Cessna 1978 skyhawk 172n Owner's manual

PILOT'S

OPERATING

HANDBOOK

~

Cessna.

1978

Skyhawk

CESSNA MODEL 172N

PERFORMANCE-

SPECIFICATIONS

CESSNA

MODEL

172N

PERFORMANCE -SPECIFICATIONS

SPEED:

Maximum

at

Sea

Level

. . . . . . . . . . . . . . . 125

KNOTS

Cruise,

75%

Power

at

8000

Ft

. . . . . . . . . . . . 122

KNOTS

CRUISE:

Recommended

lean

mixture

with

fuel

allowance

for

engine

start,

taxi,

takeoff,

climb

and

45

minutes

reserve

at

45%

power.

75%

Power

at

8000

Ft

. .

40

Gallons

Usable

Fuel

75%

Power

at

8000

Ft

. . .

50

Gallons

Usable

Fuel

Maximum

Range

at

10,000

Ft

40

Gallons

Usable

Fuel

Maximum

Range

at

10,000

Ft

50

Gallons

Usable

Fuel

RA

TE

OF

CLIMB

AT

SEA

LEVEL

SERVICE

CEILING

. . . . . .

TAKEOFF

PERFORMANCE:

Ground

Roll

. . . . . . . . .

Total

Distance

Over

50-Ft

Obstacle

LANDING

PERFORMANCE:

Ground

Roll

. . . . . . . . . . .

Total

Distance

Over

50-Ft

Obstacle

ST

ALL

SPEED

(CAS):

Flaps

Up,

Power

Off

Flaps

Down,

Power

Off

. .

MAXIMUM

WEIGHT

. . . . .

STANDARD

EMPTY

WEIGHT:

Skyhawk

......

.

Skyhawk

II

.....

.

MAXIMUM

USEFUL

LOAD:

Skyhawk

......

.

Skyhawk

II

.....

.

BAGGAGE

ALLOWANCE

..

WING

LOADING:

Pounds/Sq

Ft

POWER

LOADING:

Pounds/HP

FUEL

CAPACITY:

Total

Standard

Tanks

Long

Range

Tanks

. .

OIL

CAP

A

CITY

. . . . .

ENGINE:

Avco

Lycoming

160

BHP

at

2700

RPM

PROPELLER:

Fixed

Pitch,

Diameter

.

Range

Time

.

Range

Time

.

Range

Time

.

Range

Time

485NM

4.1

HRS

630NM

5.3

HRS

575NM

5.7

HRS

750NM

7.4

HRS

. 770

FPM

. 14,200

FT

805FT

1440

FT

520FT

1250

FT

50

KNOTS

44

KNOTS

2300

LBS

1393

LBS

1419

LBS

907

LBS

881

LBS

120

LBS

13.2

14.4

43 GAL.

54 GAL.

6QTS

0-320-H2AD

75

IN.

PILOT'S

OPERATING

HANDBOOK

~

Cessna.

SKY!HAWK

\_

1978 MODEL 172N

Serial No

..

_________

_

Registration

No

..

______

_

THIS

HANDBOOK

INCLUDES

THE

MATERIAL

REQUIRED

TO

BE

FURNISHED

TO

THE

PILOT

BY

CAR

PART

3

DJ 109-1-13

1977

CESSNA

AIRCRAFT

COMPANY

WICHITA,

KANSAS,

USA

Change 1

CONGRATULATIONS

CESSNA

MODEL

172N

••••

Welcome

to

the

ranks of Cessna owners! Your Cessna has

been

designed and

constructed

to give you

the

most

in

performance,

economy,

and

comfort. lt

is

our

desire that

you will find flying it,

either

for business

or

pleasure, a pleasant

and

profitable eKperience.

This Pilot's

Operating

Handbook has

been

prepared

as

a

guide

to

help you getthemost

pleasure

and

utility from your airplane.

It

contains information

about

your Cessna's

equipment,

operating

procedures,

and

performance;

and

suggestions for its servicing

and

care.

We

urge you

to

read

it

from

cover

to cover,

and

to

refer

to

it

frequently.

Our

interest

in

your flying pleasure has not

ceased

with your purchase of a Cessna.

World-wide,

the

Cessna Dealer Organization backed by

the

Cessna Customer Services

Department stands ready

to

serve you. The following services

are

offered

by most Cessna

Dealers:

•

THE

CESSNA

WARRANTY,

which providescoveragefor parts

and

labor,

is

availableat

Cessna Dealers worldwide. Specific benefits

and

provisions of warranty, plus

other

important benefits for you, are

contained

in

your

Customer Care Program book,

supplied with yourairplane. Warranty service

is

available

to

you

at

authorized

Cessna

Dealers

throughout

the

world

upon

presentation

of

yourCustomerCareCardwhich

establishes your eligibility

under

the

warranty.

•

FACTORY

TRAINED

PERSONNEL

to

provide you with

courteous

expert service.

e

FACTORY

APPROVED

SERVICE

EQUIPMENT

to

provide you efficient

and

accurate

workmanship.

e A

STOCK

OF

GENUINE

CESSNA

SERVICE

PARTS

on

hand

when

you

need

them.

e

THE

LATEST

AUTHORITATIVE

INFORMATION

FOR

SERVICING

CESSNA

AIR-

PLANES,

since Cessna Dealers have

all

of

the

Service Manuals

and

Parts Catalogs, kept

current

by Service Letters

and

Service News Letters, published by Cessna Aircraft

Company.

