Cessna Skywagon 185 1975, A185F Owner's Manual

ESSNA

SKYWAGON

SSE

MORE PEOPLE BUY AND FLY

CESSNA AIRPLANES

THAN

ANY OTHER MAKE

TAKE YOUR

CESSNA

HOME

FOR

SERVICE AT THE

SIGN

OF

THE

CESSNA SHIELD"

1975

MODEL

A185F

CESSNA

AIRCRAFT

COMPANY

WICHITA,

KANSAS

OWNER'S

WORLD'S

LARGEST

PRO-

DUCER OF GENERAL

MANUAL

AVIATION

AIRCRAFT

SINCE

1956

SERVICING

REQUIREMENTS

*

CONGRATULATIONS

. . . . .

ENGINE

OIL:

GRADE

--

Aviation Grade

SAE 50

Above

40°F.

Welcome

to

the

ranks of Cessna owners! Your Cessna

has been

designed and

con-

Aviation

Grade

SAE

10W30 or SAE

30 Below

40°F.

structed

to give you the most in

performance, economy,

and

comfort. Itisour

de-

Multi-viscosity

oil witharangeofSAE

10W30

is

recommended for

sire that you

will find flying it, either for business

or

pleasure, a

pleagnt

and

improved

starting

in cold weather.

Ashless

dispersant

oil,

conform_

profitable experience.

ing to Continental Motors Specification

MHS-24A, must be

used.

This

owner's Manual

has

been

preparedasa guide to help

you

get the most pleasure

NOTE

and utility from

your

Skywagon

185.

It contains

information about

your Cessna's

equipment,

operating

procedures,

and performance;

and

suggestions

for

its

servic-

Your Cessna

was

delivered from the

factory

with

a

ing and care. We urge

you

to read it from cover

to

cover,

and to refertoit

fre-

corrosion preventive aircraft engine

oil.

If

oil must

quently.

be added

during

the

first25hours,

use

only

aviation

grade straight mineral oil

conforming

to

Specification

our interest in your flying pleasure has

not

ceased

with your

purchase of a

Cessna.

No.

MIL-L-6082

World-wide,

the

Cessna Dealer

Organization

backed

by

the

Cessna

Service

Depart-

ment stands

ready

to serve you.

The

following

services are

offered

by

most Cessna

Dealers:

CAPACITY OF ENGINE SUMP

--

12

Quarts.

Do not operate on less than 9 quarts. To minimize loss

of oil through

THE CESSNA

WARRANTY--Itisdesigned to provide

you

with

the most

breather, fill

to

10

quart level

for normal flights

of less than

3 hours,

comprehensive

coverage possible:

For extended

flight,

fill to

12

quarts.

These quantities

refer to oil

a.Noexclusions b. Coverage includes parts and labor

dipstick level

readings. During oil and oil

filter changes,

one

addi~

c.

Available at

cessna Dealers world wide

tional quart

is

required when

filter

elementischanged.

d.

Best

in

the

industry

OIL

DIPSTICK

CALIBRATIONS

specific

benefits and provisions of

the

warranty

plus other important

benefits for you

are

contained in

your

Customer Care

Program book

The oil dipstick is

calibrated for both

landplane and

floatplane/amphi-

supplied with

your

aircraft. Warranty service is available

to

you at

any

authorized

Cessna Dealer

throughout

the

world upon presentation

bian use. Oil level

readings

for

the

floatplane/amphibian will

regis-

of

your Customer Care Card which establishes

your eligibility

under

ter

below the

calibrations for the landplane due to

the difference in

the warranty.

attitude of

the

aircraft.

When checking

the oil

level,

take precautions

to

assure that you

are

using

the correct calibrations for

your airplane.

FACTORY

TRAINED PERSONNEL

to provide

you

with

courteous

expert

service.

The landplane side

of the dipstick is marked with

four

lines

represent¯

FACTORY APPROVED

SERVICE EQÚlPMENT

to provide

you

with

the

ing

six, eight,

ten

and

twelve quarts. The bottom

line

is

the

six

most efficient

and accurate

workmanship

possible.

quart

level and the

top lineisthe twelve

quart

(full)

level.

The

float-

plane/amphibian

side of the dipstick

has

two x

marks. The lower

A STOCK OF GENUINE

CESSNA SERVICE

PARTS

on hand when

you

mark

indicates

nine

quarts and the upper

mark indicates twelve quarts.

need

them.

THE

LATEST

AUTHORITATIVE INFORMATION FOR

SERVICING

OIL

AND

OIL

FILTER CHANGE

--

CESSNA

AIRPLANES,

since Cessna Dealers have all of

the Service

After

first25hours

of

operation, drain engine

oil sump

and clean oil

Manuals

and

Parts

Catalogs,

kept

current

by

Service

Letters

and

pressure screen.

If optional

oil filter is

installed,

change

filter

ele-

Service

News

Letters,

published by Cessna

Aircraft

Company.

ment

at this time.

Refill

sump

with straight

mineral oil

and

use

until

a total

of

50 hours

has

accumulated or oil

consumption has

stabilized;

We urge

all Cessna owners to use the Cessna Dealer Organization

to the

fullest.

then

change

to dispersant

oil.

On aircraft not

equipped with

an

op-

A

current cessna Dealer

Directory

tional oil filter, drain

engine

oil sump

and

clean

oil

pressure screen

is

revised

frequently,

and

a current

copy

can be obtained from

your Cessna Dealer.

each

50

hours

thereafter.

On

aircraft which

have

an optional oil

filter,

Make your

Directory one

of

your

cross-country

flight

planning

aids;

a warm welcome

awaits

you at

every

Cessna

Dealer.

i

R

surfaces,

aluminum,

5-2

Radio

Selector Switches,

7-5

painted,

5-3

speaker-phone

switches,

7-6

\

transmitter selector

switch,

7

-9"MAX.

Recovery

From

Spiral

Dive,

3-5

Removable

Cabin Door,

2-13

Rough Engine

Operation Or Loss

of

Table of

Contents, iii

Power,

3-7

Tachometer,

4-3

o i2o

engine-driven

fuel

pump

fail-

Tail Wheel Lock,

Manual,

2-13,

‡

25 '"

ure,

3-8

2-15

low oil

pressure,

3-8

Take-Off,

1-5,

2-16

10

magneto malfunction,

3-7

before,

1-5,

2-14

Ad

"1

ional

Spark plug

fouling,

3-7

data

chart,

6-3

installed.

