Apollo FOX User manual

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Pilot’s Operating
Handbook
and
Maintenance Manual
APOLLO FOX
Issue: 29.08.2014

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/ CAA / Civil Aviation Administration of Hungary
This microlight aircraft meets the requirements of BCAR Sections “S” Cap 482
regulations all around her structure, used materials, performance and qualities and
has been classified with microlight category, and can be operated in accordance with
information and limitations contained in this handbook.
APOLLO FOX
Aerodynamically Controlled Microlight Aircraft
Aircraft Name - Type: Apollo Fox
Manufacturer’s address: 3300. Hungary Mester u, 3. Eger
Serial Number:
Aircraft Registration:
Date of Issue: 29.09.2014
Signature:

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The presented microlight aircraft can be operated in accordance with
limitations and information contained in this handbook.
0.1 RECORD OF REVISIONS
This page with the table of record of revision enables users to enter revisions or
amendments issued in the form of bulletins and to substitute non-existing pages
with new ones. Corrected texts shall be marked by a vertical line on the left
page margin and these pages shall also bear revision number and date of
issue.
.
Revision
number Chapters Affected Pages Affected Date of Issue Bulletin Number Bulletin Approved
By
New Page
Inserted On,
Signature

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0.2 LIST OF EFFECTIVE PAGES
Chapter Page Date Chapter Page Date Chapter Page Date

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0.2.1 TABLE OF CONTENTS
Chapter
General ...................................................... 1
Operating Limitations................................. 2
Operating data and procedures ................. 3
Normal Procedures..................................... 3.1
Emergency Procedures............................... 3.2
Performance................................................ 4
Supplements................................................ 5

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1. GENERAL
TABLE OF CONTENTS
1.1............................................................... Introduction
1.2.................................................... Certification Basis
1.3 ......................................... Definition of denotations
1.4 .......................................................Brief Description
1.4.1.......................................................... Aircraft Type
1.4.2 .................................................................Propeller
1.4.3...............................................................Power Unit
1.4.4 ...................... Three-View Drawing of the aircraft
1.4.5............................................... Aircraft dimensions
1.4.6 ..........................................................Landing gear

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1.1 Introduction
The purpose of this handbook is to provide information for personnel towards
increasing safety and efficient aircraft operation. It includes necessary instructions for
pilots and additional data provided by the manufacturer based on calculations,
loading tests and test flight records. Pilots shall be acquainted with the content of this
handbook and comply with its limitations while operating the aircraft. The
manufacturer only takes responsibility for safe operation if the pilot entirely complies
with the regulations of this handbook.
If the owner merchandises the aircraft, then reports shall be made towards the
manufacturer concerning name and address of the new owner or operating
organization.
1.2 Certification
This type of microlight has been approved by The Civil Aviation Authority of Hungary
in accordance with BCAR Section “S” Cap 482 regulations and it has been issued
Type Certificate No.:
1.3 Definition of denotations
This handbook comprises three types of denotations in order to arouse operators’
attention according to the severity of ignoring related procedures. Definitions of
denotations are given below:
WARNING
Ignorance of the related procedure leads to an immediate or
serious degradation of flight safety level.
CAUTION
Ignorance of the
related
procedure leads to a minor
degradation
of flight safety level.
NOTE
Arouse the a
ttention of any special item indirectly related to
safety but which is important or unusual.