We urge all Cessna owners

to

use

the

Cessna Dealer Organization

to

the

fullest.

A

current

Cessna Dealer Directory accompanies your new airplane. The Directory

is

revised frequently,

and

a

current

copycan

be

obtained

from your Cessna Dealer.

Make

your

Category

907

lbs.

881

lbs.

CABIN

AND

ENTRY

DIMENSIONS

Utility

Category

607

lbs.

581

lbs.

Detailed

dimensions

of

the

cabin

interior

and

entry

door

openings

are

illustrated

in

Section

6.

BAGGAGE SPACE

AND

ENTRY

DIMENSIONS

Dimensions

of

the

baggage

area

and

baggage

door

opening

are

illustrated

in

detail

in

Section

6.

SPECIFIC

LOADINGS

Wing

Loading:

13.2

lbs./

sq.

ft.

Power

Loading:

14.4

lbs./hp.

1-5

SECTION

1

GENERAL

CESSNA

cESSNA

MODEL

172N MODEL 172N

SYMBOLS,

ABBREVIATIONS

AND

TERMINOLOGY

GENERAL AIRSPEED

TERMINOLOGY

AND

SYMBOLS

KCAS

KIAS

Knots

Calibrated

Airspeed

is

indicated

airspeed

corrected

for

position

and

instrument

error

and

expressed

in

knots.

Knots

calibrated

airspeed

is

equal

to

KTAS

in

standard

atmosphere

at

sea

level.

Knots

Indicated

Airspeed

i.s

the

speed

shown

on

the

airspeed

indicator

and

expressed

in

knots.

Standard

Tempera-

ture

Pressure

Altitude

SECTION

1

GENERAL

It

is

expressed

in

either

degrees

Celsius

(formerly

Centi-

grade)

or

degrees

Fahrenheit.

Standard

Temperature

is

15°C

at

sea

level

pressure

alti-

tude

and

decreases

by

2°C

for

each

1000

feet

of

altitude.

Pressure

Altitude

is

the

altitude

read

from

an

altimeter

when

the

altimeter's

barometric

scale

has

been

set

to

29.92

inches

of

mercury

(1013 mb).

KTAS

Knots

True

Airspeed

is

the

airspeed

expressed

in

knots

relative

to

undisturbed

air

which

is

KCAS

corrected

for

altitude

and

temperature.

ENGINE POWER TERMINOLOGY

VNE

BHP

RPM

Manuevering

Speed

is

the

maximum

speed

at

which

you

may

use

abrupt

control

travel.

Static

Maximum

Flap

Extended

Speed

is

the

highest

speed

RPM

permissible

with

wing

flaps

in

a

prescribed

extended

position.

Brake

Horsepower

is

the

power

developed

by

the

engine.

Revolutions

Per

Minute

is

engine

speed.

Static

RPM

is

engine

speed

attained

during

a

full-throttle

engine

runup

when

the

airplane

is

on

the

ground

and

stationary.

Maximum

Structural

Cruising

Speed

is

the

speed

that

should

not

be

exceeded

except

in

smooth

air,

then

only

with

caution.

AIRPLANE PERFORMANCE

AND

FLIGHT

PLANNING

TERMINOLOGY

Never

Exceed

Speed

is

the

speed

limit

that

may

not

be

exceeded

at

any

time.

Stalling

Speed

or

the

minimum

steady

flight

speed

at

which

the

airplane

is

controllable.

Stalling

Speed

or

the

minimum

steady

flight

speed

at

which

the

airplane

is

controllable

in

the

landing

configu-

ration

at

the

most

forward

center

of

gravity.

Best

Angle-of-Climb

Speed

is

the

speed

which

results

in

the

greatest

gain

of

altitude

in

a

given

horizontal

distance.

Best

Rate-of-Climb

Speed

is

the

speed

which

results

in

the

greatest

gain

in

altitude

in

a

given

time.

Demon-

strated

Crosswind

Velocity

Usable

Fuel

Unusable

Fuel

GPH

NMPG

Demonstrated

Crosswind

Velocity

is

the

velocity

of

the

crosswind

component

for

which

adequate

control

of

the

airplane

during

takeoff

and

landing

was

actually

demon-

strated

during

certification

tests.

The

value

shown

is

not

considered

to

be

limiting.

Usable

Fuel

is

the

fuel

available

for

flight

planning.

Unusable

Fuel

is

the

quantity

of

fuel

that

can

not

be

safely

used

in

flight.

Gallons

Per

Hour

is

the

amount

of

fuel

(in

gallons)

consumed

per

hour.

METEOROLOGICAL

TERMINOLOGY

Nautical

Miles

Per

Gallon

is

the

distance

(in

nautical

miles)

which

can

be

expected

per

gallon

of

fuel

consumed

at

a

specific

engine

power

setting

and/

or

flight

configura-

tion.

OAT

Outside

Air

Temperature

is

the

free

air

static

temperature.

g g

is

acceleration

due

to

gravity.

