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1
Pilot’s Operating
Handbook
and
Maintenance Manual
APOLLO FOX
Issue: 29.08.2014
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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:
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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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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
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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 watercooled 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/m2
Wing area ............................................................................... 11.5 m2
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
VNE Never
exceed speed
200 Do not exceed this speed in any
operation.
VNO Normal
operating limit
speed
180 This speed may be exceeded under
smooth air only, do not apply deflections
of control surfaces over one third.
VA Design
manoeuvre
speed
124 Do not apply full or steep deflections of
control surfaces above this speed. The
aircraft might be overloaded!
VFE Wing flaps
extended
speed
130 Do not exceed this speed with flaps
extended.
VS0 Minimum
steady flight
speed
60 Flaps extended.
VS1 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 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]
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 (VNE) ........................................... 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
V
V
V
V
V
F
A 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
AEROBATICS, INTENTIONAL
STALLS
AND SPINS ARE PROHIBITED
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2.17 Cockpit view
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3. OPERATING DATA AND PROCEDURES
3.1 Normal Procedures
TABLE OF CONTENTS
3.1.1 ............................................................Introduction
3.1.2 ............................................ Outfit and Equipment
3.1.3 ............ Daily Preparation, Pre-Flight Preparation
3.1.4 .................................................... Pre-Flight Check
3.1.5 ..................... Normal Procedures and Checklists
3.1.5.1 Before engine start up (After Entering Cockpit)
3.1.5.2 ........................... Use of External Power Supply
3.1.5.3 ................................................... Engine Start up
3.1.5.4 .......................................................... Before Taxi
3.1.5.5 ...................................................................... Taxi
3.1.5.6 ................................................... Before Take-Off
3.1.5.7 ............................................................... Take-Off
3.1.5.8 ................................................................... Climb
3.1.5.9 ........................................................Cruise Flight
3.1.5.10 ............................................................. Descent
3.1.5.11 ......................................................... Downwind
3.1.5.12 ........................................................... Base Leg
3.1.5.13 ....................................................... Before Final
3.1.5.14 ................................................. Balked Landing
3.1.5.15 ............................................................. Landing
3.1.5.16 ..................................................... After landing
3.1.5.17 ................................................... Engine Cut-off
3.1.5.18 ............................................. Post-Flight Check
3.1.5.19 .................................................................... Rain
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3.1.1 Introduction
Chapter 3.1 contains procedures for normal aircraft operation.
3.1.2 Outfit and Equipment
It includes a basic set of instruments to monitor flight and power unit
parameters. Further equipment is offered as optional.
It holds the following as minimum: airspeed indicator, altimeter, vertical speed
indicator, slip indicator, engine RPM, CHT, oiltemperature, oil pressure.
II. INSTRUMENTS
Type Serial No.
Airspeed indicator
Altimeter
Vertical speed indicator
Slip indicator
Compass
Engine RPM
CHT
EGT
Water temperature
Oil temperature indicator
Oil pressure indicator
Charge indicator lamp
Intercom
Radio
Transponder
Engine ROTAX 912 UL-ULS
Propeller dm-prop dmp – 3/3 1700 mm
III. STORAGE BATTERY
Type
Voltage 12 V
Capacity 8 Ah
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3.1.3 Daily Preparation, Pre-Flight Preparation
10
11
1
3
22
4
5
5
6
7
9
3
12
8
13
1.Cockpit master switch off
• ignition off, fuel cocks – shut off, fuel quantity check, instruments, check of
condition
• safety belts, condition, no damage
• check of flaperon tie rods connection
• hand control, condition and free running
• foot control, condition and free running - brakes, condition and function -
trimming, free running - engine control, free running
• loose articles - cleanness of window panels- door, shut and locked
2. Main landing gear - landing gear legs, condition, attachment
• wheels, condition, tire pressure 1,7 bar - brake condition
3. Wings - check of wing and struts suspensions and clamping bolts
• condition of wing surface and skin
4. Pitot tube - condition and direction
5. Flaperons - condition of attachment, hinges, flaperon surface
• free motion of flaperon - check of counterweights attachment
6. Rear cockpit cover - condition and attachment
7. Fuselage - condition, undamaged condition of lattice members and skin
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8. Stabiliser and elevator - condition of hinges, attachment of stabiliser
struts
• free motion of elevator and trim tab.
