for

Nose Wheel

.............. 9

ft.

10

in.

©

Radius for inside

Gear

................

2 ft.

O

in.

@

Radius

for Outside

Gear

..............

13 ft.

O

in.

TURNING

RADII

ARE

CALCULATED

USING FULL

STEER-

ING,

ONE

BRAKE

AND

PARTIAL POWER.

1-8

February 1979

BEECHCRAFT Sundowner

180 Section

I

C23

(M-1

285

and

After) General

DESCRIPTIVE

DATA

NOTE

M-1285

thru

M-2178

are

14-volt

systems.

The

battery

switch

is

placarded

BATTERY

&

ALT

and

the

alternator

switch

is

placarded

ALT

(or

ALT

FlELD).

28-volt

systems,

M-2179

and

after,

are

placarded BATTERY

for the

battery

switch

and

ALT FIELD

for

the

alternator

switch.

All items throughout

this

handbook

that refer

to

battery

switch refer

to

either

BATTERY

&

ALT switch

or BATTERY switch

depending

upon

configuration.

ENGINE

Airplane

is equipped

with an Avco

Lycoming

O-360-A2G,

O-360-A4G,

O-360-A4J

or

O-360-A4K

engine rated

at

1

80

horsepower.

Take-off

and

maximum continuous operation (sea level):

2700 rpm,

full throttle.

Engine

cooling

has

been demonstrated for

a

100°

F day.

PROPELLER

Sensenich

M76EMMS-O-60

or

76EM8S5-0-60

fixed

pitch, two blade

propeller. Static rpm

at

maximum

per-

missible throttle settings: Not over

2350 rpm

and

not

under 2250

rpm. No

additional tolerance

permitted.

FUEL

Aviation

Gasoline

91/96

(blue) minimum grade

or 100

(green)or

100LL

(blue).

M-1285

thru

M-1516:

*59.8-gallon

system

(29.9

gallons

each tank)

.......

*58

gallons

usable

Each

tank

has

provisions

for

partial

filling

to:

20

gallons

each tank

.........

38.2 gallons usable

15

gallons

each

tank

.........

28.2 gallons

usable

Revised:

April

1979

1-9

Section i

BEECH CRAFT Sundowner 180

General

C23

(M-1285

and After)

M-1517

thru

M-1879

except

M-1875

and

prior airplanes

after

cornpliance

with Service

Instructions

No.

0624-281:

*59.8-gallon

system

(29.9 gallons each

tank)

.......

*52

gallons usable

Each

tank has provisions for partial

filling to:

20 gallons

each

tank

.........

32.2 gallons usable

15

gallons each

tank .........

22.2 gallons usable

M-1875,

M-1880

and

after:

*59.8-gallon

system

(29.9 gallons

each

tank}

.....

*57.2

gallons usable

Each

tank has provisions

for partial

filling to:

20

gallons

each tank ......... 37.4 gallons

usable

15 gallons each

tank

.........

27.4 gallons usable

*Value

given is nominal.

Tank

capacity will vary with

temperature and

manufacturing

tolerances.

OIL CAPACITY

The

oil

capacity

is

8

quarts.

APPROVED

O/L TYPES

Avco Lycoming

Specification Number 301Eapproves for

use

lubricating

oils which

conform to both

MIL-L-60828

straight mineral

type and

MIL-L-22851

ashlessdispersant

Iubricants for airplane

engines. Refer

to

the Approved

Engine

Oils

table in the

HANDLING,

SERVICING AND

MAINTENANCE

section for a list of

approved products.

1-10

February

1979

BEECHCRAFT

Sundowner 180

Section I

C23

(M-1285

and

After)

General

MAXIMUM CERTIFICATED

WEIGHTS

NORMAL CATEGORY

Maximum

Ramp

Weight

....................

2455

Ibs

Maximum

Take-Off

Weight

.................

2450

lbs

Maximum

Landing Weight ..................

2450

lbs

UTILITY/ACROBATIC

CATEGORY

Maximum

Ramp

Weight ....................

2035 lbs

Maximum

Take-Off

Weight .................

2030

lbs

Maximum

Landing

Weight

..................

2030

lbs

ALL CONF/GURATIONS

Maximum Zero Fuel Weight ...... No

Structural

Limit

Maximum

Weight

in

Baggage

Compartment

................... 270 Ibs.

CABIN

AND ENTRY DIMENSIONS

Length

(maximum) ........................ 7

ft 11

in.

Height

(maximum) ..........................

4 ft

O

in.

Width

(maximum)

..........................

3

ft

8

in.

Cabin Door

................

36

in.

wide

by

38

in.

high

BAGGAGE

SPACE

AND ENTRY DIMENSIONS

Compartment

Volume

.....................

19.5 cu ft

Door Width

(Minimum)

......................

23.6 in.

Door Height (Minimum) ...................... 18.5 in.

SPECIFIC

LOADINGS (2450 Ibs.)

Wing Loading

.........................

16.78

lbs/sq

ft

Power

Loading

..........................

13.61

lbs/hp

February

1979

1-11

Section i BEECHCRAFT

Sundowner 180

General

C23

(M-1285

and

After)

SYMBOLS, ABBREVIATIONS

AND

TERMINOLOGY

The following Abbreviations and Terminologies have

been

listed for

convenience

and

ready

interpretation where

used

within

this handbook. Whenever possible,

they

have

been categorized for

ready

reference.

GENERAL AIRSPEED

TERMINOLOGY

AND SYMBOLS

CAS

Calibrated Airspeed is the indicated speed

of an

airplane,

corrected

for

position and

instrument

error.

Calibrated

airspeed

is

equal

to true airspeed

in standard

atmosphere at

sea

level.

GS

Ground Speed

is the

speed

of an airplane

relative to the ground.

IAS Indicated Airspeed

is

the speed of an airplane

as shown on the airspeed indicator when

corrected for instrument error. IAS values

pubilshed in this handbook assume zero
instrument error.

KCAS Calibrated Airspeed expressed in "knots".

KIAS Indicated Airspeed expressed in

"knots".

TAS True Airspeed

is the

airspeed of

an airplane

relative

to

undisturbed air which is the

CAS

corrected for altitude, temperature,

and

compressibility.

1-12

February

1979

BEECHCRAFT

Sundowner 180

Section I

C23

(M-1285

and

After)

General

VA

Maneuvering Speed is

the maximum

speed

at

which application

of full available

aero-

dynamic control will

not

overstress the

airplane.

VFE

Maximum

Flap

Extended

Speed is the highest

speed permissible with wing

flaps

in

a

pre-

scribed extended position.

VNE

Never Exceed Speed is the speed

limit

that

may

not be

exceeded

at any

time.

NO

Maximum

Structural

Cruising Speed

is the

or

VC speed

that should not

be exceeded except

in

smooth air and then

only

with

caution.

VS

Stalling Speed

or the minimum

steady

flight

speed at

which the airplane is controllable.

VSO

Stalling

Speed

or the

minimum

steady

flight

speed

at

which the airplane is

controllable

in

the landing

configuration.

VX

Best

Angle-of-Climb

Speed

is the airspeed

which

delivers the greatest

gain of altitude

in the

shortest

possible horizontal distance.

VY

Best

Rate-of-Climb

Speed

is the airspeed

which delivers the greatest

gain in altitude

in the shortest

possible time.

Cruise

Recommended Climb Speed for enroute climb.

Climb

February

1979

1-13

Section I

BEECH

CRAFT Sundowner 180

General

-

C23

(M-1285

and

After)

METEOROLOGICAL

TERMINOLOGY

ISA International Standard

Atmosphere

in which

(1) The

air

is a dry perfect gas;

(2)

The temperature

at

sea

level is

15°

Celsius

(59°

Fahrenheit);

(3) The pressure at sea

level is 29.92

in Hg. (1013.2

millibars);

(4) The

temperature gradient

from sea

level

to the

altitude

at which the

temperature

is

-56.5°

C

(-69.7°

F)

is

-0.00198°

C

(-0.003566°

F)

per foot and

zero above that

altitude.

OAT

Outside

Air

Temperature

is

the free air

static

temperature, obtained

either

from

inflight

temperature

indica-

tions adjusted for instrument

error

and compressibility effects

or

ground

meteorological

sources.

Indicated The number

actually

read from an

Pressure altimeter when

the barometric

sub-

Altitude

scale

has

been set to 29.92 in

Hg.

(1013.2 millibars).

Pressure Altitude measured

from standard

Altitude

sea-level

pressure

(29.92 in. Hg) by

a

pressure

or barometric altimeter.

It is the indicated pressure altitude

corrected for

position and instrument

error. In

this

Handbook,

altimeter

instrument

errors are assumed to be

zero. Position errors

may

be

obtained from

the

Altimeter

Correction Graph.

1-14

February

1979

BEECHCRAFT Sundowner 180 Section i
C23

(M-1285

and

After)

General

Station

Actual atmospheric pressure

at field

Pressure elevation.

Wind The wind velocities

recorded

as

variables

on the charts

of this

hand-

book are to

be understood as the

head-

wind or tailwind

components of the

reported winds.

POWER

TERMINOLOGY

Takeoff and Highest

power

rating
Maximum not limited by time.
Continuous

ENGINE

CONTROLS

AND INSTRUMENTS

Throttle Used

to

control power

by

intro-

Control ducing

fuel-air

mixture

into the

intake

passages of the

engine.

Mixture This control is

used

to

set

fuel

Control flow

in all

modes of

operation

and cuts

off fuel completely for

engine shut down.

EGT This

indicator is

used to identify

(Exhaust

Gas

the

lean

and best

power fuel

Temperature)

flow

for

various power

Indicator

settings

during

cruise.

I

Tachometer indicates

the

rpm

of

the engine/

propeller.

August,

1980

1-15

Section i

BEECH CRA FT

Sundowner 180

General

C23

(M-1285

and After)

AIRPLANE

PERFORMANCE AND

FLIGHT PLANNING

TERMINOLOGY

Climb

The

ratio of

the

change

Gradient

in

height

during

a

portion

of a

climb,

to the

horizontal

distance traversed

in

the

same

time

interval.

Demonstrated

The demonstrated crosswind

velocity

Crosswind

is

the

velocity

of the crosswind

com-

Velocity ponent

for

which adequate control

of

the

airplane

during

take-off

and

land-

ing

was

actually

demonstrated

during

certification tests.

MEA Minimum

enroute

IFR

altitude.

Route

A

part

of

a

route. Each end of that

Segment

part

is

identified by:

(1)

a

geograph-

ical

location;

or

(2)

a point at which

a definite radio fix can

be

established.

GPH

U.S.

Gallons per hour.

PPH

Pounds

per

hour.

WEIGHT

AND

BALANCE TERMINOLOGY

Reference

An imaginary

vertical

plane

from

Datum

which all

horizontal

distances are

measured for

balance

purposes.

Station A location

along

the airplane

fuselage

usually

given in terms

of distance

from

the

reference datum.

1-16

. February

1979

BEECHCRAFT

Sundowner

180 Section I

C23

(M-1285

and After)

General

Arm The horizontal distance from the

ref-

erence datum to

the center of gravity

(C.G.)

of an item.

Moment The product of the weight of an item

multiplied by its

arm. (Moment divided

by a

constant

is used to

simplify

bal-

ance calculations

by reducing

the

number of digits.)

Airplane

The point

at

which an airplane would

Center of balance if suspended. Its distance

Gravity

from the reference datum is found

(C.G.) by dividing

the

total

moment

by

the

total weight of the airplane.

C.G. Arm

The arm

obtained

by

adding the

air-

plane's individual moments and

dividing

the

sum by

the

total weight.

C.G. Limits The extreme center of gravity

loca-

tions within which the airplane must
be

operated at a given weight.

Usable Fuel Fuel available for flight

planning.

Unusable Fuel remaining after a runout

test·

Fuel has been

completed

in accordance

with

governmental

regulations.

Standard Weight of a standard airplane

Empty including

unusable

fuel,

full

Weight operating

fluids and full

oil.

Basic Standard empty weight plus
Empty optional equipment.