1-6

SECTION

1

GENERAL

CESSNA

MODEL

172N l\10DEL 172N

WEIGHT

AND

BALANCE

TERMINOLOGY

M:aximum

Landing

Weight

Reference

Datum

Station

Arm

Moment

Center

of

Gravity

(C.G.)

C.G.

Arm

C.G.

Limits

Standard

Empty

Weight

Basic

Empty

Weight

Useful

Load

Gross

(Loaded)

Weight

Maximum

Takeoff

Weight

1-8

Reference

Datum

is

an

imaginary

vertical

plane

from

which

all

horizontal

distances

are

measured

for

balance

purposes.

Tare

Station

is

a

location

along

the

airplane

fuselage

given

in

terms

of

the

distance

from

the

reference

datum.

Arm

is

the

horizontal

distance

from

the

reference

datum

to

the

center

of

gravity

(C.G.)

of

an

item.

Moment

is

the

product

of

the

weight

of

an

item

multiplied

by

its

arm.

(Moment

divided

by

the

constant

1000isusedin

this

handbook

to

simplify

balance

calculations

by

reduc-

ing

the

number

of

digits.)

Center

of

Gravity

is

the

point

at

which

an

airplane,

or

equipment,

would

balance

if

suspended.

Its

distance

from

the

reference

datum

is

found

by

dividing

the

total

moment

by

the

total

weight

of

the

airplane.

Center

of

Gravity

Arm

is

the

arm

obtained

by

adding

the

airplane's

individual

moments

and

dividing

the

sum

by

the

total

weight.

Center

of

Gravity

Limits

are

the

extreme

center

of

gravity

locations

within

which

the

airplane

must

be

op.erated

at

a

given

weight.

Standard

Empty

Weight

is

the

weight

of

a

standard

air-

plane,

including

unusable

fuel,

full

operating

fluids

and

full

engine

oil.

Basic

Empty

Weight

is

the

standard

empty

weight

plus

the

weight

of

optional

equipment.

Useful

Load

is

the

difference

between

takeoff

weight

and

the

basic

empty

weight.

Gross

(Loaded)

Weight

is

the

loaded

weight

of

the

airplane.

Maximum

Takeoff

Weight

is

the

maximum

weight

ap-

proved

for

the

start

of

the

takeoff

run.

SECTION

1

GENERAL

Maximum

Landing

Weight

is

the

maximum

weight

ap-

proved

for

the

landing

touchdown.

Tare

is

the

weight

of

chocks,

blocks,

stands,

etc.

used

when

weighing

an

airplane,

and

is

included

in

the

scale

read-

ings.

Tare

is

deducted

from

the

scale

reading

to

obtain

the

actual

(net)

airplane

weight.

1-9/(1-10

blank)

CESSNA

MODEL 172N

SECTION 2

LIMITATIONS

TABLE OF CONTENTS

Introduction

. . . . . . . .

Airspeed

Limitations

Airspeed

Indicator

Markings

Power

Plant

Limitations

Power

Plant

Instrument

Markings

Weight

Limits

. . . . .

Normal

Category

. .

Utility

Category

Center

Of

Gravity

Limits

Normal

Category

Utility

Category

Maneuver

Limits

Normal

Category

Utility

Category

Flight

Load

Factor

Limits

Normal

Category

...

Utility

Category

Kinds

Of

Operation

Limits

Fuel

Limitations

Placards

.......

.

SECTION

2

LIMITATIONS

Page

2-3

2-4

2-5

2-6

2-7

2-8

2-9

2-10

2-1/(2-2

blank)

CESSNA

MODEL 172N

SECTION

2

LIMITATIONS

INTRODUCTION

Section

2

includes

operating

limitations,

instrument

markings,

and

basic

placards

necessary

for

the

safe

operation

of

the

airplane,

its

engine,

standard

systems

and

standard

equipment.

The

limitations

included

in

this

section

have

been

approved

by

the

Federal

Aviation

Administration.

When

applicable,

limitations

associated

with

optional

systems

or

equip-

ment

are

included

in

Section

9.

NOTE

The

airspeeds

listed

in

the

Airspeed

Limitations

chart

(figure

2-1)

and

the

Airspeed

Indicator

Markings

chart

(figure

2-2)

are

based

on

Airspeed

Calibration

data

shown

in

Section

5

with

the

normal

static

source.

If

the

alternate

static

source

is

being

used,

ample

margins

should

be

observed

to

allow

for

the

airspeed

calibration

variations

between

the

normal

and

alternate

static

sources

as

shown

in

Section

5.

Your

Cessna

is

certificated

under

FAA

Type

Certificate

No. 3A12

as

Cessna

Model

No. 172N.

2-3

SECTION

2

LIMITATIONS

AIRSPEED LIMITATIONS

CESSNA

MODEL

172N

Airspeed

limitations

and

their

operational

significance

are

shown

in

figure

2-1.

Maneuvering

speeds

shown

apply

to

normal

CATEGORY

Maximum

Takeoff

Weight:

2300

lbs.

Maximum

Landing

Weight:

2300

lbs.