Rudder Pedals, Stowable,

7-14

maximum

performance,

1-5

Rudder Pedal Extensions,

7-14

normal,

1-5

power check,

2-16

PRINCIPAL

wing

flap

settings,

2-16

Taxiing,

2-14

DIMENSIONS

Tire

Pressure,

inside

back cover

S

Transmitter

Selector

Switch,

7-5

True Airspeed

Indicator,

7-15

Sample

Loading Problem,

4-6

Il |||||| Il

lillllllllllllll

Securing Aircraft,

1-7

Servicing

Requirements,

5-8,

inside back cover

engine

oil,

inside back cover

W

fuel, inside

back

cover

landing

gear, inside

back

cover

Warm-Up,

2-15

oxygen,

inside back cover

Weight,

Shoulder

Harnesses,

2-12,

2-13

empty, inside front

cover

Spark

Plug

Fouling,

3-7

gross, inside

front

cover

Speaker-Phone

Switches,

7-6

Weight

and

Balance,

4-4

Spins,

3-6

baggage and

cargo

tie-down,

Stalls,

2-20

4-11

speed chart,

6-2

center

of gravity

moment

Starting

Engine,

1-4,

2-14

envelope,

4-8

Static

Dischargers,

7-7

loading

arrangements

diagram,

s2"

Static Pressure

Alternate

Source

4-9

Valve,

7-4

sample

loading

problem,

4-6

r.s

Storage,

Flyable,

5-6

Windows,

Observation,

7-15

Stowable

Rudder

Pedals,

7-14

Windshield

-

Windows,

5-2

Suction

Gage,

4-3

Winterization

Kit,

7-1

Index-5

ii

M

oil dilution,

7-2

oil

dilution table,

7-3

MAA

Plate/Finish

Trim

Plate,

5-5

oil/filter change, inside

back

Magneto

Check,

2-15

cover

malfunction,

3-7

oil grade,

inside

back cover

Maneuvers-Normal Category,

4-1

pressure

gage,

4-3

Manual

Tail

Wheel Lock,

2-13,

quick-drain

valve,

7-16

Ma2nif1o51d

Pressure/Fuel

Flow

OperaemperaColrde

elie4r

2-20

T

AB

LEOF

CO NTENTS

Indicator,

4-3

Operation

Limitations,

Engine,

Markings,

Airspeed Indicator,

4-2

Page

=

Markings,

Engine

Instrument,

4-2

Operations Authorized,

4-1

Master

Switch,

2-8

Over-Voltage

Sensor

and

Warning

SECTION I

-

OPERATING CHECKLIST..........

1-1

Maximum Glide

Diagram,

6-10

Light,

2-7

Maximum

Performance

Climb,

1-6

Owner

Follow-Up

System,

5-9

SECTION

ll-DESCRIPTION AND

Maximum

Performance

Take-Off,

publications,

5-9

1-5

Oxygen

System,

7-8

OPERATING

DETAILS ...........--

2-1

Maximum

Rate-Of-Climb

Data

duration

calculations,

7-11

Chart,

6-3

duration chart,

7-9

SECTION

lli-EMERGENCY PROCEDURES.....

3-1

Microphone-Headset,

7-6

operation,

7-8

Moment Envelope,

Center of

servicing,

7-11,

inside back

SECTION IV

-

OPERATING LIMITATIONS..-.....

4-1

Gravity,

4-8

cover

Mooring

Your Airplane,

5-1

SECTION V

-

CARE

OF

THE AIRPLANE---.....

5-1

SECTION

VI-OPERATIONAL DATA..............

6-1

N

rack,

cargo,4-12,

7-is

SECTION

VII-

OPTIONAL

SYSTEMS........------

7-1

Noise Abatement,

2-21

Painted

Surfaces,

5-3

Non-CongealingOil

Cooler,

7-1

Performance

-Specifications,

ALPHABETICAL

INDEX----------....____...._____

index-1

Normal Category

Maneuvers,

4-1

inside front cover

Normal

Climb,

1-6

Precautionary

Landing

with Engine

Normal

Landing,

1-9

Power,

3-2

Normal

Take-Off,

1-5

Primer

System, Engine,

7-3

Principal

Dimensions Diagram, ii

Progressive

Care,

Cessna

5-7

Propeller,

care,

5-3

Publications,

5-9

Observation

Windows,

7-15

Oil

System,

capacity, inside

back

cover

oil

cooler,

non-congealing,

7-1

Quick-Drain

Valve,

Oil,

7-16

Index-4

iii

REVISED

FUEL

QUANTITYDATA

I

1973

AIRCRAFT(SERIAL18502263

ANDON)

SKYWAGON

185

1974AIRCRAFT(ALLSERIALS)

1975

AIRCRAFT(ALL

SERIALS)

precautionary landing with Indicator,

Fuel

Quantity,

4-2

Due to changesin

fuel tank

manufacturing

technique,

the fuel

systems in the above noted airplanes

engine

power,

3-2

Indicator,

True

Airspeed,

7-15

havebeenfound to

contain

less

than

the

capacitypublished in the

Owner'sManuals

for landplanes and

Fuel

Systems,

2-1

Inspection

Requirements,

5-6

Owner'sManualSupplements

for

the AGcarryallor

floatplanes,

amphibians and skiplanes. Data

in

these

auxiliary

fuel

pump

switch,

2-6

Instrument

Markings,

Engine

manuals

indicates

total usable capacities

of59gallons

(standard

tanks and "selector

valve" fuel system),

capacity,

inside

back cover

4-2

78 gallons

(long

range

tanksand "selector

valve" fuel system), anci62

gallons (standard tanks

and

"on-off

fuel

flow

indicator,

4-3

Instrument

Panel

Diagram,

1-8

fuel

system). The

usable

capacity per

tank

in these systems is 29.5

gallons (standard tanks and "selector

fuel

grade, inside back cover

Integrated

Seat Belt/Shoulder

Har-

valve"

system) and39gallons

(Iong

range

tanks and "selector

valve" system);

in airplanes

having

standard fuel

quantity

indicators,

4-2

nesses with

Inertia

Reels

tanks

and

an

"on-off"

system,

single-tank

operationis

not selectable.

long range

fuel

tanks,

2-6

Interior

Care,

5-4

AII

fuel capacity

references inOwner'sManualsand

Supplements

for these airplanes should be

marked

"on-off", 2-1,

2-2

Interior

Lighting,

2-10

to

reflect the capacities

in the chart below.

schematic, 2-2,

2-3

Internal

Cabin

Dimensions

TOTAL

USABLE TOTAL .USABLE

selector

Valve,

2-3,

2-4

Diagram,

4-10

BOTHTANKS. BOTH

TANKS PER TANK PER

TANK

tank

sump

and fuel

quick-drain

CAPACITY

(STANOARD

valves,

2-5

TANKS,SEL.