Weight

February

1979

1-17

Section

i

BEECH CRAFT

Sundowner

180

General

C23

(M-1285

and After)

Payload

Weight

of

occupants, cargo

and

baggage.

Useful Difference

between

take-off

weight,

Load or

ramp

weight

if

applicable, and

basic empty weight.

Maximum Maximum weight approved for ground

Ramp maneuvering. (It

includes weight of

Weight

start, taxi,

and

run-up

fuel).

Maximum

Maximum

weight approved

for

the

Take-off

start of the

take-off

run.

Weight

Maximum

Maximum weight approved

for

the

Landing landing

touchdown.

Weight

Zero Fuel Weight

exclusive

of usable fuel.

Weight

Tare The weight of

chocks, blocks,

stands,

etc.,

used

on

the

scales when

weighing

an

airplane.

Leveling

Those

points which are used during the

Points weighing

process to

level the airplane.

Jack

Points on

the

airplane identified

by

the

Points manufacturer

as

suitable for supporting

the airplane

for

weighing or other

purposes.

1-18

February

1979

BEECHCRAFTSundowner180
C23

(M-1285

and

After)

SECTION

II

LIMITATIONS

TABLE OF

CONTENTS

SUBJECT

PAGE

Airspeed

Limitations

.....................................

...................

2-3

A¡rspeed

Indicator

Markings .............................................

2-4

Power Plant

Limitations

Engine...........................................................................2-4

Operating

Limitations..........................................

......

2-5

Fuel Grades..........................

..

. .......................

2-5

Fuel

Additives..............................

. . .

....

.................

2-5

Oil Specifications........................

..

...........................

2-5

Propeller Specifications........................ ........................

2-5

Power Plant Instrument

Markings

.....................................

2-6

OilTemperature ............................

.... ......................

2-6

Oil Pressure ...............................

.. .. ..

.........................

2-6

Fuel

Pressure................................................................

2-6

Tachometer................................. .. .

..........................

2-6

Miscellaneous

instrument

Markings..................................

2-6

Instrument

Air......................

..... ...................................

2-6

Fuel

Quantity.......................

..

. .. .. ..........................

2-7

Weight Limits.....................

........

.... ... . ........................

2-7

Normal Category

...........................................................

2-7

Utility/Acrobatic Category..............................................

2-7

Center

of

Gravity Limits.....................................................

2-7

Normal Category........................

..

............................

2-7

Utility/Acrobatic

Category........-......... ......................

2-8

Reference

Datum.....

..................... ...........................

2-8

Maneuver

Limits ...............................

.... .. ......................

2-8

Normal

Category (2450 Pounds)...................................

2-8

Revised:

October

1979

2-1

Section

il

BEECHCRAFT Sundowner

180

Limitations C23

(M-1285

and

After)

TABLE

OF CONTENTS

(Continued)

SUBJECT

PAGE

Utility

Category (2030

Pounds)

...............

2-8

Maneuver

...............................

2-8

Acrobatic

Category

(2030

Pounds)

............

2-8

Flight

Load Factors

..............................

2-9

Normal Category (2450

Pounds)

..............

2-9

Utility

Category

(2030 Pounds)

...............

2-9

Acrobatic Category

(2030

Pounds)

............

2-9

Minimum Flight Crew ...........................

2-9

Kinds

of Operation

Limits

........................

2-9

Required Equipment

for

Various

Conditions

of

Flight

...........................

2-9

Legend

....................................

2-11

Fuel

Total

Fuel ..................................

2-19

Fuel

Management

..........................

2-19

Placards

.......................................

2-20

2-2

February

1979

BEECH

CRAFT Sundowner 180 Section

11

C23

(M-1285

and

After) Limitations

The limitations

included

in

this section have

been

approved

by

the Federal

Aviation

Administration.

The

following

limitations

must be observed in

the

operation of this

airplane.

AIRSPEED LIMITATIONS

CA3

IAL

SPEED KNOTS

MPH

KNOTS

MPH

REMARKS

Never Exceed

152 175 152

175

Do not exceed

VNE

this

speed

in

any

operation

Maximum

136 156 136

156

Do

not exceed

Structural

this speed

Cruising except in

smooth

VNO

or

VC

air

and then

only

with caution

Maneuvering

118

136 118 136

Do not

make

full

VA

or

abrupt control

movements

above

this speed

Maximum

96 110

96

110

Do not extend

Flap

flaps

or

operate

Extensiory

with

flaps

ex-

Extended

tended

above

FE

tHis

speed

February

1979

2-3

Section11

BEECHCRAFTSundowner180

Limitations

C23

(M-1285

and

After)

*AIRSPEED

INDICATOR

MARKINGS

MARK-

CAS

IÞS

SIGNIF-

ING KTS NIPH

KTS

MPH

ICANCE

White

52-96 60-110

52-96 60-110

Full

Flap

Arc

Operating

51-96 59-110

51-96

59-110

Range

Green

63-136

72-156

62-136

71-156

Normal

Arc

Operating

62-136 71-156

61-136 70-156

Range

Yellow

136-152 156-175

136-152 156-175

Operate

With

Arc Caution, Only

in

Smooth

Air

Red

152

175

152 175 Maximum

Line Speed

For

AII

Operations

*

The

limits of the

arcs

on

the

airspeed

indicator are

marked in

CAS

values.

M-1285

thru

M-1586

M-1587

and after

POWER

PLANT LIMITATIONS

ENGINE

One Avco Lycoming engine

model

O-360-A2G,

O-360-

A4G,

O-360-A4J

or

O-360-A4K

engine rated at

180

hp.

Take-off

and

Maximum

Continuous

Power ...................

Full

Throttle at 2700

rpm

2-4

February

1979

BEECHCRAFT

Sundowner 180 Section

II

C23

(M-1285

and

After) Limitations

OPERAT/NGLIMITAT/ONS

Engine

Speed

............................. 2700 rpm

Oil Temperature ..............................

245°F

Oil Pressure

Minimum

................................. 25 psi

Maximum

............................... 100 psi

Fuel Pressure

Minimum

................................

0.5 psi

Maximum

................................

6.0 psi

Mixture

-

Set per

leaning

instructions on performance

charts.

I

FUEL GRADES

Aviation Gasoline 91/96 (blue)

minimum

grade or

100

(green)

or 100LL

(blue).

FUEL

ADDITIVES

Alcor

TCP

Concentrate,

mixed

according

to

the

instructions

provided

by

Alcor,

Inc.

OIL SPEC/FICATIONS

Avco Lycoming Specification

Number 301E

approves

for

use

lubricating

oils which

conform

to

both

MIL-L-6082B

straight mineral type and

MIL-L-22851

ashless dispersant

lubricants for airplane engines. Refer

to

the Approved

Engine Oils table

in the

HANDLING,

SERVICING AND

MAINTENANCE

section for

a

list

of

approved

products.

PROPELLER

SPECIFICATIONS

Sensenich

M76EMMS-O-60

or

76EM8S5-0-60

fixed

August, 1980

2-5

Section

II BEECHCRAFT Sundowner

180

Limitations

C23(M-1285and

After)

pitch,

two

blade

propeller.

Static rpm

at maximum

per-

missible

throttle

settings: Not

over

2350

rpm and not

under

2250

rpm.

No

additional tolerance

permitted.

POWER

PLANT INSTRUMENT

MARKINGS

OlL

TEMPERATURE

Caution (Yellow Arc)

. .

. ... . . . . ... . .

.

60°

to

120°F

Operating

Range

(Green

Arc)

......................

120°

to

245°F

Maximum

(Red Line)

.......................

245°F

OIL PRESSURE

Minimum

Pressure (Red

Line)

.............. 25

psi

Minimum

Pressure (Yellow

Arc)

......

25 to

60 psi

Operating Range

(Green

Arc)

.........

60 to

90

psi

Maximum

Pressure

(Red

Line)

............ 100 psi

FUEL PRESSURE

Operating Range (Green

Arc)

........

0.5

to

6.0 psi

TACHOMETER

Engine

Warm-up

..............

1000 to 1200

rpm

Restricted Operation for

O-360-A2G

engine

only (Red Arc)

.........

2150

to

2350

rpm

Normal Operating

Range

all engines

(Green

Arc) .......

1800 to

2700 rpm

Maximum RPM (Red Radial)

............

2700

rpm

MISCELLANEOUS

INSTRUMENT

MARKINGS

INSTRUMENT

AIR

Operating

Range

(Green

Arc)

.....

4.3 to 5.9

in.

Hg

2-6

Revised: October 1979

BEECHCRAFT

Sundowner 180

Section II

C23

(M-1285

and After)

Limitations

FUEL

QUANTITY

On

M-1517

thru

M

1879

except

M-1875,

or prior

air-

planes

after compliance with

S.I.

No.

0624-281

Yellow

Band ........................

E to

3/8

full

On

M-1875,

M-1880

and after

Yellow Band

........................

E to

1/3

full

WEIGHT

LIMITS

NORMAL

CATEGORY

Maximum

Ramp

Weight ....................

2455 lbs

Maximum

Take-off

and

Landing

Weight

....................... 2450 lbs

Zero

Fuel

Weight .............

No

Structural Limitation

Maximum Baggage

Compartment

Load

..........

....

.....................

270

lbs

UTILITY/ACROBATIC

CATEGORY

Maximum

Ramp Weight. .

... . . . .

. . .

. . . ...2035

lbs

Maximum

Take-off

and

LandingWeight....................2030Ibs

Zero

Fuel

Weight.

. . . . . .

.

. . . .

No

Structural

Limitation

Maximum Baggage Compartment

Load

(Utility

Category

Only). .

.

. . . . . .

. .

. .

.

.270

Ibsi

CENTER OF GRAVITY

LIMITS

NORMAL

CATEGORY

Forward:

107.8

inches

aft

of datum

to 1800 lbs with

straight

line

variation

to

114.5

inches

at

2450

lbs.

Aft: 118.3

inches aft

of datum at

all

weights.

Revised: October 1979

2-7

Section11

BEECHCRAFTSundowner180

Limitations C23

(M-1285

and

After)

UTILITY/ACROBATIC CATEGORY

Forward:

107.8

inches

aft

of datum to 1800

lbs with

straight

line

variation

to 110.2 inches aft of

datum at 2030 lbs.

Aft:

114.0 inches

aft of

datum at

all

weights.

REFERENCE DATUM
Datum is

103 inches forward of wing leading

edge.

MAC length

is

52.7 inches.

MANEUVER LIMITS

This

airplane is approved for

4

place in the Normal

Category and for

2

place in the

Utility

and

Acrobatic

Category. Maximum slip duration

is 30

seconds.

NORMAL CATEGÓRY (2450

POUNDS)

No

acrobatic

maneuvers

approved.

UTILITY CATEGORY (2030

POUNDS)

No acrobatic maneuvers

are

approved

except those

listed

below.

MANEUVER

ENTRY SPEED

(CAS)

Chandelle ...................... 116

kts/133 mph

Steep

Turn ..................... 116

kts/133 mph

Lazy Eight

...................... 116

kts/133 mph

Stall

(Except

Whip)

.........

Use

slow deceleration

Intentional

Spins

M-1494

and after (only

if

certificated as

Acrobatic}

or

prior airplanes modified

by

Kit No.

23-4007-15

per

S.I.

No.

0619-090

. . . .

. .

. . . .

. .

Use slow deceleration

IACROBATIC CATEGORY

(2030

POUNDS)

For additional approved acrobatic

maneuvers, see

FAA

Approved Airplane Flight Manual Supplement.

2-8

Revised:

October 1979

BEECHCRAFTSundowner180 Sectionll

C23

(M-1285

and

After)

Limitations

FLIGHT

LOAD FACTORS

NORMAL CATEGORY

(2450

POUNDS)

Flight maneuvering

load

factor

Flaps

Up

..............................

+3.8,

-1.9

Flaps Down ................................

+1.9

UTILITY

CATEGORY (2030

POUNDS)

Flight

maneuvering

load factor

Flaps

Up

..............................

