Flight manual
interplane
Skyboy EX
PILOT'S OPERATING HANDBOOK
and
FLIGHT MANUAL
for
IINNTTEERRPPLLAANNEE
Airplane European UL category
controlled by aerodynamic devices
LAA Type approval : ULL - 08/94
Serial Number :
Registration Number :
Date : Approved by : __________________
THIS HANDBOOK MUST BE
IN THE AIRPLANE AT ALL TIME
The airplane must be operated by the information and limitations which are presented in this handbook !
EX
Flight manual
interplane
Skyboy EX
Table of contents
1. General information page 1-1 to 1-3
2. Operational limitations page 2-1 to 2-2
3. Emergency procedures page 3-1 to 3-3
4. Normal procedures page 4-1 to 4-4
5. Other information for safe operation page 5-1
6. Performance page 6-1 to 6-2
7. Description page 7-1 to 7-3
8. Ground handling page 8-1 to 8-2
9. Supplements page 9-1
and the set of supplements
Flight manual
interplane
Skyboy EX
LIST OF THE REVISIONS AND THE REPAIRS
21.3.2000
Ordinal No. Number of document -
bulletin
It concerns to
pages No.
Date of issue : Signature :
Flight manual
interplane
Skyboy EX
Page 1 - 4
1
GENERAL INFORMATION
SKYBOY
is European type certificated side-by-side
two-seat ultralight aircraft, conforms to Czech UL-2,
Germany BFU-DULV and other European UL requirements.
SKYBOY
fills FAI UL category for international sport
competition.
In the U.S.A this
SKYBOY EX
version is the
normal Experimental aircraft.
All metal design, light high-wing airplane with braced
riveted aluminum alloy cage structure, composite semimonocoque fuselage pod and aluminum boom supporting
conventional tail surfaces. Tricycle landing gear with
steerable nose wheel.
1.1 DESCRIPTION :
Skyboy EX – standard features :
Aluminum alloy basic tubes/riveted beams skeleton with basic composite canopy with gas struts opened gull-wing
doors ( in the basic version without doors ) and rear composite fuselage fairing.
Wings NACA 4412 with forward 2°swept , pressed ribs, composite wing tips, composite leading edge and 40%
ailerons. Ceconite fabric covered wings and tail. Tubes wing struts, aerodynamic struts for option.
Standard main wheels with hydro-pneumatic shock absorbers and mechanical nose brake. Controlled nose wheel.
Hydraulic brakes for option.
Standard dual control with separate joysticks, rudder pedals, and mechanical controlled elevator trim tabs.
ROTAX 582 engine with electric starter, battery, choke, fuel shut off valve and 3-blade ground adjustable
composite propeller.
4-point safety belts, upholstered seat rest and cushion-seat back. Plywood wall kit and aluminum alloy instrument
panel. Composite “sport car” look seat-back for option.
Standard white color Acrylate light finish.
Basic Instrument set includes : Airspeed indicator ∅ 3”
Altimeter ∅ 2”
Fuel Gauge
Rotax / Westach tachometer and cooling fluid temperature gauge
Another aircraft versions :
Skyboy S former European UL version
for lower stall speed with greater wing area and Dacron cowered wing, greater
elevator area, full span ailerons and smaller maximum and cruise speed
. Out of production.
Skyboy UL USA legal FAR Pt 103 ultralight trainer version
of original aircraft with shorter wing, high-lift airfoil P3 with light
leading edge, tube struts, less elevator area and a lot of saving weight changes, to fill USA regulation with take -off weight to 450 kg.
Flight manual
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Skyboy EX
Page 1 - 5
1.2 BASIC TECHNICAL DATA
This handbook is valid for all types of the airplane :
Skyboy EX - European ultralight and USA Experimental version – certificated aircraft version of the airplane
with take -off weight to 450 kg and maximum permissible flight speed 165 km/hour
Skyboy EX 503, Skyboy EX 582, Skyboy EX 912 ... the airplane versions with various ROTAX engines
Skyboy EX SVS 1400, Skyboy EX MZ 202R , Skyboy EX 2706 E, etc … the airplane versions with other
marks of engines (Verner, Zanzottera, Hirth, …)
Skyboy ... E version of the airplane with electric engine starting
Skyboy ... R version of the airplane with rewind hand starting
Concrete identification mark can be composed : for example EX basic version is named Skyboy EX 582 E
General arrangement drawing
Flight manual
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Skyboy EX
Page 1 - 6
1.2.1 DIMENSIONS
Wing span 9,50 m 31.17 ft
Length 6.37 m 20.90 ft
Height 2,13 m 6.99 ft
Wing area 13.50 m
2
145.31 sq ft
Forward swept wing : standard - 2 °°°° ( 0 °°°° recommended for chosen heavier engine )
1.2.2 TIRES - INFLATION
Nose landing gear - Bantam 12x4 160 +20 kPa / 23,5 + 3 psi
Main landing gear - Bantam 16x4 180 +20 kPa / 26,5 + 3 psi
1.2.3 WEIGHTS Skyboy EX
Empty weight 240 kg / 529 lb
Empty equipped weight 268 kg / 591 lb
Maximum take-off weight 450 kg / 992 lb
1.2.4 POWER PLANT
1.2.4.1 Engine ROTAX 503 2V UL 582 UL-2V 912
Pusher configuration
Maximum power 37 kW 48 kW/65 SHP 59,6 kW/ 80 SHP
for 6500 rpm 6500 rpm 5800 rpm
Cylinder volume 496,7 ccm 496,7 ccm 1211 ccm
Dry weight 41 kg 48,5 kg 54 kg
Carburetter 2x BING 36 2x BING 36 2 x BING 64-3
Fuel pump MIKUNI DF 52, electric engine starting + 3,5 kg + battery
1.2.4.2 OPERATION FILLINGS
Fuel 40 l automotive petrol SUPER - BA 96
Oil (for two strokes) Castrol TTS
Proportion of mixture for two strokes Rotax 1 : 50 (see engine manual )
Gear box oil API-GL5 ( 0,5 l )
1.2.4.3 PROPELLERS
SPORTPROP Klassic 160/3/R - composite on the ground adjustable 3-blade ∅∅∅∅ 1.6 m (Rotax 582, 618, 912)
Winglet 165/3/R - on the ground adjustable 3-blade ∅1.65 m (Rotax 582/2.62 or /3.0, Rotax 912)
Winglet 165/4/R - composite on the ground adjustable 4-blade ∅ 1.65 m (Rotax 582/ 3,47)
Varia - composite in the flight variable pitch 3-blade ∅ 1.65 m
KŘEMEN PROPELLER SR 26 - wooden fixed two blade ∅ 1.6 m ( for Rotax 582 )
SR 117 - wooden 3-blade on the ground adjustable ∅ 1.6 m
SR 2000 - in flight variable pitch wooden ∅ 1.45 m
1.2.5 EQUIPMENT
BASIC : RECOMMENDED : OPTIONS :
Airspeed indicator Compass vertical velocity indicator
Altimeter Slip indicator Engine hour meter
Fuel gauge Radio / Transceiver
Tachometer Headset
Engine (water) temperature indicator GPS
Kinds and marks of the airplane instruments which are used on the concrete airplane are presented in the chapter 7.
