EVEKTOR-AEROTECHNIK SPORTSTAR Manual

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Document

EVEKTOR --- AEROTECHNIK, a.s.

Letecká 1384

686 04 Kunovice

Czech Republic

Tel.: +420 572 537 111

Fax: +420 575 537 910 e---mail: [email protected]

http://www.evektor.cz

FLIGHT MANUAL

FOR

SPORTSTAR

ULTRALIGHT AIRPLANE

Serial number:

Registration mark:

Document number: S2005FMENKT

Date of issue: October 20, 2005

This manual must be on the airplane board during operation. This manual contains information which must be provided to the pilot and also contains supplementary information provided by the airplane manufacturer --- Evektor --- Aerotechnik a.s.

This airplane must be operated in compliance with the information and limitations stated in this manual.

EVEKTOR --- AEROTECHNIK, a.s.

FLIGHT MANUAL

Doc. No. S2005FMENKT

0. TECHNICAL INFORMATION

Section 0

Technical

Information

0.1 Log of Revisions

All revisions or supplements to this manual, except actual weighing data, are issued in form of revisions, which will have new or changed pages as appendix and the list of which is shown in the Log of Revisons table.

The new or changed text in the revised pages will be marked by means of black vertical line on the left margin of page and the revision number and date will be shown on the bottom margin of page.

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0.3

General

Limitations

Emergency procedures

Normal procedures

Performance

Weight and balance

Airplane and system description

Airplane handling, servicing and maintenance

Supplements

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Section 1

General

FLIGHT MANUAL

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1. GENERAL

1.1 Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1.2 Certification basis . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1.3 Warnings, cautions, notes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1.4 Descriptive data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1.4.1 Airplane description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1.4.2 Powerplant . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1.4.3 Main technical data

1.4.4 Three---view drawing

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

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

1.5 Definitions and abbreviations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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1.1

Introduction

This Flight manual has been prepared to provide pilots and instructors with information for safe and efficient operation of the SPORTSTAR airplane. It also contains supplementary information considered to be important by the airplane manufacturer.

1.2

Certification basis

This type of airplane meets Standard Specification for Airworthiness of Light Sport

Aircraft.

1.3

Warnings, cautions, notes

The following informations apply to warnings, cautions and notes used in the Flight manual:

WARNING

MEANS THAT NON ---OBSERVATIONS OF THE

CORRESPONDING PROCEDURE LEADS TO AN

IMMEADIATE OR IMPORTENT DEGRADATION OF

THE FLIGHT SAFETY.

CAUTION

MEANS THAT NON---OBSERVATIONS OF THE COR-

RESPONDING PROCEDURE LEADS TO A MINOR OR

TO A MORE OR LESS LONG TERM DEGRADATION

OF THE FLIGHT SAFETY.

NOTE

Draws the attention to any special item not directly related to safety but which is important or unusual.

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General

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1.4

Descriptive data

1.4.1 Airplane description

SPORTSTAR airplane is an all---metal low---wing of semimonocoque structure with two side by side seats and three---wheel landing gear

For further description see chapt. 7 --- Airplane and system description.

1.4.2 Powerplant

The standard powerplant consists of ROTAX 912 S engine and WOODCOMP

KLASSIC 170/3/R propeller.

For further description see section 7 --- Airplane and system description.

If installed other propeller type --- see section 9 --- Supplements.

1.4.3 Main technical data

Wing

Span . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

MAC depth . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Wing loading . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Aileron --- area

Flap --- area

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

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

Fuselage

28.37 ft

112.7 sq.ft

4.1

8.646 m

10.47 sq.m

1.25

10.76 lbs/sq.ft

52.53 kg/sq.m

2.62

sq.ft

0.25

sq.m

5.60

sq.ft

0.52

sq.m

length width height

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

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

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

cockpit canopy max. width

Horizontal tail unit

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

19.62 ft

3.55

7.66

3.87

ft ft ft

Span . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

HTU Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Elevator area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Vertical tail unit

8.20

20.88 sq.ft

8.40

sq.ft

5.980 m

1.082 m

2.335 m

1.180 m

2.50

1.94

0.78

m sq.m

sq.m

Height . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

VTU Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Rudder area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Landing gear

4.07

10.76 sq.ft

4.31

sq.ft

Wheel track

Wheel base

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

Main and nose landing gear wheel diameter . . . . . .

6.12

4.43

14 in

1.24

1.00

sq.m

0.40

sq.m

1.865 m

1.350 m

350 mm

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1.4.4 Three---view drawing

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Section 1

General

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Figure 1-1

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1.5

Definitions and abbreviations

NOTE

The abbreviations on placards in the airplane cockpit, are printed in BOLD CAPITAL LETTERS in the text of this Flight manual.

GPS

HTU

IAS

IFR

ISA

ACCU accumulator

ALT ENC encoding altimeter

ATC bar air traffic control bar 1 bar = 100 kPa

BEACON anti---collision beacon

˚C Celsius degree

CAS

CLOCK calibrated airspeed aircraft clock foot 1 ft = 0.305 m global positioning system horizontal tail unit indicated airspeed intercom instrument flight rules international standard atmosphere lbs m

MAC max.

min.

mm m/s

OAT kg

KIAS

KCAS mph kilogram indicatedair speed in knots calibrated airspeed in knots mile per hour mph CAS indicated airspeed in miles per hour km/h CAS calibrated airspeed in km/h kts litres knots 1 kt = 1.852 km/h litre

OFF

Pa pounds 1 lb = 0.45 kg meter mean aerodynamical chord maximum minimum or minute milimeter meter per second outside air temperature system is switched off or control element is in off---position system is switched on or control element is in on---position pascal 1Pa = 1N/m 2

1--- 6

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FLIGHT MANUAL

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PSI

RPM

RWY sq.ft

pound per sq.in (1PSI = 6.89 kPa) revolutions per minute runway foot squared sq.m

VFR

XPDR meter squared manoeuvring airspeed maximum flap extended speed --- flaps in 50˚ position visibility flight rules

LOF airplane lift---off speed

V---METER voltmeter never exceed speed V

VTU maximum structural cruising speed stall speed with wing flaps in 50˚ position stall speed with wing flaps in 0˚ position vertical tail unit best angle---of---climb speed best rate---of---climb speed transponder

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General

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Section 2

Limitations

FLIGHT MANUAL

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2. LIMITATIONS

2.1 Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.2 Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.3 Airspeed indicator marking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.4 Powerplant . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2 --- 3

2 --- 4

2.5 Powerplant instrument marking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.6 Miscellaneous instrument marking . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.7 Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.8 Centre of gravity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2 --- 5

2 --- 6

2.9 Approved manoeuvres . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.10 Manoeuvring load factors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.11 Flight crew . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.12 Kinds of operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.13 Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2 --- 6

2 --- 7

2 --- 8

2.14 Oil . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.15 Maximum number of passengers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.16 Other limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.17 Limitation placards . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2 --- 8

2 --- 9

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Section 2

Limitations

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Section 2

Limitations

FLIGHT MANUAL

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2.1

Introduction

Section 2 contains operation limitation, instrument marking and basic placards necessary for safe operation of airplane and its engine, standard systems and equipment.

Limitation for optional systems and equipment are stated in section 9 --- Supplements.

2.2

Airspeed

Airspeed limitations and their meaning for operation are stated in the table below:

Maximum flap extended speed

Speed

Never exceed speed

Maximum structural cruising speed

Manoeuvring speed

KIAS mph IAS Meaning

146

103

168

118

Do not exceed this speed in any operation.

Do not exceed this speed, with exception of flight in smooth air, and even then only with increased caution.

Do not make full or abrupt control movement above this speed, because under certain conditions the aircraft may be overstressed by full control movement.

Do not exceed this speed with the given flap setting.

2.3

Airspeed indicator marking

Airspeed indicator markings and their colour---code significance are shown in the table below:

Red line

White arc

October 20, 2005

KIAS

Range mph IAS

37 43

37 --- 70 43 --- 81

S0 at maximum weight (flaps in landing position 50˚)

Operating range with extended flaps.

Lower limit--- V

(flaps 50˚) at maximum weight

Upper limit --- V

2---3

Section 2

Limitations

Green arc

Yellow arc

Red line

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Doc. No. S2005FMENKT

KIAS

Range mph IAS

42 --- 103

103 --- 146

146

49 --- 118

118 --- 168

168

Normal operation range

Lower limit --- V

S1 weight (flaps 0˚) at maximum

Upper limit --- V

Manoeuvres must be conducted with caution and only in smooth air

Maximum speed for all operations ---

2.4

Powerplant

Engine manufacturer:

Engine type:

Power:

Propeller type:

Propeller diameter:

Maximum prop speed:

Bombardier---Rotax GMBH

ROTAX 912 S maximum take---off 100 HP / 73.5 kW

Engine speed: maximum continuous 93.8 HP / 69.0 kW maximum take---off 5800 RPM max. 5 minutes maximum continuous 5500 RPM idle maximum

1400 RPM

135 ˚C 275 ˚F Cylinder head temperature:

Oil temperature:

Oil pressure:

Fuel pressure: maximum optimum operation maximum minimum optimum operation minimum see 2.13, page 2---8 Fuel grades:

Oil grades:

Reducer gear ratio: see 2.14, page 2---8

2.43 : 1

Propeller manufacturer: WOODCOMP s.r.o.

130 ˚C

7 bar

0.8 bar

266 ˚F

90 --- 110 ˚C 190 --- 230 ˚F

102 PSI

12 PSI

2 --- 5 bar 29 --- 73 PSI

0.15 bar 2.2 PSI

KLASSIC 170/3/R

3 blade, composite, on---ground adjustable

68 in 1700 mm

2600 RPM

NOTE

If installed a different propeller type --- see section 9 ---

Supplements for propeller limitations.

2---4 October 20, 2005

Section 2

Limitations

FLIGHT MANUAL

Doc. No. S2005FMENKT

2.5

Powerplant instrument marking

The colour---code of instruments is shown in the following table:

Instrument

RPM indicator

CHT indicator

Units

RPM

˚C

˚F bar

PSI

˚C

˚F

Red line

Lower limit

---

0.8

---

Green arc Yellow arc

Normal operation range

Caution range

1400 ÷ 5500 5500 ÷ 5800

90 ÷ 110

50 ÷ 90

110 ÷ 130

190

---

230

120 ÷ 190

230 ÷ 266

0.8

÷ 2

5 ÷ 7

12 ÷ 29

73 ÷ 102

---

Red line

Upper limit

5800

130

266

102

135

275

2.6

Miscellaneous instrument marking

There are not other instruments with colour marking.

2.7

Weight

Empty weight (standard equipment) . . . . . . . . . . .

695 lbs ± 2 % 315 kg ± 2 %

Maximum take---off weight . . . . . . . . . . . . . . . . . . . .

1213 lbs 550 kg

Maximum landing weight . . . . . . . . . . . . . . . . . . . . .

1213 lbs

Maximum weight in baggage compartment . . . . .

55 lbs

550 kg

25 kg

WARNING

DO NOT EXCEED MAXIMUM WEIGHTS! THEIR EX-

CEEDING LEADS TO AIRPLANE OVERLOADING

AND TO DEGRADATION OF FLIGHT CHARACTER-

ISTICS AND DETERIORATION OF MANOEUVRA-

BILITY.

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Section 2

Limitations

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Doc. No. S2005FMENKT

2.8

Centre of gravity

Empty airplane C.G. position (standard equipment) . . . . . . . . . . .

20 ± 2 %MAC

Operating C.G. range . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

20 to 34 %MAC

Reference datum is the wing leading edge.