+4.4,

-2.2

Flaps Down

.........................,......

+2.2

ACROBATIC CATEGORY (2030

POUNDS)

Flight maneuvering

load factor

Flaps

Up

..............................

+6.0,

-3.0

Flaps Down ................................

+2.0

MINIMUM FLIGHT

CREW

One (1)

Pilot

KINDS

OF OPERATION LIMITS

1. VFR

day

and night

2.

IFR

day

and night

REQUIRED EQUIPMENT

FOR

VARIOUS

CONDITIONS

OF

FLIGHT

Federal Aviation Regulations

(91.3(a), 91.24,

91.25, 91.32,

91.33, 91.52,

91.90,

91.97,

91.170)

specifý the minimum

numbers

and

typesof airplane

instruments and equipment

which must be installed

and

operable for

various kinds of

flight

conditions. This includes

VFR day, VFR

night,

IFA

day, and IFR night.

February

1979

2-9

Sectionll BEECHCRAFTSundowner180

Limitations C23

(M-1285

and

After)

Regulations

also

require that

all airplanes be

certificated

by the manufacturer fõr operations under various flight
conditions.

At

certification,

all required equipment must be

in

operating

condition and

should be maintained

to

assure

continued

airworthiness. If

deviations from

the

installed

equipment

were

not permitted,

or

if the operating

rules

did

not provide

for

various

flight

conditions,

the airplane

could

not be flown unless

all

equipment was operable.

With

appropriate

limitations,

the operation of

every

system

or

component installed

in

the airplane is not

necessary,

when

the remaining

operative

instruments

and

equipment

provide

for continued safe operation.

Operation

in

accordance

with

limitations established

to

maintain

airworthiness,

can permit

continued or

uninterrupted

operation of the

airplane

temporarily.

For the sake of

brevity,

the Required

Equipment

Listing

does not include

obviously

required items such as wings,

rudders,

flaps,

engine,

landing

gear,

etc.

Also

the

list does

not

include items which

do

not

affect the

airworthiness

of

the airplane such as

entertainment

systems,

passenger

convenience

items,

etc.

However,

it is

important

to

note

that ALL ITEMS WHICH ARE RELATED

TO THE

AIR-

WORTHINESS OF THE

AIRPLANE

AND NOT INCLUDED

ON

THE

LIST

ARE AUTOMATICALLY

REQUIRED

TO BE

OPERATlVE.

To enable the

pilot

to

rapidly determine

the FAA

equipment

requirements

necessary

for

a

flight

into

specific

conditions,

the following

equipment

requirements

and

exceptions

are

presented. It is

the

final responsibility

of

the

pilot

to determine

whether

the

lack

of,

or

inoperative

status of

a

pieceof

equipment

on

his airplane, will

limit the

conditions

under

which

he may

operate the airplane.

2-10

February

1979

BEECHCRAFTSundowner180

Section11

C23

(M-1285

and

After) Limitations

WARNING

FLIGHT IN KNOWN

ICING CONDITIONS

PROHIBITED,

LEGEND

Numbers refer

to

quantities

required to

be

operative for

a

specified condition.

(-)

lndicates that the item

may

be inoperative for

the

specified condition.

(*)

Refer

to the

REMARKS AND/OR

EXCEPT10NS

column

for

explicit

information or

reference.

February

1979

2-11

VFR Dag

2

$

SYSTEM

VF

T Nit

ht

iÏ

g

and/or

/E

? Day

g·

COMPONENT

IF/*

Niqht

=

•¯

Remarks

and/or Exceptions

GENERAL

Overwater

flight

* * *

*

-

*Per

FAR 91.33

m

COMMUNICATIONS

m

VHF communications

system

*

*

*

*

-

*Per

FAR 91.33

ELECTRICAL

POWER

Battery 1

1 1 1

m

DC alternator 1 1

1

1

Starter

Engaged 1 1 1

1

-

May

be

inoperative

Warning

Light provided ammeter is

o

(M-2278

and

after) operative and

monitored

EQUIPMENT

AND

FURNISHING

m

Seat belts

and 1

1

1

1

-

Per

Person

or Per

FAR 91.33

=

O.

C

Shoulder

harness

y

=

Emergency locator

trans-

1

1

1

1

-

Per

FAR 91.52

,

o

mitter

-

=

O

o

FIRE

PROTECTION

Portable fire extinguisher

* *

*

*

-*Optional

.'s VFR

Day

,-

e

e

SYSTEM

VFR

Night

9

a

anct/or

IFR

Day

COMPONENT

/FR

Night

Remarks

and/or

Exceptions

FLIGHT

CONTROËS

Stabilator trim

tab

indicator

1

1

1 1

-

May be

inoperative

for

ferry

flight

m

provided

tabs

are

visually

checked

m

in the

neutral

position

prior

to

I

take-off

and checked for

full

range

of

operation.

Flap

position indicator 1 1 1

1

-

May be

inoperative provided

flap

-I

(On electric

flap system) travel is

visually

inspected

prior

to

take-off.

œ

Stall warning

1

1

1 1

o

m

FUEL EO.UIPMENT

i|| x

e

Fuel boost

pump 1 1 1

1

œ

>

Engine driven

fuel pump 1 1 1

1

Fuel

quantity

indicator

2

2

2

2

-

One

may

be

inoperative

pro-

vided other side is operational

>

and

amount

of

fuel

on

board can

,

o

be established

to be adequate

for

the

intended flight.

Fuel pressure indicator 1 1 1

1

m

o

ICE AND RAIN

PROTECTION

Emergency

static

* * *

*

-*Optional

air source

Pitot

heater

*

*

1

1

-*Optional

oi

e

=

VFR

Day

SYSTEM

VFR

Night

o

an(Vor

/FR

Day

COMPON

ENT

IFR

Night

Remarks and/or

Exceptions

LIGHTS

Cockpit and instrument

-

*

-

*

-*Lights must

be

operative,

lights

Taxi

light

- - - -

N

·o

Landing light

-

*

-

*

-*Per

FAR 91.33

i

>

Rotating

beacon

*

1

*

1

-*Optional

§

-I

Position light

-

3

-

3

y

Ë

.

o

NAVIGATION

om

INSTRUMENTS

Ë

z

o

Altimeter

1

1

1 1

o

>

e

Airspeed indicator

1 1 1 1

i

2

Vertical speed

- -

-

-

i

*

Magnetic

compass 1 1 1 1

>

g

Attitude indicator

- -

1

1

e

©

Turn

coordinator

- -

1 1

Directional gyro

- -

1

1

Clock

- -

1

1 m

Transponder

* *

*

*

-*Per

FAR 91.24, 91.90, 91.97

Navigation equipment

- -

*

*

-*Per

FAR 91.33

VACUUM

r-

Vacuum system

for

-

-

1 1

f.n

instrument

air

to

Vacuum gage

-

-

1

1

VFR

Day

SYSTEM

VFR

Night

ancVor

/FR

Day

IFR

Night

COMPONENT

Remarks

and/or

Exceptions

ENGINE

INDICATING

INSTRUMENTS

o

Engine

tachometer

indicator

1

1

1 1

m

m

Exhaust

gas

temperature

*

* * *

-*Optional

o

indicator

ENGINE

OIL

g

INSTRUMENTS

o.

Oil

pressure

indicator

1 1 1

1 a.

Oil

temperature indicator

1

1

1

1

to

.1

o

BEECHCRAFTSundowner180 Section11
C23

(M-1285

and After) Limitations

FUEL

TOTAL

FUEL

with left and right

wing

fuel

systems

full:

M-1285

thru

M-1516:

Two

*29.9-gallon

tanks in wings with

a

total

of

*58

gallons

usable.

M-1517

thru

M-1879

except

M-1875

and

prior airplanes

after

compliance

with Service Instructions No.

0624-281:

Two

*29.9-gallon

tanks in

wings

with

a total of

*52

gallons

usable.

M-1875,

M-1880

and

after:

Two

*29.9-gallon

tanks in wings with a

total

of

*57.2

gallons

usable.

*Value

given is nominal. Tank capacity will

vary

with

temperature and

manufacturing

tolerances.

FUEL

MANAGEMENT

On

M-1517

thru

M-1879

except

M-1875,

and

prior

air-

planes if

service

Instruction

No.

0624-281

is

ac-

complished:

Do

not

take off when

the Fuel

Quantity

Gages indicate in

the

Yellow

Band

or

with less

than

11 gallons

in

each main

tank.

Maximum slip

duration: 30 seconds

On

M-1875,

M-1880

and

after:

Do

not take

off

when

Fuel

Quantity

Gages

indicate

in

Yellow

Band

on either gage.

Maximum

slip duration:

30 seconds

February 1979

2-19

Section

11

BEECHCRAFT

Sundowner180

Limitations

C23(M-1285and

After)

PLACARDS

On Left Cabin

Door

or Left

Side

Panel

(M-1285

thru

hi-1979

except

M-1971)

(CAS)

THIS AIRPLANE MUST

BE

OPERATED IN

COMPLIANCE

WITH THE OPERATING

LIMITATIONS STATED IN THE

FORM OF

PLACARDS,

MARKINGS AND

MANUALS.

NORMAL

CATEGORY

MAXIMUM DESIGN WEIGHT

2450

LBS

REFER

TO WEIGHT AND

BALANCE

DATA

FOR LOADING

INSTRUCTIONS

FLIGHT

MANEUVERING LOAD

FACTOR FLAPS UP #3.8

-1.9

DOWN

+1.9

MAXIMUM

MANEUVERING

$PEED 136

MPH

NO

ACROBATIC

MANEUVERS

INCLUDING

SPINS

APPROVED

UTILITY

CATEGORY

MAXIMUM

DESIGN WEIGHT

2030

LBS

REFERTOWEIGHT AND BALANCE

DATA
FOR LOADING INSTRUCTIONS
FLIGHT

MANEUVERING LOAD FACTOR

FLAPS

UP

+44

--2.2

DOWN

‡2 2

NO ACROBATIC

MANEUVERS APPROVED

EXCEPT

THOSE LISTED

BELOW:

MANEUVER MAXIMUM

ENTRY

SPEED

CHANDELLES 133

MPH

LAZY EIGHTS 133 MPH

STEEP TURNS

133

MPH

STALLS (EXCEPT

WHIP STALLS]

SLOW

DECELERATION

NOTE: MAXIMUM ALTITUDE LOSS

DURING

STALL 300

FT

2-20

February

1979

BEECHCRAFT

Sundowner 180

Section

il

C23

(M-1285

and After)

Limitations

On

Instrument

Panel

in

Full View of Pilot

(M-1285

through

M-1493,

unless

modified

by

Kit

No.

23-4007-iSand

Service

Instructions

No.

0619-090)

HIS

AIRPLANE

MUST

BE

OPERATED

AS

E

NORMAL

OR

UTILITY

CATEGORY

AIRPLANE.

INTENTIONAL SPINS ARE PROHIBITED.

NO

ACROBATIC MANEUVERS APPROVED

EXCEPT:

CHANDELLES,

LAZY

EIGHTS,

STEEP

TURNS,

ND STALLS (EXCEPT WHIP STALLS)."

On

Left

Cabin

Door or Left Side Panel

(M-1971,

M-1980

and after)

(CAS)

THIS

AIRPLANE MUST BE OPERATEDINCOMPLIANCE

WITH THE OPERATING

LIMITATIONSSTATED

IN

THE

FORM OF

PLACARDS,

MARKINGS AND

MANUALS.