Maximum

Weight

in

Baggage

Compartment:

RED LINE

MAXIMUM

LIMIT

2700

RPM

245°F

100

psi

---

Baggage

Area

1

(or

passenger

on

child's

seat)

-

Station

82

to

108: 120

lbs.

See

note

below.

2-6

Baggage

Area

2 -

Station

108

to

142: 50

lbs.

See

note

below.

NOTE

The

maximum

combined

weight

capacity

for

baggage

areas

1

and

2

is

120

lbs.

UTILITY

CATEGORY

Maximum

Takeoff

Weight:

2000

lbs.

Maximum

Landing

Weight:

2000

lbs.

Maximum

Weight

in

Baggage

Compartment:

In

the

utility

category,

the

baggage

compartment

and

rear

seat

must

be

not

occupied.

CENTER OF

GRAVITY

LIMITS

NORMAL

CATEGORY

Center

of

Gravity

Range:

Forward:

35.0

inches

aft

of

datum

at

1950

lbs.

or

less,

with

straight

line

variation

to

38.5

inches

aft

of

datum

at

2300

lbs.

Aft: 47.3

inches

aft

of

datum

at

all

weights.

Reference

Datum:

Lower

portion

of

front

face

of

firewall.

UTILITY

CATEGORY

Center

of

Gravity

Range:

Forward:

35.0

inches

aft

of

datum

at

1950

lbs.

or

less,

with

straight

line

variation

to

35.5

inches

aft

of

datum

at

2000

lbs.

Aft:

40.5

inches

aft

of

datum

at

all

weights.

Reference

Datum:

Lower

portion

of

front

face

of

firewall.

MANEUVER

LIMITS

NORMAL

CATEGORY

This

airplane

is

certificated

in

both

the

normal

and

utility

category.

The

normal

CATEGORY

Flight

Load

Factors

(Gross

Weight

-2300

lbs.):

*Flaps

Up

. . . +3.8g, -1.52g

*Flaps

Down

. . . . . . . . . . . . . . . . . +3.0g

KINDS OF OPERATION LIMITS

The

airplane

is

equipped

for

day

VFR

and

may

be

equipped

for

night

VFR

and/

or

IFR

operations.

FAR

Part

91

establishes

the

minimum

required

instrumentation

and

equipment

for

these

operations.

The

refer-

ence

to

types

of

flight

operations

on

the

operating

limitations

placard

reflects

equipment

installed

at

the

time

of

Airworthiness

Certificate

issuance.

Flight

into

known

icing

conditions

is

prohibited.

FUEL

LIMITATIONS

2

Standard

Tanks:

21.5

U.S.

gallons

each.

Total

Fuel:

43

U.S.

gallons.

Usable

Fuel

(all

flight

conditions):

40

U.S.

gallons.

Unusable

Fuel:

3

U.S.

gallons.

2

Long

Range

Tanks:

27

U.S.

gallons

each.

Total

Fuel:

54

U.S.

gallons.

Usable

Fuel

(all

flight

conditions):

50

U.S.

gallons.

Unusable

Fuel:

4

U.S.

gallons.

NOTE

To

ensure

maximum

fuel

capacity

when

refueling,

place

the

fuel

selector

valve

in

either

LEFT

or

RIG

HT

position

to

prevent

cross-feeding.

NOTE

Takeoff

and

land

with

the

fuel

selector

valve

handle

in

the

BOTH

position.

Approved

Fuel

Grades

(and

Colors):

*The

design

load

factors

are

150%

of

the

above,

and

in

all

cases,

the

100LL

Grade

Aviation

Fuel

(Blue).

structure

meets

or

exceeds

design

loads.

100

(Formerly

100/130)

Grade

Aviation

Fuel

(Green).

UTILITY CATEGORY

Flight

Load

Factors

(Gross

Weight

-

2000lbs.):

2-8

*Flaps

Up

. . . +4.4g,

-1.76g

*Flaps

Down

. . . . . . . . . . . . . . . . . +3.0g

*The

design

load

factors

are

150%

of

the

above,

and

in

all

cases,

the

structure

meets

or

exceeds

design

loads.

2-9

SECTION

2

LIMITATIONS

CESSNA

MODEL

1721'1

MODEL 172N

SECTION2

LIMITATIONS

PLACARDS

2.

Forward

of

fuel

selector

valve:

The

following

information

is

displayed

in

the

form

of

composite

ai

individual

placards.

[

___________________________

__.

BOTH

TANKS

ON

FOR

1.

In

full

view

of

the

pilot:

(The

"DA

Y-NIGHT-VFR-IFR"

entry,

TAKEOFF

&

LANDING

shown

on

the

example

below,

will

vary

as

the

airplane

ill

equipped.)

This

airplane

must

be

operated

in

compliance

with

the

operating

limitations

as

stated

in

the

form

of

placards,

markings,

and

manuals.

--------MAXIMUMS--------

Normal

Category

MANEUVERING

SPEED

(IAS)

97

knots

.

GROSS

WEIGHT

. . . . . . 2300

lbs.

.

Utility

Category

97

knots

2000

lbs.

FLIGHT

LOAD

FACTOR

Flaps

Up

+3.8, -1.52

Flaps

Down

+3.0 . . . +4.4, -1.76

+3.0

Normal

Category

-

No

Acrobatic

maneuvers

including

spins

approved.