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1.4 Brief Description
1.4.1 Aircraft type
The Apollo Fox type powered microlight is the first aerodynamically controlled
aircraft produced by Halley Ltd. After producing hundreds of weightshift controlled
aircrafts the birth of Apollo-Fox was a turning point in the profile of the Company.
Many years of experiences gained during the production and operation of other
Hungarian aircraft types helped us in the contemplation and construction. On
development,besides small size, quick assembly and easy transportation, price
reduction was a primary aspect. Neither maintenance staff nor established
aerodrome is required for operating the aircraft.
The aircraft is designed as a high-wing monoplane supported by struts. A two-spar
wing is provided with flaperon. The spars and load bearing elements are made of
high strength steel tubes. Fuselage is a lattice-work of steel tubes. The tail unit is
made of a lattice-work tube frame. Landing gear is of a conventional type, with a
nose gear.
1.4.2 Propeller
The propeller is of a conventional two-three-four bladed, tractor, rotating in clockwise
direction. It is made of wood and/or plastic, or composite type fixed pitch or
ground/air adjustable propeller and has a strengthened leading edge. The propeller
type for each serial number is depends on the order made by the plane’s owner.
1.4.3 Power Unit
The Apollo Fox microlight is powered by Rotax
912UL,or ULS engine. It is an opposed cylinder,
four-stroke, four-cylinder, centre cam shaft engine
with over-head valves. Cylinder heads are water-
cooled and cylinder air-cooled. Lubrication system is
of a crank case type. The ignition system is of a
dual ignition type. The engine is equipped with an
electric starter, DC generator, fuel delivery pump
and voltage regulator. The propeller is powered
from an integrated reduction gearbox.
WARNING
This engine
is not
certified
for aircraft,
and failure may occur at
any time! The pilot bears full responsibility for the consequences
of it’s failure.

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1.4.4 Three view drawing of the aircraft

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1.4.5 Aircraft Dimensions
Wing span....................................................................................9.2 m
Length........................................................................................5.75 m
Wing folded up length.................................................................6.47 m
Propeller diameter......................................................................1.70 m
Height (nose gear version) ........................................................ 2.28 m
Height, tail wheel version (windshield)..........................................1.78 m
Cockpit width............................................................................. 1.10 m
Number of seats................................................................................ 2
Wing surface loading........................................................ 39.13 kg/m
2
Wing area ...............................................................................11.5 m
2
Chord length without flap ..........................................................1.12 m
with flap.............................................................1.3 m
Aspect-ratio.....................................................................................7.0
Propeller clearance (in flight position)........................................0.25m
Track.........................................................................................1.85 m
Wheel base...............................................................................1.45 m
Main landing gear wheel tire ................................................35x15 cm
Tire pressure............................................................................ 1,7 bar
Nose wheel tire ......................................................................12x4 cm
Tire pressure............................................................................ 1,5 bar
1.4.6 Landing gear
The landing gear is of a conventional type with a steerable nose wheel. The landing
gear consists of two brakable main wheels and a steerable nose wheel. Landing gear
is not retractable. Both the landing gear legs and wheels can be equipped with fairing
panels. Floats and landing ski can also be fixed to the junction points of the main
wheels. Wheels with low-pressure tires (tube or tubeless) are provided with hydraulic
disc brakes. As. Nose wheel can be controlled by the rudder pedals on the ground.

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Track...................................................................................1.85 m
Wheel base ........................................................................1.45 m
Main landing gear wheel tire..............................................35x15 cm
Tire pressure......................................................................1,7 bar
Nose wheel tire...................................................................12x4 cm
Tire pressure......................................................................1,5 bar

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2. OPERATING LIMITATIONS
TABLE OF CONTENTS
2.1 ...............................................................Introduction
2.2 ................................................Airspeed Limitations
2.3 ..................................... Airspeed Indicator Marking
2.4 ................................... Engine Instruments Marking
2.5 ........................................................Power Unit Data
2.6 ..................................................................... Weights
2.7 ....................................... Centre of Gravity Position
2.8........................................................................Loading
2.9 ..................................................Flight Load Factors
2.10 ............................................................ Manoeuvres
2.11....................Maximum wind component limitations
2.12 .........................................................................Crew
2.13 .................................................Kinds of Operation
2.14 .............................................................Fuel system
2.15 .............................................................................Oil
2.16................................................ .Limitation Placards
2.17…………………………………………….Cockpit view