NORMAL

CATEGORY

MAXIMUM DESIGN WEIGHT

2450

LBS

REFER TO WEIGHf AND BALANCE

DATA

FOR LOADING INSTRUCTIONS
FLIGHT

MANEUVERING LOAD FACTOR FLAPS

UP +3.8

-1.9

DOWN

+1.9

MAXIMUM MANEUVERING SPEED 118 KTS/136 MPH

NO

ACROBATIC

MANEUVERS

INCLUDING

SPINS APPROVED

UTILITY

CATEGORY

MAXIMUM DESIGN

WEIGHT

2030 LBS

REFER TO

WEIGHT AND BALANCE

DATA

FOR LOADING

INSTRUCTIONS

FLIGHT MANEUVERINGLOAD

FACTOR

FLAP$ UP

-(-4.4

-2.2

DOWN

+2,2

NO

ACROBATIC MANEUVERS APPROVED

EXCEPT THOSE

LISTED

BELOW:

MANEUVER

MAXIMUM

ENTRY

SPEED

CHANDELLES 116

KTS/133 MPH

LAZY EIGHTS 116

KTS/l33 MPH

STEEP

TURNS

116 KTS/133 MPH

STALLS

lEXCEPT

WHIP

STALLS)

SLOW

DECELERATION

NOTE:

MAXIMUM ALTITUDE LOSS DURING STALL 300 FT

February

1979

2-21

Section II

BEECHCRAFT

Sundowner 180

Limitations C23

(M-1285

and

After)

PLACARDS

On

Left Cabin

Door or Left

Side Pane/

(Acrobatic)

(M-1285

thru

M-1979

except

M-1971)

(CAS)

HIS AIRPLANE MUST

BE OPERATED IN COMPLIANCE

WITH THE OPERATING LIMITATIONS STATED IN

THE

FORM OF

PLACARDS, MARKINGS AND

MANUALS.

NORMAL CATEGORY

MAXIMUM DESIGN WEIGHT

2450

LB5
REFER TO WEIGHT AND BALANCE DATA
FOR

LOADING INSTRUCTIONS

FLIGHT

MANEUVERINGLOAD FACTOR

FLAPS UP

+38

-19

DOWN +

y 9

MAXIMUM MANEUVERENG

SPEED

136

MPH

NO ACROBATIC MANEUVERS
INCLUDING SPINS

APPROVED

UTILITY&ACROBATIC CATEGORY

MAXIMUM DESIGN WEIGHT 2030 LES

REFER

TO WEIGHT AND BALANCE DATA

FOR

LOADING INSTRUCTIONS

FLIGHT

MANEUVERING

LOAD

FACTOR

FLAPS UP

-i-6.0 -

3.0

DOWN

-E2.0

NO ACROBAT1C MANEUVERS APPROVED

EXCEPT THOSE LISTED BELOW:

MANEUVER

MAX1MUM ENTRY SPEED

CHANDELLES

133 MPH

LAZY EIGHTS 133 MPH

STEEP TURNS 133

MPH

STALLS (EXCEPT WHIP STALLSI

SLOW DECELERATION

NOTE: MAXIMUM ALTITUDE LOSS DURING STALL

300 FT

SPINS (FOR

OPERATIONAL

LIMITATIONS SEE PLACARD ON SUN VISOR)

RECOMMENDED

ENTRY

SPEED

BARREL ROLL 130 MPH

AILERON ROLL

130 MPH

SNAP ROLL

100 MPH

SPLIT S 90 MPH

MELMANN 15400MM

On

Right and Left

Cabin

Doors

(Acrobatic)

REMOVE

DOOR

HOLD

-

OPEN ROD PRIOR

TO

OPERATION

IN

ACROBATIC CATEGORY

2-22

February

1979

BEECHCRAFTSundowner180

Section11

C23

(M-1285

and

After)

Limitations

On Left

Door

or Left Side

Panel (Acrobatic):

(M-1971, M-

1980

and

after)

(CAS)

THIS AIRPLANE MUST

BE

OPERATED

IN COMPLIANCE

WITH

THE OPERATING

LIMITATIONSSTATED IN THE

FORM OF

PLACARDS,

MARKINGS AND MANUALS.

NORMAL

CATEGORY

MAX1MUM

DESIGN WEIGHT

2450 LBS

REFER TO

WEiGHT AND BALANCE

DATA

FOR LOADING

INSTRUCTIONS

FLIGHT

MANEUVERINGLOAD FACTOR

FLAPS UP +3.8

-1.9

DOWN

+1.9

MAXIMUM MANEUVERING

SPEED

118 KTS/136 MPH

NO

ACROBATIC

MANEUVERS

INCLUDING SPINS APPROVED

UTILITY&

ACROBATIC CATEGORY

MAXIMUM DESIGN

WEIGHT 2030

LBS

REFER TO

WEIGHT AND BALANCE DATA

FOR

LOADING INSTRUCTIONS

FLIGHTMANEUVERING LOAD FACTOR FLAPS UP +6.0

--30

DOWN

+2.0

NO ACROBATIC MANEUVERS

APPROVED

EXCEPT THOSE LISTED

BELOW:

MANEUVER

MAXIMUM ENTRY SPEED

CHANDELLES 116 KTS/133 MPH

LAZY

EIGHTS

116 KTS/133

MPH

STEEPTURNS

116 KTS/133 MPH

STALLS

lEXCEPT

WHIP

STALLS) SLOW

DECELERATION

NOTE:

MAXIMUM ALTiTUDE LOSS

DURING

STALL

300 FT

SPINS

IFOR

OPERATIONAL LIMITATIONS

SEE PLACARD ON

$UN VISOR)

RECOMMENDED

ENTRY

SPEED

BARREL ROLL

113 KTS/130 MPH

AILERON ROLL

113

KTS/130 MPH

SNAP

ROLL

87 KTS/100 MPH

SPLIT

5

79

KTS/90 MPH

IMMELMANN

130

KTS/150 MPH

LOOP

122 KTS/140 MPH

On Right

Side of

Instrument Panel

(Acrobatic)

CAUTION

CONTINUOUS INVERTED

FLIGHT WILL CAU5E

LOSS OF OIL

AND

OIL PRESSURE. REAR

CG

LIMITED

AND

CARRYING

OF

BAGGAGE

OR

REAR SEAT PASSENGERS AND

USE OF

FLAPS PROHIBITED DURING ACROBATIC

MANEUVERS.

February

1979

2-23

Section II

BEECHCRAFT Sundowner 180

Limitations

.

C23

(M-1285

and After)

PLACARDS
On Upper

Right

Instrument Panel

RAISE

FLAPS

TO

INCREASE

BRAKE

EFFECTIVENESS

On

Flap

Extension Handle:

(M-1285

thru

M-1979

except

M-1971)

(CAS)

FLAPSPULL TO EXTEND, MAX

SPEED

110 MPH

RETRACTED

. . .

. . . .

0°

FIRST

NOTCH .

.

. .

. .

15°

SECOND

NOTCH . .

. .

25°

THIRD

NOTCH

.

. .

. .

35°

On Flap Extension Handle

(M-1971,

M-1980

and

after)

(CAS)

FLAPS PULL TO

EXTEND, MAX

SPEED

96

KTS/110 MPH

RETRACTED

. . . . ...

0°

FIR$TNOTCH

. . . ...

15°

SECOND

NOTCH

. ...

25°

THIRO

NOTCH . . . . .

35°

2-24

February

1979

BEECHCRAFTSundowner180

Section11

C23

(M-1

285

and

After) Limitations

On Sunvisor

Above Pilot

s Seat (Acrobatic)

I

OPERATIONAL LIMITATIONS

SPlNS:

The airplane

will not spin if orthodox eniry is used.

but will

enter a spiral dive speed

builds up

rapidly

itt u spiral

dive

requiring high

pulleul louds: ihersiare,ifa

spirol

s inadvertenity enteredrecoveryFromthespiralistobainitialedwithin1walurns

ENTRY: Stall the

airplane with

the

conirol cofumn

hard

back. rhietile in idle posilien

flops vp

carburetor hootasrequired and

wih the

nose about 25 above

lhe

horiaen.

Al the siali apply full rudder in

ihe dreclien required to spilt.

A slight

rudder application

immediateir

before

the

siell will

assure the

direrlien of spin.

The airplane nose will drap and rolella

rowards the applied

rudder When

the wines are 90 to the horimn, apply Ivil oileron

against (i.e

against ihe iniended

directionoFspin). The airplone

wil1 go slightly

inverted and enieranormal spin

It oileron

against is not upplied or

applied soo lore Ihe

airplane will enier a rapid spirai

dive and recovery musi be

init

need

by

rhe second lurn

If

Ilie

icdf Is¤ck stick is not opplied

and held Ihe airplirne may spiral

Agoin

recovery

must be inificied noi larer than the

IF oileren is applied too

early, the

airplane will not rotate and

merely

remain

in a sirnight sielled

condition

RECOVERY IMMEDIATELY MovE THE

CONTROL COtUMN

FUIL FORWARD AND SIMULTANEQUSLY

APPLY

FULL

RUDDER

°'"°""'°'"E

OlPECTION

OF THE

5PIN CONIlNUE

TO NOLD THIS

CONTROL PO51TION

UNTIL

ROTATION

5TOPS AND

TMEN NEUTRALIZE ALL

CONTROLS AND EXEEUTE ASMOOTH

PULLOUT

ALLERONS SHOUID LE

NEUTRAL

AND THROTTLE 1N lOLE POSlflON AT ALL TIMES

DURING RECOVERY

The

above

placard

reads

as follows:

"OPERATIONAL LIMITATIONS

SPINS:

The airplane

willnot

spin if

orthodox

entryisused, but

willenteraspiral

dive.

Speed

builds

up

rapidly in

a

spiral

dive,

requiring

high pullout

loads; therefore,

if

a

spiral is

inadvertently

entered

recovery from

the spiral

is to be

ini-

itiated

within

two turns.

ENTRY: Stall the airplane

with

the

control

column hard

back,

throttle

in idle

position,

flaps up, carburetor

heat

as required and with

the nose about

15°

above the

horizon.

At the

stall,

apply full

rudder in the

direction

required to spin.A

slight

rudder

application

immediately

before

the

stati will

assure the direction

of

spin. The

airplane

nose

will

drop

and rotate towardsapplied

rudder.

When

the

wings are

90°

to

the

horizon, apply

full

aileron against (i.e.

against

the intended direction

of spin). The airplane will

go

slightly

inverted and

enter

a nomial

spin.

If

aileron against is not

applied or

applied too

late,

the

airplane will

enter

a

spiral

dive, and

recovery

must be initiated by the second

turn. If

the

futi back

stick is not

applied

and

held,

the

airplane

may

spiral. Again

recovery

must be

initiated not later than the second

tum. If the

aileron is applied

too

early,

the

airplane

will not rotate

and

merely

remain in

a straight

stalled condition.

RECOVERY:

Immediately

move

the control

co!-

umn full

fonward

and

simultaneously

applyfull

rudder opposite

tothe

direction

ofthe

spin; continue

to

hold this

control

position

until

rota-

tion

stops

and then neutralize all

controis

and execute a smooth

pullout.

Ailerons

should

be

neutral

and

throttle

in idle

positionatall

times

during

recovery."

February

1979

2-25

Section II BEECHCRAFTSundowner180
Limitations

C23

(M-1285

and After)

PLACARDS

On Fuel Selector Panel

(M-1285

through

M-1516):

L TANK

R

TANK

29

GAL

29 GAL

OFF

On Fuel

Selector

Panel

(M-1517

through

M-1879

except

M-1875

or

prior airplanes

after

cornplíance

with Service

Instructions No.

0624-281)

L TANA

TANAL

OFF

OFF

2-26

February

1979

BEECHCRAFT

Sundowner

180

Section 11

C23

(M-1285

and

After)

Limitations

On

Fue/

Selector

Panel

(M-1875,

M-1880

thru

M-2224):

i

L

TANK

R

TANK

28.6

GAL

28.6

GAL

I

OFF OFF

OR

On

Fuel

Selector

Panel

(Serials

M-2225

and

after,

or

earlier airplane serials which

have

complied with

BEECHCRAFT Service Instructions

No.

1095):

OFF

Adjacent to

Engíne

Instrument Cluster

(M-1517

through

M-

1879

except

M-1875

or

prior

airplanes

after

complíance

with

Service

Instructions

No. 0624-281)

DO

NOT TAKE

OFF WHEN FUEL

OUANTITY

GAUGE

INDICATES

IN

YELLOW OR

WITH

LESS THAN

H GALLONS

IN

EACH

MAIN TANK

MAXIMUM

$LIP

DURATION

IS

30

5tcDNDS

Adjacent

to Engine

Instrument

Cluster

(M-1875,

M-1880

and

after):

DO NOT TAKE OFF WHEN

FUEL

QUANTITY

GAUGE INDiCATE5 IN

YELLOW

ON

EITHER

GAUGE MAXIMUM

SLIP

DURATION

30 5EC.