9-10. Fin and rudder - condition and attachment, free
11. Propeller - condition of blades, propeller driver, check of locking propeller nuts
(if propeller spinner is not installed). Nose gear condition, function,
attachement and tyre pressure 1.5 bar
12. Engine- condition and attachment of engine mount - condition and attachment
of suction piping, carburettors and controls
• condition and attachment of exhaust manifold - cooling, liquid condition and
quantity - check of fuel system, filter and carburettors draining off water and
dirt from the link tank - check of electrical system, ignition, cable connections,
13. Oil quantity
CAUTION
Perfom the engine check heading upwind! Do not carry it out on loose
terrain! Nobody is allowed to stand within dangerous proximity and, in
particular, within propeller level!
NOTE
After check of engine power, cool down the engine for a short time to
avoid evaporation of the cooling liquid in cylinder heads.
3.1.4 Pre-Flight Check
cockpit, check - cockpit interior equipment.
- safety belts, their undamaged condition.
- control system, free running.
- controls, free running and undamaged condition.
wings, check - wing surfaces for undamaged condition.
- wing and struts suspensions
- flaperons, undamaged condition.
fuselage, check - undamaged condition of fuselage, lattice members and
skin.
tail unit - check of its condition, surface and attachment.
landing gear - check of its condition and attachment.
engine and propeller - check of their condition and attachment.
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3.1.5 Normal Procedures and Checklists
3.1.5.1 Before engine start up (After Entering Cockpit)
- rudder control free motion
- brakes check function
- aileron and elevator control free motion
- trim free running and functional check
- wing flaps free motion, retracted
- engine control + choke free running
- master switch off
- ignition off
- sectionalizing switches off
- main fuel cock shut
- wing tank fuel cocks shut, fuel quantity check
- instruments check of values, settings
- safety belts shut, locked
- transceiver and intercom check of condition
3.1.5.2 Use of External Power Supply
The aircraft is not provided with connection for external power supply. In case of
emergency, the external power supply may be connected to battery contacts.
3.1.5.3 Engine Start up
- master switch switch on
- main fuel cock open
- wing tank fuel cocks open to tank with more fuel
- choke switch on (cold engine only)
- throttle idle
- control stick pulled backwards, clamped between
legs
- brakes braked, with chocks under wheels, if
necessary
- engine and propeller check of clearance
- ignition switch on
- starter switch on (10 sec. maximum)
- after starting the engine adjust speed to idle.
- instruments check of indications
- choke switch off
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3.1.5.4 Before Taxi
- check of free space in direction of
contemplated taxiing
- brakes functional check
- stop watch switch on, record time
3.1.5.5 Taxiing
- taxiing speed is15 km/h maximum. Steering is performed by foot control and
deceleration of main wheels.
- at crosswind hold ailerons „upwind“, using the control stick.
- at strong crosswind perform the taxiing with an assistant holding the wing by
its windward side.
3.1.5.6 Before Take-Off
- brakes brakes on
- throttle 3500 r.p.m.
- trim neutral
- wing flaps take-off position
- master switch switched on
- ignition switched on
- main fuel cock open
- tank fuel cocks fuel quantity check
- instruments check of indications
- door closed, locked
- safety belts fastened, tightened
- control check of free motion
- check of runway
3.1.5.7 Take-Off
Continuously increase engine power to maximum (max. 5800 r.p.m.), bring the
aircraft into motion. Slightly pulling the control stick backward, unstick the nose
wheel off ground. At a speed of 70 km/h, slightly pulling the control stick
backward, unstick the main landing gear. Hold acceleration after unsticking till
increase of speed to 100-110 km/h. Slowly pulling the control stick backwards,
get the aircraft to climbing at a speed of 100 - 110 km/h.
- airspeed 100 - 110 km/h IAS
- throttle max. cont. power, max. 5500
r.p.m.
- engine instruments within limits
- wing flaps retract them at a height of 50 m
- trimming trim
WARNING
Take
-
off is forbidden
- if engine running is not smooth.
- if runway is not clear.
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3.1.5.8 Climb
- throttle max. cont. power, max. 5500 r.p.m.
- airspeed 100 - 110 km/h IAS
- engine instruments within limits
3.1.5.9 Cruise Flight
- bring the aircraft into horizontal flight
- throttle 4000 - 5000 r.p.m.