Flight manual
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Skyboy EX
Page 2 - 1
2
OPERATIONAL LIMITATIONS
2.1. Airspeeds
AIRSPEED
abbreviation
IAS
mph
IAS
knots
IAS
km/h
Maximum permissible speed
VNE 103 89
165
Maximum maneuvering speed
VA 71 62
115
Maximum cruising speed
VC 93 81
150
Minimum ( stall ) speed
VSO 37 32
60
2.2. OPERATIONAL SPEED RANGE
MEANING OF
THE MARK
INCREASED
ATTENTION
OPERATIONAL
MODE RANGE
INCREASED
ATTENTION MODE
LIMIT.
VALUES
Speeds km/h
68 - 85 85 - 120 120 - 165 165
Speeds knots
36 - 46 46 - 65 65 - 89 89
Speeds mph 42 - 53 53 - 75 75 - 103 103
Colored mark yellow arc green arc yellow arc
red radial
2.3 OPERATIONAL LIMITATION FOR WIND
Maximum permission velocity component of wind for take-off and landing :
- perpendicularly to the runway axis
4 m/s … 800 ft/min
- parallely to the runway axis
10 m/s … 2000 ft/min
For training flights and practice flights there are valid limitations in accordance with the regulations for ULL.
2.4 LIMITATIONS FOR POWER UNIT
M O D E
503 582 912
Maximum permissible revolutions
6800 rpm 6800 rpm 5800 rpm
max. 5 min
Normal temperature for cylinder heads
to 220 o C 110 - 130 o C 110 - 130 o C
Maximum temperature for cylinder heads
250 o C 150 o C 150 o C
2.5 WEIGHTS
Maximum crew's weight (limit for the cabin and safety belts) 180 kg / 397 lb
Maximum crew weight connected with concrete weighing RECORD of this aircraft (limit for the aircraft) :
Quantity of the fuel in the tank
¼
of fuel
(circa 7 kg)
½
of fuel
(circa 14 kg)
Full tank
(circa 28 kg)
Maximum crew weight [ kg ]
Maximum crew weight [ lb ]
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Skyboy EX
Page 2 - 2
Minimum pilot's weight (solo flight) 65 kg / 143 lb (lighter pilot must be balanced to limitation of balance)
For special purpose, connected with concrete weighing RECORD of this aircraft :
Minimum single Pilot weight limit = =
2.6 CENTER OF GRAVITY
Max. forward center of gravity
21 % MAC
Max. rear center of gravity
36,6 % MAC
2.7 OPERATIONAL LOAD FACTORS
Maximum positive load factor in the center of gravity
+ 4
( Ultimate
+ 6
)
Maximum negative load factor in the center of gravity
- 2
( Ultimate
- 3
)
2.8 PERMISSIBLE MANOEUVRES
M A N E U V E R S
Maximum inlet speed - IAS
km/h
mph
knots
Strong banked turn to 60 degrees 115
71,5
62
Climbing turn 115
71,5
62
Acrobatic maneuvers and intentional spin are PROHIBITED !!!
2.9 KINDS OF OPERATION
The airplane is approved only for day flight according to VFR.
Other kinds of flight are P R O H I B I T E D !!!
2.10 AIR TEMPERATURE LIMITATION
Recommendable maximum ambient temperature
+ 40 o C
Recommendable minimum ambient temperature
- 10 o C
2.11 INFLUENCE OF RAIN AND MOISTURE
The airplane lifting surface and control surfaces are covered with fabrics. These fabrics can release owing to
influence of the extensive moisture. It can cause mild decrease airplane performance.
Stability and controllability are not dangerously endangered owing to influence of rain. During the flight with
expressive moisture we still recommend to increase the take-off and landing speed approximately about 5 knots
(6
mph or 10 km/hour).
kg
lb
Flight manual
interplane
Skyboy EX
Page 3 - 1
3
EMERGENCY PROCEDURES
Section 3 provides checklist and amplified procedures for coping with emergencies that may occur. Emergencies
caused by aeroplanes or engine malfunction are extremely rare if proper pre-flight inspections and maintenance
are practised. However, should an emergency arise, the basic guidelines described in this section should be
considered and applied as necessary to correct the problem.
