EVEKTOR-AEROTECHNIK SPORTSTAR User manual

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EVEKTOR --- AEROTECHNIK, a.s.
Letecká 1384
686 04 Kunovice
Czech Re ublic
Co yright E2005
EVEKTOR --- AEROTECHNIK, a.s.
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 air lane board during o eration. This manual contains information
which must be rovided to the ilot and also contains su lementary information rovided by the
air lane manufacturer --- Evektor --- Aerotechnik a.s.
This airplane must be operated in compliance ith the information and limitations
stated in this manual.

FLIGHT MANUAL
Doc. No. S2005FMENKT
Section 0
Technical
Information
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0. TECHNICAL INFORMATION
0.1 Log of Revisions
All revisions or supplements to this manual, e cept actual weighing data, are issued
in form of revisions, which will have new or changed pages as appendi and the
list of which is shown in the Log of Revisons table.
The new or changed te t 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.
Rev.
No.
Affected
Section
Affected
Pages Date Approved Date Date of insertion Signature

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Rev.
No. Signature
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insertion
DateApprovedDate
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Section

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0.2 List of Effective P ges
Section Page Date Section Page Date
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Section DatePageSectionDatePage
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0.3 T ble of Contents
Section
General 1
Limitations 2
Emergency procedures 3
Normal procedures 4
Performance 5
Weight and balance 6
Airplane and system description 7
Airplane handling, servicing and maintenance 8
Supplements 9

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FLIGHT MANUAL
Doc. No. S2005FMENKT
Section 1
General
October 20, 2005
1---1
CONTENTS
1. GENERAL
1.1 Introduction 1---3..................................................
1.2 Certification asis 1---3............................................
1.3 Warnings,cautions,notes 1---3.....................................
1.4 Descriptivedata 1---4..............................................
1.4.1 Airplanedescription 1---4............................................
1.4.2 owerplant 1---4....................................................
1.4.3 Maintechnicaldata 1---4............................................
1.4.4 Three---viewdrawing 1---5...........................................
1.5 Definitions and a reviations 1--- 6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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1.1 Introduction
This Flight manual has been prepared to provide pilots and instructors with informa-
tion for safe and efficient operation of the S ORTSTAR airplane. It also contains sup-
plementary information considered to be important by the airplane manufacturer.
1.2 Certification asis
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-
RES ONDING ROCEDURE 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 re-
lated to safety but which is important or unusual.

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Section 1
General
October 20, 2005
1---4
1.4 Descriptive data
1.4.1 Airplane description
S ORTSTAR 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 owerplant
The standard powerplant consists of ROTAX 912 S engine and WOODCOM
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 28.37 ft 8.646 m.........................................
Area 112.7 sq.ft 10.47 sq.m.........................................
MACdepth 4.1 ft 1.25 m...................................
Wing loading 10.76 lbs/sq.ft 52.53 kg/sq.m. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Aileron --- area 2.62 sq.ft 0.25 sq.m. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Flap --- area 5.60 sq.ft 0.52 sq.m...................................
Fuselage
length 19.62 ft 5.980 m........................................
width 3.55 ft 1.082 m.........................................
height 7.66 ft 2.335 m........................................
cockpit canopy max. width 3.87 ft 1.180 m. . . . . . . . . . . . . . . . . . . . .
Horizontal tail unit
Span 8.20 ft 2.50 m.........................................
HTUArea 20.88 sq.ft 1.94 sq.m....................................
Elevatorarea 8.40 sq.ft 0.78 sq.m..................................
Vertical tail unit
Height 4.07 ft 1.24 m.......................................
VTUArea 10.76 sq.ft 1.00 sq.m.....................................
Rudderarea 4.31 sq.ft 0.40 sq.m..................................
Landing gear
Wheeltrack 6.12 ft 1.865 m...................................
Wheelbase 4.43 ft 1.350 m...................................
Main and nose landing gear wheel diameter 14 in 350 mm. . . . . .

