Aeropro A240 Manuale del proprietario

AEROPRO CZ

,

Produc

er

of

Light Sport Aircraft

Mladá 835, 687 25 Hluk, Czech Republic

Pilot Operating Handbook

and

Flight Training Supplement

AEROPRO

A2

4

0

Light Sport Aircraft

Aeropro CZ

-

A2

4

0

-

Pilot Operating Handbook and Flight Training Supplement

Sept

ember 20, 2017

0

-

2

Aircraft Type:

A2

4

0

Serial Number:

____

_

____

Registration:

N

_________

Date of Issue:

September 1, 2016

version 1.0

This aircraft was manufactured in accordance with Light Sport Aircraft airworthiness standards

and does

not conform to standard category airworthiness requirements.

Aeropro CZ

-

A2

4

0

-

Pilot Operating Handbook and Flight Training Supplement

Sept

ember 20, 2017

0

-

3

RECORD OF REVISIONS

Any revisions or amendments to the present manual shall be issued in the form of bulletins with attached

new pages. It is in the interests of every user to enter such re

vision into the table of revisions and to

replace the existing page by the new one. The revised or corrected text shall be indicated by a vertical line

on left page margin and the page shall bear revision number and date of its issue.

Rev. No.

Pages Affec

ted

Date of Issue

Bulletin Number

New Page Inserted On, Signature

Aeropro CZ

-

A2

4

0

-

Pilot Operating Handbook and Flight Training Supplement

Sept

ember 20, 2017

0

-

4

TABLE OF CONTENTS:

RECORD

OF

REVISIONS

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

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

..

0

-

3

0.

GENERAL INFORMATION

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

.....

0

-

7

0.1

I

NTRODUCTION

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

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

0

-

7

0.2

C

ERTIFICATION

B

ASIS

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

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

0

-

7

0.3

M

ANUFACTURER

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

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

0

-

7

0.4

W

ARN

ING

,

C

AUTION AND

N

OTE

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

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

0

-

7

1.

AIRPLANE AND SYSTEMS

DESCRIPTION

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

.

1

-

8

1.1

E

NGINE

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

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

1

-

9

1.2

P

ROPELLER

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

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

1

-

9

1.3

F

UEL AND FUEL CAPACIT

Y

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

......

1

-

9

1.4

O

IL

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

........

1

-

11

1.5

O

PERATING WEIGHTS

&

LOADING

(

OC

CUPANTS

,

BAGGA

GE

,

FUEL

).........

1

-

11

1.6

C

OCKPIT OVERVIEW

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

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

1

-

12

1.7

A

IRCRAFT

E

LECTRICAL

S

YSTEM

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

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

1

-

17

1.8

Electric Backup Fuel Pump..

…………………………………………………….

1

-

1

7

1.9 Additional Equipment........................................................................... 1

-

17

2.

OPERATING LIMITATION

S

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

.

2

-

18

2.1

S

TALL SPEED AT MAXIMU

M TAKE

-

OFF WEIGHT

(VS

AND

VSO)

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

2

-

18

2.2

F

LAPS EXTENDED SPEED

RANGE

(VSO

TO

VFE)

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

...

2

-

18

2.3

M

AXIMUM MANEUVERING S

PEED

(VA)

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

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

2

-

19

2.4

N

EVER EXCEED SPEED

(VNE)

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

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

2

-

19

2.5

C

ROSSWIND AND WIND LI

MITATION

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

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

2

-

19

2.6

S

ERVICE CEILING

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

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

2

-

19

2.7

L

OAD FACTORS

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

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

2

-

19

2.8

P

ROHIBITED MANEUVERS

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

......

2

-

19

2.9

O

THER

L

IMITATIONS

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

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

2

-

20

3.

WEIGHT AND BALANCE I

NFORMATION

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

........

3

-

21

3.1

I

NSTALLED EQUIPMENT L

IST

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

.

3

-

21

3.2

C

ENTER OF GRAVITY

(CG)

RANGE AND DETERMINAT

ION

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

3

-

21

3.2

.1

Weight and balance determination for flight

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

3

-

21

3.2.2

Detailed calculation of CG position

…………………………...…. 3

-

21

4.

PERFORMANCE

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

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

4

-

24

4.1

T

AKE

-

OFF AND LANDING DIST

ANCES

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

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

4

-

24

4.2

R

ATE OF CLIMB

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

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

4

-

24

4.3

C

RUISE SPEEDS

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

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

4

-

24

4.4

RPM

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

.....

4

-

24

4.5

F

UEL CONSUMPTION

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

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

4

-

25

4.6

O

THER PERFORMANCE DAT

A

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

4

-

25

5.

NORMAL PROCEDURES

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

.......

5

-

26

5.1

P

REFLIGHT INSPECTION

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

.........