2.9

Approved manoeuvres

SPORTSTAR airplane is approved to perform the following manoeuvres:

--- steep turns up to bank angle of 60 °

--- climbing turns

--- lazy eights

--- stalls (except for steep stalls)

--- normal flight manoeuvres

WARNING

AEROBATICS AS WELL AS INTENTIONAL SPINS

ARE PROHIBITED !

2.10 Manoeuvring load factors

Maximum positive load factor . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4.0

Maximum negative load factor . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

---2.0

2.11 Flight crew

Minimum crew . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1 pilot

Minimum weight of crew . . . . . . . . . . . . . . . . . . . . . .

121 lbs 55 kg

Maximum weight of crew . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

acc. to point 6.3

WARNING

DO NOT EXCEED MAXIMUM WEIGHTS! THEIR EX-

CEEDING LEADS TO AIRPLANE OVERLOADING AND

TO DEGRADATION OF FLIGHT CHARACTERISTICS

AND DETERIORATION OF MANOEUVRABILITY.

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Doc. No. S2005FMENKT

2.12 Kinds of operation

Only daylight flights are allowed according to VFR.

WARNING

NIGHT FLIGHTS ACCORDING TO VFR, FLIGHTS

ACCORDING TO IFR (BY INSTRUMENTS) AND IN-

TENTIONAL FLIGHTS UNDER ICING CONDITIONS

ARE PROHIBITED.

Instruments and equipment for daylight flights according to VFR :

1 Airspeed indicator (the colour marking according to par. 2.3)

1 Sensitive barometric altimeter

1 Magnetic compass

1 Fuel gauge indicator

1 Oil temperature indicator

1 Oil pressure indicator

1 Cylinder head temperature indicator

1 Engine speed indicator

1 Safety harness for every used seat

CAUTION

ADDITIONAL EQUIPMENT NECESSARY FOR AIR-

PLANE OPERATION IS GIVEN IN APPROPRIATE

OPERATION REGULATION OF AIRPLANE OPERA-

TOR’S COUNTRY.

Section 2

Limitations

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Section 2

Limitations

FLIGHT MANUAL

Doc. No. S2005FMENKT

2.13 Fuel

Fuel tank volume (each) . . . . . . . . . . . . . . . . . . . . . .

15.85 U.S. gallons 60 litres

Total . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

31.7 U.S. gallons . .

120 litres

Usable fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

31.2 U.S. gallons 118 litres

Unusable fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

0.5 U.S. gallons 2.0 litres

(0.25 USGal/1 liter per tank)

NOTE

It is not recommended to fully tank the fuel tanks.

Due to fuel thermal expansion keep about 2.11U.S.

gallons (8.0 litres) of free space in the tank to prevent fuel bleed through the vents in the wing tips thus preventing environmental contamination. This should be adhered especially when cold fuel from an underground tank is tanked.

Approved fuel grades:

--- automotive petrol with min RON 95

--- EN 228 Premium

--- EN 228 Premium plus

--- AVGAS 100 LL

Due to higher lead content in AVGAS, the wear of valve seats and deposits in the combustion chamber and lead sediments in the lubrication system will increase.

Therefore, use AVGAS only if you encouter problem with vapour lock or if the other fuel types are not available

For other suitable fuel types refer to the engine Operator’s Manual

NOTE

Use only fuel suitable for the respective climatic zone.

Risk of vapour formation if using winter fuel for summer operation.

2.14 Oil

Performance classification SF, SG according to API

Oil volume:

--- minimum . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

--- maximum . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

0.53 U.S. gallons

0.79 U.S. gallons

2.15 Maximum number of passengers

Maximum number of passengers including pilot .

2---8

2.0 litres

3.0 litres

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FLIGHT MANUAL

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2.16 Other limitations

--- SMOKING IS PROHIBITED on the airplane board.

2.17 Limitation placards

The following placard is located on the instrument panel:

The following placard is located in the baggage compartment:

Section 2

Limitations

The following placards are located on the tilting canopy: or or

October 20, 2005

NOTE

The values stated on the placard “LOAD LIMITS” are valid for the empty weight of the airplane with standard equipment. The placard with values valid for the actual empty weight of the airplane will be placed in the cockpit.

Other placards and labels are shown in Maintenance

Manual.

2---9

Section 2

Limitations

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Section 3

Emergency

Procedures

3. EMERGENCY PROCEDURES

3.1 Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.2 Speeds for performing emergency procedures

3.3 Engine failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.3.1 Engine failure at take---off run

3.3.2 Engine failure at take---off

3.3.3 Engine failure at flight

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

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

3.4 Engine starting at flight

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

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

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

3.5 Engine fire . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.5.1 Fire on the ground . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.5.2 Fire during take---off . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.5.3 Fire at flight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.6 Fire in the cockpit (if manual extinguisher available aboard) . . . . . .

3 --- 5

3---5

3 --- 6

3 --- 3

3---3

3---4

3 --- 4

3.7 Gliding flight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.8 Emergency landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.8.1 Emergency landing --- with non---operating engine

3.8.2 Safety landing--- with engine operating

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

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

3.8.3 Landing with burst tire . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.8.4 Landing with damaged landing gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3 --- 7

3---7

3---8

3.9 Unintentional spin recovery . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.10 Other emergency procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.10.1Vibration

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

3.10.2Carburettor icing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3 --- 8

3 --- 9

3---9

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Section 3

Emergency

Procedures

3.1

Introduction

Section 3 describes operations and procedures for emergency situation solutions that could possibly occur during airplane operation.

3.2

Speeds for performing emergency procedures

Airspeed for the best gliding ratio (flaps retracted) 57 KIAS (66 mph IAS)

Precautionary landing

(engine running, flaps in landing position --- 50˚) 48 KIAS (55 mph IAS)

Emergency landing

(engine stopped, flaps in landing position --- 50˚) 48 KIAS (55 mph IAS)

3.3

Engine failure

3.3.1 Engine failure at take---off run

THROTTLE lever . . . . . . . . . . . . . . . . . . . . . . . . .

2. Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FUEL SELECTOR . . . . . . . . . . . . . . . . . . . . . . . .

4. Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

MASTER SWITCH . . . . . . . . . . . . . . . . . . . . . . . .

idle as necessary

OFF

3.3.2 Engine failure at take---off

1. Gliding speed:

Flaps in take---off position (15˚) . . . . . . . . . . . . .

Flaps retracted (0˚) . . . . . . . . . . . . . . . . . . . . . . .

2. Altitude:

--- Land in take---off direction if below 150 ft:

--- Choose an area for landing if above 150 ft:

THROTTLE lever . . . . . . . . . . . . . . . . . . . . . . . . .

4. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FUEL SELECTOR . . . . . . . . . . . . . . . . . . . . . . . .

6. Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

MASTER SWITCH . . . . . . . . . . . . . . . . . . . . . . . .

8. After touch down . . . . . . . . . . . . . . . . . . . . . . . . .

52 KIAS (60 mph IAS)

57 KIAS (66 mph IAS) idle as necessary

OFF

OFF brake according to need

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3.3.3 Engine failure at flight

1. Gliding speed . . . . . . . . . . . . . . . . . . . . . . . . . . . .

57 KIAS (66 mph IAS)

2. Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

take a decision and carry out:

--- Engine starting at flight --- paragraph 3.4, page 3---4

--- Emergency landing --- paragraph 3.8.1, page 3---7

3.4

Engine starting at flight

NOTE

It is possible to to start the engine by means of the starter within the whole range of operation speeds as well as flight altitudes. The engine started up immediately after switching the ignition to START position.

If the propeller is shut down, the altitude loss during engine starting can reach up to 1000 ft.

1. Gliding speed . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2. Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

57 KIAS (66 mph IAS) check

MASTER SWITCH . . . . . . . . . . . . . . . . . . . . . . . .

4. Unnecessary electrical equipment . . . . . . . . . .

FUEL SELECTOR . . . . . . . . . . . . . . . . . . . . . . . .

6. Choke . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

THROTTLE lever . . . . . . . . . . . . . . . . . . . . . . . . .

ON switch off

LEFT as necessary idle

The propeller is rotating:

8. Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

BOTH

The propeller is not rotating:

9. Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

START

10. If engine starting does not occur, increase gliding speed up to 108 KIAS

(124 mph IAS) (see NOTE), so that air---flow turns the propeler and engine starting occurs.

11. Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

BOTH

12. If engine starting is unsuccessful, then continue according to paragraph 3.8.1

Emergency landing.

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3.5

Engine fire

3.5.1 Fire on the ground

FUEL SELECTOR . . . . . . . . . . . . . . . . . . . . . . . .

2. Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

OFF

THROTTLE lever . . . . . . . . . . . . . . . . . . . . . . . . .

COCKPIT HEATING knob . . . . . . . . . . . . . . . . .

brake full close

HOT AIR knob (if installed) . . . . . . . . . . . . . . . . .

6. Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

MASTER SWITCH . . . . . . . . . . . . . . . . . . . . . . . .

8. Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

9. Manual extinguisher (if available) . . . . . . . . . . .

OFF

OFF leave use

3.5.2 Fire during take---off

FUEL SELECTOR . . . . . . . . . . . . . . . . . . . . . . . .

THROTTLE lever . . . . . . . . . . . . . . . . . . . . . . . . .

OFF

4. Gliding speed . . . . . . . . . . . . . . . . . . . . . . . . . . . .

full

HOT AIR knob (if installed) . . . . . . . . . . . . . . . . .

52 KIAS (60 mph IAS)

5. Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

6. Land

MASTER SWITCH . . . . . . . . . . . . . . . . . . . . . . . .

OFF

8. Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

9. Manual extinguisher (if available) . . . . . . . . . . .

OFF immediately after touch---down leave use

3.5.3 Fire at flight

FUEL SELECTOR . . . . . . . . . . . . . . . . . . . . . . . .

THROTTLE lever . . . . . . . . . . . . . . . . . . . . . . . . .

OFF full

HOT AIR knob (if installed) . . . . . . . . . . . . . . . . .

Section 3

Emergency

Procedures

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4. Gliding speed . . . . . . . . . . . . . . . . . . . . . . . . . . . .

57 KIAS (66 mph IAS)

5. Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

OFF

MASTER SWITCH . . . . . . . . . . . . . . . . . . . . . . . . .

OFF

NOTE

For extinguishing the engine fire, you can perform slip under assumption that you have enough altitude and time.

If you manage to extinguish the engine fire, then it is possible to switch on the MASTER SWITCH again.

You will switch off all the section switches and after switching on the MASTER SWITCH the electrical system is switched on which is necessary to complete the flight.

7. Emergency landing . . . . . . . . . . . . . . . . . . . . . . .

8. Airplaine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

9. Manual extinguisher (if available) . . . . . . . . . . .

carry out according to paragraph 3.8.1

leave use

3.6

Fire in the cockpit (if manual extinguisher available aboard)

1. Fire source . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

identify

MASTER SWITCH in case that the source of fire is electrical equipment.

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

3. Manual extinguisher . . . . . . . . . . . . . . . . . . . . . . .

4. After fire extinguishing . . . . . . . . . . . . . . . . . . . . .

OFF use aerate the cockpit

5. Carry out safety landing according to 3.8.2

3---6

WARNING

NEVER AGAIN SWITCH THE DEFECTIVE SYSTEM.

NOTE

If a defective electrical system circuit was detected as the fire source, then switch off appropriate circuit breaker and switch over MASTER SWITCH to ON position.

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3.7

Gliding flight

NOTE

Gliding flight can be used for example in case of engine failure.

Section 3

Emergency

Procedures

Wing flaps position

Airspeed

Retracted (0˚) Take---off (15˚)

57 KIAS

(66 mph IAS)

52 KIAS

(60 mph IAS)

3.8

Emergency landing

3.8.1 Emergency landing --- with non---operating engine

1. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2. Landing area . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3. Safety harness

4. Flaps

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

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

5. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

6. Radiostation . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

57 KIAS (66 mph IAS) choose, determine wind direction tighten up landing position (50˚)

48 KIAS (55 mph IAS) notify situation to ATC --- if possible

OFF 7.