VALVE

SYS.)

61

Gal.

55

Gal. 30.5 Gal. 27.5 Gal.

Fuses

and

Circuít

Breakers,

2-9

CAPACITY(LONGRANGE

80

Gal. 74

Gal. 40 Gal.

37

Gal.

TANKS,

SEL.

VALVESYS.)

T

KAQ0N-OFFASNY98

)

61

Gal.

58

Gal.

30.5 Gal•

SeleNc

ble

Landing,

2-20

G

after,

1-7

When

figuringweight

and

balance

data,

consideration should be

given

to the reduction

in

weight and

balked,

1-7,

2-21

change

in moment/1000 which

resultsfrom

a reduced

fuel capacity,

before,

1-6

For

quick

re-computation

of

cruise

performance

data,

use the

informationin the CruisePerformance

Glide,

Maximum,

6-10

distance

table,

6-9

charts provided in Owner's

Manuals

and Supplementsby multiplying

the ENDR. HOURS

and

RANGE

Graph, Loading,

4-7

forced,

3-2

MILES

figures

by

0.93

(for standard tank and "selector

valve"

or

"on-off"

system

values) or

0.94 (for

Gross

Weight,

inside

front

cover

normal,

1-7

long

range

tank

and "selector

valve"

system

values);

this

will

provide

conservative endurance and range

Ground

Handling,

5-1

Landing

Gear

Servicing,

inside

basedonthe reduced

fuel

capacities.

Ground

Service

Plug

Receptacle,

back

cover

Pages

in the Owner's

Manuals

or

Supplements

which are

affected by the change

in

fuel capacity are

7.2

listed in

the chart

below.

main/tail

wheel

tire

pressure,

inside

back

cover

MANUAL

PAGESÁFFECTED

Leaning With A

Cessna

Economy

197

ONUNAELR'S

I

2-1

2-14 4-6 4-7 5-8 6-4

6-5 6-6

&7

6-8

7-1 7-2 - - -

- - Mixture

Indicator

(E

GT),

2-19

H

Let-Down,

1-6

197S3UAGLCEAMRERNTALL

I

3-4355-3 5-4 -

--- --

-

'

- -

-

- -

-

- -

Lighting

Equipment,

2-9

19,7g|F,LUO HIS

I

1-9

1-10

1-15 1-16 1-17 1-18 1-19

2-13

2-14 2-20

2-21

2-22 2-23

224

3-7 3-8393-10

Handling, Ground,

5-1

1en

eerriorr11ighhtinng,

22-190

1974 OWNER'S

Imide

2-1232-4

2-5 2-17

4-6 4-7 6-4 6-5 6-6 6-7

6-8

Imide

Harnesses, Shoulder,

2-12,

2-13

Limitations,

Airspeed,

4-2

MANUAL

Cover

Headset-Microphone,

7-6

. .

. Limitations,

Engine Operation,

1974 AGCARRYALL

imide

34

3-5535-4

-

- -

-

- -

-

- - - -

_

Heating,

Ventilating

and

Defrosting

4-2

SUPPLEMENT

cm

System,

Cabin,

2-11

sKi'sLUO 14

1-9 1-10 1-15

1-16

1-17

1-18 1-19 2-13

2-14 2-20

2-21

2-22

2-23

2-24

3-7

&8

39 310

Loa4di9ng

Arrangements

Diagram,

197MADNWUNAELR'S

I

21

2-3

24

2-6

4-6

4-7

64

6-5 6-6 6-7

6-8

Cm

_ _

_ _ _

Loading,

Cargo,

4-11

Loading

Graph,

4-7

s"uÊPLCEAMRERNTALL10nne

34

3-5

53

5-4

-

- - - - -

-

- - - -

-

Loading

Problem,

Sample,

4-6

1975

FLOATbAMPHIB,

imide

19

1-10 1-15 1-16

1-17

1-18

1 19

2-13

2-14 2-20

221 2 22

2-23

2 24

3-7

3-8

3-9

3

10

Long

Range

Fuel

Tanks,

2-

6

SKI SUPP ENT

Cm

Indicator,

Fuel

Flow,

4-3

Low

Oil

Pressure,

3-8

REFERENCE SERVICE LETTER SE 75

-

7

Index-3

D

EmCelræg

cy3L5et-Downs

Through

Diagram,

Emergency Locator

Transmitter

cargo

loading,

4-11

(ELT),

3-10

--

..--.

cargo

pack,

4-12

ELT control

panel,

3-10

electrical system,

2-8

ELT

operation,

3-11

OPERATlNG CHECK

LIST

exterior inspection,

1-2

Empty

Weight,

inside

front

cover

fuel

system, 2-2,

2-3

Engine,

instrument

panel,

1-8

before

starting,

1-4

internal cabin

dimensions,

4-10

instrument

markings,

4-2

One

of the

first

steps in

obtaining

the

utmost

performance,

service,

loading

arrangements,

4-9

oil, inside back

cover

and

flying

enjoyment from your

Cessna is to familiarize

yourself with

maximum

glide,

6-10

operation

limitations,

4-2

your

aircraft's

equipment,

systems,

and

controls.

This

can

best be

done

principal

dimensions,

ii

primer system,

7-3

by reviewing

this

equipment while

sitting

in the aircraft.

Those items

radio selector

switches,

7-5

starting,

1-4,

2-14

whose function

and

operation

are

not obvious are

covered in Section

II.

Dimensions,

Internal

Cabin,

4-10

Engine Failure,

3-1

Dimensions, Principal,

ii

after take-off,

3-1

Section

I

lists,

in Pilot's

Checklist

form, the steps necessary

to

Disorientation

In

Clouds,

3-4

during

flight,

3-1

operate your

aircraft

efficiently and

safely. It

is

not

a

checklist

in its

emergency

let-downs

through

Enroute

Climb,

1-6,

2-17

true

form

as

it

is considerably

longer,

but it

does

cover briefly

all of

the

clouds,

3-5

maximum

performance,

1-6

points

that

you

should

know

for

a

typical flight.