Utility

Category

-

Baggage

compartment

and

rear

seat

must

not

be

occupied.

--NO

ACROBATIC

MANEUVERS

APPROVED--

EXCEPT

THOSE

LISTED

BELOW

Maneuver

Chandelles

Lazy

Eights

Steep

Tums

Reem.

Entry

Speed

. . . . 105

knots

. . . . 105

knots

. . . . 95

knots

Maneuver

Reem.

Entry

Speed

!§pins

. . .

Slow

Deceleration

Stalls

(except

whip

stalls)

Slow

Deceleration

Altitude

loss

in

stall

recovery

-- 180 feet.

Abrupt

use

of

the

controls

prohibited

above

97

knots.

Spin

Recovery:

opposite

rudder

-

forward

elevator

neutralize

controls.

Intentional

spins

with

flaps

extended

are

prohibited.

Flight

into

known

icing

conditions

prohibited.

This

airplane

is

certified

for

the

following

flight

operations

as

of

date

of

original

airworthiness

certificate:

DAY

-

NIGHT

-

VFR

-

IFR

2-10

3.

On

the

fuel

selector

valve

(standard

tanks):

BOTH

-40

GAL.

ALL

FLIGHT

ATTITUDES

LEFT-

20

GAL.

LEVEL

FLIGHT

ONLY

RIGHT

-20

GAL.

LEVEL

FLIGHT

ONLY

OFF

On

the

fuel

selector

valve

(long

range

tanks):

BOTH

-50

GAL.

ALL

FLIGHT

ATTITUDES

LEFT

-25

GAL.

LEVEL

FLIGHT

ONLY

RIGHT

-25

GAL.

LEVEL

FLIGHT

ONLY

OFF

4.

Near

fuel

tank

filler

cap

(standard

tanks):

FUEL

100LL/

100

MIN.

GRADE

AVIATION

GASOLINE

CAP.

21.5 U.S.

GAL.

Near

fuel

tank

filler

cap

(long

range

tanks):

FUEL

100LL/

100

MIN.

GRADE

AVIATION

GASOLINE

CAP.

27 U.S.

GAL.

2-11

SECTION

2

LIMITATIONS

CESSN,

gSSNA

MODEL

172}

~oDEL

172N

SECTION

3

EMERGENCY

PROCEDURES

5.

Near

flap

indicator:

SECTION 3

L----A_v_m_v

s_L1-Ps_w_1T_H-FL-AP_s_Ex-TE-N-DE-D---~

EMERGENCY

PR

QC

ED

LJ

RES

2-12

6.

In

baggage

compartment:

120

POUNDS

MAXIMUM

BAGGAGE

AND/OR

AUXILIARY

PASSENGER

FORWARD

OF

BAGGAGE

DOOR

LATCH

50

POUNDS

MAXIMUM

BAGGAGE

AFT

OF

BAGGAGE

DOOR

LATCH

MAXIMUM 120

POUNDS

COMBINED

FOR

ADDITIONAL

LOADING

INSTRUCTIONS

SEE

WEIGHT

AND

BALANCE

DATA

TABLE

OF CONTENTS

Introduction

. . . . . · · · · · · · · · · · · · ·

Airspeeds

For

Emergency

Operation

. . . . . . .

OPERATIONAL

CHECKLISTS

Engine

Failures

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

.

Engine

Failure

During

Takeoff

Run

Engine

Failure

Immediately

After

Takeoff

Engine

Failure

During

Flight

.....

.

Forced

Landings

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

Emergency

Landing

Without

Engine

Power

Precautionary

Landing

With

Engine

Power

Ditching

.......

.

Fires

..........

.

During

Start

On

Ground

Engine

Fire

In

Flight

..

Electrical

Fire

In

Flight

Cabin

Fire

......

.

Wing

Fire

......

.

Icing

..........

.

Inadvertent

Icing

Encounter

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

Static

Source

Blockage

(Erroneous

Instrument

Reading

Suspected)

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

·

Landing

With

A

Flat

Ma.in

Tire

. . . . . . .

Electrical

Power

Supply

System

Malfunctions

Over-Voltage

Light

Illuminates

.....

Ammeter

Shows

Discharge

. . . . . . .

AMPLIFIED

PROCEDURES

Engine

Failure

. . . . . . . ·

Forced

Landings

. . . . . . · ·

Landing

Without

Elevator

Control

Fires

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

.

Page

.

3-3

.

3-3

3-4

3-5

3-6

3-7

3-8

3-9

3-11

3-12

3-1

SECTION

3

EMERGENCY

PROCEDURES

CESSN,

CESSNA

MODEL

172)

?vfODEL

172N

SECTION

3

EMERGENCY

PROCEDURES

TABLE OF

CONTENTS

(Continued)

Emergency

Operation

In

Clouds

(Vacuum

System

Failure)

Executing

A 180°

Turn

In

Clouds

. . . . . . . . . .

Emergency

Descent

Through

Clouds

Recovery

From

A

Spiral

Dive

Flight

In

Icing

Conditions

. . . . . .

Static

Source

Blocked

. . . . . .

Spins

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

.