FUEL SELECTOR . . . . . . . . . . . . . . . . . . . . . . . .

8. Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

MASTER SWITCH . . . . . . . . . . . . . . . . . . . . . . .

OFF

OFF before touch down

3.8.2 Safety landing--- with engine operating

1. Area for landing . . . . . . . . . . . . . . . . . . . . . . . . . .

choose, determine wind direction, carry out passage flight with speed of 59 KIAS

(68 mph IAS),flaps in take---off position (15˚)

2. Radiostation . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3. Safety harness . . . . . . . . . . . . . . . . . . . . . . . . . . .

notify situation to ATC --- if possible tighten up

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4. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

6. Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

landing position (50˚)

48 KIAS (55 mph IAS) carry out

3.8.3 Landing with burst tire

CAUTION

WHEN LANDING AT HOLDING, KEEP THE WHEEL

WITH BURST TIRE ABOVE THE GROUND AS LONG

AS POSSIBLE BY MEANS OF AILERONS. IN CASE OF

NOSE WHEEL BY MEANS OF ELEVATOR.

1. At running hold airplane direction by means of foot control and brakes

3.8.4 Landing with damaged landing gear

1. In case of nose landing gear damage touch down at the lowest possible speed and try to keep the airplane on main landing gear wheels as long as possible

2. In case of main landing gear damage touch down at he lowest possible speed and if possible keep direction at running

3.9

Unintentional spin recovery

NOTE

The airplane has not, when using normal techniques of pilotage, tendency to go over to spin spontaneously.

Standard procedure of recovery from spin:

THROTTLE

2. Control stick

3. Pedals lever . . . . . . . . . . . . . . . . . . . . . . . . .

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

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

4. Control stick . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

idle ailerons --- neutral position push down the pedal against the sense of rotation push froward and hold the power lever until rotation stops

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5. Pedals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

6. Control stick . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Section 3

Emergency

Procedures immediately after rotation stopping, set the rudder to neutral position recover the diving

CAUTION

ALTITUDE LOSS PER ONE TURN AND RECOVERING

FROM THE SPIN IS 500 UP TO 1000 ft.

3.10 Other emergency procedures

3.10.1Vibration

If abnormal vibrations occur on the airplane then:

1. Set engine RPM to the mode in which the vibrations are the lowest

2. Land on the nearest possible airport, possibly perform safety landing according to par. 3.8.2. Safety landing.

3.10.2Carburettor icing

Carburettor icing happens when air temperature drop in the carburettor occurs due to its acceleration in the carburettor and further cooling by evaporating fuel. Carburettor icing mostly happens during descending and aproaching for landing (low engine RPM). Carburettor icing shows itself by engine power decreasing and by engine temperature increasing.

Recommended procedure for engine power regeneration is as follows:

CARBURETTOR PREHEATER (if installed) . .

THROTTLE lever . . . . . . . . . . . . . . . . . . . . . . . . .

ON set idle and cruising power again

NOTE

Ice coating in the carburettor should be removed by decrease and reincrease of engine power.

3. If the engine power is not successfully increased, then carry out landing at the nearest suitable airport or, if it is not possible, carry out precautionary landing according to par. 3.8.2 Precautionary landing.

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Section 4

Normal

Procedures

4. NORMAL PROCEDURES

4.1 Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4.2 Recommended speeds for normal procedures . . . . . . . . . . . . . . . . . .

4.2.1 Take---off . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4.2.2 Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4.3 Assembly and disassembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4.4 Pre --- flight check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4 --- 3

4.5 Normal procedures and checklist

4.5.1 Before engine starting

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

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

4.5.2 Engine starting

4.5.3 Before taxiing

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

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

4.5.4 Taxiing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4.5.5 Before take---off . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4.5.6 Take---off . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4.5.7 Climb

4.5.8 Cruise

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

4.5.9 Descent . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4.5.10Before landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4.5.11Balked landing

4.5.12Landing

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

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

4.5.13After landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4.5.14Engine shut---off . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4.5.15Airplane parking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4 --- 7

4---7

4---8

4---9

4---11

4---12

4---13

4---14

4 --- 3

4---3

4 --- 3

4 --- 4

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Section 4

Normal

Procedures

4.1

Introduction

Section 4 describes operations and recommended procedures for normal operation of the airplane. Normal procedures following from system installation and optional equipment, which require supplementation of this Manual, are shown in section 9 --- Supplements.

4.2

Recommended speeds for normal procedures

4.2.1 Take---off

Climbing speed up to 50 ft

(flaps in take---off pos. --- 15˚) . . . . . . . . . . . . . . . . .

55 KIAS (63 mph IAS)

Best rate---of---climb speed V

(flaps in take---off pos. --- 15˚) . . . . . . . . . . . . . . . . . .

55 KIAS (63 mph IAS)

Best rate---of---climb speed V

(flaps retracted --- 0˚) . . . . . . . . . . . . . . . . . . . . . . . . .

62 KIAS (71 mph IAS)

Best angle---of---climb speed V

(flaps in take---off pos. --- 15˚) . . . . . . . . . . . . . . . . . . .

52 KIAS (60 mph IAS)

Best angle---of---climb speed V

(flaps retracted --- 0˚) . . . . . . . . . . . . . . . . . . . . . . . .

56 KIAS (64 mph IAS)

4.2.2 Landing

Approaching speed for normal landing

(flaps in landing position --- 50˚) . . . . . . . . . . . . . .

48 KIAS (55 mph IAS)

4.3

Assembly and disassembly

Description of assembly and disassembly is given in the SPORTSTAR. Maintenance Manual.

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Normal

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4.4

Pre --- flight check

Carry out pre---flight check according to the following procedure:

Figure 4-1 Scheme of airplane pre---flight check

WARNING

CHECK BEFORE PRE --- FLIGHT CHECK THAT

IGNITION IS SWITCHED OFF !

4---4

NOTE

The word “condition”, used in procedures of pre--flight check, means visual check of surface, damage, deformation, scratches, attrition, corrosion, icing or other effects decreasing flight safety.

1. Left landing gear leg --- check

D landing gear leg attachment and condition

D landing gear wheel condition

D tire condition and inflation

D condition and attachment of wheel covers, mudguards (if installed)

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Section 4

Normal

Procedures

2. Left wing --- check

D wing surface condition

D leading edge condition

D landing light condition --- if installed

D condition of the Pitot tube

D draining of fuel tank (see chapter 8.5, page 8---6)

D closing of the fuel tank cap

3. Left wing tip --- check

D surface condition

D attachment check

D fuel tank vent --- cleanness

D condition and attachment of the position lights and the anticollision beacon

--- if installed

4. Left aileron --- check

D surface condition

D attachment

D free movement

5. Left wing flap --- check

D surface condition

D attachment

6. Rear part of fuselage --- check

D surface condition

D condition of antennas (top and bottom fuselage surface) --- if installed

7. Tail units --- check

D tail skid condition

D surface condition

D condition of rudder and elevator attachment

D freedom of rudder and elevator movement

D condition of trim tab, condition of elevator trim tab control

8. Rear part of fuselage --- check

D surface condition

9. Right wing flap--- see 5.

10. Right aileron--- see 4.

11. Right wing tip --- see 3.

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12. Right wing --- see 2. except the landing light (if installed) and Pitot tube

13. Right landing gear leg --- see 1.

14. Front part of the fuselage --- right hand side --- check

D tilting canopy attachment and condition

D condition of the nose landing gear leg

D nose wheel condition

D condition of the nose weel control rods

15. Engine

Checks before the first flight of day --- it is necessary to remove upper engine cowling:

D condition of engine bed

D condition of engine attachment

D condition of exhaust system

D condition of engine cowlings

D visual check on fuel and electrical system condition

D check on cooling liquid volume in the expansion tank on the engine body

(replenish as required up to max. 2/3 of the expansion tank volume)

Checks before every flight:

D cleanness of air intakes

D check on oil level (between marks --- flattenings on the dip stick)

D check on cooling liquid level in the overflow bottle (level should be between min. and max. mark)

D proper closing of the upper cowling

16. Propeller --- check

D attachment

D condition of blades, hub and spinner

17. Front part of fuselage --- left hand side --- check

D tilting canopy attachment and condition

18. Cockpit --- check

NOTE

Turn handle clockwise to open cockpit. When keyway is in hadle axis, cockpit is locked. Unlock it first with key to keyway perpendicular position to the handle axis.

D receivers of condensate

(only before the first flight of day) . . . . .

check on absence of water

4---6 October 20, 2005

FLIGHT MANUAL

Doc. No. S2005FMENKT

Section 4

Normal

Procedures

D all switches . . . . . . . . . . . . . . . . . . . . . . .

D instrument equipment . . . . . . . . . . . . . .

OFF check on condition

D check on presence of loose object in the cockpit

D check on adjusting and securing the rudder pedals (see section 7.3.3, page

7---4) --- if installed adjustable rudder pedals

WARNING

RIGHT AND LEFT PEDAL OF RUDDER CONTROL

MUST BE SET TO THE SAME POSITIONS AND

WELL SECURED!

D Flight Manual and other required documents . . . . . . . . . . . . . . . . . . . . . . . .

check on completness and validity

4.5

Normal procedures and checklist

4.5.1 Before engine starting

1. Pre---flight check and check on weight and centre of gravity position . . . . . . . .

2. Safety harnesses . . . . . . . . . . . . . . . . . . . . . . . . .

3. Control stick . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4. Rudder pedals . . . . . . . . . . . . . . . . . . . . . . . . . . .

5. Wing flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

6. Trim tab . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PARKING BRAKE handle (if installed) . . . . . . .

8. Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

9. Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

10. Canopy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

done check, fasten free free function check function check release brakes function check

OFF close

October 20, 2005 4---7

Section 4

Normal

Procedures

FLIGHT MANUAL

Doc. No. S2005FMENKT

4.5.2 Engine starting

MASTER SWITCH . . . . . . . . . . . . . . . . . . . . . . . .

7. Space in the propeller area . . . . . . . . . . . . . . . .

BEACON (if installed) . . . . . . . . . . . . . . . . . . . . .

9. Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2. Fuel gauge indicators . . . . . . . . . . . . . . . . . . . . .

check of fuel quantity

FUEL SELECTOR . . . . . . . . . . . . . . . . . . . . . . . .

LEFT

Pull the safety button on the fuel selector, turn the handle to the left and then release safety button. Now the handle can be freely moved between left and right position. Safety button prevents unintentionally switch the selector to OFF position.

4. Electric fuel pump (if installed) . . . . . . . . . . . . . . .

THROTTLE lever . . . . . . . . . . . . . . . . . . . . . . . . .

idle

6. Choke . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

as necessary

(open by pulling up and lock by turning) free

ON (if necessary)

START (see CAUTION) after starting up BOTH

4---8

CAUTION

ACTIVATE STARTER FOR 10 SEC. AS A MAXIMUM,

THEN LET IT COOL DOWN FOR 2 MINUTES.

AFTER STARTING UP ENGINE, DO NOT CARRY OUT

SUDDEN RPM CHANGES, AFTER POWER DE-

CREASE WAIT FOR ABOUT 3 S IN ORDER TO REACH

CONSTANT RPM BEFORE REACCELERATION.

10.

THROTTLE

11. Oil pressure lever . . . . . . . . . . . . . . . . . . . . . . . . .

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

as necessary (see NOTE) up to 10s min. pressure

12. Electric fuel pump (if installed) . . . . . . . . . . . . . . .

OFF

NOTE

After starting up engine, adjust throttle for smooth engine running at about 2500 RPM. Check oil pressure.

