Dynali H3 EASYFLYER SPORT Technical specifications

DYNALI HELICOPTER COMPANY
101, avenue Thomas Edison,1402 -Thines BELGIQUE
Tel : [phone] Fax : [phone]
[email protected]
______________________________________________________________________
FLIGHT MANUAL
DYNALI H3 EASYFLYER ʻSPORTʼ
Microlight Helicopter
S/N : ______________________
Registration : _______________
Ref. DYNH3SPORT/01/01/T01
Copyright © by Dynali Helicopter Company, Thines, Belgium
DYNALI HELICOPTER COMPANY
101, avenue Thomas Edison,1402 - Thines BELGIQUE
Tel : [phone] Fax : [phone]
Mail : [e-mail]
______________________________________________________________________
MANUEL DʼUTILISATION
DYNALI H3 EASYFLYER ʻSPORTʼ
Hélicoptère ultra-léger
S/N : ______________________
Immatriculation : _____________
Ref. DYNH3SPORT/01/01/T01
Copyright © by Dynali Helicopter Company, Nivelles, Belgium

FLIGHT MANUAL
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This document is protected by copyright, all associated rights, in particular those
related to the translation, printing, reproduction of photographs or the storage of data
are reserved. Any unauthorised reproduction may result in legal proceedings.
DYNALI HELICOPTER COMPANY
101, AVENUE THOMAS EDISON
1402, THINES
BELGIQUE
TEL : [phone]
FAX : [phone]
E-MAIL : [email protected]

FLIGHT MANUAL
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INTRODUCTION
RECORDING OF REVISIONS
The validity of the present flight manual depends upon the regularity with which it is updated.
The signature of the owner constitutes a guarantee for himself and other users that the
manual is up to date. The composition of the manual is defined by the list of current pages.
Revisions
Incorporated
N°
Date
Date
Responsable
Signature
Original edition
August
2014
27/08/14
J. Tonet

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1 GENERAL................................................................................................................................. 7
1.1 DESCRIPTION..............................................................................................................................7
1.2 TECHNICAL CHARACTERISTICS ...............................................................................................7
1.2.1 MAIN ROTOR ......................................................................................................................................... 7
1.2.2 REAR ROTOR ........................................................................................................................................ 7
1.2.3 MAIN TRANSMISSION ........................................................................................................................... 8
1.2.4 ENGINE .................................................................................................................................................. 8
1.2.5 FUEL ....................................................................................................................................................... 8
1.2.6 ENGINE COOLING AND LUBRICATION ............................................................................................... 8
VIEWS AND DIMENSIONS .......................................................................................................10
2 LIMITS IN USE ....................................................................................................................... 11
2.1 LIMITS IN WEIGHT.....................................................................................................................11
2.2 BALANCE LIMITS .......................................................................................................................11
2.3 SPEED LIMITS............................................................................................................................12
2.4 LOAD FACTOR LIMITS ..............................................................................................................12
2.5 AUTHORISED OPERATION.......................................................................................................13
2.6 LIMITS ENGINE AND ROTOR RPM...........................................................................................14
2.7 TRANSMISSION LIMITS.............................................................................................................15
2.8 NOISE LEVEL .............................................................................................................................15
2.9 PLACARDS .................................................................................................................................16
3 EMERGENCY PROCEDURES............................................................................................... 17
3.1 ENGINE FAILURE– GENERAL ..................................................................................................17
3.2 ENGINE FAILURE ABOVE 500FT..............................................................................................17
3.3 ENGINE FAILURE AT LOW ALTITUDE AND LOW SPEED ......................................................17
3.4 GOVERNOR FAILURE ...............................................................................................................18
3.5 FORCED DITCHING WITHOUT ENGINE POWER ....................................................................18
3.6 FORCED LANDING UNDER POWER ........................................................................................18
3.7 REAR TRANSMISSION OR REAR ROTOR FAILURE IN TRANSITION....................................18
3.8 REAR TRANSMISSION OR REAR ROTOR FAILURE IN HOVERING FLIGHT ........................19
3.9 ENGINE FIRE ON START-UP ....................................................................................................19
3.10 ENGINE FIRE IN FLIGHT .........................................................................................................19
3.11 ALARM AND WARNING LIGHTS .............................................................................................19
4 NORMAL PRE-FLIGHT AND CHECK-OUT PROCEDURES .................................................21
4.1 PRE-FLIGHT INSPECTION ........................................................................................................21
4.1.1 TARMAC AND ENVIRONMENT ........................................................................................................... 21
4.1.2 AIRFRAME............................................................................................................................................ 21
4.1.3 CABIN INTERIOR .................................................................................................................................22
4.2 STARTUP....................................................................................................................................22
4.3 TAKE OFF...................................................................................................................................23
4.4 CRUISE.......................................................................................................................................23
4.5 APPROACH AND LANDING.......................................................................................................23
4.6 AUTOROTATION........................................................................................................................24
4.7 ENGINE SHUT DOWN PROCEDURE........................................................................................24
4.8 CHECKOUT ................................................................................................................................25
5 PERFORMANCE ....................................................................................................................26
5.1 GENERAL ...................................................................................................................................26
5.2 ALTITUDE DENSITY DIAGRAMME ...........................................................................................26
5.3 DIAGRAMME : HOVER IN GROUND EFFECT ..........................................................................27
5.4 DIAGRAMME : HOVER OUTSIDE GROUND EFFECT..............................................................28
5.5 DIAGRAMME HEIGHT/ AIRSPEED............................................................................................29
5.6 ENGINE PERFORMANCE DIAGRAMME...................................................................................30