August,

1980

2-2T

Section11 BEECHCRAFTSundowner180

Limitations

C23

(M-1285

and After)

PLACARDS

Above Right and

Left Cabin

Doors:

{M-1285

thru

M-1412

and

M-1415,

M-1419,

M-1423,

M-1439

and

M-1447)

oPEN

On Left

Cabin Door

(Acrobatic)

e o

EMERGENCYEXIT

TURN HANDLE

CLOCKWISE

&

PULL

LATCH

ABOVE ARM

REST,

THEN

KICK-OUT

TO

JETTISON DOOR

On

Right Cabin

Door

(Acrobatic)

De

EMERGENCY

EXIT

TURN

HANDLE

COUNTER-

CLOCKWISE & PULL LATCH

ABOVE ARM

REST,

THEN

KICK-OUT

TO

JETTISON

DOOR

2-28

August, 1980

BEECHCRAFTSundowner180

Section11

C23

(M-1285

and After) Limitations

On

Baggage

Compartment Door

TO

LEVEL

AIRCRAFT

-

LEVEL

BAGGAGE

COMPARTMENT FLOOR

On Pedestal Between

Front

Seats:

D

O

w

r¯¯¯¯¯

NO
N

O

s

E

U

P

I

On Second Window Frame

Right Side

(M-1658andafteras

required

by

weight and balance

data)

BAGGAGE, CARGO

OR FAMILY

SEATS

I

LOAD IN

ACCORDANCE

WITH

WEIGHT

& BALANCE

-DATA

MAXIMUMSEAT CAPACITY

POUNDS

February 1979

2-29

Section 11

BEECHCRAFT

Sundowner

180

Limitations

C23

(

M-1285

and

After)

PLACARDS
On

Lower Sidewall

Adjacent to

Pilot

(when

installed)

e

WARNING

o

EMERGENCY AIRSPEED STATIC

SOURCE

SEE

FLIGHT

MANUAL

NORMAL

EMERGENCY

PROCEDURES

OFF

FOR

AIRSPEED ALTIMETER

CALIBRATION ERROR

ON

EMERGENCY

or;

o

WARNING

o

EMERGENCY AIRSPEED

STATIC

SOURCE

ON

EMERGENCY

SEE PILOTS

CHECK

LIST

OR

FLLGHT MANUAL

EMERGENCY PROCEDURES

'

FOR

AIRSPEED

&

ALTIMETER

CALLBRATION ERROR

OFF

NORMAL

Of

wARNING

o

EMERGENCY

AIRSPEED

STATIC

SOURCE

EMERGENCY

(

',

ON

SEE PILOTS CHECK

LIST

I

y

OR FLIGHT MANUAL '.

OFF

EMERGENCY PROCEDURES

FOR

AIRSPEED&ALTIMETER

NORMAL

CALIBRATION

ERROR

On Aft Cabin

Bulkhead:

HAT SHELF

NO

HEAVY

OBJECTS

2-30

February

1979

BEECHCRAFT Sundowner 180 Section

II

C23

(M-1285

and

After)

Limitations

On

Baggage

Compartment Door

BAGGAGE COMPARTMENT

270 POUNDS

MAXIMUM CAPACITY

On Upper

Aft Corner

of

Each Cabin

Door

(when

installed)

NSTRUCTIONS

-

SHOULDER STRA

l.

OCCUPANT

SHORTER THAN

4FT

71N

DO

NOT

USE

SHOULDER

STRAP

2.

NEVER USE SHOULDER STRAP

WITH OUT

LAP

BELTS

or;

INSTRUCTION-SHOULDER

STRAP

l.

OCCUPANTS

SHORTER

THAN

4

FT.

7 IN.

DO

NOT

USE

SHOULDER

STRAP.

2. PLACE

SEAT

BACK IN

THE

UPRIGHT

POSITION

DURING

TAKEOFF AND

LANDING.

February

1979

2-31

Section11 BEECHCRAFTSundowner180
Limitations C23

(M-1285

and After)

INTENTIONALLY

LEFT

BLANK

2-32

February 1979

BEECHCRAFT Sundowner 180

C23(M-1285andAfter)

SECTION III

EMERGENCY PROCEDURES

TABLE

OF

CONTENTS

SUBJECT PAGE

EmergencyAirspeeds.......................................................3-3

Engine Failure

During

Take-Off

Ground

Roll.........................................

3-4

After LiftoffAnd

In

Flight................................................

3-4

If

No

Restart...............................................................3-5

Engine

Discrepancy

Checks

Condition:

Rough

Running

Engine.............................

3-5

Condition:

Loss

Of

Engine Power ..............................

3-5

Airstart

Procedure.............................................................3-6

Engine

Fire

In

Flight.........................................................................3-6

On

The

Ground .............................................................

3-7

Emergency

Descent.........................................................3-7

Maximum Glide

Configuration...........................................3-7

Landing

Emergencies

Landing

Without Power.................................................

3-7

Systems

Emergencies......................................................

3-8

Starter

Energized

Warning

Light Illuminated.....................

3-8

Alternator-Out

Proced ure

..............................................

3-8

Unscheduled

Electric Stabilator

Trim ............................

3-9

Emergency Static

Air

Source

System............................

3-9

Unlatched Door

in Flight..............................................

3-10

Spins...............................................................................

3-10

Entry--..--..-......-.-- ..................

3-11

Recovery.....-..

-.........

..--.-................

3-11

August,

1980

3-1

Section

III

BEECH CRAFT Sundowner

180

Emergency Procedures C23

(M-1285

and After)

INTENTIONALLY

LEFT

BLANK

3-2

February

1979

BEECHCRAFT

Sundowner

180 Section

III

C23

(M-1285

and

After)

Emergency Procedures

A//

airspeeds

quotedin

this section

are indicated

airspeeds

(IAS).

EMERGENCY AIRSPEEDS

Emergency

Descent

.................................... 152

kts/175

mph

|

Glide

................................................................ 78

kts/90 mph

Emergency Landing

Approach.........................

68

kts/78

mph

Stall

warning

horn is

inoperative when

the

battery

and

al-

ternator

switches

are

turned off.

NOTE

On

serials

M-2225

and after,

or

on

airplanes

which have complied

with BEECHCRAFT

S.l.

No.

1095,

a

fuel

selector

stop

has been added

to the

selector

valve

guard.

The

fuel selector

stop

minimizes

the possibility of

inadvertently

turning

the

fuel

selector valve to

the

OFF

detent position. The

stop

is

a

spring

which

must

be

depressed before the

selector

valve

handle

can be

rotated to the

OFF

position.

The

following

information

is

presented

to

enable

the

pilot

to

form, in advance,

a

definite plan

of action for coping

with

the most probable

emergency situations

which

could

occur in

the

operation of the airplane. Where

practicable,

the emergencies requiring

immediate

corrective

action are

treated

in check list

form

for

easy

reference

and

familiari-

zation.

Other

situations,

in

which

more

time is

usually

per-

mitted

to

decide on and execute

a

plan

of

action,

are

discussed at some length.

August, 1980

3-3

Section III BEECHCRAFT Sundowner 180
Emergency Procedures

C23

(M-1285

and

After)

ENGINE FAILURE
DURING

TAKE-OFF

GROUND ROLL

1. Throttle

-

CLOSED

2.

Braking

-

MAXIMUM

NOTE

Conduct

the following procedures

imme-

diately

if it appears

certain that the airplane

will run off the

runway.

(Otherwise conduct

these procedures at the pilot's

discretion.)

3. Fuel Selector Valve

-

OFF

4.

Battery Switch,

Alternator

Switch,

and Fuel Boost

Switch

-

OFF

5. Magneto/Start Switch

-

OFF

AFTER LIFTOFF AND IN

FLIGHT

Landing

straight ahead is

usually advisable. // sufficient

altitude is available for

maneuvering, accomplish

the

following:

1.

Mixture

-

FULL

RICH,

then

LEAN as

required

2. Fuel Boost Pump

-

ON

3.

Fuel Selector Valve-SELECT OTHER TANK (Check to

feel detent

and

check

visually)

4. Magnetos

-

CHECK LEFT and

RIGHT,

then BOTH

NOTE

The most probable cause of engine failure

would be loss of fuel flow or improper
functioning

of

the

ignition system.

3-4

Revised:

April 1979

BEECH

CRAFT Sundowner

180 Section III

C23

(M-1285

and

After)

Emergency

Procedures

IF

NO RESTART:

1. Establish

maximum

glide

2.

Throttle

-

CLOSE

3. Fuel

Selector

Valve

-

OFF

4. Mixture

-

IDLE

CUT-OFF

5. Magneto/Start

Switch

-

OFF

6. BATTERY

&

ALT, ALT, and FUEL BOOST switches

-

OFF (With

electric flaps

installed,

it

will

be

necessary

to set

desired flaps

before

securing

battery.)

When

certain of

reaching

the selected

landing

site:

7.

Airspeed

-

68

kts/78 mph

8. Flaps

-

AS REQUIRED

ENGINE

DISCREPANCY

CHECKS

CONDITION: ROUGH RUNN/NG

ENGINE

1. Mixture

-

FULL

RICH,

then

LEAN

as

required

2. Magneto/Start

Switch

-

CHECK

LEFT and RIGHT,

then

BOTH

CONDITION:

LOSS

OF

ENGINE

POVVER

1.

Fuel Pressure Gage

-

CHECK

If

fuel flow

is

abnormal/y

low:

a. Mixture

-

FULL RICH

b. Fuel Boost Pump

-

ON

(Lean

as

required)

c.

Fuel

Boost Pump

-

OFF

if performance

does not

improve in a few

moments

February

1979

3-5

Section III

BE

ECH

CRAFT Sun

downer

180

Emergency

Procedures .

C23(M-1285

and

After)

2. Fuel

Quantity

Indicator

-

CHECKfor fuel

supply

in tank

being

used

//

tank being used

is

empty:

a.

Fuel Tank Selector

Valve

-

SELECT OTHER

FUEL

TANK

(feel for detent

and

check

visually)

b.

Fuel Boost

Pump

-

ON

AIR START PROCEDURE

1. Fuel Selector

Valve

-

SELECT TANK MORE

NEARLY

FULL (check

to

feel detent and

check visually)

2. Throttle

-

FULL

FORWARD

3.

Mixture

-

FULL RICH

4. Fuel Boost

Pump

-

ON

until power

is

regained, then

OFF. (Leave on

if engine

driven

fuel pump is

inoperative.)

5.

Throttle

-

ADJUST

to

desired power

6. Mixture

-

LEAN

as

required

ENGINE FIRE

IN FLIGHT

The

red ventilation

controls

must be closed

to

shut off

all

heating system

outlets

so

that smoke

and

fumes will

not

enter the cabin. The control labeled

CABIN

AIR must be

pulled out

to

close. The control

labeled

DEFROST must be

pushed

in

to

close.

In the event of an engine

fire,

shut

down

the engine

as

follows

and make

a

landing:

1. Fuel Selector Valve

-

OFF

2. Mixture

-

IDLE

CUT-OFF

3.

Throttle

-

CLOSE

4.

Cabin Air Control (Red

Knob)

-

pull

OFF

3-6

February 1979

BEECHCRAFT

Sundowner 180

Section

III

C23

(M-1285

and After)

Emergency Procedures

5. Defrost

Valve

(Red

Knob)

-

push

OFF

6.

Battery

Switch

-

OFF

7.

Alternator

Switch

-

OFF

8. Magneto/Start Switch

-

OFF

9.

Do not attempt to restart engine

ON THE

GROUND

1.

Fuel Selector Valve

-

OFF

2.

Throttle

-

CLOSED

3. Mixture

-

IDLE

CUT-OFF

4.