Pressure must increase within 10s. Increase engine

RPM until oil pressure is stabilised over 2 bar (29 PSI).

Electric fuel pump operates during engine starting period only. It is not intended for long continuous operation for long time.

October 20, 2005

FLIGHT MANUAL

Doc. No. S2005FMENKT

13. Engine instruments . . . . . . . . . . . . . . . . . . . . . . .

14. Choke . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

15. Engine warming up . . . . . . . . . . . . . . . . . . . . . . .

check as necessary see NOTE

NOTE

Begin warming up with engine running at 2000 RPM.

for about 2 minutes, continue at 2500 RPM. Warming time depends on outside air temperature until oil temperature reaches 50 ˚ C (122 ˚F).

16.

FUEL SELECTOR . . . . . . . . . . . . . . . . . . . . . . . .

RIGHT

Verify proper engine feeding from the right tank for approx. 1 minute.

17.

FUEL SELECTOR . . . . . . . . . . . . . . . . . . . . . . . .

LEFT

NOTE

Start engine with the fuel selector set to to LEFT . If you would start the engine with the fuel selector set to

RIGHT and the left tank is full, than fuel bleed from the left tank vent may occur (and pollute environment) because a fuel return hose is led only into the left tank and returning fuel will overfill the left tank.

18. Radiostation/avionics . . . . . . . . . . . . . . . . . . . . . .

19. Other electrical equipment . . . . . . . . . . . . . . . . .

ON as necessary

Section 4

Normal

Procedures

4.5.3 Before taxiing

1. Transponder (if installed) . . . . . . . . . . . . . . . . . .

2. Outside lights (if installed) . . . . . . . . . . . . . . . . .

SBY as necessary

4.5.4 Taxiing

THROTTLE

2. Brakes lever . . . . . . . . . . . . . . . . . . . . . . . . .

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

as necessary check by depressing

3. Rudder pedals . . . . . . . . . . . . . . . . . . . . . . . . . . .

function check

4. Direction of taxiing --- control by rudder pedals (these are mechanically connected with nose wheel control), possibly by slacking up left and right wheel of the main landing gear.

4.5.5 Before take---off

1. Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2. Ignition check . . . . . . . . . . . . . . . . . . . . . . . . . . . .

brake carry out, see NOTE

October 20, 2005 4---9

Section 4

Normal

Procedures

FLIGHT MANUAL

Doc. No. S2005FMENKT

NOTE

Carry out ignition check in the following way :

Set engine speed to 4000 RPM. Switch ignition gradually to L , BOTH , R position and return to BOTH ..

RPM drop with one ignition circuit switched off must not exceed 300 RPM. Maximum RPM difference at using one of the L or R circuits is 120 RPM.

3. Engine instruments

4. Control stick

5. Wing flaps

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

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

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

6. Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

check free take---off pos. (15˚)

NEUTRAL

7. Fuel gauge indicators . . . . . . . . . . . . . . . . . . . . .

FUEL SELECTOR . . . . . . . . . . . . . . . . . . . . . . . .

CARBURETTOR PREHEATER (if installed) . .

check on fuel quantity check LEFT check function then OFF

NOTE

If CARBURETTOR PREHEATER is switched ON , then engine RPM drop reaches approximately 50 RPM

10. Engine instruments . . . . . . . . . . . . . . . . . . . . . . .

check

11. Flight instruments

13. Ignition

14. Choke

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

12. Radiostation / avionics . . . . . . . . . . . . . . . . . . . .

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

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

check check, set check BOTH close (in inserted position)

15.

MASTER SWITCH

16. Safety harnesses

17. Canopy

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

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

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

18. Transponder (if installed) . . . . . . . . . . . . . . . . . .

check ON tighten up closed

ON or ALT

4---10 October 20, 2005

FLIGHT MANUAL

Doc. No. S2005FMENKT

4.5.6 Take---off

THROTTLE lever . . . . . . . . . . . . . . . . . . . . . . . . .

Section 4

Normal

Procedures max. take---off power

2. During take---off run smootly lighten up the nose landing gear until airplane take---off occurs.

3. Airpeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4. Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5. After reaching 150 ft , set flaps to

6. Trim

. . . . . . . . . .

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

55 KIAS (63 mph IAS) brake retracted pos. (0˚) as necessary

WARNING

TAKE --- OFF IS PROHIBITED:

SSSS IF ENGINE RUNNING IS IRREGULAR

SSSS IF CHOKE IS OPEN

SSSS IF VALUES OF ENGINE INSTRUMENTS ARE NOT

WITHIN THE REQUIRED RANGE

4.5.7 Climb

THROTTLE lever . . . . . . . . . . . . . . . . . . . . . . . . .

2. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

max. continuous power

62 KIAS (71 mph IAS)

3. Engine instruments . . . . . . . . . . . . . . . . . . . . . . .

4. Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

check as necessary

4.5.8 Cruise

THROTTLE lever . . . . . . . . . . . . . . . . . . . . . . . . .

2. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3. Engine instruments . . . . . . . . . . . . . . . . . . . . . . .

4. Fuel quantity . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

as necessary

103 KIAS (118 mph IAS) check check

CAUTION

FUEL GAUGES DISPLAY TRUE FUEL QUANTITY

ONLY ON GROUND AND IN A LEVEL FLIGHT. TO

READ TRUE FUEL QUANTITY AFTER TRANSITION

FROM CLIMB/DESCENT WAIT APPROX. 2 MINUTES

TO FUEL TO LEVEL.

FUEL SELECTOR . . . . . . . . . . . . . . . . . . . . . . . .

as required

October 20, 2005 4---11

Section 4

Normal

Procedures

FLIGHT MANUAL

Doc. No. S2005FMENKT

NOTE

It is recommended to alternately switch the tanks during cruise to equally consume fuel from both tanks and minimize airplane tendency to bank with unbalanced tanks.

Do not fly with the fuel selector set to RIGHT if the left tank is full to avoid fuel bleed from left tank vent.

When the left tank fuel gauge indicates approx. 1/8 of fuel quantity (needle in the middle between 1/4 and 0) then switch to the right tank to consume remaining fuel and then switch back the left tank to complete the flight at left tank. If the engine conks out due to fuel consumption from either tank, then immediately switch the fuel selector to other tank and engine run will be recovered within 7 seconds.

CARBURETTOR PREHEATER (if installed) . .

as necessary

4.5.9 Descent

THROTTLE lever . . . . . . . . . . . . . . . . . . . . . . . . .

2. Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3. Engine instruments . . . . . . . . . . . . . . . . . . . . . . .

CARBURETTOR PREHEATER (if installed) . .

as necessary as necessary check as necessary

CAUTION

AT LONG APPROACHING AND DESCENDING FROM

HIGH ALTITUDE IT IS NOT SUITABLE TO REDUCE

THROTTLE TO MINIMUM FOR THE REASON OF POS-

SIBLE ENGINE UNDERCOOLING AND SUBSEQUENT

LOSS OF POWER. PERFORM DESCENDING AT IN-

CREASED IDLE AND CHECK OBSERVANCE OF THE

ALLOWED VALUES ON ENGINE INSTRUMENTS.

4.5.10Before landing

1. Fuel quantity . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

check

CAUTION

FUEL GAUGES DISPLAY TRUE FUEL QUANTITY

ONLY ON GROUND AND IN A LEVEL FLIGHT. TO

READ TRUE FUEL QUANTITY AFTER TRANSITION

FROM CLIMB/DESCENT WAIT APPROX. 2 MINUTES

TO FUEL TO LEVEL.

4---12 October 20, 2005

FLIGHT MANUAL

Doc. No. S2005FMENKT

FUEL SELECTOR . . . . . . . . . . . . . . . . . . . . . . . .

3. Engine instruments . . . . . . . . . . . . . . . . . . . . . . .

4. Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5. Safety harnesses . . . . . . . . . . . . . . . . . . . . . . . . .

6. Free area of landing . . . . . . . . . . . . . . . . . . . . . . .

CARBURETTOR PREHEATER (if installed) . .

LEFT check check by depressing pedals tighten up check

Section 4

Normal

Procedures

8. Approaching speed . . . . . . . . . . . . . . . . . . . . . . . .

59 KIAS (68 mph IAS)

9. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

take---off pos. (15˚)

10. Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

as necessary

FINAL

1. Flaps

2. Maintain airspeed . . . . . . . . . . . . . . . . . . . . . . . . . .

48 KIAS (55 mph IAS)

3. Trim

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

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

CARBURETTOR PREHEATER (if installed) . .

landing pos. (30˚ or 50˚) as necessary

OFF

4.5.11Balked landing

THROTTLE

2. Flaps lever . . . . . . . . . . . . . . . . . . . . . . . . .

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

max. take---off power take---off pos. (15˚ )

3. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

55 KIAS (63 mph IAS)

4. Flaps in 150 ft . . . . . . . . . . . . . . . . . . . . . . . . . . . .

retracted pos. (0˚)

5. Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

THROTTLE lever . . . . . . . . . . . . . . . . . . . . . . . . .

7. Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

8. Climb at airspeed . . . . . . . . . . . . . . . . . . . . . . . . .

as necessary max. continuous power check

62 KIAS (71 mph IAS)

4.5.12Landing

THROTTLE lever . . . . . . . . . . . . . . . . . . . . . . . . .

2. Touch---down on main landing gear wheels . .

3. Brakes after nose landing gear wheel touch---down . . . . . . . . . . . . . . . . . . . . . . .

idle carry out as necessary

October 20, 2005 4---13

Section 4

Normal

Procedures

FLIGHT MANUAL

Doc. No. S2005FMENKT

4.5.13After landing

1. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2. Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3. Outside lights (if installed) . . . . . . . . . . . . . . . . .

4. Transponder (if installed) . . . . . . . . . . . . . . . . . .

retracted pos. (0˚)

NEUTRAL

OFF

4.5.14Engine shut---off

THROTTLE lever . . . . . . . . . . . . . . . . . . . . . . . . .

2. Engine instruments . . . . . . . . . . . . . . . . . . . . . . .

3. Radiostation / avionics . . . . . . . . . . . . . . . . . . . .

4. Other electrical equipment . . . . . . . . . . . . . . . . .

5. Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

BEACON (if installed) . . . . . . . . . . . . . . . . . . . . .

MASTER SWITCH . . . . . . . . . . . . . . . . . . . . . . . .

idle check

OFF

4.5.15Airplane parking

1. Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

MASTER SWITCH . . . . . . . . . . . . . . . . . . . . . . . .

check OFF check OFF

FUEL SELECTOR . . . . . . . . . . . . . . . . . . . . . . . .

OFF

Pull the safety button on the fuel selector, turn the handle to the OFF position and then release safety button. Now the handle is blocked in the OFF position.

Safety button prevents unintentionally switch the selector from the OFF position.

PARKING BRAKE handle (if installed) . . . . . . .

5. Canopy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

brake as necessary close, lock as necessary

NOTE

It is recommended to use parking brake (if installed) for short---time parking only, between flights during a flight day. After ending the flight day or at low temperatures of ambient air, do not use parking brake, but use the wheel chocks instead.

4---14 October 20, 2005

Section 5

Performance

FLIGHT MANUAL

Doc. No. S2005FMENKT

5. PERFORMANCE

5.1 Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5.2 Approved data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5.2.1 Airspeed indicator system calibration

5.2.2 Stall speeds

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

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

5.2.3 Take---off distance

5.2.4 Landing distance

5.2.5 Climb performance

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

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

5.3 Additional information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5.3.1 Cruise . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5.3.2 Horizontal speeds . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5.3.3 Endurance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5.3.4 Balked landing climb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5.3.5 Effect on flight performance and characteristics . . . . . . . . . . . . . . . . . . . .