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2.1 Introduction
This chapter contains operating limitations, instrument markings and basic
placards necessary for safe operation of the microlight, its engine, standard
systems and equipment.
2.2 Speed Limitations
Related speed limits are summarised in the table below:
Speed km/h
IAS Remarks
V
NE
Never
exceed speed
200 Do not exceed this speed in any
operation.
V
NO
Normal
operating limit
speed
180 This speed may be exceeded under
smooth air only, do not apply deflections
of control surfaces over one third.
V
A
Design
manoeuvre
speed
124 Do not apply full or steep deflections of
control surfaces above this speed. The
aircraft might be overloaded!
V
FE
Wing flaps
extended
speed
130 Do not exceed this speed with flaps
extended.
V
S0
Minimum
steady flight
speed
60 Flaps extended.
V
S1
Minimum
steady flight
speed
65 Flaps retracted.

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It is allowed to fly with opened or removed door/s
The maximum IAS with opened door is 120 km/h, avoid slip
manoeuvre with door/s open.
In case of opened door and hi her airspeed the doors can
dama e the win s undersurface!
The maximum IAS with removed door/s 140 km/h
Both cases must be sure the objects in the ba a e
compartment are secured and no movin objects what can fall
out from the cockpit. The object fallen out from the cockpit can
make serious dama e on the aircraft body/win s etc!
2.3 Airspeed Indicator Marking
Marking km/h IAS Signification
White
arc 60 ÷
÷÷
÷130 Range of flaps use
Green
arc 90 ÷
÷÷
÷180 Normal operating range
Yellow
arc 180 ÷
÷÷
÷200 Manoeuvres must be executed with special
caution and in smooth air
Red line
200 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 1500 ÷5100 5100 ÷5800 5800
Oil temperature
[°C] 50 90 ÷110 110 ÷130 130
Cooling liquid
temperature
[°C]
50 80÷100 100÷120 120
Oil pressure
[bar] 0,8 1,5 ÷4,0 4,0 ÷5,0 7,0.
at cold start
Fuel quantity
[ l ] Indicator on the
instrument
panel
Visual check Visual check 60

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2.5 Power Unit Data
Engine model....................................... .ROTAX 912 UL-ULS
Max. power - take-off........................... 80-100 HP
- continuous...................... 79-89 HP
Max. engine speed (MSL) - take-off ........5800 r. p .m. (max. 1 min.)
- continuous.............5500 r. p .m. (max. 5 min.)
Max. cylinder head temperature.........................150 °C
Max. cooling liquid temperature .........................100 °C
Min. cooling liquid temperature…………………. .50 °C
Min. oil temperature ...........................................50 °C
Optimal oil temperature ……………………......... 90-110 °C
Oil pressure -normal........................................1,5-5 bar
-maximum...................................7 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
Consumption at 75% of power setting................17,5 l/h
Normal cruise…………………………………….....12-14 l/h
Calibre..................................................................92 mm
Travel:............................................................67,0 mm
Piston displacement............................................1.200-1350 cm³
Compression ratio:..............................................9,0:1
Weight:.................................................................70,0-71,0 kg
Ignition equipment: .............................................DUCATTI dual system
Ignition point:......................................................24°before upper dead center
Firing order:........................................................1-4-2-3
Igniter plug:.........................................................NGK DCPR7E-DCPR8E
Generator: ......................................................... AC, magnets
13,5-14,2 V/250 W DC
Carburettor: ....................................................2 x BING constant pressure64/32
Air filter: .............................................................surface 700 – 700 cm²