ENGINE FAILURE
3.1.1 Engine failure during take-off run
1. Throttle - decrease to idling
2. Ignition - switch off
3. Brake
3.1.2 Engine failure during TAKE-OFF
1. Speed - to keep gliding flight with speed 46 to 48 knots (53-56 mph or 85-90 km/h).
2. Altitude - to altitude 80 ft ( 25 m ): land in take-off direction
- over 80 ft ( 25 m ): choose landing area
3. Course - the best in runway direction, in free space without obstacles, with head wind
4. Fuel valve - shut off
5. Engine igniter - switch OFF
6. Safety harness - tighten
7. Master switch - switch off before landing
8. Land
note :
3.1.3 Engine failure in flight
1. Speed - keep gliding flight with speed 46 to 48 knots (53-56 mph or 85-90 km/h).
2. Altitude - below altitude 80 ft (25 m ) land in take-off direction
- over 80 ft (25 m ): choose landing area
3. Wind - evaluate direction and velocity
4. Landing area - choose free area without obstacles
5. Course - the best in runway direction, in free space without obstacles, with head wind
6. Fuel cock - shut off
7. Engine igniter - switch off
8. Safety harness - tighten
9. Master switch - switch off before landing
10. Land
3.1.4 Vibration
If any forced aeroplane vibrations appear, it is necessary:
1. To set engine speed to such power rating where the vibrations are lowest.
2. To land on the nearest airfield or to perform a emergency landing
Skip 6-10 if necessary
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Skyboy EX
Page 3 - 2
3.2 IN –FLIGHT START
1. Speed - gliding at 46 to 48 knots (53-56 mph or 85-90 km/h)
2. Altitude - check
3. Landing area - choose according to altitude
4. Master switch - switch on
5. Fuel cock - open
6. Choke - as necessary (for cold engine)
7. Throttle - for 1/3 power
8. Ignition - switch on
9. Starter - push button (or pull the rewind starter cable grip) to start the engine
If the engine cannot be started up, increase the flight speed so that air flow can rotate the propeller,
thus enabling engine starting.
WARNING
The loss of altitude during in-flight engine starting is about 650 ft (200 m) and must be taken into consideration.
3.3 EMERGENCY LANDING
3.3.1 Emergency landing
1. Emergency landing is generally carried out in case of engine failure when the engine cannot be
started up.
2. Speed - 110 km/h (60 kts)
3. Trim - trim the aeroplane
4. Safety harness - tighten
5. Flaps - as needed
6. Radio station - report your location if it is possible
7. Fuel cock - shut off
8. Ignition - switch off
9. Master switch - switch off
3.3.2 Landing with a flat tire
1. When floating at landing, keep the damaged wheel above ground as long as possible using ailerons
2. Maintain the direction at landing run, applying foot control
3.3.3 Landing with a defective landing gear
1. If the main landing gear is damaged, perform touch-down at the lowest speed possible and maintain
direction at landing run, if possible
If the nose wheel is damaged perform touch-down at the lowest speed possible and hold the nose wheel over a
runway by means of the elevator control as long as it is possible
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Skyboy EX
Page 3 - 3
3.4 FIRE, SMOKE
3.4.1 Fire on ground
1. Fuel cock - shut off
2. Throttle - full
3. Master switch - switch off
4. Ignition - switch off
5. Abandon the aeroplane
6. Extinguish fire if it is in your power or call for a fire brigade.
3.4.2 Fire during take-off or in flight
1. Fuel cock - shut off
2. Throttle - full ( maximum )
3. Speed - to keep gliding flight with speed 46 to 48 knots (53-56 mph or 85-90 km/h)
4. Master switch - switch off after using up fuel in carburettors and engine stopping
information : Time, needed for exhaustion of the fuel rest in carburetors takes approximately 30 seconds.
5. Altitude - to altitude 80 ft ( 25 m ) the landing in take-off direction
- over 80 ft (25 m ): choose emergency landing area
6. Course - recommended is in runway direction, in free space without obstacles, with
head wind
7. Ignition - switch off
8. Emergency landing - according to the item 3.2 Land and brake
9. Abandon the aeroplane
10. Extinguish fire if it is in your power or call for a fire-brigade
3.5 CARBURETOR 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.
To recover the engine power, the following procedure is recommended:
1. Speed - 60 kts ( 110 km/h )
2. Throttle - set for 1/3 power
3. If possible, leave the icing area
4. 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 possible) or depending on circumstance,
precautionary landing
3.6 RECOVERY FROM UNINTENTIONAL SPIN
WARNING
Intentional spins are prohibited! Spin characteristics of this airplane have not been tested.
A procedure bellow is only for information.
There is no tendency to entry spontaneously in uncontrollable spin if normal pilot techniques are used.
In case of recovery from intentional spin a standard procedure can be used:
1. Throttle - reduced to idle
2. Control stick - ailerons neutralised
3. Rudder pedals - full opposite rudder
4. Control stick - forward elevator control as required to stop a spinning
5. Rudder pedals - immediately after stop of a rotation neutralise the rudder
6. Recovery the dive
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Skyboy EX
Page 4 - 1
4
NORMAL PROCEDURES
Chapter 4 includes lists of standard operations and recommended procedures, needed for normal aircraft
operation.