Rough

Engine

Operation

Or

Loss

Of

Power

Carburetor

Icing

. .

Spark

Plug

Fouling

. . . . . . . . .

Magneto

Malfunction

. . . . . . . . .

Low

Oil

Pressure

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

Electrical

Power

Supply

System

Malfunctions

Excessive

Rate

Of

Charge

......

.

Insufficient

Rate

Of

Charge

. . . . . . .

3-2

Pag

3-1

3-t

3-1

3-1·

3-11

INTRODUCTION

Section

3

provides

checklist

and

amplified

procedures

for

coping

with

e:rnergencies

that

may

occur.

Emergencies

caused

by

airplane

or

engine

malfunctions

are

extremely

rare

if

proper

preflight.

inspection~

~nd

:maintenance

are

practiced.

Enroute

weather

emergencies

can

be

mm1m-

ized

or

eliminated

by

careful

flight

planning

and

good

judgment

when

unexpected

weather

is

encountered.

However,

should

an

emergency

arise,

the

basic

guidelines

described

in

this

section

should

be

considered

and

applied

as

necessary

to

correct

the

problem.

Emergency.

proce~ures

associated

with

ELT

and

other

optional

systems

can

be

found

m

Section

9.

3-1

1

3-1;

AIRSPEEDS FOR

EMERGENCY

OPERATION

3-1'

Engine

Failure

After

Takeoff:

Wing

Flaps

Up

. .

Wing

Flaps

Down

Maneuvering

Speed:

2300

Lbs

..

1950

Lbs

..

1600

Lbs

....

Maximum

Glide:

2300

Lbs

....

Precautionary

Landing

With

Engine

Power

Landing

Without

Engine

Power:

Wing

Flaps

Up

. .

Wing

Flaps

Down

. . . .

OPERATIONAL CHECKLISTS

ENGINE FAILURES

ENGINE FAILURE

DURING

TAKEOFF

RUN

1.

Throttle

--

IDLE.

2.

Brakes

--

APPLY.

3.

Wing

Flaps

--

RETRACT.

4.

Mixture

--

IDLE

CUT-OFF.

5.

Ignition

Switch

--

OFF.

6.

Master

Switch

--

OFF.

65

KIAS

60

KIAS

97

KIAS

89

KIAS

80

KIAS

65

KIAS

60

KIAS

65

KIAS

60

KIAS

3-3

SECTION

3

EMERGENCY

PROCEDURES

CESSNJ

ESSNA

MODEL

172~

~ODEL

172N

SECTION

3

EMERGENCY

PROCEDURES

ENGINE

FAILURE

IMMEDIATELY

AFTER TAKEOFF

1.

Airspeed

--

65

KIAS

(flaps

UP).

60

KIAS

(flaps

DOWN).

2.

Mixture

--

IDLE

CUT-OFF.

3.

Fuel

Selector

Valve

--

OFF.

4.

Ignition

Switch

--

OFF.

5.

Wing

Flaps

--

AS

REQUIRED.

6.

Master

Switch

--

OFF.

ENGINE

FAILURE

DURING

FLIGHT

1.

Airspeed

-- 65

KIAS.

2.

Carburetor

Heat

--

ON.

3.

Fuel

Selector

Valve

--

BOTH.

4.

Mixture

--

RICH.

5.

Ignition

Switch

--

.BOTH

(or

START

if

propeller

is

stopped).

6.

Primer

--

IN

and

LOCKED.

FORCED

LANDINGS

EMERGENCY

LANDING

WITHOUT

ENGINE

POWER

1.

Airspeed

-- 65

KIAS

(flaps

UP).

60

KIAS

(flaps

DOWN).

2.

Mixture

--

IDLE

CUT-OFF.

3.

Fuel

Selector

Valve

--

OFF.

4.

Ignition

Switch

--

OFF.

5.

Wing

Flaps

--

AS

REQUIRED

(40°

recommended).

6.

Master

Switch

--

OFF.

7.

Doors

--

UNLATCH

PRIOR

TO

TOUCHDOWN.

8.

Touchdown

--

SLIGHTLY

TAIL

LOW.

9.

Brakes

--

APPLY

HEAVILY.

PRECAUTIONARY

LANDING

WITH

ENGINE

POWER

1.

Wing

Flaps

--

20°.

2.

Airspeed

--

60

KIAS.

3.

Selected

Field

--

FLY

OVER,

noting

terrain

and

obstructions,

then

retract

flaps

upon

reaching

a

safe

altitude

and

airspeed.

4.

Avionics

Power

Switch

and

Electrical

Switches

--

OFF.

5.

Wing

Flaps

--

40°

(on

final

approach).

6.

Airspeed

--

60

KIAS.

7.

Master

Switch

--

OFF.

8.

Doors

--

UNLATCH

PRIOR

TO

TOUCHDOWN.

3-4

9.

Touchdown

--

SLIGHTLY

TAIL

LOW.

10.

Ignition

Switch

--

OFF.

1~.

Brakes

--

APPLY

HEAVILY.

DITCHING

1.

Radio

--

TRANSMIT

MAYDAY

on

121.5

MHz,

giving

location

and

intentions.

2.

Heavy

Objects

(in

baggage

area)

--

SECURE

OR

JETTISON.