- airspeed 110 - 150 km/h IAS
- engine instruments within limits
3.1.5.10 Descent
- throttle increased idle
- airspeed 110 km/h IAS
- engine instruments within limits
CAUTION
At long final and when descending from a considerable height, it is not
advisable to reduce the engine throttle control to minimum. In such
case the engine becomes undercooled and a loss of power occurs.
When descending, apply increased idle so that engine instrument
indications stay within the limits for normal use.
3.1.5.11 Downwind
- throttle 3500 - 4500 r.p.m.
- airspeed 110 km/h IAS
- engine instruments within limits
- fuel check fuel quantity
-safety belts tighten
- base leg and before final space check of free space
- at base leg and before final space check free space
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3.1.5.12 Base Leg
- throttle 3000 r.p.m.
- airspeed 110 km/h IAS
- engine instruments within limits
- wing flaps take-off
- trimming trim
- space before final check of free space
3.1.5.13 Before Final
- airspeed 100 km/h IAS
- throttle adjust as needed
- engine instruments within limits
- wing flaps for landing
- trimming trim
- engine instruments within limits
- check of clear landing strip ( people, obstacles).
3.1.5.14 Balked Landing
- throttle max.take-off power, max. 5800 r.p.m.
- airspeed 100 - 110 km/h IAS
- engine instruments within limits
- wing flaps take-off
- trimming trim
- wing flaps retract at a height of 50 m
- trimming trim
- speed max. cont. power, max. 5500 r.p.m.
- climb 100 - 110 km/h IAS
3.1.5.15 Landing
At a height of about 10 m reduce the engine speed to idle. Maintain speed of
90-100 km/h till flattening-out. When floating at a height of 0.5 -1 m above
ground, decelerate gradually by pulling the control stick backward. At a speed of
about 60 km/h the aircraft touches-down on main wheels. At landing run it is
necessary to hold the elevator up and to apply brakes with feeling, keeping in
mind a potentiality of turning the aircraft over on propeller. At wind speed over 7
m/sec it is advisable to land with increased idle.
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3.1.5.16 After landing
- brakes finish braking slowly, may also be
applied for control of direction of
movement
-wing flaps retract
3.1.5.17 Engine Cut-off
- throttle cool down the engine at 2000 r.p.m.
- engine instruments within limits
- transceiver switch off
- ignition switch off
- master switch switch off
- sectionalizing switches switch off
- main fuel cock shut
3.1.5.18 Post-Flight Check
- check of drive for - damage of fuel system. fuel leakage
- damage of oil system, oil leakage
- damage of cooling circuit, liquid leakage
- damage of electrical system, ignition
- check of aircraft exterior for damage - - fuselage
- wings, flaperons
- tail unit
- landing gear
- fibreglass covers
- wash down the aircraft, clean it of dirt
- cover the cockpit with a protective cover
3.1.5.19 Rain
When flying in rain, no additional steps are required. Aircraft qualities and
performance are not changed essentially.
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3.2 EMERGENCY PROCEDURES
TABLE OF CONTENTS
3.2.1. ...........................................................Introduction
3.2.2. ........................................................ Engine Failure
3.2.2.1. ........................ Engine Failure at Take-Off Run
3.2.2.2. ................................ Engine Failure at Take-Off
3.2.2.3 ...................................... In-Flight Engine Failure
3.2.3 ................................................... Carburettor Icing
3.2.4 ....................................... In-Flight Engine Starting
3.2.5 ........................ Engine Fire, Fumes in the Cockpit
3.2.5.1 ......................................................... Ground Fire
3.2.5.2. ............................................. Fire during take-off
3.2.5.3 ........................................................ In-Flight Fire
3.2.6 ..................................................... Descent, Gliding
3.2.7 .............................................. Emergency Landing
3.2.7.1………………………………..Precautionary landing
3.2.7.2…………………………...…..Blown-out tyre landing
3.2.7.3……………………………….Damaged landing gear
3.2.8……….........................................................Vibrations
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3.2.1 Introduction
Chapter 3.2 contains procedures for various emergencies which may occur. A
thorough performance of maintenance system should prevent occurrence of
such extreme cases.