4.1 PRE - FLIGHT INSPECTION
1. COCKPIT
- Engine igniter switch OFF
- Attachment and position of the pilot seat
- Check of the safety belts
- Condition of the instruments equipment
- Function of the hand control
- Function of the directional control
- Attachment and freedom of engine control
- Brake function
- Condition of the laminate shell and transparent canopy
2. LANDING GEAR
- Condition of the landing gear and brake control
- Attachment of the landing gear and check of the shock absorber
- Inflation of the tires
3. WING
- Attachment of the struts and locking of the connecting bolts
- Checking of the skin and skin strain
- Condition and deflection of the ailerons, skin strain and locking of the steering hinges
- Checking of the ropes of wing skin strain
4. POWER PLANT
- Condition of the engine, propeller and locking of bolted connection
- Condition of the silentblock and engine attachment to fuselage structure
- Condition and attachment of the exhaust with special emphasis on SPRING
- Engine fixation
- Condition of the ignition system
- Condition of the fuel system and pump
- Attachment and fixation of the fuel tank
- Checking amount of fuel
- Attachment condition of the accumulator + input conductors ( versions E )
Flight manual
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Skyboy EX
Page 4 - 2
5. CONTROL CABLES
- condition and tension of the rudder cables and elevator-trim tab ropes
- checking of locking of the turnbuckles and guide-bowdens and hoses
6. TAIL UNIT
- condition of the horizontal and vertical surfaces, skin strain
- checking of the elevator and rudder deflection and locking of the hinges
- tension of the stabilizer ropes, locking of the turnbuckles
- checking of the tail skid
4.2 BEFORE ENTRANCE INTO THE PILOT'S COCKPIT
1. Wing surface - checking of the entirety and strain skin, checking of the strut system
2. Tail unit surface - checking of the skin entirety
- checking of the bracing ropes
3. Dismantling juncture - checking of the locking
4. Power unit - condition of the propeller fittings
- engine inspection and his attachment
5. Fuel system - checking of the fuel quantity
- checking of shut-down of fuel tank
6. Pilot’s cockpit - attachment and condition of the safety belts
- purity of the transparent canopy
4.3 AFTER ENTRANCE INTO THE PILOT'S COCKPIT
1. Engine igniter - switch OFF
2. Directional control - free movement
(after lifting of the nose wheel by pressure of tail unit girder by assistant)
3. Hand control - free movement
4. Brake - checking of function
5. Instruments - checking of values
6. Safety belts - button up and tighten up
4.4 ENGINE STARTING
1. Engine igniter - switch OFF
2. Fuel condition lever - open
3. Engine throttle - idling speed during the cold engine start use saturator
4. Hand fuel pump - overfull carburetor
5. Brake - apply the brake or the main gear must be secured by Scotch blocks
6. Engine igniter - to position S W I T C H O N
7. Starting - carry out the starting by handle of manual staring or by the pushbutton
if the airplane has electrical starting.
After engine starting increase revolutions moderately and switch off the saturator as soon as possible.
8. Engine revolutions - idling speed
Flight manual
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Skyboy EX
Page 4 - 3
4.5 ENGINE TEST
1. Operating minimum - 2 minutes are minimum time since engine starting. Warm up the engine
with increasing revolutions (2500 - 3000 rpm )
2. Handle control - neutral position
3. Brake - the brake tighten up, the main gear must be secured by Scotch blocks or an
assistant must hold the airplane
4. Acceleration - reach maximum revolutions during 3 sec. watch equability of engine
starting and regularity of engine operation
5. Max. power mode - watch regularity of engine operation
6. No-load speed - equable engine operation
N O T I C E :
4.6 TAXIING
On an airfield the taxiing speed is maximum 5 kts (
10 km/h / 6 mph
= walking speed )
4.7 PROCEDURES BEFORE TAKE-OFF
1. Directional control - freedom of movement
2. Handle control - freedom of movement
3. Instruments - checking of values, fuel quantity
4. Safety belts - checking of connection and tightness
5. Fuel condition lever - position " O P E N "
6. Change over switch for igniter - position " O N "
7. Balance - for two pilots - position "heavy on the tail"
- for solo flight - position " neutral "
8. Choke - checking of the shut-down and locking
9. Checking of the space for final airport pattern
- stop on the holding patter upright to the runway on the runway threshold
10. Announce to radio service ( if the airplane is equipped with a transceiver )
4.8 TAKE - OFF
1. Checking of opening fuel
2. Instruments
3. Clear runway
4. Checking of time
Set the airplane in motion by continuous increasing power.
After reach out of speed 35 knots (40 mph or 65 km/hour) use the elevator for lift out of the airplane.
After attainment of speed 40 to 46 knots (47 to 53 mph or 75 - 85 km/hour ) climb with speed 400 to 1000 ft/min
( 2 to 5 m/s ) - it depends on the weight of airplane and type of the engine.
N O T I C E :
TAKE - OFF IS P R O H I B I T !!!
- If the engine operation is irregular
- If the wind speed exceed permit limits
Carry out the engine test up the wind !
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Skyboy EX
Page 4 - 4
4.9 CIRCUIT FLIGHT
After attainment circuit height adjust the speed of horizontal flight on the value 43 to 54 knots
(50 to 62 mph or 80 - 100 km/hour )
by decrease of revolutions.
4.10 GLIDING FLIGHT
After attainment of suitable height for gliding flight or when an emergency situation arises, take over the airplane
into the gliding flight with starting speed 40 knots
(47 mph or 75 km/hour ).
By flight height and situation adjust the speed to the safety gliding speed 46 to50 knots
( 53 to 56 mph or 85 - 90
km/hour ).
At this speed finish all phases of landing.
4.11 ELEMENTAL PROCEDURES ON THE LEVEL OF LANDING T
1. Revolutions - increased idling or engine idling
2. Safety belts - tightened
3. Checking of circuit - T space and runway
- space between 3. and 4. turn
4. Checking of fuel
4.12 LANDING
Adjust angle of glide so that it corresponds with the safety gliding speed 46 to51knots
(53 to 60 mph or 85 - 95 km/hour).