3.

Approach

--

High

Winds,

Heavy

Seas

--

INTO

THE

WIND.

Light

Winds,

Heavy

Swells

--

PARALLEL

TO

SWELLS.

4.

Wing

Flaps

-- 20° -40°.

5.

Power

--

ESTABLISH

300

FT/MIN

DESCENT

AT

55

KIAS.

NOTE

If

no

power

is

available,

approach

at65

KIAS

with

flaps

up

or

at

60

KIAS

with

10° fJ 1.ps.

6.

Cabin

Doors

--

UNLATCH.

7.

Touchdown

--

LEVEL

ATTITUDE

AT

ESTABLISHED

RATE

OF

DESCENT.

8.

Face

--

CUSHION

at

touchdown

with

folded

coat.

9.

Airplane

--

EVACUATE

through

cabin

doors.

If

necessary,

open

window

and

flood

cabin

to

equalize

pressure

so

doors

can

be

opened.

10.

Life

Vests

and

Raft

--

INFLATE.

FIRES

DURING

START

ON

UROUND

1.

Cranking

--

CONTINUE,

to

get

a

start

which

would

suck

the

flames

and

accumulated

fuel

through

the

carburetor

and

into

the

engine.

If

engine

starts:

2.

Power

-- 1700

RPM

for

a

few

minutes.

3.

Engine

--

SHUTDOWN

and

inspect

for

damage.

If

engine

fails

to

st'Lrt:

4.

Throttle

--

FULL

OPEN.

5.

Mixture

--

IDLE

CUT-OFF.

3-5

SECTION

3

CESSN,

CESSNA

MODEL

1721

:MODEL

172N

SECTION

3

EMERGENCY

PROCEDURES

EMERGENCY

PROCEDURES

6.

7.

8.

9.

10.

Cranking

--

CONTINUE.

Fire

Extinguisher--

OBTAIN

(have

ground

attendants

obtain

ifn\

installed).

Engine

--

SECURE.

a.

Master

Switch

--

OFF.

b.

Ignition

Switch

--

OFF.

c.

Fuel

Selector

Valve

--

OFF.

Fire

--

EXTINGUISH

using

fire

extinguisher,

wool

blanket,

or

dir

Fire

Damage

--

INSPECT,

repair

damage

or

replace

damage

components

or

wiring

before

conducting

another

flight.

11.

Vents/Cabin

Air/Heat

--

OPEN

when

it

is

ascertained

that

fire

is

completely

extinguished.

CABIN FIRE

1.

Master

Switch

--

OFF.

2.

Vents/Cabin

Air/Heat

--

CLOSED

(to

avoid

drafts).

3.

Fire

Extinguisher

--

ACTIVATE

(if

available).

I

WARNING

I

ENGINE

FIRE IN FLIGHT

1.

2.

3.

4.

5.

6.

Mixture

--

IDLE

CUT-OFF.

Fuel

Selector

Valve

--

OFF.

Master

Switch

--

OFF.

4.

Cabin

Heat

and

Air

--

OFF

(except

overhead

vents).

Airspeed

--

100

KIAS

(If

fire

is

not

extinguished,

increase

glidi WING

speed

to

find

an

airspeed

which

will

provide

an

incombustiblr

mixture).

1.

Forced

Landing

--

EXECUTE

(as

described

in

Emergency

Landini

2.

Without

Engine

Power).

3.

After

discharging

an

extinguisher

within

a

closed

cabin,

ventilate

the

cabin.

Land

the

airplane

as

soon

as

possible

to

inspect

for

damage.

FIRE

Navigation

Light

Switch

--

OFF.

Pitot

Heat

Switch

(if

installed)

--

OFF.

Strobe

Light

Switch

(if

installed)

--

OFF.

ELECTRICAL FIRE IN FLIGHT

NOTE

1.

Master

Switch

--

OFF.

2.

Avionics

Power

Switch

--

OFF.

3.

All

Other

Switches

(except

ignition

switch)

--

OFF.

4.

Vents/Cabin

Air/Heat

--

CLOSED.

5.

Fire

Extinguisher

--

ACTIVATE

(if

available).

WARNING

After

discharging

an

extinguisher

within

a

closed

cabin,

ventilate

the

cabin.

If

fire

appears

out

and

electrical

power

is

necessary

for

continuance

o

flight:

3-6

6.

Master

Switch

--

ON.

7.

Circuit

Breakers

--

CHECK

for

faulty

circuit,

do

not

reset.

8.

Radio

Switches

--

OFF.

9.

Avionics

Power

Switch

--

ON.

10.

Radio/Electrical

Switches

--

ON

one

at

a

time,

with

delay

afteJ

each

until

short

circuit

is

localized.

Perform

a

sideslip

to

keep

the

flames

away

from

the

fuel

tank

and

cabin,

and

land

as

soon

as

possible

using

flaps

only

as

required

for

final

approach

and

touchdown.

ICING

INADVERTENT

ICING

ENCOUNTER

1.

Turn

pitot

heat

switch

ON

(if

installed).

2.

Turn

back

or

change

altitude

to

obtain

an

outside

air

temperature

that

is

less

conducive

to

icing.

3.