A

more

convenient

plastic

executing

180°

turn in

normal,

1-6

enclosed

checklist,

stowed in the

map

compartment

,

is

available for

clouds,

3-4

Engine-Driven

Fuel

Pump Failure,

quickly checking

that

all important

procedures

have

been performed.

recovery

from spiral

dive,

3-5

3-8

Since

vigilance

for

other

traffic

is

so

important

in

crowded

terminal

areas,

Ditching,

3-3

Equipment,

Cold Weather,

7-1

it is

important

that

preoccupation

with checklists

be

avoided in flight.

Excessive Rate of Electrical

Procedures

should be carefully

memorized and

performed from memory.

Charge,

3-9

Then the

checklist

should be quickly scanned to ensure

that

nothing has

E

Executing

180°

Turn

in

Clouds,

been missed.

3-4

Economy

Mixture

Indicator,

2-19

Exterior Care,

5-2

The

flight and

operational

characteristics of your

aircraft are

normal

Electric

FireinFlight,

3-3

Exterior

Inspection Diagram,

1-2

in

all

respects. There

are no "unconventional"

characteristics or

opera-

Electrical Power

Supply

System

Exterior

Lighting,

2-9

tions

that

need to be

mastered.

All

controls respond in

the

normal

way

Malfunctions,

3-8

within

the entire range

of operation.

All airspeeds

mentioned

in Sections

excessive

rate

of

charge,

3-9

I,IIand

III are indicated

airspeeds.

Corresponding

calibrated airspeed

insufficient

rate of charge,

3-9

F

may

be obtained

from

the

Airspeed

Correction Table in

Section

VI.

Electrical

System,

2-7

ammeter,

2-7

File,

Aircraft,

5-5

circuit breakers and fuses,

2-9

Fires,

3-3

ground

service plug

receptacle,

electrical

fire

in

flight,

3-3

7-2

engine

fire

in

flight,

3-3

master

switch,

2-7

Flight in

Icing

Conditions,

3-6

over-voltage

sensor and

Flyable Storage,

5-6

warning

light,

2-7

Forced

Landings,

3-2

schematic,

2-8

ditching,

3-3

Emergency

Landing Without Engine emergency landing

without

Power,

3-2

engine power,

3-2

Index-2 1-1

ALPHABETICAL INDEX

5

Refer to inside back

coveraf this

manual

for quantities,

materials, and

spapifications

of frequentlý used service

items.

A

fuel,

inside

back

cover

oil,

inside

back

cover

¯

6

4

¯¯

Aft

Baggage Compartment

2-13

Care,

Afteg

Landing,

1-7

exterior,

5-2

Airáraft,

interior,

5-4

yile,

5-5

propeller,

5-3

8 3

securing,

1-7

Cargo

Loading,

4-11

Airspeed Correction

Table,

6-1

Cargo

Pack, 4-12,

7-13

Airspeed

Indicator, True,

7-15

flight

operation,

7-13

EXTERIOR

INSPECTION

Airspeed Indicator

Markings,

4-2

speed

differential

table,

7-13

Airspeed

Limitations,

4-2

Center

of

Gravity

Moment

Alternate

Source

Valve,

Static

Envelope,

4-8

Pressure,

7-4

Cessna Customer

Care

Program,

Alternator

Check,

2-15 5-7

Aluminum

Surfaces,

5-2

Cessna Progressive

Care,

5-7

Ammeter,

2-7

Circuit

Breakers and

Fuses,

2-9

Authorized

Operations,

4-1

Climb,

2

Auxiliary

Fuel

Pump

Switch,

2-7

enroute, 1-6,

2-17

maximum

rate-of-climb

data

chart,

6-3

Note maximum

performance,

1-6

normal

1-6

Visually

check aircraft for general

condition

during

walk-

'

around inspection.

In

cold

weather,

remove

even small

Baggage Compartment, Aft,

2-13

Cold

Weather

Equipment,

7-1

accumulations

of frost,

iceor

snow

from

wing,

tail and

Balked

Landing,

1-7,

2-21

engme

primer

system,

7-3

control surfaces.

Also,

make sure

that control surfaces

ground

service plug

contain no internal accumulations

of ice or debris.

If

a

Before

Landing,

1-6

receptacle,

7-2

night flight is

planned,

check operation of all lights, and

Before

Starting

Engine,

1-4

non-congealing

oil

cooler,

7-1

make

sureaflashlight is available. Before

Take-Off,

1-5,

2-14

oil dilution

system,

7-2

alterñator

check,

2-15

a. Remove control

wheel

lock.

magneto

check,

2-15

static pressure

alternate

b. Check îgnition switch OFF.

SOurce

Valve,

7-4

c.

Turn on master switch

and

check fuel

quantity

indicators;

then

wárm-up,

2-15

winterization

kit,

7-1

d.

Cbhrenc umla ro ac1h.e

knob ON

(full in). If optional fuel tank

Cold

Weather

Operation,

2-21

selector valve is

installed,

check that handle is in BOTH

ON

Correction

Table,

Airspeed,

6-1

position. Cruise Performance

Chart, 2-18,

e.

Check

baggage door

securely

locked·

6-4,

6-5, 6-6, 6-7,

6-8

Cabin Door,

Removable,

2-13

Cruise, 1-6,

2-17

a. Remove rudder gust

lock,

if installed.

b. Disconnect

tail

tie-down.

Cabin

Heating,

Ventilating

and

leaning with

EGT,

2-19

Defrosting

System,

2-11

Cylinder

Head Temperature

Gage,

Figure

Capacity,

4-3

1-2

Index-1

CESSNA

ECONOMY

MIXTUREINDICATOR

c. Check tail

wheel tire for

proper inflation.

d. Check

control surfaces for freedom of movement and

security.

a.

Check

aileron for free

and correct movement and security.

The

Cessna

Economy Mixture

Indicator is an exhaust gas

temperature

(EGT)

sensing

device which

visually

aids the pilot in adjusting

the cruise

a.

Disconnect

wing

tie-down.

mixture.

Exhaust

gas temperature varies

with

fuel-to-air

ratio, power

b.

Check fuel

tank

vent opening for

stoppage,

c.