After leveling out (circa height 16 ft , 5 m ) in dwell, decrease flight speed by continuous pulling of the elevator,
until the airplane lands with speed circa 35 knots
(40 mph or 65 km/hour )
at first on the main gear. After finishing
elevator effect the airplane lands on the nose-wheel undercarriage.
4.13 ELEMENTAL PROCEDURES AFTER LANDING
1. Revolutions - according requirement
2. Speed - adjust on rolling speed maximum 5 knots
(6 mph or 10 km/hour )
After landing run quickly leave runway usually in direction of the alignment of landing T axis.
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Skyboy EX
Page 5 - 1
5
OTHER INFORMATION FOR SAFETY OPERATION
5.1 GENERALLY
All given information and procedures with recommended piloting technique are valid for following flight
cases. A pilot must not get into these flight cases when he observes normal and emergency procedures .
5.2 STALLS AND RECOVERY TO NORMAL FLIGHT
5.2.1 WING LEVEL STALL
Pull the elevator reasonably in successive steps, the airplane will has speed 34 knots (40 mph or 64 km/hour
). During this speed the altitude control bears on the stop, the airplane bow decreases and the airplane
descends in successive steps.
Piloting technique for recovery to normal flight - reasonably push the elevator. Don't use the ailerons
when the airplane is yawed along longitudinal axis during the stall. Level the directional control after
descent and the restoration of rudder efficiency.
5.2.2 STALLING SPEED
WEIGHT OF
AIRPLANE
RATE OF
ENGINE
Stalling SPEED
[ kg ] IAS
[ km/hour ]
IAS
[ mph ]
IAS
[ knots ]
450 - MTOW
idling speed
64
40 34
300 - solo flight
idling speed
55
34 30
comment :
Stalling speed acquirement is showed by the tilting of airplane nose down, or higher increasing of negative
vertical speed .
Horizontal flight can be returned after lost of height approximately 150 feet ( 50 meters ).
During the stall airplane is fully controllable.
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Page 6 - 1
6
PERFORMANCE
6.1 GENERALLY
These performance are valid for the standard version of airplane with maximum take-off weight 450 kg with
usual flying without wind in ISA conditions - 0 m MSA by the temperature 15 ° C.
6.1.1 CALIBRATION OF THE SPEED MEASUREMENT SYSTEM
IAS [ km / h ]
60 70 80 90 100 110 120 130 140 150 160 170
CAS [ km / h ]
IAS [ knots ]
30 40 50 60 70 80 90
CAS [ knots ]
6.2 TAKE-OFF AND LANDING
These values are determined for take-off and landing from a dry grass airfield and concrete airstrips without
slope of runway and without wind.
6.2.1 LENGTH OF TAKE-OFF RUN AND TAKE-OFF
JČ 9.3.2000
Skyboy
503 582 912
Take-off run grass
120m/ 400 ft 100m / 330 ft
[ m / ft ] concrete
100m / 330 ft 85m / 280 ft
Take-off over 15m grass
250m/ 820 ft 200m/ 660 ft
[ m / ft ] concrete
230m/ 750 ft 185m/ 610 ft
6.2.2 LENGTH OF LANDING AND LANDING RUN
JČ 9.3.2000
Skyboy
503 582 912
Landing over 15 m grass
250m/ 820 ft 250m/ 820 ft
[ m / ft ] concrete
280m/ 920 ft 280m/ 920 ft
Run without braking grass
100m/ 330 ft 100m/ 330 ft
[ m / ft ] concrete
130m/ 430 ft 130m/ 430 ft
6.3 CLIMBING
6.3.1 OPTIMAL CLIMBING SPEED
JČ 9.3.2000
FLIGHT
SOLO FLIGHT
MTOW - 450 kg
ALTITUDE SPEED
RATE OF CLIMB
SPEED
RATE OF CLIMB
[ m ]
[ ft] km/hr
knots
[ m/s ]
ft/min
km/hr
knots
[ m/s ]
ft/min
503 0 -
500
0 - 1500 80 45 2,5 490 90 49 2,1 410
582
0 -
500
0 - 1500 80
45
4,8
950
90
49
3,2
630
912 0 -
500
0 - 1500 80 45 6 1 200 90 49 4,5 900
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Page 6 - 2
6.3.2 CEILING
Service ( practical ) ceiling 3 000 to 3 500 m, 5 000 to 5 500 with four stroke engines ( Rotax 912 etc)
6.4 GLIDING FLIGHT WITH INOPERATIVE ENGINE
JČ 9.3.2000
PERFORMANCE DOUBLE SOLO SPEED IAS
THE LEAST DESCENT
690 ft/min
( 8,4 m/s
)
490 ft/min
(
2,5 m/s
)
46 knots
( 85 km/hour )
THE BEST GLIDING
1 : 6,8
1 : 9,7
46 knots
( 85 km/hour )
6.5 HORIZONTAL - CRUISE FLIGHT
6.5.1 SPEEDS AND FUEL CONSUMPTIONS
JČ 9.3.2000
TYPE MODE
REVOLUTIONS
SPEED CONSUMPTION
[ rpm ] [km/h] knots [ l / h ]
503
MAX. CONTINUOUS POWER
6 500 115 62 18
CRUISE POWER
5 900 90 46 12
MAX. CONTINUOUS POWER
6 500 145 78 20
582
CRUISE POWER
5 000 110 59 13
LONG-RANGE CRUISE POWER
4 700 100 54
estimate
11
MAX. CONTINUOUS POWER
5 500 162 87 18
912
CRUISE POWER
5 000 130 70 12
LONG-RANGE CRUISE POWER
4 000 100 54
estimate
9
6.5.2 FLIGHT RANGE AND ENDURANCE
( stat. miles )
JČ 9.3.2000
TYPE MODE
RANGE ENDURANCE
[ miles / km ] [ min ] [ hour : min ]
503
MAX. CONTINUOUS POWER
155
miles
/ 250 km
135 2 : 15
CRUISE POWER
186
miles
/ 300 km
200 3 : 20
MAX. CONTINUOUS POWER
180
miles
/
290 km
120 2 : 00
582
CRUISE POWER
200
miles
/
330 km
180 3 : 00
LONG-RANGE CRUISE POWER
230
miles
/ 370 km
220 3 : 40
MAX. CONTINUOUS POWER
220
miles
/ 360 km
135 2 : 15
912
CRUISE POWER
270
miles
/ 430 km
200 3 : 20
LONG-RANGE CRUISE POWER
290
miles
/ 470 km
270 4 : 30
Flight manual
interplane
Skyboy EX
Page 7 - 1
7
AIRCRAFT DESCRIPTION
Chapter 7 describes basic layout of the aircraft, to explain all basic needed information for the Skyboy
operation.