5.3.6 Demonstrated crosswind performance

5.3.7 Ceiling

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

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

5.3.8 Noise data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5---3

5---4

5---4

5---6

5---7

5---8

5---9

5---9

5---10

5---11

5---12

5---13

5---14

October 20, 2005

5---1

Section 5

Performance

FLIGHT MANUAL

Doc. No. S2005FMENKT

Intentionally left blank

5---2

October 20, 2005

Section 5

Performance

FLIGHT MANUAL

Doc. No. S2005FMENKT

5.1 Introduction

Section 5 provides data for airspeed calibration, stall speeds, take---off performance and nonapproved additional information, provided by the airplane type certificate owner.

The stated performance data has been computed from actual flight tests with the

SPORTSTAR airplane and ROTAX 912 S engine in good condition and using average piloting techniques.

CAUTION

THE PERFORMANCE STATED IN THIS SECTION IS

VALID FOR ROTAX 912 S (100 HP) TOGETHER WITH

WOODCOMP KLASSIC 170/3/R PROPELLER

INSTALLED IN THE AIRPLANE, OTHERWISE SEE

SECTION 9 --- SUPPLEMENTS FOR ACTUAL PER-

FORMANCE.

October 20, 2005

5---3

Section 5

Performance

FLIGHT MANUAL

Doc. No. S2005FMENKT

5.2 Approved data

5.2.1 Airspeed indicator system calibration

NOTE

Assumed zero instrument error.

Valid for airplane take---off weight 1213 lbs (550 kg) .

flaps 0 ˚ kts CAS

15 ˚

104

109

113

118

122

127

132

137

100

105

110

115

120

125

130

135

140

146

50 ˚

5---4

October 20, 2005

135

140

145

150

155

160

168

100

105

110

115

120

125

130

100

105

109

114

118

123

127

132

137

141

146

151

158

FLIGHT MANUAL

Doc. No. S2005FMENKT flaps 0 ˚ mph CAS

15 ˚

50 ˚

Section 5

Performance

5---5

Section 5

Performance

FLIGHT MANUAL

Doc. No. S2005FMENKT

5.2.2 Stall speeds

Conditions: --- wing level stall --- engine at idle power

--- turning flight stall --- engine at 75% max. continuous power

--- airplane weight: 1213 lbs (550 kg)

NOTE

The stated stall speeds are valid for all flight altitudes.

Altitude losses shown in the table present max. values determined on the basis of flight tests using average piloting technique.

Altitude loss ft

(

Wi l

Turn flight di t d turn,

30 ˚ bank) l

Flaps position

Retracted (0 ˚ )

Take---off (15 ˚ )

Landing (50 ˚ )

Retracted (0 ˚ )

Take---off (15 ˚ )

Landing (50 ˚ )

KIAS

Stall speed

KCAS

200

Wi l l

(

Turn flight di t d turn,

30 ˚ bank)

Flaps position

Retracted (0 ˚ )

Take---off (15 ˚ )

Landing (50 ˚ )

Retracted (0 ˚ )

Take---off (15 ˚ )

Landing (50 ˚ )

Stall speed mph IAS

46 mph CAS

Altitude loss ft

200

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5.2.3 Take---off distance

Conditions: --- engine: max. take---off power

--- flaps: Take---off (15 ˚ )

--- carburetter preheating: OFF

--- airplane weight: 1213 lbs (550 kg)

--- Altitude: 0 ft ISA

--- ambient air temperature: ISA

Dray concrete

Grass

Take---off run

570 ft (174 m)

660 ft (200 m)

Take---off distance to height of 50 ft (15 ft)

1310 ft (399 m)

1395 ft (425 m)

Section 5

Performance

Corrections: --- Influence of wind: Add 4% on every 1 kt (1.15 mph) of tail wind

--- RWY inclination: Add 8% of the take---off run distance on 1% of ruway inclination up the slope

5.2.4 Landing distance

Conditions: --- engine: idle

--- flaps: Landing 50 ˚

--- carburetter preheating: OFF

--- airplane weight:

--- Altitude: 0 ft ISA

1213 lbs (550 kg)

--- ambient air temperature: ISA

Dray concrete

Grass

Landing distance from height of

50 ft (15 ft)

1185 ft (360 m)

1125 ft (343 m)

Braked landing run

545 ft (165 m)

485 ft (148 m)

Corrections: --- Influence of wind: Add 4.5 % on every 1 kt (1.15 mph) of tail wind

--- RWY inclination: Add 8% of the landing run distance on 1% of ruway inclination down the slope

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5.2.5 Climb performance

Conditions: --- engine: maximun take---off power

--- flaps: retracted (0 ˚ )

--- carburetter preheating: OFF

--- airplane weight: 1213 lbs (550 kg)

--- ambient air temperature: ISA

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Best rate of climb for various altitudes is mentioned in the following table:

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5.3 Additional information

5.3.1 Cruise

Conditions: --- flaps: retracted (0 ˚ )

--- carburetter preheating: OFF

--- airplane weight: 1213 lbs (550 kg)

--- ambient air temperature: ISA

5---10

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5.3.2 Horizontal speeds

In the following table states Indicated airspeeds (IAS) and corresponding True air speeds versus altitude, all for various engine speeds.

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5.3.3 Endurance

Conditions: --- flaps: retracted (0 ˚ )

--- carburetter preheating: OFF

--- airplane weight: 1213 lbs (550 kg)

--- ambient air temperature: ISA

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5.3.4 Balked landing climb

Conditions: --- engine: maximum take---off power

--- carburetter preheating: OFF

--- flaps: landing position (50 ˚ )

--- airplane weight: 1213 lbs (550 kg)

--- ambient air temperature: ISA

Section 5

Performance

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5.3.5 Effect on flight performance and characteristics

Flight performances and characteristics are not considerably affected by rain or insect stuck on the airplane surface.

5.3.6 Demonstrated crosswind performance

Maximum demonstrated speed of wind at airplane operation . . . . . . . . . . . . . . . . . . . . . . . . .

24 kts (28 mph)

Maximum demonstrated speed of cross wind for take---off and landing . . . . . . . . . . . . . . . . . . . . . .

10 kts (12 mph)

Maximum demonstrated speed of tail wind . . . . .

6 kts (7 mph)

5---14

Figure 5-1 Influence of wind on take---off and landing

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5.3.7 Ceiling

Service ceiling of SPORTSTAR . . . . . . . . . . . . . . . .

13 800 ft

5.3.8 Noise data

Not measured.

Section 5

Performance

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Section 6

Weight &

Balance

6. WEIGHT AND BALANCE

6.1 Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

6.2 Weight and balance record . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

6.3 Permitted payload range . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

6 --- 3

6 --- 5

6 --- 7

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Section 6

Weight &

Balance

6.1

Introduction

This section includes airplane weighing procedure a determination of its centre of gravity position, further then determination of allowed loading range at which

SPORTSTAR airplane can be safely operated.

Proceduresfor weighing the airplane and the calculation method for establishing the permitted payload range are contained in the Maintenance manual for the

SPORTSTAR airplane.

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6---4

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6.2 Weight and balance record

Section 6

Weight and balance

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6.3 Permitted payload range

Section 6

Weight and balance

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Section 7

Airplane and System

Description

7. AIRPLANE AND SYSTEM DESCRIPTION

7.1 Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.2 Airframe . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.2.1 Fuselage

7.2.2 Wing

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

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

7.2.3 Horizontal tail unit (HTU) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.2.4 Vertical tail unit (VTU) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.3 Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.3.1 Longitudinal control

7.3.2 Lateral control

7.3.3 Rudder control

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

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

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

7.3.4 Elevator trim tab control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.4 Controls in cockpit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.5 Instrument panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.6 Inside and outside marking and placards . . . . . . . . . . . . . . . . . . . . . . .

7.7 Landing gear and brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.7.1 Landing gear

7.7.2 Brakes

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

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

7.8 Seat and safety harnesses . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.9 Baggage compartment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.10 Canopy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.11 Power unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.11.1General

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

7.11.2Engine control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.11.3Engine intruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.11.4Engine cooling system

7.11.5Engine lubrication system

7.11.6Engine intake system

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

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

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

7.11.7Ignition system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7---6

7---6

7---4

7---4

7---5

7---3

7---3

7---6

7---7

7---7

7---8

7---9

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7.12 Fuel system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.12.1Fuel tank . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.12.2Fuel selector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.12.3Fuel filter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.12.4Indication of fuel quantity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.12.5Fuel tank draining . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7---10

7---10

7.13 Electrical system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.13.1Lightning

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

7.13.2Electrical system scheme . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7---12

7---12

7.14 Pitot---static system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7---14

7.15 Supplementary equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.15.1Ventilation and heating system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7---15

7---15

7.16 Navigation and communication equipment . . . . . . . . . . . . . . . . . . . . . .

7---15

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Section 7

Airplane and System

Description

7.1 Introduction

This section describes systems of the airplane and its operation.

More detailed information on optional systems and equipment are available in section 9, Supplements.

7.2 Airframe

The airframe of SPORTSTAR airplane is of semimonocoque structure consisting of metal reinforcement, frames and duralumin sheet skin.

7.2.1 Fuselage

The fuselage is of semimonocoque structure consisting of reinforcements and duralumin skin. Fuselage section is rectangular in the lower part and eliptic in the upper part. The fin is an integral part of fuselage. The cockpit for two---member crew is located in the middle part of the fuselage that is accessible after uncovering the single---piece organic glass canopy. The engine compartment in the front part of the fuselage is separated from the cockpit by the steel fire wall to which the engine bed is attached.

7.2.2 Wing

The wing is of rectangular shape, single---spar structure with the auxiliary spar with suspended ailerons and split wing flaps. Riveting is used for connecting individualstructural elements. Fiber---glass wing tips are riveted on the wing eds.

7.2.3 Horizontal tail unit (HTU)

The VTU of conventional type consists of the stabilizer and elevator with the trim tab. Single---spar structure of HTU consists of duralumin ribs, spar and skin. Top view of HTU is of rectangular shape.

7.2.4 Vertical tail unit (VTU)

VTU is of trapezoidal shape. Its fin is an integral part of the fuselage. The rudder is suspended on the fin by means of two hinges. The VTU structure consists of the duralumin spar and skin.

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7.3 Control

Airplane control consists of ailerons, elevator and rudder. Directional control is connected by means of pull rods with nose landing gear control. Main landing gear brakes are controlled by pedals of directional control.

Airplane is equipped with coupled control enabling flight with two---member crew.

7.3.1 Longitudinal control

Longitudinal control is actuated by the control stick. Longitudinal movement of control stick is transferred to the elevator by mechanical system of pull rods and levers.

7.3.2 Lateral control

Lateral control is actuated by the control stick. From the control stick the movement is transferred through the system of levers and pull rods to ailerons.

7.3.3 Rudder control

Rudder control is controlled by pedals of foot control. The rudder is interconnected with foot control pedals by cable system.

Foot control pedals adjustable into three positions can be installed as an option.

Way of adjustment of ruder pedals:

1. Release the pin from the adjusting groove

2. Set pedal to one of three possible positions

3. Check on the pin locking---on in the adjusting groove

WARNING

RIGHT AND LEFT PEDAL OF RUDDER CONTROL

MUST BE ADJUSTED IN THE SAME POSITIONS

AND SECURED!

7.3.4 Elevator trim tab control

The elevator trim tab is controled by the lever located in between the pilot seats.

The control lever is interconnected with the trim tab by means of cables and pulleys.

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Section 7

Airplane and System

Description

1 Control stick

2 Instrument panel

3 Carburetter pre---heating knob

(if installed)

4 Cockpit heating / canopy defog selector (if installed)

5 Hot air supply knob (if installed)

6 Throttle lever

7 Ignition

8 Choke

9 Master switch

10 Fuel selector

11 Rudder control pedals

12 Emergency parachute system lever (if installed)

13 Flap control lever

14 Trim control lever

15 Headset sockets

Figure 7-1 Cockpit control elements

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7.5 Instrument panel

See section 9 --- Supplements.