The chapter describes basic emergencies and procedures for their solving. Not
all emergencies that may occur can be listed here in full, therefore their solution
depends on experience of the crew controlling course of such events.
3.2.2 Engine Failure
3.2.2.1 Engine Failure at Take-Off Run
- throttle reduce to idle
- ignition switch off
- apply brakes
3.2.2.2 Engine Failure at Take-Off
- speed 110 km/h IAS
- choice of landing area - after take-off and up to 50 meter land
in direct straight ahead if possible
in direct straight ahead if possible
- over 50 m: choose landing area
The landing area is to be preferably chosen in direction of free runway or a free
clear area, upwind, if possible.
- master switch switch off
- ignition switch off
- main fuel cock shut
- tank fuel cocks change over to shut position
- wing flaps extend as required
- safety belts tighten
3.2.2.3 In Flight Engine Failure
- airspeed 110 km/h IAS
- area selection depending on flight altitude
- master switch switched on
- ignition switched on
- main fuel cock open
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- throttle set for start
- starter start the engine
if the engine cannot be started up, proceed in accordance with 3.2.2.2.
procedure
.
3.2.3 Carburettor Icing
Carburettor icing mostly occurs when getting into an area of ice formation. The
carburettor icing shows itself through a decrease in engine power and an increase
of engine temperatures and drag. To recover the engine power, the following
procedure is recommended:
use carburetter preheating system
- airspeed 80 - 90 km/h IAS
- throttle max. at 1/3 of power ≈ (3500 r.p.m.)
- if possible, leave the icing area
- increase gradually the engine power to cruise conditions after 1-2 minutes
if you fail to recover the engine power, land on the nearest airfield (if feasible) or
depending on circumstances, off-airfield, following the procedure given under
3.2.2.2.
3.2.4 In-Flight Engine Starting
- airspeed 110 km/h IAS
- area selection depending on flight altitude
- master switch switch on
- main fuel cock open
- choke switch on (cold engine only)
- throttle adjust to 1/3 of travel
- ignition switch on
- starter start up
- if the engine cannot be started up, increase the flight speed to 140-150 km/h
so that air flow can rotate the propeller, thus enabling engine starting.
CAUTION
Loss of height needed for in-flight engine starting is about
150 -200 m.
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3.2.5 Engine Fire, Fumes in the Cockpit
Recommended procedures to follow, when fire or fumes in engine compartment
and cockpit are detected.
3.2.5.1Ground Fire
- main fuel cock shut
- throttle full throttle
- ignition: switch off after using up fuel in carburettors and engine stopping
- master switch switch off
-abandon the aircraft and extinguish fire (if possible)
3.2.5.2 Fire during take-Off
- throttle idle
- main fuel cock shut
- tank fuel cocks shut
- airspeed 100 - 110 km/h and land
- brakes stop
- throttle full cruise
- ignition switch off after using up fuel in
carburettorsand engine stopping
- abandon the aircraft and extinguish fire (if possible)
3.2.5.3 In-Flight Fire
main fuel cock shut
- tank fuel cocks shut
- throttle full travel
- landing area selection guide the aircraft to an airfield,
or choose an area for
emergency landing
- ignition switch it off after using up fuel in
carburettors and engine stopping
- master switch switch off
- airspeed extend as needed
- safety belts tighten
- perform emergency landing
- abandon the aircraft and extinguish fire (if possible)-
NOTE
Time needed to pump fuel out of carburettors is around 30 sec.
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3.2.6 Descent, Gliding
- airspeed 110 km/h
- throttle increased idle
- wing flaps retracted
- engine instruments values within permitted limits
CAUTION
At long final and when descending from a considerable height, it is not
advisable to reduce the engine throttle control to minimum. In such
case the engine becomes undercooled and a loss of power occurs.
When descending, apply increased idle so that engine instrument
readings range within the limits for normal use.
gliding ratio ......................................................... 1 : 14
optimum gliding speed ................................ 100 km/h IAS
sinking ................................................................ 2.3 m/s
3.2.7 Emergency Landings
Recommended procedures for various types of emergency landing.