7.1 COCKPIT
Followed picture describes positions of all basic control levers, drivers, installation of instruments and cabin
equipment, needed for basic pilot information about correct use of this plane:
ACCOMMODATION:
Individual integral side-by-side seats for two persons in enclosed cabin, the main pilot’s seat being to port.
Special shape of the integral composite seat rest enables not only better comfort, but higher pilot safety
during the crash. Cushion seat rests and seat backs and four point safety belts are standard.
Sport car – style upholstered composite seat rests and gull-wing doors opened by gas struts for option.
Dual control standard: dual control sticks, dual rudder pedals, dual throttles and central elevator trim
handle. Choke and fuel valve levers standard, primer and hydraulic brakes controlled by pedals on the port
side ( left ) position for option.
Flight manual
interplane
Skyboy EX
Page 7 - 2
7.2 INSTRUMENT PANEL
Skyboy instrument panel is equipped with the standard airspeed indicator, altimeter, tachometer, cylinder head
or cooling fluid indicator and fuel gauge.
Provision is made to install the optional compass, bank indicator, vertical velocity indicator, or exhaust temperature gauges,
engine-hour counter, Volt-meter, oil pressure gauge, radio/transceiver, headsets, intercom, GPS etc.
Installed instruments
Basic set :
Pos. Name
Type manufacturer serial number
1
Air Speed indicator
2
Altimeter
3
Fuel gauge
4
Tachometer
5
Engine temperature indicator
- CHT
Recommended addition :
6
Compass
7
slip indicator
Options :
8
Vertical speed indicator
9
10
Engine hours counter
11
Engine exhaust temperature
indicator
12
Oil temperature indicator
13
Oil pressure indicator
14
15
Volt meter
16
17
Transceiver (Radio)
18
Headset
19
Intercom
20
21
Navigation - GPS
22
23
24
25
26
27
Flight manual
interplane
Skyboy EX
Page 7 - 3
7.3 AIRCRAFT TECHNICAL DESCRIPTION
7.3.1 AIRFRAME :
Strut-braced high-wing monoplane, with braced aluminum alloy cage structure,
composite fuselage pod and aluminum boom supporting conventional tail surfaces.
Glass-fiber/epoxy semi-monocoque fuselage pod with optional gull-wing doors.
Wings can be easy dismount and horizontal tail surfaces can be quickly folded for transportation and
storage.
7.3.2 FUSELAGE
has a simple strength all-metal basic structure - with a ridge beam ∅ 120 x 2 mm and box
top beam with hinges of wings and engine mounting and upper cross beam with undercarriage and strut
hinges, both riveted from aluminum alloy plates.
Airframe structure is connected through aluminum alloy tubes.
7.3.3 COMPOSITE CANOPY
-fuselage fairing with integral seats, floor and instrument panel cover has
the fixed center part of windshield, which is usable for flying in the open air without doors. Two
dismountable side doors with large windows are opened through gas struts and lockable.
7.3.4 WINGS
have aluminum tube spars and aluminum alloy pressed ribs, 100 % double surface Ceconite
fabric covered.
Airfoil NACA 4412 for EX version with composite leading edge, high-lift airfoil P3 for UL version,
with small composite leading edge.
40% span ailerons, controlled through torsion tube.
7.3.5 TAIL
is classical cables braced cross-type, with flat profile, riveted and screw-connected from aluminum
alloy tubes and Al profiles and covered by hot-air stressed fabric.
Elevator can be weight balanced, with wire-controlled trim-tab. Horizontal tail surfaces have foldable
hinges, to be able quickly folded to fin for transportation.
Rudder is controlled through wires in plastic tubes (without any pulleys).
7.3.6 THREE-AXIS CONTROL:
40% span ailerons, elevator with trim tab, and rudder.
Classical dual CONTROL with control sticks between pilots and dual rudder pedals with optional brakes
drivers for left side pilot.
Elevator and ailerons are controlled through rods and levers system, rudder and trim tab through cables.
Rudder control is connected with nose wheel steering.
Dual throttle is located on the both sides of canopy, elevator trim-tab handle and engine control is located
on the central panel between both pilots.
7.3.7 LANDING GEAR:
Non-retractable tricycle type, with hydro-pneumatic shock absorbers.
Main wheels 16x3", nose wheel 12x3".
Steerable nose gear with rubber block shock absorbers.
Standard nose gear with Drum Toe Brakes, controlled by handle on the joystick.
Main wheels with hydraulic disc brakes, controlled separately by pedal drivers for option.
7.3.8 POWER PLANT:
Standard 48 kW (65 hp) Rotax 582 UL - DCDI two-cylinder two-stroke
engine with 2.58:1 Rotax “B” reduction gearbox, mounted on the top flat area of inter-wing axial
beam, riveted from aluminum alloy sheets.
