Aeropro EuroFOX Technical specifications

A E R O P R O s.r.o.,Production of UL Planes
Dlhá 126, 949 07 Nitra, Slovak Republic
Tel./Fax: [phone]
FLIGHT MANUAL
AEROPRO
EUROFOX

AEROPRO EURO FOX FLIGHT MANUAL
- date- 2
Aircraft Name - Type:
EuroFOX 912 in version:
AEROPRO EuroFOX Pro
EuroFOX Basic
EuroFOX modell 99
EuroFOX Space Bugrad
Serial Number:
Registration Mark: ………………………..
Date of Issue: ………………………..
Stamp, Signature
This ultralight has not been registered by state administration and
is to be operated at operator’s own responsibility.
This ultralight can be operated in compliance with information and
limitations contained herein.

AEROPRO EURO FOX FLIGHT MANUAL
- date- 3
DATA OF THE AEROPLANES
Type Produktion Serial
Number:
Destination and
year of
production
Fuselage
Engine
PROPELLERs

AEROPRO EURO FOX FLIGHT MANUAL
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RECORD OF REVISIONS
Any revisions or amendments to the present manual shall be issued in
the form of bulletins with attached new pages. It is in the interests of
every user to enter such revision into the table of revisions and to
replace the existing page by the new one. The revised or corrected text
shall be indicated by a vertical line on left page margin and the page
shall bear revision number and date of its issue.
Rev.
No. Chapters Affected Pages Affected Date of Issue Bulletin Number
Bulletin
Approved On New Page Inserted On,
Signature

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0.1 LIST OF EFFECTIVE PAGES
Chap. Page Date Chp. Page Date Chap. Page Date
0 1 2-9 4-11
2 4-12
3 3 3-1
4 3-2
5 3-3 5 5-1
6 3-4 5-2
1 1-1 3-5 5-3
1-2 3-6 5-4
1-3 3-7
1-4 6 6-1
1-5 4 4-1 6-2
4-2 6-3
2 2-1 4-3
2-2 4-4 7 7-1
2-3 4-5 7-2
2-4 4-6
2-5 4-7
2-6 4-8
2-7 4-9
2-8 4-10

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0.2 TABLE OF CONTENTS
Chapter
General ..................................................................................................................1
Operating Limitations...............................................................................................2
Emergency Procedures ...........................................................................................3
Normal Procedures..................................................................................................4
Performance ............................................................................................................5
Weight and C.G. Position ........................................................................................6
Supplements............................................................................................................7

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CHAPTER 1
1. GENERAL
TABLE OF CONTENTS
1.1 Introduction
1.2 Certification Basis
1.3 Warning, Caution and Note
1.4 Brief Description
1.4.1 Aircraft Type
1.4.2 Power Unit
1.4.3 Propeller
1.4.4 Aircraft Dimensions
1.4.5 Deflections of Control Surfaces
1.4.6 Landing Gear
1.4.7 Other equipment
1.5 Three-View Drawing

AEROPRO EURO FOX FLIGHT MANUAL
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1.1 Introduction
This manual is designed to acquaint personnel with information towards
increasing safe and efficient aircraft operation.
This manual contains instructions necessary for pilots. Further it
contains additional data supplied by the aircraft manufacturer.
1.2 Certification Basis
This type of ultralight has been approved by Technical Board of LAA of
the Czech Republic in compliance with UL-2 regulation and it has been
issued Type Certificate No. ULL 03/96. Slovak Republic civile Aviation
Authotity has inssued Typ Certificate N: V – 82/2004 and DAeC has
issued Typ Certificate No: 61139.
1.3 Warning, Caution and Note
The following definitions apply to warnings, cautions and notes in the
flight manual:
WARNING Means that the non-observation of the corresponding
procedure leads to an immediate or important degradation
of the flight safety.
CAUTION Means that the non-observation of the corresponding procedure
leads to a minor or to a more or less long term degradation of
the flight safety.
NOTE Draws the attention of any special item not directly related to
safety but which is important or unusual.

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1.4 Brief Description
1.4.1 Aircraft Type
EuroFOX is an ultralight designed as a high-wing monoplane supported
by struts. A two-spar wing is provided with flaperon. Fuselage is a lattice-
work of steel tubes. Tail unit is formed of a lattice-work tube frame.
Landing device is a type of trigear undercarriage with a controllable nose
wheel
1.4.2 Power Unit
The EUROFOX ultralight is powered by ROTAX 912 UL engine. It is a
four-cylinder, four-stroke, opposed-cylinder, centre-camshaft engine with
over-head valves. Engine cooling is of a combined type, cylinder heads
are water-cooled, while cylinders are air-cooled. Dry sump lubrication.
The ignition system is of a dual, distributorless and capacitor flywheel
magneto type. The engine is equipped with an electric starter, AC
generator and a mechanical fuel delivery pump. The propeller is
powered from an integrated reduction gear with mechanical damping.
WARNING This engine has not been certified as an aircraft one and its
failure may occur at any time! The aircraft pilot is fully
responsible for consequences of such failure.
1.4.3 Propellers
The propeller made by Woodcomp/FITI/DUC company is a three-
bladed, right-handed, tractor, composite.
1.4.4 Aircraft Dimensions
Wing span..................................................................................9,125 m
Length........................................................................................5,605 m
Height ........................................................................................2,25 m
Wing area with flap..................................................................11,4 m
2
Chord length without flap...........................................................1,12 m
with flap...........................................................1,3 m
Wing loading ..........................................................................39,47 kgm
-2
Aspect-ratio................................................................................7,3
Propeller clearance (in flight position).......................................0,22 m

