Apollo Fox Pilot's Operating Handbook And Maintenance Manual

Brand: Apollo

Model: Fox

Category: Toys

Type: Pilot's Operating Handbook And Maintenance Manual

Apollo Fox is an aerodynamically controlled microlight aircraft designed as a high-wing monoplane supported by struts. It is powered by a Rotax 912UL, or ULS engine, and has a two-spar wing with flaperon. The aircraft is easy to assemble and transport, and does not require a maintenance staff or established aerodrome. It is suitable for recreational flying and pilot training.

Some of the key features of the Apollo Fox include:

Maximum speed of 112 mph (180 km/h)
Cruise speed of 87 mph (140 km/h)
Stall speed of 39 mph (63 km/h)
Range of 373 miles (600 km)
Endurance of 4 hours
Payload capacity of 440 pounds (200 kg)

Some of the key features of the Apollo Fox include:

Maximum speed of 112 mph (180 km/h)
Cruise speed of 87 mph (140 km/h)
Stall speed of 39 mph (63 km/h)
Range of 373 miles (600 km)
Endurance of 4 hours
Payload capacity of 440 pounds (200 kg)

Pilot’s Operating

Handbook

and

Maintenance Manual

APOLLO FOX

Issue: 29.08.2014

/ 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:

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

New Page

Inserted On,

Signature

0.2 LIST OF EFFECTIVE PAGES

Chapter Page Date Chapter Page Date Chapter Page Date

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

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

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

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.

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.

1.4.4 Three view drawing of the aircraft

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

Wing area ............................................................................... 11.5 m

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.

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

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

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

Never

exceed speed

200 Do not exceed this speed in any

operation.

Normal

operating limit

speed

180 This speed may be exceeded under

smooth air only, do not apply deflections

of control surfaces over one third.

Design

manoeuvre

speed

124 Do not apply full or steep deflections of

control surfaces above this speed. The

aircraft might be overloaded!

Wing flaps

extended

speed

130 Do not exceed this speed with flaps

extended.

Minimum

steady flight

speed

60 Flaps extended.

Minimum

steady flight

speed

65 Flaps retracted.

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 higher airspeed the doors can

damage the wings undersurface!

The maximum IAS with removed door/s 140 km/h

Both cases must be sure the objects in the baggage

compartment are secured and no moving objects what can fall

out from the cockpit. The object fallen out from the cockpit can

make serious damage on the aircraft body/wings 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]

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

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

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

) ........................................... 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

C.G. Position:

+ 0,

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

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

50 100 150 200

V[km/h]

A C

Load

envelope

for maximum take-off weight of 450 kg

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.

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

200 km/h

Max. Flap Extended speed V

130 km/h

Stalling speed

64 km/h

AEROBATICS, INTENTIONAL

STALLS

AND SPINS ARE PROHIBITED

2.17 Cockpit view

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Apollo Fox Pilot's Operating Handbook And Maintenance Manual

Brand: Apollo

Model: Fox

Category: Toys

Type: Pilot's Operating Handbook And Maintenance Manual

Some of the key features of the Apollo Fox include:

Maximum speed of 112 mph (180 km/h)
Cruise speed of 87 mph (140 km/h)
Stall speed of 39 mph (63 km/h)
Range of 373 miles (600 km)
Endurance of 4 hours
Payload capacity of 440 pounds (200 kg)

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Apollo Fox Pilot's Operating Handbook And Maintenance Manual

Apollo Fox Pilot's Operating Handbook And Maintenance Manual

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