BATTERY

&

ALT

and Magneto/Start Switches

-

OFF

5.

Extinguish with

Fire Extinguisher.

EMERGENCY DESCENT

1. Throttle-IDLE

2.

Airspeed

-

ESTABLISH

152 kts/175 mph

MAXIMUM

GLIDE CONFIGURATION

1.

Flaps-UP

2.

Airspeed

-

78

kts/90 mph

Glide

distance

is

approximately 1.7

nautical miles

(2

statute

miles) per

1000 feet of

altitude

above

the

terrain.

LANDING

EMERGENCIES

LANDING

WITHOUT

POWER

When assured

of

reaching

the

landing

site

selected,

and

on final approach:

1. Airspeed

-

68

kts/78 mph

2. Fuel Selector Valve-OFF

3.

Mixture

-

IDLE

CUT-OFF

4.

Magneto§tart

Switch

-

OFF

5. Flaps

-

AS

REQUIRED

August,

1980

3-7

Section III

BEECHCRAFTSundowner180

Emergency

Procedures

C23(M-1285

and After)

6. Battery

Switch,

Alternator

Switch, and

Fuel Boost

Switch

-

OFF

7.

Upper Cabin

Door Latch

-

OPEN (if

installed)

SYSTEMS

EMERGENCIES

STARTER ENGAGED WARNING LIGHT ILLUMINATED
(If

Installed)

The STARTER

ENGAGED

warning

light illuminates

whenever

the starter is

engaged. If this

light

remains

illuminated

after

Magneto/Start

Switch is

released from

the

START position,

the

starter

relay

is

still energized.

Consequently,

electrical power is

still

being

supplied to the

starter, and

it

remains engaged.

Continuing

to supply

power

to the starter will

eventually

result in the

complete

loss

of electrical system power, substantial starter

damage,

and

possible

damage to other

electrical

system

components.

If light remains

i//uminated on the

ground:

1.

Battery Switch and

Alternator Switch

-

OFF

2.

Do

Not Take Off.

// light

remains i//uminated in flight

after air start:

1.

Battery

Switch

and

Alternator Switch-OFF

2.

Land As Soon As

Practical.

ALTERNATOR-OUT

PROCEDURE

I

An

inoperative alternator

will

place the

entire

electrical

operation

of the airplane

on

the

battery. Alternator

malfunction

will

be indicated

by

a

fluctuation

of the

ammeter

needle,

or

by a discharge

indication. If this

condition develops:

3-8

August, 1980

BEECHCRAFT

Sundowner 180 Section III

C23

(M-1285

and

After)

Emergency

Procedures

1. Alternator Switch-OFF

MOMENTARILY,

THEN

ON

(this

resets

overvoltage relay)

If

alternator-out

condition

persists:

2.

Alternator

Switch

-

OFF

3. Nonessential

Electrical Equipment

-

OFF to conserve

battery power.

WARNING

Deactivation

of the

battery switch,

alternator

switch,

or

alternator

circuit

breaker

during

flight

is

prohibited, except

as required by

an actual

emergency.

UNSCHEDULED

ELECTRIC STABILATOR

TRIM

1. Airplane

Attitude

-

MAINTAIN

using

stabilator control.

2. Stabilator

Trim

Thumb Switch

(On

Control Wheel)

-

MOVE

IN

DIRECTION OPPOSITE

UNSCHEDULED

PITCH

TRIM to open

circuit

breaker.

3. Stabilator Trim

ON-OFF

Switch (On

Instrument

Panel)

-

OFF

4. Manual

Stabilator

Trim Control Wheel

-

RETRIM AS

DESIRED.

EMERGENCY

STATIC

AIR

SOURCE

SYSTEM

THE EMERGENCY

STATIC

AIR

SOURCE

SHOULD BE

USED FOR

CONDITIONS

WHERE THE

NORMAL

STATIC

SOURCE HAS BEEN

OBSTRUCTED. When the

airplane

has

been

exposed to

moisture

anc‡/or

icing

conditions

(especially on the ground), the possibility

of

obstructed

static ports

should

be

considered.

Partial

obstructions

will

result

in the

rate

of

climb

indication

being sluggish during

a

climb

or descent. Verification

of suspected

obstruction

is

possible

by

switching to

the

emergency system and

noting

August, 1980

3-9

Section III

BEECHCRAFT

Sundowner

180

Emergency

Procedures

C23

(M-1285

and

After)

a sudden

sustained

change in

rate of

climb. This

may

be

accompanied

by abnormal indicated

airspeed and altitude

changes

beyond normal calibration

differences.

Whenever any

obstruction

exists

in

the Normal Static Air

System or

the

Emergency

Static Air

System is desired

for

use:

1. Pilot's Emergency

Static Air Source

-

Switch

to

ON

EMERGENCY.

2.

For Airspeed

Calibration

and Altimeter

Correction,

refer

to

PERFORMANCE section.

CAUTION

Be

certain the

emergency static air

valve is

in

the

NORMAL

position when

system

is not

needed.

UNLATCHED

DOOR IN

FLIGHT

if

the

cabin

door

is

not

locked

it may come

uniatched

in

flight.

This

may

occur

during

or

just

after

take-off.

The door

will trail

in a

position approximately

3

inches open.

A

buffet

may

be

encountered with

the

door

open in flight.

Return to the field in a

normal manner. If practicable,

during

the

landing

flare-out

have

a

passenger

hold

the

door to prevent

it

from swinging open.

SPINS

WARNING

Intentional

spins are prohibited when

operating

in the

Normal Category.

Intentional

spins are also

prohibited in

the Utility

Category

unless the airplane is

approved for

spins

and

equipped with

a

spin

kit, or

if

the

airplane

is

approved for operation

in

the

Acrobatic

Category.

Refer

to

Service

Instructions

No.

0619-090.

3-10

August,

1980

BEECHCRAFTSundowner180

Section III

C23

(M-1285

and

After)

Emergency

Procedures

The

airplane

will not spin

if

orthodox

entry

is

used, but will

enter

a

spiral

dive. Speed builds

rapidly

in

a spiral dive,

requiring

high

pullout

loads.

Therefore,

if a

spiral

is

inadvertently

entered

recovery

from

the spiral is

to be

initi-

ated within two turns.

ENTRY

Stall the airplane with

the control

column hard

back,throttle in

idle

position, flaps

up,

carburetor

heat

as

required and with

the nose

about

15°

above the horizon.

At the

stall, apply

full

rudder in the direction

required to

spin.

A

slight

rudder

application

immediately

before the

stall will assure the

direction of spin.

The airplane

nose

will

drop

and rotate towards the

applied

rudder. When

the

wings are

90°

to the

horizon,

apply

full aileron

against the

intended direction of

spin.

The

airplane

will

go slightly

inverted

and

enter

a

normal spin.

If

aileron against

the

direction of

spin is not

applied

or

applied

too

late,

the

airplane will

enter

a

rapid

spiral

dive,

and

recovery

must be

initiated

by

the

second turn.

If the

full

back stick is

not

applied and

held,

the

airplane

may

spiral. Again

recovery

must

be initiated

not

later

than

the

second

turn.

If aileron is

applied

too early,

the

airplane

will

not rotate

and merely

remain

in

a

straight

stalled

condition.

RECOVERY

Ifaspin is entered inadvertently:

Immediately

move the control column full

forward

and

simultaneously

apply full rudder

opposite

to the direction

of the

spin; continue

to

hold this

control position

until

rotation

stops

and

then neutralize

all

controls

and

execute

a smooth pullout.

Ailerons

should

be

neutral

and

throttle

in

idle

position at

all times during

recovery.

August,1980

3-11

Section III BEECH

CRAFT

Sundowner

180

Emergency

Procedures

C23

(M-1285

and After)

INTENTIONALLY

LEFT

BLANK

3-12

February

1979

BEECHCRAFTSundowner180

C23

(M-1285

and After)

SECTION IV

NORMAL

PROCEDURES

TABLE

OF

CONTENTS

SUBJECT

PAGE

Speeds

for

Safe

Operation................................................

4-3

Preflight Inspection ...........................................................

4-4

Before

Starting

..................................................................

4-5

External

Power

.................................................................

4-6

Starting

Engine

Using Auxiliary

Power

Unit.......................

4-7

Starting

.............................................................................

4-7

After

Starting,

And

Taxi.....................................................

4-8

Before

Takeoff..................................................................

4-8

Takeoff..............................................................................4-9

Climb..............................................................................4-10

Cruise.............................................................................

4-10

Leaning

Using

the Exhaust

Gas

Temperature

Indicator (EGT)............................................................

4-10

Descent

..........................................................................

4-11

Before

Landing

...............................................................

4-11

Balked Landing

...............................................................

4-12

After

Landing ..................................................................

4-12

Shutdown........................................................................

4-12

Environmental

Systems

..................................................

4-12

Heating

and Ventilation ...............................................

4-12

Cold Weather

Operation

.................................................

4-13

Preflight Inspection......................................................

4-13

Engine.........................................................................

4-13

Icing

Conditions..............................................................

4-14

Engine

Break-In

Information

...........................................

4-14

Noise

Characteristics......................................................

4-15

August, 1980

4-1

Section IV BEECH

CRAFT

Sundowner

180

Normal Procedures

C23(M-1285

and

After)

INTENTIONALLY LEFT

BLANK

4-2

February 1979

BEECHCRAFT

Sundowner 180 Section

IV

C23

(M-1285

and After)

Normal

Procedures

A//

airspeeds

quoted in this section are

indicated

airspeeds

(/AS)

SPEEDS FOR SAFE

OPERATION

Take-off

Lift-off

65

Knots/75 mph

50

Ft.

74 Knots/85 mph

Maximum

Climb

Best Rate

(Vy}

75 Knots/86

mph

Best

Angle

(v

)

69

Knots/79

mph

Cruise Climb

82 Knots/95

mph

Maximum Turbulent

Air

Penetration

118 Knots/136 mph

Balked

Landing

64

Knots/74

mph

Landing

Approach

68

Knots/78

mph

Maximum Demonstrated

Crosswind

17

Knots/20

mph

B19-604-10

February

1979

4-3

SectionlV BEECHCRAFTSundowner180

Normal Procedures

C23

(M-1285

and After)

PREFLIGHT INSPECTION

1. CABIN:
a.

Parking

Brake

-

SET

b.

Control Lock

-

REMOVE

c.

All Switches

-

OFF

d.

Fuel Drain Tool

(M-1971, M-1980

and

after)

- OB-

TAIN (See Section

VIII for

use) (See cabin door side

pocket. This tool can be used for opening the oil

and

fuel

filler

caps.)

2.

LEFT

WING

TRAILINGEDGE:

a. Flap

-

CHECK

b. Fuel Vent Line

-

UNOBSTRUCTED

c. Aileron

-

CHECK

d.

Wing

Tip-CHECK

e.

Position

Light-CHECK

3. LEFT WING LEADING EDGE:
a. Pitot

Tube

-

CHECK, (Remove

Cover)

b. Landing

Light-CHECK

c. Tie

Down

and Chocks

-

REMOVE

d.

Stall

Warning

-

CHECK for movement of vane

e.

Fuel Tank

-

CHECK

QUANTITY;

Filler

Cap

-

SECURE.

4. LEFT LANDING

GEAR:

a.

Tire

and Brake

-

CHECK

b.

Fuel

Sump

-

DRAIN

5. NOSE SECTION:
a. Left Cowl

-

SECURE

b. Induction Air Intake

-

CLEAR, Filter

-

CHECK for

condition and

security

of attachment.

c.

Propeller

-

CHECK,

General

Condition,

Nicks,

etc.

d.

Tire

and Nose Gear

-

CHECK

e. Engine Oil-CHECK

(See Servicing,

Section

8}Cap

and

Dipstick

-

SECURE

4-4

February

1979

BEECHCRAFT

Sundowner 180 Section IV

C23

(M-1285and

After)

Normal

Procedures

f. Right

Cowl-SECURE

g. Fuel Strainer

-

DRAIN

h.

Chocks

-

REMOVE

6.