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Section 1
General
October 20, 2005
1---5
1.4.4 Three---view drawing
Figure 1-1

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Section 1
General
October 20, 2005
1---6
1.5 Definitions and a reviations
NOTE
The abbreviations on placards in the airplane cockpit,
are printed in BOLD CAPITAL LETTERS in the text of
this Flight manual.
ACCU accumulator
ALT ENC encoding altimeter
ATC air traffic control
bar bar 1 bar = 100 k a
BEACON anti---collision beacon
˚C Celsius degree
CAS calibrated airspeed
CLOCK aircraft clock
ft foot 1 ft = 0.305 m
G S global positioning system
HTU horizontal tail unit
IAS indicated airspeed
IC intercom
IFR instrument flight rules
ISA international standard atmosphere
kg kilogram
KIAS indicatedair speed in knots
KCAS calibrated airspeed in knots
mph mile per hour
mph CAS indicated airspeed in miles per hour
km/h CAS calibrated airspeed in km/h
kts knots 1 kt = 1.852 km/h
litres litre
lbs pounds 1 lb = 0.45 kg
m meter
MAC mean aerodynamical chord
max. maximum
min. minimum or minute
mm milimeter
m/s meter per second
OAT outside air temperature
OFF system is switched off or control element is in off---position
ON system is switched on or control element is in on---position
a pascal 1 a = 1N/m
2

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Section 1
General
October 20, 2005
1---7
SI pound per sq.in (1 SI = 6.89 k a)
R M revolutions per minute
RWY runway
sq.ft foot squared
sq.m meter squared
V
A
manoeuvring airspeed
V
FE
maximum flap extended speed --- flaps in 50˚ position
VFR visibility flight rules
V
LOF
airplane lift---off speed
V---METER voltmeter
V
NE
never exceed speed
V
NO
maximum structural cruising speed
V
SO
stall speed with wing flaps in 50˚ position
V
S1
stall speed with wing flaps in 0˚ position
VTU vertical tail unit
V
X
best angle---of---climb speed
V
Y
best rate---of---climb speed
X DR transponder

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General
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FLIGHT MANUAL
Doc. No. S2005FMENKT
Section 2
Limitations
October 20, 2005
2---1
CONTENTS
2. LIMITATIONS
2.1 Introduction 2---3..................................................
2.2 Airspeed 2---3.....................................................
2.3 Airspeedindicator arking 2---3....................................
2.4 Powerplant 2---4...................................................
2.5 Powerplant instru ent arking 2---5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2.6 Miscellaneous instru ent arking 2---5. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2.7 Weight 2---5.......................................................
2.8 Centreofgravity 2---6..............................................
2.9 Approved anoeuvres 2---6........................................
2.10Manoeuvringloadfactors 2---6......................................
2.11Flightcrew 2---6...................................................
2.12Kindsofoperation 2---7............................................
2.13Fuel 2---8..........................................................
2.14Oil 2---8...........................................................
2.15 Maxi u nu ber of passengers 2---8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2.16Otherli itations 2---9..............................................
2.17Li itationplacards 2---9............................................

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FLIGHT MANUAL
Doc. No. S2005FMENKT
Section 2
Limitations
October 20, 2005
2---3
2.1 Introduction
Section 2 contains operation limitation, instr ment marking and basic placards
necessary for safe operation of airplane and its engine, standard systems and
eq ipment.
Limitation for optional systems and eq ipment are stated in section 9 --- S pple-
ments.
2.2 Airspeed
Airspeed limitations and their meaning for operation are stated in the table below:
Speed KIAS mph IAS Meaning
V
NE
Never exceed speed 146 168 Do not exceed this speed
in any operation.
V
NO
Maxim m str ct ral cr is-
ing speed 103 118
Do not exceed this
speed, with exception of
flight in smooth air, and
even then only with in-
creased ca tion.
V
A
Manoe vring speed 86 99
Do not make f ll or
abr pt control movement
above this speed, be-
ca se nder certain con-
ditions the aircraft may be
overstressed by f ll con-
trol movement.
V
FE
Maxim m flap extended
speed 70 81 Do not exceed this speed with the given flap setting.
2.3 Airspeed indicator arking
Airspeed indicator markings and their colo r---code significance are shown in the
table below:
M
a
r
k
i
n
g
Range
M
e
a
n
i
n
g
M
a
r
k
i
n
g
KIAS mph IAS
M
e
a
n
i
n
g
Red line 37 43 V
S0
at maxim m weight (flaps in land-
ing position 50˚)
White arc 37 --- 70 43 --- 81
Operating range with extended flaps.
Lower limit--- V
S0
at maxim m weight
(flaps 50˚)
Upper limit --- V
FE