Standard pusher 3-blade GFK- on the ground adjustable propeller and electric starter for EX version ,
two blade fixed wooden propeller Křemen SR 26 with rewind starter for UL version.
Flight manual
interplane
Skyboy EX
Page 8 - 1
8
GROUND HANDLING
8.1
ASSEMBLING FOR TRANSPORTATION AND HANGARING
The airplane can be easily assembled into a transportation state.
This assembling includes:
- turning up the stabilizers towards the fin
- disconnecting aileron controls
- detaching the wings
- folding the struts to the wing
8.1.1 Detaching the wings
1 - It is necessary to disconnect both control rods from the wing horn levers before detaching the wings. A helper
will then hold the wing tips.
2 - Take apart the bolt from the lower wing strut hinge on the fuselage
3,4 - Take apart both wing hinges on the fuselage. It is better to hold the wing before loosing the last pin. (It is
easier to do it with three men and to loose then both wing hinges on the fuselage simultaneously)
- Step back from the airplane with the wing. The wing can be put on the leading edge or on the upper
skin, but never put it on a surface that could damage it. If there is no soft - grassy surface, put a piece of foam
under the wing. The struts can be folded then up to the wing.
Repeat the procedure with the second wing
For the transportation, we recommend to put the dismantled pins into the loosen forks of the wing hinges again and to lock them.
Fig.1: Dispatching of the wing and turning up the stabilizers
8.1.3 Turning up the stabilizers
1 - Take the locks out of the lower hinge pins for the stabilizer stretching cables. Slacken off the pins or quick-
stretcher (if installed) and loosen then the pin on the opposite side.
2,3 - Then, turn up both sides of the stabilizer to the fin. Secure both sides of the stabilizer by binding together the
brackets for aft hinges of the stretching cables are by joining them by transportation jig.
ATTENTION! Set the elevators into the neutral position before turning them up to prevent the undesirable stressing
of the elevator-connecting lever. The upper cables will be slackened in the turned-up position, thus, take care of the
proper position of the stretching cable terminal eyes when setting the airplane back into the flight configuration to
prevent their breaking.
Flight manual
interplane
Skyboy EX
Page 8 - 2
Fig.2: Quick-stretcher of the stabilizer cables
1 - stretcher bracket
2 - stretcher lever with fork
3 - safety pin
4 - cable stirrup
5 – cables
Locking procedure:
Put the lever fork (fig.2) on the pin of the stretcher body
(fig.1). Stretch the cables by turning in the arrow direction.
Secure the lever (fig.2) with a pin (fig.3) and lock this pin.
8.2 Parking
8.2.1 General
Parking the airplane in the open air should be considered as a emergency measure in view of the dangerous effects of the
strong wind and slackening of the skin due to rain or excessive humidity.
It is recommended to turn up the stabilizers to the fin for parking and to connect the rear cable hinges together in the
same way as for hangaring.
Ground equipment: - pressure sensor plug of the airspeed indicator
- securing cable for joining the turned up stabilizers
8.2.2 Pressure sensor plug of the airspeed indicator
Airspeed indicator is protected against blowing through by means of a rubber plug put on the input pipe of the total
pressure sensor located in front of the laminate cockpit cover in the input hub of the cabin ventilation.
The plug is provided with a red flag.
8.3 Mooring
The airplane should be moored if parked
outside the hangar to protect it against possible
damage in case of increased wind intensity.
The airplane mooring equipment consists of the
following:
- 3 mooring bolts
- 2 long and 1 short mooring cables
Mooring bolts should be screwed in the ground
and the airplane should be moored by means of
cables as shown in Fig. 3.
Fig.3: Airplane mooring
1 - Mooring cable
2 - Mooring bolt
3 - Cable to join stabilizers
I - Mooring ring(bolt) detail
II - Cable fixing to the landing gear hinge
III - Cable fixing to the wing hinge
8.4 Hangaring
Moving the airplane during hangaring, parking, etc. is recommended by pushing the empty airplane. Grip the backbone
fin tube of the airplane close to the fin and push it slightly down to pick up the nose landing gear.
The airplane can be then controlled simple by side movements. If the assistance of further persons is needed, the wing
struts near their hinges on the wing are the recommended positions for pushing the airplane.
Pushing or leaning on the control surface skin is forbidden.
8.5 Towing
Towing the airplane with a car is not allowed.
Flight manual
interplane
Skyboy EX
Page 9 - 1
9
SUPPLEMENTS
The Flight Manual includes filled and confirmed supplements for the concrete airplane :
9.1 RECORD ABOUT THE WEIGHING AND LOCATION OF CENTERS
OF GRAVITY POSITIONS
9.2 RECORD ABOUT THE MEASURING OF DEFLECTIONS OF
CONTROL SURFACES
9.3 RECORD ABOUT THE LEVELLING OF THE AIRPLANE
9.4 RECORD ABOUT THE TEST FLIGHT OF THE AIRPLANE
9.5 ENGINE MANUAL
RECORD
about the weighing and location of gravity for the airplane
Skyboy
Page 1
Type
:
Skyboy
Producer :
Interplane
s.r.o. Zbraslavice - CZECH REPUBLIC
Serial number :
Matriculation :
ALL DIMENSIONS ARE IN METERS
THE WEIGHING IS MADE ON THE WHEELS OF THE LANDING GEAR
REFERENCE PLANE - leading edge of profile in half
of the wing span
R
1A
… needed additional ballast for staying of airplane without crew on the three wheels ( 0,5 to 3 kg )
Recommended ballast position is on the pedal tubes = above the position of front wheel.