R/GHT LAND/NG

GEAR:

a.

Fuel

Sump

-

DRAIN

b. Tire and Brake

-

CHECK

7. RIGHT

WING

LEADING

EDGE:

a.

Fuel Tank

-

CHECK

QUANTITY;

Filler

Cap

-

SECURE

b.

Tie

Down

and

Chocks

-

REMOVE

c.

Taxi Light

-

CHECK

d. Wing Tip

-

CHECK

e.

Position Light

-

CHECK

8.

R/GHT

WlNG TRA/L/NG

EDGE

a.

Aileron

-

CHECK

b. Flap

-

CHECK

c. Fuel Tank Vent

Line

-

UNOBSTRUCTED

9.

R/GHT FUSELAGE:

a. Static Pressure

Button

-

UNOBSTRUCTED

b.

Emergency Locator

Transmitter

-

ARMED

10. EMPENNAGE:

a. Control

Surfaces

-

CHECK

b.

Tie Down

-

REMOVE

c.

Position

Light-CHECK

11.

LEFT

FUSELAGE-

a.

Static Pressure Button

-

UNOBSTRUCTED

b. All Antennas

-

CHECK

c.

Baggage

Door

-

CHECK

BEFORE

STARTING

1.

Seats

-

POSITION

AND

LOCK;

Seat

Backs

-

UPRIGHT

2. Seat Belts

and Shoulder

Harnesses

-

FASTEN

August, 1980

4-5

Section

IV

BEECHCRAFT

Sundowner

180

Normal Procedures

C23

(M-1285

and

After)

3.

Parking Brake

-

SET

4.

All Avionics

-

OFF

5.

Circuit

Breakers

-

IN

6.

Flaps

-

UP

7.

Light

Switches

-

AS

REQUIRED

8. Electric Stabilator Trim

Switch

-

OFF

(if

installed)

9.

Battery

Switch

-

ON

10.

Alternator Switch-ON (If

external

power is

used,

turn

Alternator

Switch

-

OFF)

11. Fuel

Boost

Pump-ON

(Check for operation,

then

OFF)

12.

Fuel

Selector Valve

-

ROTATE thru

360°

and check

for

freedom of

movement;

set on tank

more

nearly

full

(feel

for detent

and

check

visually)

NOTE

On serials

M-2225

and after,

or

on

airplanes

which have

complied with

BEECHCRAFT S.I.

No.

1095, a

fuel selector

stop

has

been

added

to the

selector valve

guard. The fuel selector

stop

minimizes the

possibility

of inadvertently

turning

the fuel selector

valve to

the OFF

detent position. The

stop

is

a

spring which

must be depressed

before

the

selector

valve

handle

can be rotated to the

OFF

position.

WARNING

Do not

take off if

either fuel quantity gage

indicates in

yellow

arc.

EXTERNAL

POWER

The

following

precautions

shall

be

observed

while

using

external

power:

1.

The

Battery

Switch shall be ON

and all avionics

and

electrical switches OFF. This

protects the voltage

reg-

ulators

and associated

electrical equipment from

volt-

age transients

(power fluctuations):

4-6

August,

1980

BEECH

CRA

FT

Sundowner 180 Section IV

C23

(M-1285

and

After)

19ormal

Procedures

2. The airplane has

a

negative ground

system.

Connect

the

positive

and negative

leads of the

external

power

unit

to

the corresponding

positive and

negative

terminals of

the airplane's external

Dower

receptacle.

3. In order

to

prevent

arcing,

no

power

shall be

supplied

while

the connection

is

being made.

STARTING

ENGINE USING AUXILIARY

POWER

UNIT

1.

Alternator,

Electrical,

and Avionics Equipment

-

OFF

2.

Auxiliary

Power

Unit

-

CONNECT

3.

Auxiliary

Power

Unit

-

SET

OUTPUT

(*13.75

to

14.25

volts

for

14-volt

system

and

27.75

to 28.25

volts

for

28-volt

system)

4.

Auxiliary

Power

Unit-ON

5. Engine

-

START

using

normal procedures

6.

Auxiliary

Power Unit

-

OFF (after engine has been

started)

7.

Auxiliary Power

Unit

-

DISCONNECT

8. Alternator

Switch

-

ON

STARTING

CAUTION

Vernier-type

engine controls

should

not be

rotated clockwise after

being

advanced

to

the

full forward

position.

1.

Mixture

-

FULL

RICH

2.

Throttle

-

FAST IDLE

position

3. Fuel

Boost

Pump

-

ON

(cold

weather

starts,

use

eight

to ten

strokes

of

engine prime,

as required)

4.

Magneto/Start Switch

-

START

position

(release

to

BOTH

position when

engine

fires)

CAUTION

DO NOT

PUMP

THROTTLE

TO START

*NOTE

-

M-1285

thru

M-2178

are

14-volt

systems.

M-

2179

and

after

are

28-volt

systems.

August, 1980

4-7

Section

IV BEECHCRAFT Sundowner 180

Normal Procedures

C23

(M-1285

and After)

Flooded Engine:

a.

Mixture

-

IDLE

CUT-OFF

b.

Throttle

-

FULL OPEN

c. Starter

-

ENGAGE (retard throttle

to fast

idle

when

engine

fires)

d. Mixture

-

ADVANCE

TO

FULL

RICH

5.

Starter Engaged

Warning

Light (if installed)

EXTINGU1SHED

-

CHECK;

should

be

illuminated

during start,

and extinguished after start.

CAUTION

If the

STARTER ENGAGED

Waming Light is

inoperative

(or

not installed),

ensure that the

ammeter indication is less than 25% of full
charge

at

1000

to

1200 rpm

within two

minutes

with

no

additional electrical equipment on. If

not,

turn

off

the

Battery Switch

and Alternator

Switch and do

not

take

off.

6. External

Power

(if

used)

-

OFF

-

DISCONNECT

7.

ALT

(alternator) switch

-

ON

8.

Oil Pressure

-

ABOVE

RED

RADIAL

WITHIN 30

SECONDS

9.

Warm-up

-

1000 to

1200

RPM

10. All

Engine Indicators

-

CHECK

11.

Fuel

Boost Pump

-

OFF

(for

test

of

engine driven

pump)

12.

Parking Brakes

-

RELEASE

AFTEA

STARTING,

AND

BEFORE TAXI

1.

Lights

-

AS REQUIRED

2.

Avionics Equipment

-

ON, AS

REQUIRED

3. Brakes

-

RELEASE

AND CHECK

BEFORE

TAKEOFF

1.

Seat

Belts

and

Shoulder

Harnesses

-

CHECK

4-8

August,

1980

BEECHCRAFT Sundowner 180 Section

IV

C23

(M-1285

and After)

Normal

Procedures

NOTE

All reclining seats

must be

in

the upright

posi-

tion

during

take-off.

2.

Parking

Brake

-

SET

3. Avionics

-

CHECK

4. Engine instruments

-

CHECK

5. Flight Instruments

-

CHECK

AND

SET

6.

Starter Engaged

Warning

Light (if

installed)

-

CHECK

(should

not be

illuminated).

If

light

is

not installed or is

inoperative,

the

ammeter

indication

should

be

less

than 25% of full

charge

at 1000

to

1200 rpm and

should

show

some

decrease from

the

initial

indication.

7.

Throttle

-

2200

RPM

8.

Magnetos

-

CHECK at

2200

rpm, maximum

drop

of

125

rpm

on

each magneto,

variance

between

individual

magnetos

should

not exceed

50

rpm.

9.

Carburetor

Heat

-

CHECK (Set

cold

for

takeoff)

10.

Throule

-

FAST

IDLE

11.

Stabilator

Trim

-

TAKE-OFF

RANGE

(Green,

White

or

Black

Band)

12.

Flaps

-

CHECK

and

SET

13.

Controls

-

CHECK

FREE and for proper direction of

travel

14.

Fuel Boost

Pump

-

ON

15.

Mixture

-

FULL

RICH (or

as

required

by

field

elevation)

(tighten

friction on

push-pull

type control)

16.

Doors

and

Window

-

SECURE

17.

Parking

Brake

-

RELEASE

18.

Instruments

-

CHECK

(engine instruments in green

range

at the

start

of the takeoff

run)

TAKEOFF
Takeoff

..................... Full

Throttle

-

2700

RPM

1. Power

-

SET

takeoff power

and

mixture

before

brake

release.

August,

1980

4-9

Section IV BEECHCRAFT

Sundowner

180

Normal Procedures

C23

(M-1285

and

After)

2.

Airspeed

-

ACCELERATE

to

and

maintain takeoff

speed.

3.

Airspeed

-

ESTABLISH DESIRED CLIMB

SPEED when

clear of

obstacles.

CLIMB

NOTE

Do

not turn Fuel

Boost

Pump off

during climb.

1. Throttle

-

FULL

FORWARD

2.

Temperature

-

MONITOR

3.

Mixture

-

LEAN AS REQUIRED FOR SMOOTH

OPERATION

CRUISE

1.

Power

-

SET AS DESIRED

(Use

tables

in

PER-

FORMANCE

Section)

2. Fuel

Boost

Pump

-

OFF

3.

Mixture

-

LEAN AS REQUIRED

(tighten friction on

push-pull

type control)

LEANING

USING

THE

EXHAUST

GAS

TEMPERATURE

INDICATOR (EGT)

For level flight

at 75%

power

or less,

the EGT

unit

should

be

used in the

following manner:

1. Lean

the mixture

and note

the point

on the indicator

that the temperature peaks and

starts

to fall.

a.

CRUISE

(LEAN)

MIXTURE

-

Enrich

mixture until

the

EGT shows

a

drop of

25°F

below

peak on the

rich

side

of

peak.

b. BEST POWER

MIXTURE-Enrich mixture until the

EGT

shows a

drop

of

75°F

below

peak on the rich

side

of

peak.

CAUT/QN

Do not

continue

to

lean

mixture beyond that

necessary

to establish

peak temperature.

4-10

August,

1980

BEECHCRAFTSundowner180

SectionlV

C23

(M-1285

and

After)

Normal Procedures

2. Continuous

operation

is

recommended

at

25°F

or

more below

peak

EGT

only

on the rich side of peak.

3. Changes

in

altitude

and

power

settings require the

peak

EGT

to be

rechecked and the mixture

reset.

DESCENT

1. Altimeter

-

SET

2.

Carburetor Heat

-

FULL ON or FULL

OFF,

AS

REQUIRED

3. Power

-

AS

REQUIRED

(avoid

prolonged idle

settings

which

may cause

low

cylinder

head temperatures).

4.

Mixture-ENRICH

AS

REQUIRED

BEFORE

LANDING

1. Seat

Belts and

Shoulder

Harnesses

-

SECURE.

NOTE

All

reclining

seats must be

in the upright

position during

landing.

2. Fuel

Selector

Valve

-

SELECT

TANK MORE NEARLY

FULL

(feel

for detent

and check

visually).

3. Mixture

-

FULL RICH(or as required by

field

elevation)

(tighten

friction on

push-pull

type

control)

4. Landing Light-AS REQUIRED

5. Flaps

-

DOWN (maximum

extension

speed,

96 kts/110

mph)

NOTE

The Flaps

Up landing

procedure wi!I increase

the

Flaps

Down

landing

distances (total over

50 foot

obstacle)

by

50%.

6.

Airspeed

-

ESTABLISH LANDING

APPROACH

SPEED

Flaps Down

-

68 kts/78 mph

Flaps

Up

-

80 kts/92 mph

7. Carburetor Heat

-

AS REQUIRED

August, 1980

4-11

Section

IV

BEECHCRAFT Sundowner

180

Normal

Procedures

C23(M-1285

and

After)

NOTE

Carburetor heat should

be in the full COLD (IN)

position

before

full

throttle

application in the

event of

a

go-around.

8. Fuel Boost

Pump

-

ON

BALKED

LANDING

1.

Carburetor

Heat

-

COLD

2.