Pull

cabin

heat

control

full

out

and

open

defroster

outlet

to

obtain

maximum

windshield

defroster

airflow.

Adjust

cabin

air

control

to

get

maximum

defroster

heat

and

airflow.

4.

Open

the

throttle

to

increase

engine

speed

and

minimize

ice

build-

up

on

propeller

blades.

5.

Watch

for

signs

of

carburetor

air

filter

ice

and

apply

carburetor

3-7

SECTION

3 CESSNA.

EMERGENCY

PROCEDURES

MODEL

172N

heat

as

required.

An

unexplained

loss

in

engine

speed

couid

be

caused

by

carburetor

ice

or

air

intake

filter

ice.

Lean

the

mixture

for

maximum

RPM,

if

carburetor

heat

is

used

continuously.

6.

Plan

a

landing

at

the

nearest

airport.

With

an

extremely

rapid

ice

build-up,

select

a

suitable

"off

airport"

landing

site.

7.

With

an

ice

accumulation

of

1/4

inch

or

more

on

the

wing

leading

edges,

be

prepared

for

significantly

higher

stall

speed.

8.

Leave

wing·

flaps

retracted.

With

a

severe

ice

build-up

on

the

horizontal

tail,

the

change

in

wing

wake

airflow

direction

caused

by

wing

flap

extension

could

result

in

a

loss

of

elevator

effective-

ness.

9.

Open

left

window

and,

if

practical,

scrape

ice

from

a

portion

of

the

windshield

for

visibility

in

the

landing

approach.

10.

Perform

a

landing

approach

using

a

forward

slip,

if

necessary,

for

improved

visibility.

11.

Approach

at

65

to

75

KIAS

depending

upon

the

amount

of

the

accumulation.

12.

Perform

a

landing

in

level

attitude.

STATIC

SOURCE

BLOCKAGE

(Erroneous

Instrument

Reading

Suspected)

1.

Alternate

Static

Source

Valve

--

PULL

ON.

2.

Airspeed

--

Consult

appropriate

calibration

tables

in

Section

5.

LANDING

WITH

A FLAT

MAIN

TIRE

1.

Approach

--

NORMAL.

2.

Touchdown

--

GOOD

TIRE

FIRST,

hold

airplane

off

flat

tire

as

long

as

possible.

ELECTRICAL POWER SUPPLY

SYSTEM

MALFUNCTIONS

OVER-VOLTAGE LIGHT ILLUMINATES

1.

Avionics

Power

Switch

--

OFF.

2.

Master

Switch

--

OFF

(both

sides).

3.

Master

Switch

-- ON.

4.

Over-Voltage

Light

--

OFF.

5.

Avionics

Power

Switch

-- ON.

If

over-voltage

light

illuminates

again:

6.

Flight

--

TERMINATE

as

soon

as

possible.

CESSNA

,MODEL

172N

AMMETER

SHOWS

DISCHARGE

1.

Alternator

--

OFF.

SECTION

3

EMERGENCY

PROCEDURES

2.

Nonessential

Radio/Electrical

Equipment

--

OFF.

3.

Flight

--

TERMINATE

as

soon

as

practical.

3-8 3-9I (3-10

blank)

C:ESSNA

:tJODEL 172N

SECTION

3

EMERGENCY

PROCEDURES

AMPLIFIED PROCEDURES

ENGINE FAILURE

If

an

engine

failure

occurs

during

the

takeoff

run,

the

most

important

thing

to

do

is

stop

the

airplane

on

the

remaining

runway.

Those

extra

items

on

the

checklist

will

provide

added

safety

after

a

failure

of

this

type.

Prompt

lowering

of

the

nose

to

maintain

airspeed

and

establish

a

glide

attitude

is

the

first

response

to

an

engine

failure

after

takeoff.

In

most

cases,

the

landing

should

be

planned

straight

ahead

with

only

small

changes

in

direction

to

avoid

obstructions.

Altitude

and

airspeed

are

seldom

sufficient

to

execute

a 180°

gliding

turn

necessary

to

return

to

the

runway.

The

checklist

procedures

assume

that

adequate

time

exists

to

secure

the

fuel

and

ignition

systems

prior

to

touchdown.

After

an

engine

failure

in

flight,

the

best

glide

speed

as

shown

in

figure

3-1

should

be

established

as

quickly

as

possible.

While

gliding

toward

a

suitable

landing

area,

an

effort

should

be

made

to

identify

the

cause

of

the

failure.

If

time

permits,

an

engine

restart

should

be

attempted

as

shown

in

the

checklist.

If

the

engine

cannot

be

restarted,

a

forced

landing

without

power

must

be

completed.

12,000

I-

10,000

u.

z

<:

8000

a::

LU

I-

LU

6000

:::>

0

a'.l

<( 4000

I-

J::

~

w 2000

J::

*SPEED

65

KIAS

1---~~+--+--+-I

*PROPELLER

WINDMILLING

*FLAPS

UP

*ZERO

WiND

2 4 6 8 10

12 14 16

18

GROUND DISTANCE -

NAUTICAL

MILES

Figure

3-1.

Maximum

Glide

20

3-11 j

Cessna 1978 Skyhawk 172N Owner's manual

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