Check main wheel tire

for proper mflation.

and RPM. However,

the difference

between the peak EGT

and the EGT at

d. Before

first flight

of day and

after

each refueling,

use sampler

the cruise mixture

setting is

essentially

constant and this provides

a

use-

cup and

drain

small

quantity

of fuel from fuel

tank

sump

quick-

ful

leaning aid.

Operating

instructions are included in Section

II.

drain valve to check for

water, sediment, and

proper fuel grade.

e. Use

sampler cup and drain small quantityoffuel from fuel

line

quick-drain

valve located on the

bottom of

the fuselage

below the

cabin door.

f.

Visually

check fuel quantity; then check

fuel

filler cap secure

and

vent

unobstructed.

a.

Inspect

flight

instrument

static source

opening

on

side

of fuselage

OIL QU

ICK-DRAIN

VA

LVE

for

stoppage (both sides).

b.

Check

propeller and spmner for

nicks and security,

and

propeller

for oil leaks.

c. Check

induction

air filter

for restrictions

by

dust or other

foreign

An optional oil

quick-drain

system

is

offered to facilitate

draining

matter.

the

engine oil sump by

eliminating the need

for removal of the

lower

cowl-

d. Ch kl

s

fDo enot o

rate

th less

than nine

quarts.

Fill

ing.

The

system

consists

of

a hose from the

engine sump to an

on-off

e. Before

first flight of the

day

and after each

refueling,

pull

valve

(spring-loaded

in the off

position)

located on

the

lower

left side of

out

strainer

drain knob

for about four seconds

to clear fuel

the

engine

mount.

The valve handle

is

accessible through the

opening at

strainer

of possible water

and

sediment.

Check strainer

the

bottom of

the lower

cowling.

Rotating the

handle

clockwise

will open

drain

closed.Ifwater

is observed,

the fuel

system

may

the

valve.

contain

additional

water,

and further

draining

of the system

at

the

strainer,

fuel tank sumps,

and fuel

line

drain

valves

will be necessary.

a.

Visually

check fuel quantity;

then check

fuel

filler cap secure

and vent

unobstructed.

b.

Check main

wheel

tire for

proper inflation.

c. Before first flight of

day

and after each

refueling,

use sampler

cup and

drain small

quantity of fuel from fuel

tank

sump

quick-

drain

valve to check for

water, sediment,

and

proper fuel grade.

d. Use

sampler cup

and

drain small quantity of

fuel from fuel line

quick-drain

valve located on

the

bottom of the

fuselage below the

cabin door.

e. Remove

pitot tube

cover,

if

installed, and

check pitot tube

open-

ing

for

stoppage.

a.

Check

stall warning

vent

opening

for

stoppage.

b.

Check

fuel

tank

vent

opening

for stoppage.

c.

Disconnect wing

tie-down.

a. Check

aileron for free and

correct movement and security.

1-1.

7-16

1-3

BEFORE STARTING ENGINE.

OBSERVATION

WINDOWS

(1) Exterior

Preflight

--

COMPLETE.

(2)

Seats, Belts,

Shoulder Harnesses

--

ADJUST

and

LOCK.

(3)

Fuel

Shutoff Valve--ON-

Special

windows

are

available to increase the

area of visibility

for

(4)

Fuel

Selector

Valve (if

installed)

--

BOTH ON·

the pilot

and copilot.

Two

windows in the cabin roof provide

visibility

(5)

Brakes

--

TEST and

SET·

above the aircraft.

Two

additional windows in the

lower portion of the

(6)

Radios,

Autopilot, Electrical Equipment

--

OFF.

cabin

doors

increase visibility

below

and to

each

side

of

the aircraft.

A

(7) Wing Flaps

--

CHECK ALL

POSITIONS.

pair of

domed windows,

which

replace

the

standard

flat windows

in the

(8) Cowl

Flaps

--

OPEN (move

lever

out of

locking detent

to

re-

cabin

doord,

permit

a

lineofvision beyond

the

side of the fuselage

to

pro-

position).

vide

almost vertical observation of the

area

beneath the

aircraft.

Each

(9) Tail Wheel

Lock--UNLOCK.

openable

domed windowisheld in the closed position by

two

over-center

latches equipped with

push-button

locks which must be

depressed before

the latch

can be released. The windows

may

be opened below

120

MPH,

ST

A

RTI

NGENG

IN

E.

as

indicatád byaplacard just

below

the lower forward

corner

of the

left

window.

(1)

Master

Switch--ON.

(2) Mixture

--

RICH.

(3)

ProIieller

--

HIGH

RPM.

(4)

Throttle

--

CLOSED.

(5) Auxiliary

Fuel Pump

--

ON.

(6)

Throttle

--

ADVANCE

for

8-10

GPH;

then RETARD

to IDLE.

(7)

Auxiliary

Fuel Pump

--

OFF.

(8)

Propeller

Area

--

CLEAR.

(9)

IgnitionSwitch--START.

TRUE AIRSPEED

INDICATOR

(10)

Throttle

--

ADVANCE

slowly.

(11)

Ignition

Switch

--

RELEASE

when

engine

starts.

NOTE

A

true

airspeed

indicator

is

available

to replace the

standard

air-

speed

indicator in your

airplane.

The true

airspeed

indicator has

a

cali-

The engine

should start

in two to three

revolutions·

brated

rotatable

ring which

works in

conjunction with the airspeed

indi-

If

it does

not continue

running,

start again at

step

cator dial

inamanner similar to the operation

of a flight

computer.

(4)

above. If

the engine

does not

start,

leave

auxi-

liary

fuel

pump switch off,

set

mixture to

idle

cut-

TO

OBTAIN TRUE

AIRSPEED,

rotate ring until pressure altitude

off, open

throttle,

and crank

until engine fires or

is aligned

with outside air temperature in degrees

Fahrenheit. Then

for

approximately 15 seconds.

If

still

unsuccessful,

read true airspeed on rotatable ring opposite airspeed needle.

start agaili using

the normal

starting

procedure after

allowing

the

starter

motortocool•

NOTE

(12)

Throttle

--

IDLE.

(13) Oil

Pressure

--

CHECK.

Pressure altitude should not be

confused

with indicated

altitude.

To obtain

pressure

altitude, set barometric

NOTE

scale on altimeter

to

29. 92

and read pressure

altitude

If

oil

pressure is not

indicated

within

30 seconds

in normal

on

altimeter.