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6 WEIGHT AND BALANCE SHEET ..........................................................................................31
6.1 EMPTY WEIGHT ET BALANCE .................................................................................................31
6.2 PROCEDURE FOR WEIGHING EMPTY ....................................................................................31
6.2.1 PREPARATION OF THE AIRCRAFT ................................................................................................... 31
6.2.2 METHOD TO DETERMINE EMPTY C.G. POSITION........................................................................... 31
6.3 CALCULATION OF WEIGHT AND BALANCE............................................................................32
6.4 INDIVIDUAL WEIGHT SHEET ....................................................................................................33
6.5 LATERAL BALANCE...................................................................................................................34
7 SYSTEMS............................................................................................................................... 35
7.1 GENERAL ...................................................................................................................................35
7.2 AIRFRAME..................................................................................................................................35
7.3 UNDERCARRIAGE .....................................................................................................................35
7.4 MAIN ROTOR .............................................................................................................................35
7.5 REAR (ANTI-TORQUE) ROTOR ................................................................................................36
7.6 TRANSMISSIONS.......................................................................................................................36
7.7 ENGINE.......................................................................................................................................37
7.8 FLIGHT CONTROLS...................................................................................................................37
7.9 ENGINE –CLUTCH –DRIVE BELTS.........................................................................................38
7.10 FUEL CIRCUIT..........................................................................................................................38
8 HANDLING AND MAINTENANCE..........................................................................................39
8.1 GENERAL ...................................................................................................................................39
8.2 OBLIGATORY DOCUMENTS.....................................................................................................39
8.3 MAINTENANCE ..........................................................................................................................40
8.4 MAINTENANCE AND PROCEDURES .......................................................................................40

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WARNING
This flight manual is designed as an operational guide for the pilot and included all necessary
information required by the regulations.
It also includes additional information provided by the manufacturer.
It cannot be considered in any case as a pilot or flight instruction manual
It is the responsibility of the pilot to ensure the certification and the flight condition of the
machine.
The pilot must imperatively remain within the flight envelope indicated by the instruments and
by the contents of this manual.
Prior to any flight the pilot in command must be aware of all the limits, performances,
procedures and characteristics of the helicopter.

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1GENERAL
1.1 DESCRIPTION
The Dynali H3 EasyFlyer ʻSportʼis a microlight two-seater helicopter in a side-by side
configuration. It has a maximum takeoff weight of 450kg, with an empty weight of 280kg. It is
powered by a Rotax 912ULS on which various equipments allow to increase the power from
100 to 110 HP. Its structure is based on a stainless steel frame. The tail structure is made
from aluminium and the tail struts are in carbon. The cabin cell is in carbon and the canopy in
perspex. The fuel tank can hold 60 liters. In the standard version, the Dynali H3 EasyFlyer
ʻSportʼis equipped with dual controls, a central exhaust, two cooling fans and an engine
governor.
1.2 TECHNICAL CHARACTERISTICS
1.2.1 MAIN ROTOR
Semi-rigid type on teetering hinge
Main Rotor – Diameter.................................................................................. 7,14 m
Number of blades................................................................................................... 2
Blade chord.................................................................................................... 18 cm
Blade twisting....................................................................................................... 6°
Blade weight ................................................................................................... 12 kg
Blade tip speed at 100% of nominal configuration ................................... 692 km/h
1.2.2 REAR ROTOR
Rigid type without articulation.
Rear rotor – Diameter .....................................................................................0,8 m
Number of blades................................................................................................... 4
Blade chord................................................................................................... 5,5 cm
Blade twisting....................................................................................................... 5°
Blade weight ....................................................................................................78 g
Blade tip speed at 100% of nominal configuration ................................... 580 km/h