7.6 Inside and outside marking and placards

See Maintenance Manual.

7.7 Landing gear and brakes

7.7.1 Landing gear

The airplane is equipped with a sort of fixed nose landing gear. Main landing gear legs are produced from composite spring. Nose landing gear leg is welded from two pieces --- the tube and the yoke--- in which the nose wheel is mounted. The nose landing gear is spring---loaded by a rubber rope. The nose wheeel is controllable, wheel control is coupled with rudder control by means of two pull rods.

Wheels can be fitted with fiber---glass aerodynamic covers.

7.7.2 Brakes

The SPORTSTAR airplane is equipped with disk hydraulic brakes on main landing gear wheels. Brake system is composed of brake pedals (these are a part of rudder control pedals), brake pumps, hoses for leading brake liquid, brake yokes with wheel cylinders and brake pads. By depressing the brake pedals compression of brake pumps occurs, which generates pressure in brake circuit and hydraulic cylinders press the brake pads onto the brake disks. Braking pressure can be regulated only by force of brake pedals depressing.

The airplane can be equipped by mechanical manually controlled parking brake.

PARKING BRAKE handle is located in between the pilot seats.

7.8 Seat and safety harnesses

SPORTSTAR is a two---seat airplane with side---by---side seats. Seats are fixed, non---adjustable and fitted with light upholstery.

Each of seats is fitted with four---point safety harness which is composed of safety belts, shoulder straps and lock. The safety harness is anchored in the middle of the frame behind the baggage compartment and on the seat sides .

7.9 Baggage compartment

Baggage compartment is positioned behind seat rests.

Maximum weight of baggage is 55 lbs (25 kg) and is stated on the placard in the baggage compartment. The baggage compartment is fitted with rubber straps for baggage fixation.

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Airplane and System

Description

7.10 Canopy

The cocpit canopy is of a semidrop shape. The framework is composed of metal structure on which the organic glass canopy is fixed by bolts.

The canopy is attached to the fuselage in the front part by two swivel pins by means of which it can be folded up forwards. In order to make opening easier, the actual weight of canopy is balanced by two gas struts, besides the canopy is provided with holders on the lower framework for easier handling. The canopy is provided with the lock in the rear upper part of framework for locking.

7.11 Power unit

7.11.1General

The engine ROTAX 912 ULS. is used to power SPORTSTAR airplane as a standard. ROTAX 912 ULS is a four---cylinder, four---stroke engine with opposite cylinders, central cam shaft and OHV valve mechanism with maximum power of 100 hp

(73.5 kW) at 5800 RPM.

The on---groun adjustable, composite, 3---blade propeller WOODCOMP KLASSIC

170/3/R. is standardly mounted on the engine ROTAX 912 ULS Other propeller type can be installed on customer ’ s request --- see section 9 for detailed information.

7.11.2Engine control

Engine power is controlled by means of THROTTLE lever, which is located in the middle of the instrument panel and which controls engine power range from idle up to maximum take---off . Engine power controller is mechanically interconnected with the flap on carburetters.

If the lever is fully pushed in, then this position corresponds to maximum engine power. If the lever is fully pulled out, then this position corresponds to idle. Rapid changes in engine power setting can be made by pressing down the round button on the lever body and by its pulling out or pushing in. Small changes in power setting can be performed through lever turning (conterclockwise --- power increase).

The lever is fitted with the locking ring, counterclockwise turning of which ensures locking of the lever in requested position.

7.11.3Engine intruments

The following analog instruments located on the instrument panel serve for engine performance monitoring. The digital engine monitoring system can be installed in the airplane instead of analog engine instruments.

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Description

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RPM indicator

The electrical RPM indicator is controlled by signal from the generator RPM transmitter. Working range of the RPM indicator is 0 --- 7000 RPM.. Colour code is stated in section 2, page 2---5.

Cylinder head thermometer

The cylinder head thermometer transmitter senses temperature of cylinder No. 3.

Working range of the cylinder head thermometer is 50  150 ˚ C (120  300 ˚ F).

Colour code is stated in section 2, page 2---5.

Oil thermometer

Oil temperature on engine input is measured by the sensor located behind the oil pump. Working range of oil thermometer is 50  150 ˚ C. (120  300 ˚ F). Colour code is stated in section 2, page 2---5.

Oil pressure gauge

Oil pressure on the oil input into engine is measured by means of sensor which is located behing the oil filter. Working range is 0 --- 10 bar. (0  150 PSI). Colour code is stated in section 2, page 2---5.

7.11.4Engine cooling system

Engine cooling is combined, cylinder heads are cooled by water, cylinders are cooled by air.

Cooling circuit of cylinder heads is designed as a closed system containing pump, expansion reservoir (1) with pressure closure (3), cooler of cooling liquid (2) and drainage reservoir (4). Scheme of cylinder head cooling system is shown in Fig. 7-2.

When changing, the cooling liquid is filled up through the cap of expansion reservoir (1), during airplane operation it is replenished into drainage reservoir (4) between the lines of maximum and minimum level.

7---8

Figure 7-2 Scheme of cylinder head cooling system

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Section 7

Airplane and System

Description

7.11.5Engine lubrication system

Engine lubrication system is performed with the dry crank case. Engine lubrication system is equipped with oil pump (1) ensuring oil feeding from reservoir (4) located on the fire wall through the oil cooler (5) and the oil cleaner (6) to the lubricated points of engine. The pressure sensor (2) is located behind the oil pump. The oil recervoir is aerated by the hose (7) which is led under the airplane. Oil pressure and temperature are indicated on instruments in right side of the instrument panel. Oil is replenished through the lid in the upper part of the oil reservoir.

Figure 7-3 Scheme of engine lubrication system

7.11.6Engine intake system

Engine intake system ensures delivery of sufficient air into engine. Air is taken into the engine through openings on the engine covers through the air filters.

The intake system can be equipped with carburettor heating system. Hot air from the heat exchanger (located on the exhaust collector) is taken to the mixing chamber.

Amount of in---taken hot air is regulated by flaps in mixing chamber inlets. Flaps are controlled by the CARBURETTOR PREHEATER knob on the instrument panel.

7.11.7Ignition system

The engine is equipped with the double contactless ignition system. Each ignition circuit has own source of energy, control unit, 2 ignition coils and 4 spark plugs. It is fully autonomous on the other circuit of accumulator. High voltage current is distributed to the spark plugs through high---voltage cables. Ignition sequence of individual engine cylinders:

Ignition circuits are controlled by the ignition switch on the instrument panel.

Positions of ignition switch:

OFF

BOTH

START engine ignition is off only ignition circuit B is on only ignition circuit A is on both circuits are on both circuits are on and starter is cranking the engine

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Description

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7.12 Fuel system

Fuel system serves for keeping fuel in the airplane and its feeding to the engine.

Fuel system of SPORTSTAR airplane is composed of integral fuel tanks, fuel line, fuel selector, fuel filter, mechanical fuel pump --- located on the engine (auxiliary electrical fuel pump can be installed), distribution pipe of fuel with, return branch of fuel, fuel gauges and fuel tanks draining valves.

7.12.1Fuel tanks

Fuel is contained in the wing integral tanks having volume 60 l (15.85 U.S. gallons) each. Each tank is fitted with air venting (output is under the wing tip) and draining valve on the bottom side of the wing. Fuel is led from the tanks through the hoses to the fuel selector located on a central console under the instrument panel and then through a fuel filter to the engine pump and carburetors. Fuel return hose goes from the fuel pump into the left tank, which is due to considered as a “ primary ” tank. See figure 7---4 Scheme of fuel system.

7.12.2Fuel selector

The fuel selector serves for tank selection and fuel delivery interruption in case of engine fire or long parking of airplane.

To move selector from OFF (closed) position it necessary pull the safety button on the fuel selector, turn the handle from the OFF position to the left and then release safety button. Now the handle can be freely moved between LEFT and RIGHT position. Safety button prevents unintentionally switch the selector to OFF position.

To move selector to OFF (closed) position it is necessary pull the safety button on the fuel selector, turn the handle to the OFF position and then release safety button.

Now the handle is blocked in the OFF position. Safety button prevents unintentionally switch the selector from the OFF position during parking.

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Section 7

Airplane and System

Description

7.12.3Fuel filter

The fuel filter separates all mechanical impurities from fuel. The fuel filter is located in the cockpit on the left airframe panel.

7.12.4Indication of fuel quantity

Fuel quantity is measured by a float fuel gauge transmitter in each tank and indicated on fuel gauge on the instrument panel. LH fuel gauges indicates fuel quantity in the left (primary) tank, RH indicator in the right tank. True fuel quantity is indicated only on ground and in level flight and it takes approx. 2 minutes to level fuel after transition from climb/descent.

7.12.5Fuel tank draining

Draining of the fuel tank is specified in chapter 8.5 in page 8---6.

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Description

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7---12

Figure 7-4 Scheme of fuel system

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Section 7

Airplane and System

Description

7.13 Electrical system

The airplane is equipped with 14 V DC electrical installation. A generator with power of 250 W is the primary source of electrical energy. The secondary source of energy is the accumulator 12V/16Ah that is located in the engine compartment on the fire wall. It is used for engine starting and in case of generator failure as an emergency source of energy and also serves as the smoothing filter of power system.

DC voltage is distributed to individual systems by main busbar. Each system is protected by fuse or circuit breakers. If overloading of any of the circuits occurs, then the fuse is broken or circuit breaker is pulled out. The fuses or circuit beakers are listed in the Maintenance Manual.

After switching MASTER SWITCH on and by turning the ignition key to START position the starter is activated. The starter is power supplied from the accumulator before engine start. After engine has been started and idle RPM reached, generator starts supplying current into electrical network.

7.13.1Lightning

Airplane can be equipeed with a external lighting.

External lighting can be composed of position lights and anticollision beacons which are located in wing tip and landing headlight which is located in left wing leading edge or in the lower engine cowling. Position lights are switched by POS.

LIGHTS switch and anticollision beacon by BEACON switch. Landing headlight is switched by LDG LIGHT (or REFLECTOR ) switch.

7.13.2Electrical system scheme

See Maintenance Manual.

October 20, 2005 7---13

Section 7

Airplane and System

Description

FLIGHT MANUAL

Doc. No. S2005FMENKT

7.14 Pitot---static system

Pitot---static tube for sensing static and total pressure is located under the left half of the wing. Total pressure is sensed through the opening in the Pitot---static tube face. Static pressure is sensed through openings on the tube circumference. System of pressure distribution to individual instruments are made by means of flexible plastic hoses. Transparent draining reservoirs are located in the pressure branch of static and total pressure on the left fuselage side by the wing leading edge.

Static pressure is led to altimeter, airspeed indicator, variometer and altitude encoder (if installed). Total pressure is led only to the airspeed indicator.

Wing Pilot cockpit km/h ft m/s

(if installed)

Pitotstatic tube

Condensate reservoir

Static pressure

Total pressure

Figure 7-5 Scheme of pitot---static system

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Doc. No. S2005FMENKT

7.15 Supplementary equipment

Section 7

Airplane and System

Description

7.15.1Ventilation and heating system

Cockpit ventilation is ensured by two sliding windows located on the tilting canopy.

Cocpit heating is ensured by hot air from the heat exchanger. The heat exchanger is located on the exchaust pipe collector. Air from outside atmosphere is warmed up in the exhaust pipe collector and delivered through air hoses into the cockpit.

Hot air quantity is regulated by the flap which is controlled by the HOT AIR knob on the instrument panel. The cockpit heating system can be equipped with a windshield blowing system.