A. VALUES DETERMINED BY WEIGHING :
WEIGHTS (measured on the balance )
DIMENSIONS :
Theoretical :
Reaction of the nose wheel
R
1
= kg X1 = m
X1 = 0,997 m
Additional ballast for weighing
R
1A
= kg
Reaction of left main wheel
R
2L
= kg X2 = m
X2 = 0,782 m
Reaction of right main wheel
R
2P
= kg
Basic weight of the airplane
M
L
= kg
BASIC WEIGHT CONTAINS :
a) weight of the airplane structure assembled by the technical specification
b) operating substances inclusive of inexhaustible fuel
R
2
= R
2L
+ R2P
M
L
= R
2L
+ R
2P
+ R1- R1A
RECORD
about the weighing and location of gravity for the airplane
Skyboy
Page 2
B. VALUES DETERMINED BY CALCULATION
Position of the airplane
center of gravity
regarding reference plane
Center of the gravity position
of basic weight
( position of the center of gravity regarding MAC - mean
aerodynamic chord )
(R2L+ R2P) . X2 - R1. X1 + R
1A
. X
1
X
L
=
M
L
(……+……) x ….. - …… x ……+ …… x……
=
…………..
X
L
. 100 % . 100 %
X
T
= =
b
MAC
1,5
XL = m
XT = % MAC
Connected with chosen engine and equipment, the airplane empty weight is 220 to 290 kg.
This weight would never extend 296 kg !
For normal range of crew weight range from minimum 65 kg of one pilot to maximum crew weight :
Centers of gravity positions of the basic weight MUST BE in the range
47 to 52 % MAC
Forward centers of gravity positions (under 47 % MAC) are the resource of bigger forces and force gradients to the
controls. Backward centers of gravity positions (over 52 % MAC)
are INADMISSIBLE
for the holding
of positive force gradients in the controls - especially during higher flight speeds and speeds near the stall speed.
This center of gravity position of basic empty weight accords with technical specification and secures the
observance of specified operating
centers of gravity positions from 21 to 36,6 %
MAC for
approving range of the crew weight according to the flight manual.
Maximum crew weight is 450 kg – ML ( the empty weight of this aircraft ) – fuel weight (circa 0,72 kg/l ):
Quantity of the fuel in the tank
¼
of fuel (circa 7 kg) ½ of fuel (circa 14 kg )
Full tank
(circa 28 kg
)
Maximum crew weight [ kg ]
Maximum crew weight [ lb ]
If you want to reduce the control forces for flying in maximum take-off weight configuration and you have no
problem with lower weight single flights, you can use rearer centers of gravity positions too.
For this purpose, you need to recalculate minimum single pilot weight ( for 2 ° forward swept wing ) :
ML * ( X
L
- 0,55 )
Minimum single Pilot weight limit = =
0,85
… or measure the airplane including some concrete lower weight pilot on the pilot seat to decide 36,6% gravity
position limit. For this measurement you can use the same table ( excluding additional ballast of course ).
Date : Technician worker :
kg
lb
RECORD
about leveling of airplane
Skyboy
Type
Skyboy
Producer
Interplane s.r.o. Zbraslavice - CZECH REPUBLIC
Serial number
Matriculation
MEASURING OF CONTROL SURFACES
DEFLECTIONS :
- The measuring of elevator and ailerons deflections was
made with help of common measuring jig, which
consists from the pro- tractor with a clamp for
clamping to the control surface and the plumb bob,
which is clamped in the center of the protractor.
- The measuring of rudder deflection was made with
help of the protractor or we simplify the measuring
so, that we measure a distance from the rudder
surface to the hollow of elevator. This distance
would be circa 15 mm in the narrowest place.
THE TENSION OF THE RUDDER CONTROL CABLES :
cable : demanded :
measured :
left
100 + 30 N
right
100 + 30 N
VERIFICATION OF FUNCTIONAL ABILITY OF THE ALL CONTROLS :
Date : Technician worker :
demanded : measured values :
ELEVATOR
up
30 O + 1.5 O
down
15 O + 1.5O
RUDDER
to left
25 O ±±±± 2 O
to right
25 O ±±±± 2 O
neutral
0 °°°°
AILERONS
ailerons up
18 °°°° ±±±± 1 °°°°
ailerons down
10 °°°° ±±±± 1 °°°°
left aileron right aileron
Picture : Control surfaces deflections
RECORD
about leveling of airplane
Skyboy
Type
Producer
inter
plane
s.r.o.
Zbraslavice
-
CZECH REPUBLIC
Serial number
Matriculation
1. Measurement of the main arrangement of the wing and tail
Measurement is made in airplane position with central tube in the angle 10,2°, when wing root is in the water level.
Acceptable difference of the vertical measurement is ± 3 mm
4. Measurement of the central tube
Acceptable difference of the measurement is
± 5 mm
on the end of central tube. Followed values are measured in interplane by using
of hose water level, applied between the water leveled crossbeam hinges and rear end of the tube top surface
:
2. Measurement of aerodynamic area angles
3. Measurement of the undercarriage legs angles
Acceptable difference of the angles measurement is
± 0,3 °°°°
( it takes ±5 mm on the end of 1 m long late )
F
ollowed values are measured in interplane by using of protractor with water level, applied to late, or directly on the surface :
Date : Technician worker :
measured : difference
point
left wing right wing
(1)
Left
– (1)
Right wing
1-2
1-3
Acceptable difference of the horizontal measurement is
± 5
mm
4-5
poin
t
left wing right wing
difference
6
7
8
elevator ribs :
left elevator right elevator
11
12
fin :
( measured on the tube with tail reinforcing cable hinges )
13
undercarriage legs :
14
15
measured :
point
central fuselage tube
17-18-19
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