Be

sure to

return altimeter

barometric

temperatures

and

60

seconds in cold

temperatures, shut

scale to

original

barometric

setting after

pressure

alti-

off engine and investigate the cause.

tude

has been obtained.

1-4

7-15

STOWABLE

RUDDER

PEDALS

BEFORE

TAKE-OFF.

(1)

Parking

Brake

--

SET.

(2)

Fuel

Selector

Valve (if installed)

--

BOTH

ON.

Stowable

right-hand

rudder

pedals

are

available

as

part of the

option-

(3) Flight

Controls

--

FREE

and

CORRECT.

al

right-hand

flight controls installation.

The pedals fold forward and

(4)

Stabilizer

and

Rudder

Trim

--

SET.

stow against

the

firewall,

thereby

permitting the right

front

passenger

to

(5)

Cowl

Flaps

--

OPEN.

extend his feet forward for

greater

comfort,

and also

to

rest

his feet

on (6) Throttle

--

1700 RPM.

the rudder pedals

during

flight

without,

in

any

way,

interfering

with the

a.

Magnetos

--

CHECK

(RPM

drop

should not

exceed

150 RPM

flight

operation

of the pilot's

rudder

pedals.

on

either

magneto

or

50

RPM

differential between

magnetos).

b.

Propeller

--

CYCLE

from

high

to low RPM;

return

to high

A

push-pull

control on

the instrument

panel actuates the pedal

unlock-

RPM

(full in).

ing mechanism. The pedals

are

stowed

simplybysqueezing the double

c. Engine

Instruments

--

CHECK.

buttons of the control knob and pulling

the

knob out to release the pedals;

d.

Suction

--

CHECK

(4. 6to5. 4

In.

Hg.).

the pedals

can

then

be

pushed

forward against the firewall where

they

are

e.

Ammeter

·--

CHECK.

retained

by spring

clips

withinabracket.

The pedals are

restored to

(7)

Flight

Instruments and

Radios

--

CHECK and

SET.

their

operating

positions

by

pushing

the

control

knob

full

in,

and

inserting

(8) Cabin

Doors

--

CLOSED

and

LOCKED.

the toe of the shoe

underneath

each

pedal

and pulling each pedal aft

until

(9) Tail

Wheel

Lock--AS

DESIRED.

it

snaps

into position. The pedals

are

again

ready

for

flight

use by

the

(10)

Parking

Brake

--

RELEASE.

right front passenger.

(11)

Throttle

Friction Lock--ADJUST.

(12)

Wing

Flaps

--

0°-20°.

TAKE-OFF.

I

RUDDER

PEDAL EXTENSIONS

NORMAL

TAKE-OFF.

(1) Wing Flaps

--

0°-20°.

(2)

Power

--

FULL

THROTTLE and 2850 RPM.

Rudder

pedal

extensions are available

as

optional equipment

for

use

(3)

Elevator

Control

--

MODERATELY TAIL

LOW.

on

either the pilot's or copilot's

rudder pedals.

The extensions allow

the

(4)

Climb Speed

--

100

MPH.

user to position

his

seat

approximately

one

and

one half

inches aft of

his

(5)

Wing Flaps

--

UP

after obstacles are

cleared.

normal seat

position,

primarily

for improved

visibility

through the

option-

al

domed observation

window

in the cabin

door.

MAXIMUM

PERFORMANCE

TAKE-OFF.

A

standard

rudder

pedal

face,

two

spacer blocks,

and

two clips

com-

prise

the rudder pedal extension

assembly.

The extensions are

easily

in-

(1) Wing

Flaps

--

20°.

stalled

by hooking the clip

on

the bottom

of

the extension under the bottom (2)

Brakes

--

APPLY.

of

the rudder

pedal, and then

pressing the top

clip over

the top of the

rud-

(3) Power

--

FULL

THROTTLE and

2850

RPM.

der pedal. Itemovalisaccomplished

by grasping the top clip

and

lifting

(4)

Mixture

--

LEAN FOR

FIELD

ELEVATION.

it up and over

the rudder

pedal,

allowing

the extension to

fall free.

(5)

Brakes

--

RELEASE.

7-14

1-5

(6) Elevator

Control

--

MAINTAIN TAIL

LOw·

CARGO PACK

(7) Climb Speed--64 MPH (until all

obstacles

are cleared).

(8)

Wing Flaps

--

UP

after obstacles are

cleared.

FLIGHT OPERATION

WITH

A CARGO

PACK.

ENROUTE

C

LIM

B.

All flight characteristics

for

a cargo pack

equipped

aircraft

are

identical to

an aircraft without

a cargo pack. There

is,

however, a

NORMAL

CLIMB·

slight climb

and cruisà performance differential

between

the

two aircraft.

(1)

Airspeed

-- 110-120

MPH.

The

climb performance

of the

aircraft

equipped with

a cargo pack is

(2)

Power

--

25 INCHES

Hg.

and 2550

RPM•

approximately 40 ft/min

less

than

that

shown in the

MAXIMUM

RATE-OF-

(3)

Mixture

--

LEAN FOR ALTITUDE

AS

NECESSARY'

CLIMB DATA

table for

the

standard airplane.

(4) Cowl

Flaps--AS

REQUIRED.

MAXIMUM

PERFORMANCE

CLIMB

To obtain

the speed performance

for the aircraft

equipped with

a

cargo pack,

the speed

differentials

shown in the table

below should

be

subtracted from the TAS MPH

figures

shown in the

CRUISE

PERFORM-

(1)

Airspeed

--

101

MPH

(sea

level) to 94 MPH

(10,

000 feet).

ANCE tables for the standard

airplane.

Cruising range

is

computed by

(2)

Power

--

FULL

THROTTLE and

2700 RPM.

multiplying the cargo pack

TAS by

the

endurance.

(3)

Mixture

--

LEAN

FOR

ALTITUDE.

(4) Cowl Flaps

--

OPEN.

For

cargo loading,

refer to Section

IV.

CR

UISE.

(1) Power

-- 15-25

INCHES Hg.,

2200-2550

RPM (no

more

than 75/o).

(2) Cowl

Flaps

--

AS

REQUIRED.

(3)

Stabilizer and Rudder

Trim

--

ADJUST.

(4)

Mixture

--

LEAN

for cruise

as

determined

from

your

Cessna

SPEED

DIFFERENTIAL

TABLE

Power

Computer, or in

accordance

with the

Cruise procedures

in

Section

H.