5

-

26

5.1.1

Daily preparation

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

........

5

-

26

5.1.2

Preflight Inspection

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

......

5

-

28

5.2

E

NGINE STARTING

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

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

5

-

28

5.2.1

Use of External Power Supply

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

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

5

-

29

5.2.2

Engine Starting

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

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

5

-

29

5.3

T

AXIING

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

5

-

29

5.3.1

Prior to taxiing

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

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

5

-

29

Aeropro CZ

-

A2

4

0

-

Pilot Operating Handbook and Flight Training Supplement

Sept

ember 20, 2017

0

-

5

5.3.2

Taxiing

…………………………………………………………………

5

-

29

5.3.3

Engine warm

-

up, power check

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

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

5

-

3

0

5.4

N

ORMAL TAKE

-

OFF

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

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

5

-

30

5.4.1

Prior to tak

e

-

Off

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

...........

5

-

30

5.4.2

Take

-

off

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

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

5

-

31

5.5

B

EST ANGLE OF CLIMB S

PEED

(VX)

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

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

5

-

31

5.5.1

Climbing

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

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

5

-

31

5.6

B

EST RATE OF CLIMB SP

EED

(V

Y

)

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

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

5

-

32

5.6.1

Climbing

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

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

5

-

32

5.7

C

RUISE

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

..

5

-

32

5.7.1

Cruise Flight

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

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

5

-

32

5.8

A

PPROACH

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

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

5

-

32

5.8.1

Descent

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

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

5

-

32

5.8.2

Downwind

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

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

5

-

32

5.9

N

ORMAL LANDING

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

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

5

-

33

5.9.1

On base leg

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

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

5

-

33

5.9.2

On final

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

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

5

-

33

5.9.3

Landing

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

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

5

-

33

5.9.4

After landing

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

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

5

-

33

5.9.5

Engine stopping

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

...........

5

-

33

5.9.6

Post

-

flight check

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

..........

5

-

34

5.10

S

HORT FIELD TAKE

-

OFF AND LANDING PROC

EDURES

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

5

-

34

5.11

A

BORTED LANDING PROCE

DURES

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

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

5

-

34

5.12

I

NFORMATION ON STALLS

,

SPINS AND ANY OTHER

USEFUL PILOT INFORMA

TION

....

5

-

34

5.12.1

Rain

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

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

5

-

34

6.

EMERGENCY PR

OCEDURES

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

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

6

-

35

6.1

I

NTRODUCTION

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

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

6

-

35

6.2

E

NGINE

F

AILURE AND

E

MERGENCY LANDINGS

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

.....

6

-

35

6.2.1

Engine failure during take

-

off Run

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

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

6

-

35

6.2.2

E

ngine failure during take

-

off

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

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

6

-

35

6.2.3

In

-

flight engine failure

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

.

6

-

35

6.2.4

Additional information for engine failure and emergency landing procedures....

6

-

36

6.2.5

Carburetor icing

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

..........

6

-

36

6.3

I

N

-

F

LIGHT

E

NGINE

S

TARTING

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

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

6

-

37

6.4

F

IRES

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

....

6

-

37

6.4.1

Engine fire on the ground

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

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

6

-

37

6.4.2

Engine fire during t

ake

-

off

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

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

6

-

37

6.4.3

Engine fire in

-

flight

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

......

6

-

38

6.4.4

Cockpit or electrical fire

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

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

6

-

38

6.5

G

LIDING

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

6

-

38

6.6

P

RECAUTIONARY

L

ANDING

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

...

6

-

38

6.7

B

LOWN

-

O

UT

T

IRE

L

ANDING

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

.

6

-

39

6.8

D

AMAGED

L

ANDING

G

EAR

L

ANDING

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

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

6

-

39

6.9

V

IBRATIONS OR OTHER E

NGINE PROBLEMS

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

...........

6

-

39

6.10

I

NADVERTENT ICING EN

COUNTER

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

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

6

-

39

6.11

E

XTREME TURBULENCE EN

COUNTER

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

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

6

-

40

6.12

E

LECTRICAL SYSTEM MAL

FUNCTIONS

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

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

6

-

40

6.12.1

Charging

indicator is illuminated

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

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

6

-

40

6.13

I

NADVERTENT

R

ESCUE

S

YSTEM

S

TALL AND SPIN RECOVE

RY

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

6

-

40

6.13.1

The following general procedure should be followed should a stall occur:

6

-

40

6.13.2

The following general procedure should

be followed should a spin occur:

6

-

40

6.14

RESCUE SYSTEM …………………………………………………...6

-

4

0

6.14.1

Operation of Rescue System………………………………………

.

….6

-

4

0

Aeropro CZ

-

A2

4

0

-

Pilot Operating Handbook and Flight Training Supplement

Sept

ember 20, 2017

0

-

6

7.