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1.4.5 Deflections of Control Surfaces
Elevator...................................................................up ............35°± 2°
...........................................................................down ............27°± 2°
Trim tab...................................................................up ............15°± 3°
...........................................................................down ............50°± 3°
Rudder...................................................................................±27°± 3°
Ailerons...................................................................up ............18°± 2°
...........................................................................down ........8.5°± 1°
Wing flaps...........................................................................0 ÷20°± 2°
1.4.6 Landing Gear
Track....................................................................................1.96 m
Wheel base..........................................................................1.3 m
Main landing gear wheel tire................................................ 14x4
Tire pressure.........................................................................200 kPa
Nose wheel tire........................................................................12x4
Tire pressure.........................................................................200 kPa
1.4.7 Other equipment
This aircraft is equipped with a hang glider release which can be used for
pulling of the advertisement flag.

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1.5 Three-View Drawing
9,125
5,605
2,25
0,2

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CHAPTER 2
2. OPERATING LIMITATIONS
TABLE OF CONTENTS
2.1 Introduction
2.2 Speed Limitations
2.3 Airspeed Indicator Marking
2.4 Engine Instruments Marking
2.5 Power Unit
2.6 Weights
2.7 Centre of Gravity Position
2.8 Operating Load Factors
2.9 Manoeuvres
2.10 Crew
2.11 Kinds of Operation
2.12 Fuel
2.13 Oil
2.14 Other Limitations
2.15 Limitation Placards

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2.1 Introduction
Chapter 2 contains operating limitations, instrument markings and basic
placards necessary for safe operation of the ultralight, its engine,
standard systems and equipment.
2.2 Speed Limitations
Speed limits are given in the synoptical table below.
Speed km/h IAS Remarks
V
NE
Never exceed
speed 185 Do not exceed this speed in any operation.
V
NO
Normal operating
limit speed 160 This speed may be exceeded under smooth air only, do not apply deflections
of control surfaces over one third.
V
A
Manoueuvring
speed 140 Do not apply full or steep deflections of control surfaces above this speed. The
aircraft might be overloaded!
V
FE
Maximum wing-
flaps extended
speed
120 Do not exceed this speed with wing flaps
extended.
V
S0
Minimum steady
flight speed
60
with extended wing flaps
V
S1
Minimum steady
flight speed
70
wing flaps retracted

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2.3 Airspeed Indicator Marking
Marking km/h IAS Signification
White arc 60 ÷
÷÷
÷120 Range of wing-flaps use.
Green arc 90 ÷
÷÷
÷160 Normal range of operation.
Yellow arc
160 ÷
÷÷
÷185 Manoeuvres must be
conducted with special
caution and in smooth air
Red line 185 Never exceed speed
2.4 Engine Instruments Marking
Instrument Red line
bottom limit Green arc normal
operation
Yellow arc
caution range
Red line,
upper limit
Tachometer
[r.p.m.] 1400 1400 ÷5500 5500 ÷5800 5800
Oil
temperature
[°C]
50 90 ÷110 110 ÷140 140
Cooling liquid
temperature
[°C]
60 60 ÷95 95 ÷110 110
Oil pressure
[kPa] 150 150 ÷400 400 ÷500
700
at cold start
Fuel pressure
[Bar] 0,0÷0,2 0,2÷0,45 0,45÷1 1
Fuel quantity
[ l ]
4
signal warning
sight check sight check 55

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2.5 Power Unit
Engine manufacturer..........ROTAX GmbH., Austria
Engine model.....................................ROTAX 912 UL
Max. power - take-off......................................59,6 kW
- continuous………………………..58,0 kW
Max. engine speed (MSL) - take-off (max. 5 min)...........5800 r.p.m.
- continuous...........................5500 r.p.m.
Max. cylinder head temperature ...........................................150 °C
Max. oil temperature.............................................................130 °C
Min. oil temperature................................................................50 °C
Oil pressure - min............................................................0,8 bar
- normal…………………………………2,0 -5,0 bar
Oil consumption ...........................................................max. 0.1 l/h
Fuel pressure - minimum…………………………………..0,15 bar
- maximum..................................................0,4 bar
Consumption at starting...........................................................22.7 l/h
Consumtion at 75% of power rating.........................................16.2 l/h
Specific consumption............................................................285 g/kWh
WARNING
This engine has not been certified as an aircraft one and
its failure may occur at any time! The ultralight pilot is fully
responsible for consequences of such failure.