SPEED

DIFFERENTIAL

BHP

MPH

LET-DOWN.

(1) Mixture

--

ENRICHEN

(as

required).

7 5

-7

(2)

Power--AS

DESIRED.

(3) Cowl

Flaps

--

CLOSED.

65

-8

55

-9

BEFORE

LANDING.

45

-9

(1) Mixture

--

RICH.

(2) Fuel Selector Valve (if

installed)

--

BOTH ON.

(3)

Cowl Flaps

--

CLOSED.

Figure

7-4.

9-13

1-6

AMBIENT

FILLING

AMBIENT

FILLING

(4)

Propeller

--

HIGH

RPM.

TEMPERATURE PRESSURE

TEMPERATURE

PRESSURE

(5)

Airspeed

--

85-95

MPH

(flaps

UP).

°F

PSIG

°F

PSIG

(6)

Wing Flaps

--0-

40°

(below.110

MPH).

(7) Airspeed

--

75-85

MPH (flaps

DOWN).

(8)

Stabilizer and Rudder Trim

--

ADJUST FOR

LANDING.

0

1600

50

1825

NOTE

10

1650

60

1875

20 1700 70

1925

The

ability

of

the

aircraft to land three-point is

dependent

30

1725 80

1975

upon

the stabilizer

being

adjusted

for

hands-off

trim

40 1775 90

2000

in

the

glide.

(9)

Tail

Wheel

Lock

--

AS

DESIRED.

pression

of

the

oxygen. Because of this,

merely

filling to 1800

psi

will

not resultina

properly

filled

cylinder. Fill

to

the pressures

indicated

BA

LKED

LANDI

N

G.

in

the table

above

for

the

ambient

temperature.

(1) Power--FULL

THROTTLE

and 2850 RPM.

IMPORTANT

(2)

Wing

Flaps

--

RETRACT

TO

20°.

(3)

Airspeed--80 MPH.

Oil,

grease,

or

other lubricants

in contact

with

oxygen

(4)

Wing

Flaps

--

RETRACT

slowly.

create

a serious fire

hazard, and

such

contact

must be

(5)

Cowl

Flaps

--

OPEN.

avoided

when

handling oxygen equipment.

NORMAL

LANDING.

(1)

Landing

Technique

--

Conventional for

all flap settings.

AFTER LANDING.

(1)

Wing Flaps

--

UP.

(2) Tail

Wheel

Lock

--

UNLOCK.

(3)

Cowl

Flaps

--

OPEN.

(4) Stabilizer

and

Rudder

Trim

--

SET

FOR

TAKE-OFF.

SECURING

AIRCRAFT.

(1)

Parking

Brake

--

SET.

(2)

Radios,

Electrical

Equipment

--

OFF.

(3)

Mixture--IDLE

CUT-OFF.

(4)

Ignition Switch--OFF.

(5)

Master Switch--OFF.

(6) Control Lock

--

INSTALLED.

7-12

1-7

(6) Unplug

the

delivery hose from

the

outlet

coupling

when

discontin-

INSTRUMENT

PANEL

uing use of the

oxygen

system.

This

automatically

stops

the

flow of

oxygen.

(7)

Position

oxygen

supply

control

knob

OFF.

1

2

3

4

5 6

7

8

91011

12 13

14

15

OXYGEN DURATION

CALCULATION.

The

Oxygen Duration

Chart

(figure

7-3)

should be used in

determining

the usable duration (in

hours)

of

the oxygen

supply

in

your airplane.

The

following

procedure

outlines

the method

of finding

the

duration

from the

chart.

(1) Note

the available oxygen

pressure

shown

on

the pressure

gage.

(2) Locate this

pressure

on the scale on

the left side of the

chart,

then go

across the chart

horizontally

to

the

right

until you intersect

the line

representing

the

numberofpersons

making

the

flight. After

intersecting

the

line, drop down

vertically to

the bottom of

the

chart

and read the duration

in hours given

on

the

scale.

(3) As an example of

the above

procedure,

1400

psi of pressure will

safely

sustain the pilot

only

for

nearly 6

hours

and 15 minutes.

The

same

pressure.will

sustain the pilot and

three passengers for

approx-

imately

2 hours

and

30 minutes.

NOTE

The

Oxygen

Duration Chart is

based on

a

standard

con-

figuration

oxygen

system

having

one

orange

color-coded

hose

assembly

for the

pilot

and green

color-coded

hoses

353431 32 31 30 29

28 27

26

25 24

23 22 21 20 19 18 17 16

for the

passengers.

If

orange

color-coded

hoses

are

provided

for pilot and

passengers,

it will be

necessary

1.

FlightInstrumentGroup

22. MixtureContro1Knob tO

COmpute

new oxygen

duration figures due

to

the

greater

2.

Aircraft

Registration Number

23. Autopilot Control Unit (Opt.)

3.

Localizer

Reversed

Indicator

24.

Propeller Control Knob

COBSumption of

oxygen with

these

hoses.

This is

accom-

Lights (Opt.)

25. Throttle (With

Friction

Lock)

liShed

by

computing the

total

duration available to

the

4.

Marker Beacon

Indicator 13. Over-Voltage

Warning

Light

26. Microphone (Opt.)

Lights and

Switch (Opt.) 14. Cylinder

Head Temperature,

27. Circuit Breakers pilot

only

(from

PILOT

ONLY line

on

chart),

then

di-

5.

Transponder (Opt.) Oil

Temperature and Oil

28. Static Pressure Alternate

viding

this

duration by

the

number

of persons

(pilot

and

6.

Magnetic

Compass Pressure Gages Source

Va1ye (Opt.)

7.

Radio

Selector Switches (Opt.) 15. Optiona1Radio

Space

29. Electrical

Switches

passengers)

using

oxygen.

8.

Radios (Opt.)

16.

Map

Compartment

30.

Parking

Brake

HandÏe

9. Manifold Pressure/Fuel Flow 17. Stowable Rudder

Pedal

31.

Ignition

Switch

Indicator

Control

Space

(Opt.)

32.

Auxiliary

Fuel Pump Switch

10. Tachometer 18. Cowl Flap Handle

33. Master Switch

11.

Economy

Mixture Indicator (Opt.)

19. Cabin

Heat Control

34.

Headphone and

Auxiliary

OX

YGENSY STEMSERV ICI

N G.

12.