AIRCRAFT GROUND HAND

LING AND SERVICING

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

7

-

41

7.1

S

ERVICING FUEL

,

OIL

,

COOLANT

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

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

7

-

41

7.1.1

Servicing fuel

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

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

7

-

44

7.1.2

Servicing oil

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

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

7

-

41

7.1.3

Servicing coolant

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

.........

7

-

41

7.2

L

ANDING GEAR TIRE DIM

ENSION AND

PRESSURE

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

...

7

-

42

7.3

T

OWING AND TIE

-

DOWN INSTRUCTIONS

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

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

7

-

42

7.3.1

Aircraft towing instructions

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

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

7

-

45

7.3.2

Aircraft tie

-

down instructions

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

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

7

-

42

7.4

P

ARKING BRAKE OPERA

TION

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

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

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

7

-

42

8.

REQUIRED PLACARDS AN

D MARKINGS

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

.........

7

-

43

8.1

A

IRSPEED INDICATOR RA

NGE MARKINGS

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

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

7

-

43

8.2

O

PER

ATING LIMITATION ON

INSTRUMENT PANEL

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

..

7

-

44

8.3

P

ASSENGER WARNING

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

...........

7

-

44

8.4

“N

O INTENTIONAL SPINS

”

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

......

7

-

44

8.5

M

ISCELLANEOUS PLACARD

S AND MARKINGS

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

........

7

-

44

9.

SUPPLEMENTARY INFORM

ATION

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

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

8

-

45

9.1

F

LIGHT FAMILIARIZATIO

N PROCEDURES

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

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

8

-

45

9.2

P

ILOT OPERATING ADVIS

ORIES

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

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

8

-

45

9.3

F

URTHER

I

NFORMATION

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

.......

8

-

45

10. APPENDIX

10.1 Airplane weight and balance statement………………………………..10

-

1

Aeropro CZ

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A2

4

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Pilot Operating Handbook and Flight Training Supplement

Sept

ember 20, 2017

0

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7

0.

General information

0.1

Introduction

This handbook is provided with your aircraft to allow you to attain as much knowledge about the aircraft

and its opera

tion as possible. This manual is following

ASTM F2746

-

09 Standard Specification for Pilot’s

Operating Handbook (POH) for Light Sport Airplane

. Read this manual thoroughly before your first flight

and make sure you understand all the information contained w

ithin. This aircraft is equipped with a non

-

certified engine that meets the ASTM F

-

2339 engine standard. Flying this aircraft must always be done

with the possibility of a safe landing due to loss of engine power.

Pay attention to the fact that you as the

pilot are fully responsible for the safety of your passengers and

persons or property on the ground.

0.2

Certification basis

This aircraft was manufactured in accordance with Light Sport Aircraft airworthiness standards and does

not conform to standard categ

ory airworthiness requirements.

0.3

Manufacturer

A

eropro

CZ

Mladá 835

687 25 Hluk

Czech Republic

0.4

Warnings, cautions and notes:

In this handbook the following is used to highlight especially important information:

WARNING

Information which could prevent

personnel injury or loss of life

CAUTION

Information which could prevent damage to equipment

NOTE

Information of special importance to pilots

Aeropro CZ

-

A2

4

0

-

Pilot Operating Handbook and Flight Training Supplement

Sept

ember 20, 2017

1

-

8

1.

Airplane and systems description

The

Aeropro

A2

4

0

is an

S

-

LSA

aircraft

designed as a high

-

wing mono

plane. A two

-

spar wing is equipped

with

external airfoil

flaperons. Fuselage is an open truss structure welded of

chromoly

steel tubes. Tail

unit is formed of a lattice

-

work tube frame. The

A2

4

0

is equipped with t

ricycle

-

gear with a steerable

nosewheel

.

Wing area including flaperon

s

…………………

………

……………..

122.53 sq. ft

Chord length (inc

luding flaperon)………………

……….

……………

4.265 ft

Win

g loading...........................................................................

10.1 lbs/sq. ft

Power loading........

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

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

........

12.35 lbs/HP

Aspect

-

ratio

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

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

6.74

:1

Propeller

clearance..........................

..

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

...

.........

1

.5

inches

Aeropro CZ

-

A2

4

0

-

Pilot Operating Handbook and Flight Training Supplement

Sept

ember 20, 2017

1

-

9

1.1

Engine

The

A2

4

0

is powered by the Rotax 912ULS

100

-

hp

engine. It is a four

-

cylinder, four

-

stroke, horizontally

-

opposed, center

-

camshaft engine with overhead valves. Engine cooling is of a combined type; cylinder

heads ar

e water

-

cooled while cylinders are air

-

cooled. The engine has dry

-

sump lubrication. The ignition

system is a dual, electronic and capacitor flywheel magneto type. The engine is equipped with an electric

starter, AC generator and a mechanical fuel deliver

y pump. The propeller is driven by an integrated

reduction gearbox with mechanical damping.