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Propeller manufacturer ..........................Woodcomp/FITI/DUC
Propeller diameter ..............................................................1580-1620mm
Max. propeller speed ..........................................................3200 r.p.m.
Max. flight speed...................................................................185 km/h
Blade angle at 75% ................................................................15 °
Max. out-of-balance.............................................................0.5 g/600 mm
Propeller purpose ............................................................. tractor
2.6 Weights
Empty weight (standard version).......................................... 265 kg
Max. take-off weight.............................................................450 kg
Max. landing weight..............................................................450 kg
Max. fuel weight......................................................................45 kg
Max. baggage weight in baggage compartment....................10 kg
2.7 Centre of Gravity Position
Prescribed range of C.G. position.....................................18 ÷ 32 % MAC

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2.8 Operating Load Factors
At take-off weight of 450 kg
Maximum positive centre of gravity load factor..................... + 4 g
Maximum negative centre of gravity load factor .................... - 2 g
1
2
3
4
-1
-2
0
A
G
50 100 150 200 V[km/h]
n
VV
V
V
V
FA C
G
NE
V
V
S1
S0
2.9 Manoeuvres
This aircraft has been certified in normal category.
Permissible manoeuvres and manoeuvre entry speeds are given below.
Turn, bank of 60°.................................................................140 km/h
Side slip...............................................................................120 km/h
WARNING Aerobatics, intentional stalls and spins are prohibited.
Load envelope for maximum take-off weight of 450 kg

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2.10 Crew
Number of seats .......................................................................2
Minimum crew weight .............................................................55 kg
Max. crew weight ..................................................................160 kg
Max. crew weight at 28 l of fuel and zero baggage...............145 kg
Max. crew weight at 55 l of fuel and zero baggage...............123 kg
Maximum permissible cockpit load.......................................160 kg
2.11 Kinds of Operation
Only VFR day flights (under condition of ground contact) at ambient
temperature over 0°C are permitted.
Flights at ambient temperature over -10°C are permitted in case only
when is the aeroplane EUROFOX equipped with carburator heating
under no icing conditions.
WARNING IFR flights and flying in clouds are prohibited.

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2.12 Fuel
Fuel tank capacity - wing tanks................................................
2 x 40 l
- link tank ...............................................................................5 l
Max. fuel quantity....................................................................85 l
Usable fuel quantity................................................................84 l
Unusable fuel quantity..............................................................1 l
Fuel specification ...................unleaded EUROSUPER ROZ 95
in accordance with DIN 51607
Type recommended in the Slovak Republic.....................BA 95 Natural
The fuel system includes two wing tanks of 40 l fuel capacity each, a link
tank of 5 l capacity , drain cock, fuel cocks, a fuel filter, an engine fuel
pump and connecting line.
The fuel is gravity fed from the right-hand or left-hand wing tank into the
link tank depending which wing tank fuel cock is open. The fuel is then
further directed from the link tank via the main fuel cock and fuel filter
into the mechanical fuel pump on the engine which delivers the fuel to
carburettors.
The amount of fuel in tank is indicated by a fuel gauge which is a part of
every tank. Minimum fuel quantity in the link tank is indicated visually by
lighting up a warning light on the instrument panel. The remaining fuel,
i.e.4 l, is in that case enough for 15 minutes of flight.
The drain cock outlet is behind the left seat on the outside bottom side of
the fuselage; to drain off water and dirt, the drain pipe is to be pressed
into fuselage and subsequently a fuel sample is to be taken.
It is not advisable to change the used type of gasoline during engine
operation.Since fuel will be in most cases refuelled from a barrel or a
fuel can and not from the filling pump, it is necessary to pay a due
attention to this activity. Refuelling should be carried out in places not
endagering either the aircraft, its attendance or environment. Prior to
refuelling it is always necessary to check gasoline for absence of water.
Sampling should be done both from the transportation containers and
from tanks and aircraft fuel system through drain sump. When refuelling,
a funnel must be used provided with a strainer to trap impurities, or,
even better, with a buckskin leather which can trap also eventual fuel
moisture content. Fuel dumping is performed similarly as sampling by
means of a drain cock. When filling fuel into tanks, be careful to avoid
staining of cockpit window panels and glass with fuel as it contains
corrosive components that will cause a fast deterioration and damage to
cockpit glazing.

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2.13 Oil
Oil tank capacity ........................................................................3.0 l
Oil quantity................................................................................2.5 l
Minimum oil quantity..................................................................2.0 l
Oil specification................................................................ API SF, SG
for 4-stroke motorcycle engines
First charge...........................................Shell Advance VSX 4 10W-40
2.14 Other Limitations
No Smoking aboard the aircraft.
-It is not allowed to fly without back cockpit covering
2.15 Limitation Placards
Manufacturer: AEROPRO s.r.o. Nitra, SR
Max. take-off weight: 450 kg
Empty weight: 265 kg
Never exceed speed V
NE
185 km/h
Max. Flap Extended speed V
FE
110 km/h
Stalling speed V
S0
65 km/h
AEROBATICS, INTENTIONAL STALLS
AND SPINS ARE PROHIBITED