Fuel

Quantity

Indicators

and 20.

Cigar

Lighter .

Microphone Jacks

Ammeter 21. Cabin Air ControI

35. Primer

The oxygen

cylinder,

when fully

charged,

contains

approximately

48 cubic feet of

oxygen,

underapressure of 1800

psi at

70°F.

Filling

pressures

will

vary,

however,

due

to

the ambient

temperature in

the

Figure

2-1·

filling

area, and

because

of

the temperature

rise resulting

from

com-

1-8

7-11

or

alcohol

will

usually

necessitate

the use of oxygen

at less than

10,

000

feet.

NOTE

For safety reasons,

no smoking

should

be

allowed

in

the

airbraft

while

oxygen is being

used.

DESCRIPTION

AND

OPERATING

DETAILS

When ready to use

the

oxygen

system,

proceed

as

follows:

The

following paragraphs

describe the

systems

and equipment whose

(1)

Select mask

and

hose.

.

function

and operation

is not

obvíous

when

sitting

in

the aircraft

.

This

NOTE

section

also covers

in somewhat greater detail

some

of the

items listed

in

Checklist

form

in Section

I

that require

further

explanation.

The hose provided for

the

pilot is

ofahigher flow rate

than those for the passengers; it is

color-coded

with

an

orange

band adjacent

to the

plug-in

fitting. The

passen-

ger hoses are

color-coded

withagreen

band. If

the

air- FUEL

SYSTEMS.

craft

ownýr

prefers, he

may

provide higher

flow hoses

for all passengers. In

any case, it is

recommended that

The

aircraft

contains, as

standard

equipment, an

"ON-OFF"

fuel

the

pilot

asethe larger

capacity

hose. The pilot's mask

shutoff

valve system.

An optional selector

valve system which

provides

is

equipped

with a

microphone to facilitate use of the

fuel tank

selection

capability is also

available. Details

of both systems

radio

white

using

oxygen.

An

adapter

cord

is furnished

are

discussed

in the

following

paragraphs.

Optional

long range

fuel

tanks

with the

niicrophone-equipped

mask to mate

the

mask

are

also

available.

microphone

lead

to

the AUX

MIKE JACK located on

the

left

side of

the

instrument panel.

To connect

the

"ON-OFF"

FUEL

SYSTEM.

oxygen mask

microphone,

connect

the

mask

lead

to the

adapter

cord

and

plug the cord

into the AUX

MIKE

Fuel

is

supplied

to

the

engine from

two

tanks,

one

in each

wing. The

JACK. (If

an optional

microphone-headset

combination

total usable

fuel,

for

all

flight

conditions, is 62

gallons.

has been in

use,

the microphone lead

from

this

equip-

ment is

already

plugged

into the

AUX MIKE JACK. It

Fuel

from each

wing

tank

flows by

gravity

through

a

fuel

accumulator

will be

necessary

to disconnect

this lead from the AUX

tank, shutoff

valve,

fuel

strainer,

by-pass

in

the

electric

auxiliary

fuel

MIKE

JACK so

that

the adapter cord from

the oxygen

pump

(when it is

not

operating)

and

engine-driven

fuel

pump to

the

cylind-

mask

microphone canbeplugged

into the jack.)

A

switch

ers via

a

fuel

control

unit

and manifold.

Vapor

and

excess fuel

from the

is

incorporated

on the left hand control

wheel to

operate

engine-driven

fuel

pump and

fuel

control

unit are

returned

to the

main

the microphone.

fuel

tanks

by

way

of

the fuel

accumulator

tank.

(2) Attach mask

to face and

adjust metallic nose

strap

for

snug

mask

To

provide

fuel

flow

to the

engine, squeeze

together the

double

buttons

fit.

of

the

fuel

shutoff

valve control knob

(located

on the

floor

console),

re-

(3) Select

oxygen outlet located

nearest

to the

seat

you

are

occupy-

leasing

the

lock, and

push the knob full

in. Fuel

will flow

from

both

wing

ing, and

plug

delivery

hose

into

it. When the oxygen

supply is

turned

fuel

tanks

simultaneously.

on, oxygen

will flow

continuously

at

the proper

rate of flow for

any

NOTE

altitude without

any

manual

adjustments.

(4)

Position

oxygen

supply

control

lmob

ON.

With full

fuel, the

tanks

may

not

drain

evenly because

(5) Check the

flow indicator in the

face

mask hose. Oxygen is

flow-

fuel

may be

sloshed into

the interconnect

vent

line,

ing if the

indicator is being forced

toward the mask.

preventing

absolutely equal

vent

pressures

in each

7-10

2-1

FUEL SYSTEM

SCHEMATIC

OXYGEN DURATION

CHART

"Oll-OFF"

FUEL$YSTEM

(48

cuBic FEET CAPACITY)

VENTED FILLER

CAPS

il emninilininninnuiliniu sii

1000

VENT

LFFT FLEl

TANK

RIGHT

¥UEl

TANK

FUEL ACCUMULATOR TANK

TO ENSURE MAXIMUM FUEL CAPACITY DURING REFUEl ING, THE TANKS

SHOUlD

BE

RE-TOPPED

IMMEDIATELY

AFTER

INITIAL

FILLING TO COMPENSATE FOR

- -

CROSS-FEEDING.

IÏuEL-OFF

wa¯

VALVE

FUEL

SHUT-OFF

KNOB

FUEL

-----

ENGINE

STRAINER

ENGINE

FRIMER

CHECK VALVE

AUXILIARY

(FUEL

RETURN)

FUEL PUMP

AUXILIARY

FUEL

PUMP SWITCH

400

ENGINE

01||

lil

FUEL PUMP

THROTTLE

c2TROL

----

O

UNIT

MIXTURE

O

I

2

3

4 5 6

7 8

9

ELF

OXYGEN

DURATION

-

(HOURS)

I

¯¯¯

-CODE-----

FUEL SUPPLY

INU

TION

0001Il000EXCESSFUELAND

NOTE:

This chart

is based on

a pilot with an arange

color.coded

oxygen

NOZZLE

VAPORRETURN

line fitting

and

passengers with green

color-coded

line fittings.

FUEL FLOW

VENT

INDICATV)R

Figure

2-2.

Figure

7-3.

2-2

7-9

Cessna Skywagon 185 1975, A185F Owner's Manual

Specifications and Main Features

Frequently Asked Questions

User Manual