7.16 Navigation and communication equipment

Description of operation of navigation and communication equipment see section

9 --- Supplements.

October 20, 2005 7---15

Section 7

Airplane and System

Description

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FLIGHT MANUAL

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Section 8

Airplane Handling,

Servicing and Maintenance

8. AIRPLANE HANDLING, SERVICING AND MAINTENANCE

8.1 Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

8.2 Airplane inspection period . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

8.3 Modifications or airplane repairs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

8.4 Road transport . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

8.4.1 Airplane towing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

8.4.2 Airplane parking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

8.4.3 Airplane anchoring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

8.4.4 Airplane jacking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

8.4.5 Levelling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

8.4.6 Road transport . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

8.5 Draining of fuel tanks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

8.6 Cleaning and care . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

8 --- 6

8 --- 7

8 --- 3

8 --- 4

8---4

8---5

8---6

October 20, 2005 8---1

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Servicing and Maintenance

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Section 8

Airplane Handling,

Servicing and Maintenance

8.1

Introduction

This section includes the procedures for airplaine handling, maintenance and operation recommended by the manufacturer.

It is necessary to follow the set---down lubrication plan, scope and periodocity of preventive maintenance depending on climatic and flight conditions according to the Maintenance manual of SPORTSTAR .

Airplane owner should be in a permanent touch with the manufacturer, either directly or through the network of business representatives, which enables him to get the newest information concerning airplane operation, handling and maintenance. The manufacturer distributes this information to users through Service bulletins (Mandatory bulletins), Information bulletins (letters) and further instructions.

Mandatory bulletins are especially important for keeping up airworthiness and the manufacturer considers them mandatory although they do not come into effect before Airworthiness Directive is issued by aviation authority of user‘s country.

All correspondence with the airplane manufacturer, distributor or service center must contain the airplane serial number . The airplane serial number is shown on the title sheet of this Manual and on the production plate behind the rest of pilot seats.

The manufacturer delivers along with airplane SPORTSTAR the“ Flight manual“ and the “ Maintenance Manual”.

8.2

Airplane inspection period

Periodical inspections and reviews of airplane must be carried out at the latest in the following intervals:

--- after first 25 hours of operation

--- after every 50 hours of operation

--- after every 100+ 5 hours of operation

--- annual inspection

Details on periodical inspections are provided in the Maintenance Manual of

SPORTSTAR.

October 20, 2005 8---3

Section 8

Airplane Handling,

Servicing and Maintenance

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Doc. No. S2005FMENKT

8.3

Modifications or airplane repairs

All airplane repairs and modifications of airplane must be carried out by qualified personnel in an approved service center.

Before implementation of airplane repairs contact the Civil aviation authority of the country in which the airplane is registered, which evaluates influence of modification on flight airworthiness.

Basic repairs of airplane are described in the Maintenance Manual of SPORTSTAR.

8.4

Road transport

8.4.1 Airplane towing

It is possible to move the airplane on a short distance by holding the fuselage end in the position before the fin, enventually by holding the root part of wings.

The hand towing bar can be used for airplane relocation which will be fastened to the nose wheel axis.

To turn the airplane on the spot, push on the fuselage end part in the area before the fin, lift the nose wheel and turn the airplane in required direction.

WARNING

SWITCH OFF IGNITION BEFORE GROUND HAN-

DLING WITH THE AIRPLANE!

CAUTION

AVOID EXCESSIVE PRESSURES ON THE AIRFRAME

STRUCTURE, ESPECIALLY ON THE WING TIPS OF

HTU, VTU ETC.

WHEN HANDLING THE AIRPLANE BY MEANS OF

THE TOWING BAR, PROPELLER BLADES MUST BE

SET TO HORIZONTAL POSITION.

MAXIMUM

DEFLECTION OF THE NOSE WHEEL IS ± 10˚.

AT MANUAL ENGINE STARTING GRASP THE PRO-

PELLER BLADE AREA, I.E. NOT ONLY PROPELLER

EDGE.

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Section 8

Airplane Handling,

Servicing and Maintenance

8.4.2 Airplane parking

It is the most suitable solution to place the airplane into a hangar possibly into another covered room with stable temperature, good venting, low humidity and dust--free environment. In case of parking out of the hangar it is necessary to anchor the airplane and at long---term parking to cover the canopy, possibly the whole airplane with suitable tarpaulins.

8.4.3 Airplane anchoring

The airplane is anchored at parking out of hangar after termination of flight day or according to need. Anchoring of the airplane is necessary for its protection against possible damage, caused by wings and gusts. For this purpose the airplane is equipped with fixing eyes on the lower side of wings.

Procedure:

1. Check of fuel cock closing, off---position of all switches, ignition and master switch.

2. Lock manual control, e.g. by using safety belts

3. Close vent windows

4. Close and lock the cockpit canopy

5. Anchor the airplane to the ground by means of cables pulled through fixing eyes which are located on the lower side of wings. Further it is necessary to anchor the nose landing gear.

NOTE

In case that long---term airpplane anchoring is supposed, namely in winter period, it is suitable to cover the canopy, eventually the whole airplane by appropriate tarpaulins which must be properly secured to the airplane structure.

October 20, 2005 8---5

Section 8

Airplane Handling,

Servicing and Maintenance

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Doc. No. S2005FMENKT

8.4.4 Airplane jacking

Airplane jacking presents no big difficulties due to relatively low airplane empty weight and can be performed by two persons.

First, it is necessary to prepare two suitable rests which will support the airplane.

The airplane can be jacked in the following way:

--- by pushing from the above to the fuselage rear part in the position before the fin the front part of fuselage can be jacked and subsequently supported under the fire wall.

--- Rear part of fuselage can be slightly jacked only by grasping in the position near the auxiliary skid and by pushing from below and then the lower part of fuselage can be supported by the rest located in the area of the skid.

--- Wings van be jacked by pushing on the wing from below in the area of the main spar. It is necessary to avoid jacking by grasping the wing tip.

8.4.5 Levelling

Levelling procedure is described in the Maintenance manual for SPORTSTAR airplane.

8.4.6 Road transport

The airplane can be transported on communication after its laoding on an appropriate trail. It is necessary to dismount wings. The airplane must be secured against possible movement. This way you will preclude possible damage to the airplane.

8.5

Draining of fuel tanks

Draining should be done prior to first flight each day.

There is a drain valve of each wing tank located on its bottom.

Procedure:

1. Put a transparent cup under the drain valve.

2. Using screwdriver (or appropriate jig) press and turn drain valve counterclockwise to open it.

3. Drain required quantity of fuel.

NOTE

Draining serves to elimination of impurities and deposits from the fuel. Drain until clean fuel flows from the drain valve.

4. Using screwdriver (or appropriate jig) turn drain valve clockwise to close it.

5. Repeat procedure for the opposite tank.

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Section 8

Airplane Handling,

Servicing and Maintenance

8.6

Cleaning and care

Always use appropriate cleaning agents when cleaning airplane surface. Residuum of oil and fat can be removed form the airplane surface (excluding the canopy) by suitable detergents, posibbly by petrol.

The canopy only to be cleaned by washing with ample stream of tepid water with addition of appropriate detergents. Use soft rag, sponge or wash leather. Use suitable polishing agent after wiping rests of water.

CAUTION

NEVER DRY---CLEAN THE CANOPY AND NEVER USE

PETROL NOR CHEMICAL SOLVENTS!

Coating, upholstery and carpets in the cocpit can be removed from the cocpit, brushed and, if need be, cleaned with warm water with addition of appropriate detergent. Dry up upholstery after doing this .

October 20, 2005 8---7

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Airplane Handling,

Servicing and Maintenance

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SPORTSTAR

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Section 9

Supplements

9. Supplements

9.1 Introduction

This section contains the appropriate supplements necessary to safely and efficiently operate the airplane when equipped with various optional systems and equipment not provided with the standard airplane.

9.2 List of inserted supplements

Inst. Date Doc. No. Title of inserted supplement

Oct 20/05 S2005FMENKTS01 Transceiver KY97A

Oct 20/05 S2005FMENKTS02 Intercom PM 1000

Oct 20/05 S2005FMENKTS03 Transponder KT76A



Aug 27/07 S2005FMENKTS04 Aircraft description of S/N 2007 1003

Oct 20/05 S2005FMENKTS05 GPS/COMM receiver KLX 135

Oct 20/05 S2005FMENKTS06 Flight clock LC-2

Oct 20/05 S2005FMENKTS07 Transceiver FILSER ATR 600

Oct 20/05 S2005FMENKTS08 GPS/NAV/COMM receiver

GARMIN GNS 430/430A

Oct 20/05 S2005FMENKTS09 Transponder ATC GARMIN GTX 327

Oct 20/05 S2005FMENKTS10 Intercom PCD7100-I

(PS ENGINEERING

INCORPORATED)

Oct 20/05 S2005FMENKTS11 Rocket activated parachute rescue system Magnum Speed Soft 601

Oct 20/05 S2005FMENKTS12 Horizon RCA 26

Oct 20/05 S2005FMENKTS13 Float operation CZAW 1150

Oct 20/05 S2005FMENKTS14 Horizon LUN 1202

Oct 20/05 S2005FMENKTS15 Towing gear

Oct 20/05 S2005FMENKTS16 Pitot tube heating



Oct 20/05 S2005FMENKTS17 Emergency Locator Transmitter

AK-450

- - S2005FMENKTS18 Not used



Oct 20/05 S2005FMENKTS19 Stall warning system ACI type T1b

- - S2005FMENKTS20 Not used

October 20, 2005

9 - 1

Section 9

Supplements

Inst. Date Doc. No.

SPORTSTAR

FLIGHT MANUAL

Doc. No. S2005FMENKT

Title of inserted supplement

9 - 2

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SPORTSTAR

FLIGHT MANUAL

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9.3 Supplements inserted

Section 9

Supplements

October 20, 2005

9 - 3

Section 9

Supplements

SPORTSTAR

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9 - 4

October 20, 2005

Section 9

ELT AK---450

FLIGHT MANUAL

Doc. No. S2005FMENKTS17

SUPPLEMENT

EMERGENCY LOCATOR TRANSMITTER

MODEL AK---450

AMERI---KING CORPORATION

Registration mark:

Serial number:

This Supplement must be contained in the Flight Manual if Emergency Locator Transmitter (ELT) AK---450 is installed on the airplane in accordance with the approved airplane manufacturer documentation.

Information contained in this Supplement add or replace information from the basic Flight

Manual in the further mentioned parts only. Limitations, procedures and information not mentioned in this Supplement are contained in the basic Flight Mnaual.

October 10, 2005 1 of 10

Section 9

ELT AK---450

FLIGHT MANUAL

Doc. No. S2005FMENKTS17

RECORD OF REVISIONS

Rev.

No.

Affected Pages Description/Validity Approved /Date

Incorporated/Date

2 of 10 October 10, 2005

Section 9

ELT AK---450

FLIGHT MANUAL

Doc. No. S2005FMENKTS17

SECTION 1 -- GENERAL

This Supplement adds information necessary for operation of the airplane with the

Emergency Locator Transmitter (ELT) AK---450 that is installed in accordance with the approved airplane manufacturer documentation.

SECTION 2 -- LIMITATIONS

CAUTION

NEVER UNREASONABLY ACTIVATE ELT

SECTION 3 -- EMERGENCY PROCEDURES

Before performing a forced landing, especially in remote and mountainous areas, the ELT should be activated manually by pressing the ON button on the remote unit. The red LED on the remote unit illuminates.