3.2.7.1 Precautionary Landing
- choose landing area, evaluate wind direction and speed, area surface,
surrounding obstacles and total safety of the manoeuvre under consideration
- perform approach and fly-over at a speed of 95 km/h along the deliberate area
at a height of 50 m to estimate the area condition, obstacles and to determine
magnetic course of landing
- make orbiting approach to land
- perform landing from the very beginning of the chosen are
a
3.2.7.2 Blown-Out Tyre Landing
- carry out normal approach-to-land
- when floating at landing, keep the damaged wheel above ground as long as
possible using ailerons
- maintain the direction at landing run, applying foot control
3.2.7.3 Damaged Landing Gear Landing
-carry out a normal approach-to-land
-if the nose wheel is damaged, perform a touch-down on main wheels and hold
the aircraft on wheels as long as possible till the speed is lost
-if the main landing gear is damaged, perform touch-down at the lowest speed
possible and maintain direction at landing run, if possible
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3.2.8 Vibrations
If any forced vibrations appear in the aircraft, it is necessary:
- to set engine speed to such power rating where the speed is lowest
- to land on the nearest airfield, or to perform a precautionary landing off-airfield
- if the vibrations are increasing, carry out an emergency landing off-airfield,
following procedures given under 3.2.2.2.
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4. PERFORMANCE
TABLE OF CONTENTS
4.1 ...............................................................Introduction
4.2 ..............................................................Performance
4.2.1 .........................................................Position Error
4.2.2 ..................................................... Minimum Speed
4.2.3 ....................................... Take-Off Characteristics
4.2.4 .................................................................. Landing
4.2.5 ................................................................. Climbing
4.3 ............................................. Additional Information
4.3.1 ...........................................................Cruise Flight
4.3.2 .............................................................. Endurance
4.3.3 ................................ Take-off from Grass Surface
4.3.4 ................... Rain Effect on Flight Characteristics
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4.1 Introduction
Chapter 4 contains data on airspeed calibration (position error of airspeed
indicator), on minimum flying speeds and data on take-off characteristics.
The data are based on particular flight measurements undertaken with the
aircraft of this type under normal conditions and with application of average
piloting technique.
4.2 Performance
4.2.1 Position Error
The table below gives data on calibrated airspeed CAS and indicated airspeed
IAS. Delta V indicates an airspeed system position error.
V CAS V IAS delta V
km/h km/h km/h
75.83481 70 5.834813
82.72482 80 2.724817
100.9777 100 0.977747
118.6061 120 -1.39388
135.5541 140 -4.44588
153.5682 160 -6.43182
CHYBA RYCHLOMĚRNÉ SOUSTAVY LETOUNU FOX (deltaV) V ZÁVISLOSTI NA
PŘÍSTROJOVÉ RYCHLOSTI (V IAS) V H = 0 MSA
-8
-6
-4
-2
0
2
4
6
0 20 40 60 80 100 120 140 160
V IAS (km/h)
deltaV(km/h)
Airspeed system position error (delta V) of Apollo Fox
aircraft vs. indicated air speed (V IAS) at H = 0 MSA
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4.2.2 Minimum Speed (450 kg)
Minimum speed ..................................... ............ 64 km/h IAS
4.2.3 Take-Off Characteristics (450 kg)
Take-off distance over a 15 m obstacle ............ 130 m
4.2.4 Landing
Landing distance over a 15 m obstacle . ............ 450 m
4.2.5 Climbing (450 kg)
Rate of climb ................................... solo ............ 4,7 m/s
Gliding ratio at stopped engine ............. ............ 1 : 14
Optimum gliding speed ......................... ............ 100 km/h
Sinking at stopped engine ..................... ............ 2.3 m/s
4.3 Additional Information
4.3.1 Cruise Flight
Cruising speed ...................................... ............ 110 - 180 km/h
Never exceed speed VNE....................... ............ 200 km/h
4.3.2 Endurance
Ceiling ................................................... ............ 4500 m
Flying range ...................................... ca. ............ 500 km
4.3.3 Take-off from Grass Surface
Take-off distance over a 15 m obstacle ............ 143 m
4.3.4 Rain Effect on Flight Characteristics
Flying qualities and characteristics are not substantially changed.
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5. SUPPLEMENTS
TABLE OF CONTENTS
5.1 ............................................................... Introduction
5.2 .................................. List of Inserted Supplements
5.1 Introduction
This chapter contains supplements necessary for safe and efficient operation of
the aircraft fitted with equipment other than the standard one.
5.2List of Inserted Supplements
Date Supplement No. Supplement Title
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