Apollo FOX Manual de usuario
1
Pilot’s Operating
Handbook
and
Maintenance Manual
APOLLO FOX
Issue: 29.08.2014
2
/ 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:
3
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
4
0.2 LIST OF EFFECTIVE PAGES
Chapter Page Date Chapter Page Date Chapter Page Date
5
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
6
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.
Tabla de contenidos
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