Power

-

FULL THROTTLE, 2700

RPM

3. Airspeed

-

64 kts/74

mph

until clear

of obstacles,

then

trim to BEST

RATE-OF-CLIMB

4. Flaps

-

UP

AFTER LANDING

1.

Landing and Taxi

Lights

-

AS

REQUIRED

2.

Flaps

-

UP

3. Trim Tab-SET

TO

0°

SHUTDOWN

1.

Brakes

-

SET

2.

Fuel

Boost

Pump

-

OFF

3.

Electrical

and Avionics Equipment

-

OFF

4.

Throttle

-

CLOSE

5.

Mixture

-

IDLE

CUT-OFF

6. Magneto/Start

Switch

-

OFF,

after engine stops

7.

Battery

Switch

-

OFF

8. Alternator Switch

-

OFF

9. Control

Lock

-

INSTALL,

if

conditions

warrant.

10.

Install

wheel chocks and release

brakes

if

the airplane

is to

be left

unattended.

ENVIRONMENTAL

SYSTEMS

HEATING

AND

VENTILATION

Refer to the SYSTEMS DESCRIPTION Section for

op-

eration

of

heating

and ventilation controls.

4-12

August,

1980

BEECHCRAFT Sundowner 180 Section IV

C23

(M-1285

and

After) Normal

Procedures

COLD

WEATHER

OPERATION

PREFLIGHT INSPECTION

AII accumulations

of

ice,

snow and

frost

must be

removed

from

the

wings,

tail,

control

surfaces

and hinges,

pro-

peller,

windshield,

pitot

tube,

static

ports,

antennas,

fuel

cell filler caps,

crankcase

vents,

and fuel

vents.

If

such

accumulations are

not removed

completely, the airplane

shall

not be

flown. The

deposits will not blow off in flight.

While

an adverse weight

factor is

clearly

involved

in the

case

of heavy deposits, it

is

less

obvious

that

even slight

accumulations will disturb

or completely

destroy

the

de-

signed

aerodynamic

properties

of the airfoils.

The normal preflight procedures

should then

be

com-

pleted, with

particular attention

given to

check of flight

controls for

complete

freedom of

movement.

ENGINE

Use

engine

oil in accordance with Consumable

Materials

in the

HANDLING,

SERVICING

AND MAINTENANCE

Section.

WARNING

Ascertain that magneto

switch

and

battery

master switch are off before

moving

propeller

by

hand.

Always

pull the propeller

through by hand,

opposite

the

direction of

rotation,

several

times to

clear the

engine and

"limber

up" the

cold,

heavy

oil

before

using

the

starter.

This will

also lessen the load

on the battery

if

external

power is not

used.

During

cold weather

starts,

use

8

to

10

strokes of engine

primer, as required.

February

1979

4-13

Section IV BEECHCRAFT Sundowner

180

Normal Procedures

C23(M-1285

and

After)

CAUTIO/V

Do not pump throttle

to

start.

Under very cold

conditions,

it

may

be

necessary to

preheat

the engine prior

to a start. Particular

attention should

be

given

to

the oil

cooler and engine

sump to

ensure

proper

preheat.

A start

with

congealed oil in the system

may

pro-

duce an indication of

normal pressure

immediately

after

the

start, but

then the

oil pressure may

decrease when

re-

sidual oil in the engine

is pumped back

with

the

con-

gealed oil

in the

sump. Ifan engine heater

capable of

heat-

ing both

the engine

sump and cooler is not

available,

the

oil should

be

drained while

the engine

is hot and stored in

a warm area until the next

flight.

If there is no

oil pressure within

the first

30

seconds of

running, or

if

oil

pressure

drops

after

a few minutes of

ground operation,

shut

down and check for broken

oil

lines,

oil cooler leaks

or the

possibility of congealed oil.

NOTE

It is advisable

to use external

power

for

start-

ing

in cold weather.

During

warm-up,

monitor

engine temperatures

closely,

since it

is quite possible

to exceed the cylinder

head

temperature

limit

in

trying to

bring

up the oil

temperature.

During

letdown

arid landing, give

special

attention to

en-

gine temperatures, since

the

engine

will

have a

tendency

toward overcooling.

ICING

CONDITIONS

Flight in Known

Icing

Conditions

Prohibited.

ENGINE

BREAK-IN

INFORMATION

See Systems Description

section

4-14

February

1979

BEECHCRAFT

Sundowner 180 Section IV

C23

(M-1285

and

After)

Normal Procedures

NOISE CHARACTERISTICS

Approach

to

and departure

from an

airport

should

be

made

so as to

avoid

prolonged

flight at

low altitude near

noise-

sensitive areas.

Avoidance

of

noise-sensitive

areas,

if

practical, is preferable

to overflightat relatively

low

altitudes.

For VFR

operations over outdoor assemblies of

persons,

recreational and

park areas,

and other

noise-sensitive

areas,

pilots

should

make

every

effort to fly

not less than

2000

feet above the

surface,

weather

permitting,

even

though

flight at a

lower level

may be

consistent with

the

provisions of government

regulations.

NOTE

The preceding recommended procedures

do

not

apply where

they

would conflict with

Air

Traffic Control clearances

or

instructions, or

where,

in

the pilot's judgement,an altitude of

less than

2000 feet is

necessary to

adequately

exercise his

duty

to

see and

evoidother

airplanes.

Flyover noise level established in

compliance

with

FAR

36

is:

73.3

dB(A)

No

determination has been made

by

the Federal

Aviation

Administration

that

the noise

level

of

this

airplane is or

should

be

acceptable or unacceptable

for operation at, into,

or

out

of any

airport.

Revised:

October

1979

4-15

BEECHCRAFT

Sundowner 180

C23

(M-1285

and After)

SECTION V

PERFORMANCE

TABLE OF

CONTENTS

SUBJECT

PAGE

Introduction

to

Performance

and

Flight

Planning

........................

.. .. .. ............................

5-3

Conditions

............................ ... ..

......................

5-3

Comments Pertinent

to

the

Use

of

Performance Graphs.....................................................

5-7

Airspeed Calibration

-

Normal System ..............................

5-8

Airspeed Calibration-Alternate

System ...........................

5-9

Altimeter Correction

-

Normal

System.............................

5-10

Altimeter Correction-Alternate

System..........................

5-11

Power

Off

Stall

Speeds....................... . ........................

5-12

Wind

Components ............................ .

.

.. .....................

5-13

Take-Off

Distance

-

Hard

Surface...................................

5-14

Take-Off

Distance

-

Grass

Surface .................................

5-15

Normal Climb..............................

. ...... . . ......................

5-16

Time,

Fuel,

and Distance to

Climb ..................................

5-17

Cruise Performance.......................... . . .. ....................

5-18

Landing

Distance

-

Hard Surface

....................................

5-20

Landing

Distance

-

Grass Surface

..................................

5-21

January,

1982

5-1

Section V

BEECHCRAFT

Sundowner

180

Performance

C23

(M-1285

and

After)

INTENTIONALLY LEFT

BLANK

5-2

February

1979

BEECHCRAFT Sundowner 180

Section V

C23

(M-1285

and

After)

Performance

INTRODUCTION TO

PERFORMANCE

AND

FLIGHT

PLANNING

The graphs andtables in

this

section

present performance

information for flight planning at various parameters of

weight, power,

altitude and

temperature. Examples have

been presented on some performance

charts. Calculations

for

flight time,

block

speed

and fuel required

for

a sample

VFR

trip

from Denver

to

Wichita are detailed beloW. All

examples and

calculations assume the

following

conditions:

CONDITIONS
At

Stapleton International

(DEN):

Outside Air

Temperature..................................15°C

(59°F)

Field

Elevation..........................................................5330

ft

Altimeter

Setting...............................................29.60 in.

Hg

Wind..............................................................

270°at

10 kts

Runway

26L

length................................................10,000 ft

i

Route

of Trip

*DEN-V4-GLD-V132-HUT-V73-ICT

For VFR

Cruise

at 9,500 feet

AVG MAG

WIND OAT

CRS/AVG 9500 9500 ALT

ROUTE

MAG DIST

FEET FEET

SETTING

SEGMENT VAR

NM DIR/KTS

°C

IN.HG

DEN-TXC

083°/12°E

80**

010/30

-5

29.60

TXC-GLD

093°/11°E

73

010/30

-5

29.60

GLD-HUT

105°/9°E

195 220/10 0 29.56

HUT-ICT

116°/8°E

33**

220/10

9

29.56

*REFERENCE:

Enroute

Low

Altitude

Chart

L-6

**Includes

distance between airport

and VORTAC.

January,

1982

5-3

Section

V

BEECHCRAFT

Sundowner 180

Performance C23

(M-1285

and

After)

At Wichita

Mid-Continent

(ICT):

Outside AirTemperature

..................................

25°C

(77°F)

FieId

Elevatio

n..........................................................

1332 ft

Altimeter

Setting ...............................................29.56

in. Hg

Wind..............................................................

180°at

10 kts

Runway

19L

Length

.................................................7300

ft

To

determine

pressure

altitude

at origin and destination

airports, add 100

feet to field

elevation

for each .1 in.

Hg

below

29.92 and

subtract

100 feet from

field elevation

for

each .1 in. Hg

above

29.92.

Pressure

Altitude

at DEI :

29.92

-

29.60

=

.32 in.

Hg

The

pressure altitude

at DEN is 320

feet above the

field

elevation.

5330

+

320

=

5650

ft

Pressure

Altitude

at

ICT:

29.92

-

29.56

=

.36

in. Hg

The pressure

altitude

at ICT is

360 feet

above

the field

elevation.

1332 +

360

=

1692

ft

NOTE

For

flight

planning, the

difference

between

cruise

altitude

and cruise

pressure

altitude

has

been ignored.

5-4

January,

1982

BEECHCRAFT Sundowner 180 Section

V

C23

(M-1285

and

After)

Performance

Enter

the

CRUISE

PERFORMANCE table

for

73

percent

maximum continuous

power

(or

full

throttle)

at 9500

feet:

THROTTLE

ALTITUDE

SETTING FUEL FLOW TAS

FEET RPM

GPH

KNOTS

9500

2662

10.5

123

I

Time and fuel

used

were calculated

as follows:

Time

=

Distance

Ground Speed

Fuel

Used

=

(Time) (Fuel

Flow)

Results are:

FUEL

EST TIME AT

USED

GROUND

CRUISE

FOR

ROUTE

DISTANCE

SPEED ALTITUDE

CRUISE

SEGMENT NM

KNOTS HRS: MIN

GAL

DEN-TXC

*65

117

:33 5.8

TXC-GLD

73 121 :36 6.3

GLD-HUT

195

125

1:34 16.4

HUT-ICT

33 124 :16 2.8

*Distance

required

to

climb has

been

subtracted

from

segment distance.

January, 1982

5-5

Section

V

BEECHCRAFT Sundowner

180

Performance

C23

(M-1285

and

After)

TIME

-

FUEL

-

DISTANCE

TIME FUEL

DISTANCE

ITEM HRS: MINS GAL

NM

Start, Runup,

Taxi and

Take-

off acceleration 0:00

1.3

0

Climb

0:11 2.0

15

I

Cruise

2:59 31.3

366

Total

3:10

34.6

381

Total

Flight Time:

3 hours, 10

minutes

Block

Speed: 381 NM

÷

3 hours, 10 minutes

=

120 knots

Reserve Fuel

(45

minutes

at

57%

maximum continuous

power)

Enter

the

CRUISE POWER

SETTINGS

table for 57%

MCP at 2300

RPM. The fuel

flow at

57% MCP is

7.8

gallons per hour.

Reserve fuel

=

(45 min)

(7.8

GPH)

=

5.9 gallons

|

Total Fuel

=

34.6 + 5.9

=

40.5

gallons

The estimated landing

weight is determined

by

subtracting

the

fuel required for

the

trip

from

the ramp

weight:

Assumed ramp

weight

=

2450 lbs

|

Estimated fuel from DEN

to

ICT

=

(34.6 gal)

(6

Ibs/gal)

=

208

ibs

Estimated

landing

weight

=

2450

-

208

=

2242 lbs

5-6

January,

1982