Immediately after a forced landing where emergency assistance is required, the ELT should be utilized as follows:

CAUTION

THE REMOTE UNIT COULD BE INOPERATIVE IF

DAMAGED DURING FORCED LANDING. HOWEVER,

TURNING THE ELT ON REQUIRES MANUAL SWITCH-

ING TO ON POSITION OF THE MAIN SWITCH WHICH

IS LOCATED ON THE ELT MAIN UNIT.

1. ENSURE ELT ACTIVATION

--- Press the ON button on the remote unit, even if the LED illuminates.

--- Ensure that the external ELT antenna has no damage. If the antenna has broken, continue according to item 3.

--- If the aircraft ’ s radio is operable and can be safely used (no threat of fire or explosion), turn ON and select 121.5 MHz. If the ELT can be heard transmitting, it is working properly.

2. PRIOR TO SIGHTING RESCUE AIRCRAFT

--- Conserve airplane battery. Do not activate radio transceiver.

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3. WHEN LEAVING THE SCENE OF THE ACCIDENT

--- Disconnect remote unit and external antenna.

--- Remove ELT main unit from the aircraft.

--- Attach an auxiliary antenna (stored on the ELT case) to the ELT and fully extend it.

Keep the antenna vertically oriented as much as possible.

--- Place main switch to ON position. The ELT LED ON light should be illuminated.

--- When portable ELT is used in cold weather, unit should be kept as warm as possible by placing it inside your clothing with the antenna protruding.

4. AFTER SIGHTING RESCUE AIRCRAFT

--- Press RESET button on the remote unit or on the main unit to prevent radio interference. Attempt contact with rescue aircraft with the radio transceiver set to a frequency to 121.5 MHz. If no contact is established, press ON button on the remote unit or switch on main switch on the main unit immediately.

5. FOLLOWING RESCUE

--- Press the RESET button on the remote unit or main unit to terminate emergency transmission.

SECTION 4 -- NORMAL PROCEDURES

PREFLIGHT CHECK

On the main ELT unit (in the baggage compartment)

1. Main switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ARM

2. Red LED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

check off

On the remote ELT unit (on the instrument panel)

3. Red LED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

check off

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IN FLIGHT

NOTE

The ELT may be activated inadvertently by heavy turbulence. The ELT should then be reset by pressing

RESET button on the remote unit. Ensure that the ELT does not transmit --- red LED must not illuminate. If the

RESET button on the remote unit does not cause the

LED ON light to extinguish, the RESET button on the main unit should be pressed.

POSTFLIGHT CHECK

On the remote ELT unit (on the instrument panel)

1. Red LED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

check off

On the main ELT unit (in the baggage compartment)

2. Red LED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

check off

3. Main switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

OFF

Section 9

ELT AK---450

SECTION 5 -- PERFORMANCE -- NOT AFFECTED

SECTION 6 -- WEIGHT AND BALANCE -- NOT AFFECTED

October 10, 2005 5 of 10

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ELT AK---450

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Doc. No. S2005FMENKTS17

SECTION 7 -- AIRPLANE AND SYSTEM DESCRIPTION

The emergency locator transmitter model AK---450 is installed in this aircraft. It is intended to be rigidly attached to the aircraft before the crash, but readily removable from the aircraft after a crash. The aircraft mounted antenna may be disconnected and an auxiliary antenna (stored on the ELT case) attached to the ELT. The ELT can be tethered to a survivor. The ELT is intended to aid SAR teams in locating the crash site or survivor(s).

The ELT is automatically activated upon sensing a change of velocity of 3.5 +/--- 0.5 feet/ second, along its longitudinal axis. When activated ELT is transmitting the standard swept tone on 121.5 and 243.0 MHz . The entire ELT system is self powered by its own internal batteries.

Figure 2 1 --- ELT remote unit

6 of 10

Figure 3 2 --- ELT main unit

October 10, 2005

FLIGHT MANUAL

Doc. No. S2005FMENKTS17

NOTE

For detailed description see Installation and Operation

Manual For Model AK---450, document No. IM---450,

Rev. A dated 10/18/95 or later applicable version, which is delivered with the ELT.

Section 9

ELT AK---450

SECTION 8 -- AIRPLANE HANDLING, SERVICING

AND MAINTENANCE

TESTING ELT FUNCTION

NOTE

The ELT function should be tested every 3 months.

The test consist of turning the unit “ ON ” and then resetting it to verify that the transmitter, latch circuit, batteries and associated equipment are operating properly. Regulations require that the transmitter test only be done during the first 5 minutes of each hour and must not last more then 3 audio sweeps (1.5 seconds). If you are at location where there is an control tower or other monitoring facility, notify the facility before beginning the tests.

Never activate the ELT while airborne.

1. Monitor 121.5 MHz using the aircraft COM receiver or portable hand held receiver.

Turn the squelch all the way down or OFF.

On the main unit

2. Main switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ARM

On the remote unit

3. ON button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

push

Verify that both the LED ON lights, located on the main unit and the remote unit, are illuminated. Verify that the audio sweep tone can be heard on the COM receiver.

On the remote unit

4. RESET button . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

push

Verify that the both LED ON lights are extinguished and the audio sweep tone should stop.

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Section 9

ELT AK---450

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Doc. No. S2005FMENKTS17

PERIODIC MAINTENANCE

NOTE

The ELT inspection must be performed a minimum of one time each 12 months.

Inspection procedure is mentioned in the Installation and Operation Manual For Model

AK---450, document No. IM---450, Rev. A dated 10/18/95 or later applicable version.

You can also obtain manual from http://www.ameri---king.com/pdf/9.1.22.pdf

BATTERY REPLACEMENT

NOTE

Battery replacement procedure is mentioned in the item 2.5 of the Installation and Operation Manual For

Model AK---450, document No. IM---450, Rev. A dated

10/18/95 or later applicable version.

MAIN UNIT

The ELT main unit is designed to use only DURACELL MN1300 alkaline batteries which are dated by the manufacturer. The use of any other battery will void any warranties of the

ELT producer and ELT does not meet the requirements of TSO---C91a.

Battery replacement is required upon reaching the date marked upon each cell. All cells must be replaced at the same time and the cells must have the same expiration date.

The expiration date of the batteries must be indicated on the outside of the ELT battery case and recorded in the aircraft log book. Adhesive labels are provided to record this information.

REMOTE UNIT

The ELT remote unit is designed to be powered by a single Duracell DL1/3NB 3 Volt Lithium battery. Under normal operating condition the lithium battery must be replaced every eight years . Alkaline type cells are available from various manufacturers and may be used in place of the lithium cell. Under normal operating conditions, the alkaline battery must be replaced every four years .

The expiration date of the battery must be indicated on the outside of the ELT battery case and recorded in the aircraft log book. Adhesive labels are provided to record this information.

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NOTE

The all batteries (for main and remote unit) must be also replaced when the ELT has been in use for more than one cumulative hour or when ELT was activated for an unknown period of time (i.e. unintentional activation).

Section 9

ELT AK---450

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Section 9

Stall warning system

ACI type T1b

FLIGHT MANUAL

SUPPLEMENT No. 19

STALL WARNING SYSTEM

ACI type T1b

Registation number:

Serial number:

This Supplement must be contained in Flight Manual if stall warning system ACI type T1b is installed on the aircraft in accordance with the approved documentation of aircraft manufacturer.

Information contained in this Supplement add or replace information of basic Flight

Manual in the further mentioned parts only. Limitations, procedures and information non mentioned in this Supplement are contained in basic Flight Manual.

October 20, 2005 1 of 5

Section 9

Stall warning system

ACI type T1b

FLIGHT MANUAL

Doc. No. S2005FMENKTS19

RECORD OF REVISIONS

Rev.

No.

Affected Pages Description/validity Approved/Date

Incorporated by/

Date

2 of 5 October 20, 2005

FLIGHT MANUAL

Doc. No. S2005FMENKTS19

Section 9

Stall warning system

ACI type T1b

SECTION 1 -- GENERAL

This Supplement adds information necessary for aircraft operation with stall warning system ACI type T1b that is installed according to the approved aircraft manufacturer documentation.

SECTION 2 -- LIMITATIONS

2. 17 Limitation placards

The following placard is added on the instrument panel:

SECTION 3 -- EMERGENCY PROCEDURES

3.10.3 Stall warning system (SWS) audio signalization

When SWS audio alarm is heard:

1. Control stick . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

release or pull to increase airspeed, adjust engine power

SWS audio alarm must end.

October 20, 2005 3 of 5

Section 9

Stall warning system

ACI type T1b

FLIGHT MANUAL

Doc. No. S2005FMENKTS19

SECTION 4 -- NORMAL PROCEDURES

4.4 Pre---flight check

2. Left wing --- check

D stall speed vane conditon and its free movement

12. Right wing --- see 2. except the landing light (if installed), Pitot tube and stall speed vane

D stall speed vane conditon and its free movement

18. Cockpit check

D Perform stall warning system check:

MASTER SWITCH

Stall speed vane (on the left wing)

ON lift

The audio alarm must sound when vane is lifted.

Stall speed vane

MASTER SWITCH release

OFF

NOTE

During ground manoeuvring in blustery wind conditions the

SWS audio alarm may sound occasionally.

SECTION 5 -- PERFORMANCE -- NOT AFFECTED

5.2.2 Stall speeds

If airplane speed is approximately 8 kts (9 mph) and less above stall speed the audible alarm is heard.

SECTION 6 -- WEIGHT AND BALANCE -- NOT AFFECTED

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Section 9

Stall warning system

ACI type T1b

SECTION 7 -- AIRPLANE AND SYSTEM DESCRIPTION

7.15 Miscellaneous equipment

7.15.1 Stall warning system

Stall warning system ACI type T1b is installed on this airplane to warn pilot that airspeed is decreasing near to stall.

Stall speed vane (sensor) is located on the left wing, audible alarm box is located in the cockpit (behind the instrument panel).

Fig. --- Stall speed vane on the left wing

SECTION 8 -- AIRPLANE HANDLING, SERVICING

AND MAINTENANCE

Lubricating points

Annualy apply a drop of engine oil to each end of the stall warning system vane shaft on the left wing.

--- END ---

October 20, 2005 5 of 5

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FLIGHT MANUAL

FOR

SPORTSTAR

ULTRALIGHT AIRPLANE

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TECHNICAL INFORMATION

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6. WEIGHT AND BALANCE

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CONTENTS

7. AIRPLANE AND SYSTEM DESCRIPTION

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CONTENTS

8. AIRPLANE HANDLING, SERVICING AND MAINTENANCE

9. Supplements

SUPPLEMENT

EMERGENCY LOCATOR TRANSMITTER

MODEL AK---450

AMERI---KING CORPORATION

RECORD OF REVISIONS

SECTION 1 -- GENERAL

SECTION 2 -- LIMITATIONS

SECTION 3 -- EMERGENCY PROCEDURES

SECTION 4 -- NORMAL PROCEDURES

SECTION 5 -- PERFORMANCE -- NOT AFFECTED

SECTION 6 -- WEIGHT AND BALANCE -- NOT AFFECTED

SECTION 7 -- AIRPLANE AND SYSTEM DESCRIPTION

SECTION 8 -- AIRPLANE HANDLING, SERVICING

AND MAINTENANCE

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FLIGHT MANUAL

SUPPLEMENT No. 19

STALL WARNING SYSTEM

ACI type T1b

RECORD OF REVISIONS

SECTION 1 -- GENERAL

SECTION 2 -- LIMITATIONS

SECTION 3 -- EMERGENCY PROCEDURES

SECTION 4 -- NORMAL PROCEDURES

SECTION 5 -- PERFORMANCE -- NOT AFFECTED

SECTION 6 -- WEIGHT AND BALANCE -- NOT AFFECTED

SECTION 7 -- AIRPLANE AND SYSTEM DESCRIPTION

SECTION 8 -- AIRPLANE HANDLING, SERVICING

AND MAINTENANCE

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