Engine manufacturer

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

.

..

Rotax GmbH., Austria

Engine model.........................

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

Rotax 912ULS

Ma

x. power

-

take

-

off............

...... 100 hp

-

continuous......

....

.

..

94 hp

Max. engine speed (MSL)

-

take

-

off................

5800 RPM (max. 5 min)

-

continuous.....

..

...

.

5500 RPM

Max. cylinder head temperature.......

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

....

280



F

Min. o

il temperature………………………………………

….

…

..

12

2



F for full

-

throttle operation

Normal ope

rating temperature……………………………

….

...

…

190

–

230



F

M

ax. oil temperature....................................................

.

...

.....

.

..

300



F

M

inimum oil pressure……………...................…

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

....

.

..

…

12 psi min oil pressure below 3,500 rpm

M

aximum oil pressu

re (cold start only)…………………

…..

..

.

..

103 psi

N

ormal oil pressure range..........................

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

.........

...

.

..

29

–

73 psi

Oi

l consumption

…………………………………………

…

….

...

max 0.06 quarts/hour

Fuel pressure

-

minimum...............

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

.

....

.18 bar (2.2 psi)

-

maximum.............

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

..

.

.4

bar (5.8

psi)

Pr

opeller gearbox reduction ratio....

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

.

.....

...

.

2.43 : 1

For more details see

Operator’s Manual f

or all versions of

Rotax 912

supplied with the engi

ne.

WARNING

This aircraft is equipped with a non

-

certified engine that

meets

the

ASTM F

-

2339

engine standard.

Flying this aircraft must always be done with the possibility of a safe landing due

to loss of engine power. The pilot is fully responsible for consequences of such

failure.

1.2

Propeller

The

standard

propeller is manu

factured by

Woodcomp

in the

Czech Republic

.

The propeller is a

3

-

blade,

ground

-

adjustable prop.

Propeller

is 68" diameter.

For additional propeller information see

Operators Manual and Technical description

supplied with the

propeller.

1.3

Fuel and fuel cap

acity

Fuel tank capacity

-

wing tanks

(two)............................

.

....

10.6 U.S. gallons each

-

central connecting tank

(header tank)

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

1.

3

U.S. gallons

Max. fuel quantity

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

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

22.

5

U.S. gallons

Usable fuel quantity.........................

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

.

2

.

0

U.S. gallons

Unusable fuel quantity

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

0.

5

U.S. gallons

Fuel specifications…

……....

..

p

remium unleaded auto fuel (Standard Spec. for Automotive

Spark

-

Ignition Engine, Fuel

, ASTM D 4814) or AVGAS 100 LL

Aeropro CZ

-

A2

4

0

-

Pilot Operating Handbook and Flight Training Supplement

Sept

ember 20, 2017

1

-

10

Due to the higher lead content in AVGAS, the wear of the valve seats, deposits in th

e combustion

chamber and lead sediments in the lubrication system will increase. Therefore, use AVGAS only if you

encounter problems with vapor lock or if other fuel types are not available.

For additional information concerning fuel specification consult

the

Operator’s Manual for all versions

of Rotax 912

supplied with the engine.

The fuel system consists of two 10.6 U.S. gallon

s wing tanks, a 1.

1

U.S. gallons

central header tank

behind the left seat, a fuel drain valve positioned below the header tank,

three fuel valves, one fuel filter,

an engine driven fuel pump

,

a backup electric fuel pump (not shown in the diagram below),

and the

connecting fuel lines.

The fuel is gravity

-

fed from the right

-

hand and/or left

-

hand wing tank, through the wing tank fu

el values,

into the central header tank. The fuel is then further directed from the central tank through the fuel filter

and the electric fuel boost pump through the main fuel valve and to the mechanical fuel pump on the

engine which then delivers the fuel

to the carburetors.

The amount of fuel in each tank is indicated by a visual sight tube which is a part of each tank. Minimum

fuel quantity in the central tank is indicated by a red warning light on the instrument panel. The remaining

fuel (0.9 U.S. gall

on), is enough for approximately 10 minutes of flight. The low fuel warning light can be

tested at any time by pushing the control button next to the light on the instrument panel. If the red light

does not light up when the control button is pushed and he

ld, consider the bulb to be blown out and so do

not rely on the minimum fuel quantity warning light:

-

In this case, make a more conservative estimate for

fuel on board, regularly check the fuel quantity in wing tanks and land as soon as you are not confid

ent of

the fuel quantity in the wing tanks.

Although it is normal to leave both wing tank fuel values open, occasionally, one tank will drain faster than

the other. Should this situation occur, manipulate the fuel tank valves to ensure continuous flow of

fuel to

the engine is maintained.

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