FLIGHT MANUAL
Doc. No. S2005FMENKT
Section 2
Limitations
October 20, 2005
2---4
Marking Meaning
Range
Marking Meaning
mph IASKIAS
Green arc 42 --- 103 49 --- 118
Normal operation range
Lower limit --- V
S1
at maxim m
weight (flaps 0˚)
Upper limit --- V
NO
Yellow arc 103 --- 146 118 --- 168 Manoe vres m st be cond cted with
ca tion and only in smooth air
Red line 146 168 Maxim m speed for all operations ---
V
NE
.
2.4 Powerplant
Engine anufacturer: Bombardier---Rotax GMBH
Engine type: ROTAX 912 S
Power: maxim m take---off 100 HP / 73.5 kW
maxim m contin o s 93.8 HP / 69.0 kW
Engine speed: maxim m take---off 5800 RPM max. 5 min tes
maxim m contin o s 5500 RPM
idle 1400 RPM
Cylinder head
te perature:
maxim m 135 ˚C 275 ˚F
Oil te perature: maxim m 130 ˚C 266 ˚F
optim m operation 90 --- 110 ˚C 190 --- 230 ˚F
Oil pressure: maxim m 7 bar 102 PSI
minim m 0.8 bar 12 PSI
optim m operation 2 --- 5 bar 29 --- 73 PSI
Fuel pressure: minim m 0.15 bar 2.2 PSI
Fuel grades: see 2.13, page 2---8
Oil grades: see 2.14, page 2---8
Reducer gear ratio: 2.43 : 1
Propeller anufacturer: WOODCOMP s.r.o.
Propeller type: KLASSIC 170/3/R
3 blade, composite, on---gro nd adj stable
Propeller dia eter: 68 in 1700 mm
Maxi u prop speed: 2600 RPM
NOTE
If installed a different propeller type --- see section 9 ---
S pplements for propeller limitations.

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Section 2
Limitations
October 20, 2005
2---5
2.5 Powerplant instru ent arking
The colo r---code of instr ments is shown in the following table:
Red line Green arc Yellow arc Red line
Instr ment Units Lower limit
Normal
operation
range
Ca tion
range Upper limit
RPM indicator RPM --- 1400 ÷5500 5500 ÷5800 5800
O
i
l
t
e
m
p
e
r
a
t
r
e
i
n
d
i
c
a
t
o
r
˚C --- 90 ÷110 50 ÷90
110 ÷130 130
O
i
l
t
e
m
p
e
r
a
t
r
e
indicator
˚F --- 190 ÷230 120 ÷190
230 ÷266 266
O
i
l
p
r
e
s
s
r
e
i
n
-
d
i
c
a
t
o
r
bar 0.8 2÷50.8 ÷2
5÷77
O
i
l
p
r
e
s
s
r
e
i
n
-
dicator
PSI 12 29 ÷73 12 ÷29
73 ÷102 102
CHT indicator ˚C --- --- --- 135
CHT indicator ˚F --- --- --- 275
2.6 Miscellaneous instru ent arking
There are not other instr ments with colo r marking.
2.7 Weight
Empty weight (standard eq ipment) 695 lbs ± 2 % 315 kg ± 2 %. . . . . . . . . . .
Maxim m take---off weight 1213 lbs 550 kg. . . . . . . . . . . . . . . . . . . .
Maxim m landing weight 1213 lbs 550 kg. . . . . . . . . . . . . . . . . . . . .
Maxim m weight in baggage compartment 55 lbs 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.