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WARNING
This engine is not certified for aircraft, and failure may occur at
any time! The pilot bears full responsibility for the consequences
of it’s failure.
Propeller manufacturer: .....................................DM prop.
Propeller diameter..............................................1700 mm
Max. propeller speed..........................................2600 r.p.m.
Max. airspeed (V
NE
) ...........................................200 km/h
Blade angle at 75% ...........................................18 °
Max. out-of-balance ............. ……………….. 0.5 g/600 mm
Propeller purpose...............................................tractor
2.6 Weights
Empty weight (standard version)..........................275 kg
Max. take-off weight.................... .................... 450 kg
With – Emergency parachute.................................472,5
Max. landing weight .............................................450 kg/ 472,5 Kg
Max. fuel weight................................................. 48 kg
Max. baggage weight in baggage compartment....10 kg
Maximum crew weight…………………………….. 180kg
Minimum crew weight........................................ 55 kg
Maximum weight of baggage behind pilot’s seat….10 kg
2.7 Centre of Gravity Position
The weight and C.G. position found – empty weight :
Weight:
275
kg
C.G. Position:
+ 0,
37
metre
WARNING
The C.G.limits in flight position must be between :
+ 0,31metre and + 0,49 metre
2.7. a
Positions/distances from leading edge:
Pilots:+500 mm
Fuel tank: +400 mm
Baggage compartment: +920 mm

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2.8 Loading
This section contains values of payload at which the aircraft can be safely operated.
Aircraft weighing procedures and computations to determine range of safe payload
are included.
Table of Weights
Max. Take-Off Weight No Baggage 5 kg Baggage 10 kg Baggage
450 kg Max. Crew Weight Max. Crew Weight Max. Crew Weight
Empty 275 kg 175 kg 170 kg 165 kg
+ Fuel 30 l 154 kg 149 kg 144 kg
+ Fuel 60 l 133 kg 128 kg 123 kg
2.9 Flight 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
Load envelope for maximum take-off weight of 450 kg

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2.10 Manoeuvres
This aircraft has been certified in normal category.
Permissible manoeuvres and manoeuvre entry speeds are given below.
Turn, bank of 60°...............................................124 km/h
Side slip ............................................................124 km/h
WARNING
Aerobatics, intentional stalls and spins are prohibited.
2.11 Maximum wind component limitations
Maximum permitted wind speed components for take-off and landing:
aligned with runway axis...................................10 m/s
perpendicular to runway.....................................4 m/s
tail wind..............................................................3 m/s
2.12 Crew
Number of seats ................................................2
Minimum crew weight.........................................55 kg
Max. crew weight ...............................................175 kg
Maximum permissible cockpit load.....................180 kg
2.13 Kinds of Operation
Only VFR day flights (by permanent visual ground contact.)
WARNING
IFR flights and flying in clouds are prohibited.
2.14 Fuel system
Fuel tank capacity wing tanks ............................2 x 30 l
Link tank.............................................................6 l
Max. fuel quantity...............................................66 l
Usable fuel quantity............................................60 l
Unusable fuel quantity on ground.......................6 l
Unusable fuel quantity in the air with engine on...2 l
Fuel specification unleaded Minimum.............RON 95
in accordance with DIN 51607
CAUTION !The fuel tanks (wings+center tank) contains 6 litres of fuel after complete
defueling on the ground. This amount is the unusable fuel quantity on ground. In the air with
operating engine the unusable fuel is 2 litres. The engine can completely empty the center
link tank.

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The fuel system includes two wing tanks of 30 l fuel capacity each, a link tank of 6 l
capacity , drain cock, fuel cocks, a fuel filter, an engine fuel pump, electric fuel pump
and connecting line.
The fuel is gravity flown 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 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.6 l, is in that case enough for 15 minutes of flight. The drain cock
outlet is connected to the link tank to drain off water and dirt. 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 endangering 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.
2.15 Oil
Oil tank capacity.................................................4.0 l
Oil charge...........................................................2.5 l
Minimum oil quantity ..........................................2.0 l
Oil specification, synthetic based motorcycle oil API SG, JASO MA
2.16 Limitation Placards
Manufacturer:
Halley Ltd.
Max. take-off weight: 450 kg/472,5 Kg
Empty weight: 275 kg
Never exceed speed V
NE
200 km/h
Max. Flap Extended speed V
FE
130 km/h
Stalling speed
V
64 km/h
AEROBATICS, INTENTIONAL
STALLS
AND SPINS ARE PROHIBITED

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2.17 Cockpit view