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1.2.3 MAIN TRANSMISSION
Main transmission and Main Transmission Gearbox (MTG)
Main Transmission.....................................................................................4V-belts
Main transmission gearbox (MTG)..................................... 90° conic spiral gearing
Reduction ration MTG....................................................................................3,55/1
Rear transmission and Rear Transmission Gearbox (RTG)
Rear transmission ............................................................................................ shaft
Rear transmission gearbox (RTG) ..................................... 90° conic spiral gearing
Reduction ratio RTG ........................................................................................... 2/1
Reduction ratios
engine / main transmission shaft ..................................................................... 2,9/1
engine / engine gear ......................................................................................2,43/1
engine / main rotor ....................................................................................... 10,63/1
rear rotor / main rotor .....................................................................................7,32/1
1.2.4 ENGINE
4 stroke, flat 4 cylinders, with twin carburettors.
H3 EasyFlyer ʻSportʼ
Carburettors
Injection
Engine
Rotax 912ULS
Rotax 912ULS-I
Bore
1350 cm3
1350 cm3
Max. power output
100 HP
110 HP
Cooling system
water, oil, air
1.2.5 FUEL
Regular fuel......................................................................................... SP 95 to 100
Occasional fuel ...............................................................................AVGAS 100 LL
Hourly consumption:...................................................................................... 20 L/h
Total fuel capacity :...........................................................................................60 L
Usable fuel capacity:.........................................................................................60 L
Non usable capacity :..........................................................................................0L
Low level warning light........................................................................................ 7 L
1.2.6 ENGINE COOLING AND LUBRICATION
Engine coolant
Glycol diluted at 50%

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Quantity........................................................................................................ 6L max
Engine oil
Type ................................................motorcycle engine oil with anti-friction additive
Capacity ............................................................................................................ 3,2L
Recommended oils ......................................................motorcycle 20W40 to 5W60
Consumption....................................................................... 0,1 liter/hour maximum
Oil MTG
Type ........................................................................................ hypoïd SAE 75 to 90
Capacity ........................................................................................................... 0,5 L
Oil RTG
Type ....................................................................................... hypoïd SAE 75 to 90
Capacity........................................................................................................ 125 ml
Oil in the free-wheel
Type ......................................................................... Specific oil available on order
Capacity .......................................................................................................... 40 ml
Spark plugs
Type ................................................................................................... NGK BPR8E
Spark electrode distance ................................................................... 0,6 to 0,7 mm
Cylinder compression ratio Rotax 912ULS .......................................................... 11

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VIEWS AND DIMENSIONS
Airframe length..............................................................................................6,20 m
Maximum Length (including main rotor)........................................................8,00 m
Height ........................................................................................................... 2,50 m
Height on wheels ......................................................................................... 2,60 m
Interior cabin width........................................................................................ 1,30 m
Width of undercarriage.................................................................................. 1,80 m

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2LIMITS IN USE
2.1 LIMITS IN WEIGHT
Maximum takeoff weight at sea level ............................................................ 450 kg
Standard empty weight ................................................................................. 280 kg
Maximum empty weight ................................................................................ 280 kg
Standard payload .......................................................................................... 170 kg
N.B : Suspended load totally prohibited.
The maximum take-off weight is limited by the national regulations related to ultralight
helicopters and by the engine output.
GENERAL RULE : always keep 1ʼʼinHg (MAP) power margin in relation to
atmospheric pressure.
2.2 BALANCE LIMITS
The balance envelope is conditioned by the correct adjustment of the flight controls which
allow for full travel. The original setting of the horizontal stabiliser must not be modified.
Longitudinal balance is limited between the extreme afterward balance and the extreme
forward balance, corresponding to the limits tested in flight.
Between the forward and afterward balance limits, all variations are authorised insofar as the
maximum takeoff weight of 450 Kg is not exceeded.
Datum point .......................................................................................................rotor mast
Extreme forward balance authorised (from the mast).........................................+136mm
Extreme aft balance authorised (from the mast)..................................................-136mm
Minimum weight of solo pilot ................................................................................... 50 kg
Maximum weight of solo pilot (imperatively left hand seat).................................... 125kg
SOLO PILOT ALWAYS ON THE LEFT
N.B : For a standard H3 with properly adjusted flight controls :
-Maximum forward center of gravity = 2 pilots weighing 200kg in total
-Maximum backward center of gravity = 1 pilot weighing
-Maximum lateral center of gravity = 1 pilot weighing 135kg

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2.3 SPEED LIMITS
Maximum speed (Vmax) ........................................................................... 145 km/h
Speed not to be exceeded (VNE)............................................................. 155 km/h
Speed not to be exceeded (VNE) without lateral panels............... ........... 100 km/h
Green arc (up to Vmax) .................................................. from 70 km/h to 145 km/h
Yellow arc (Vmax to VNE) ............................................ from 145 km/h to 155 km/h
Red arc (above VNE)................................................................................ 155 km/h
Maximum crosswind limit ............................................................................ 30 km/h
N.B : colour code for instruments
Green : Normal operating range.
Yellow : Operating range requiring special attention.
Red : Indicates limits of operation.
2.4 LOAD FACTOR LIMITS
Limit of positive load factor ................................................................................+5g
Limit of negative load factor .................................... Negative load factor prohibited
N.B : As on all twin blade helicopters negative load factors are formally prohibited.

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2.5 AUTHORISED OPERATION
-Daytime VFR flight is authorised.
-Night time VFR flight is prohibited.
-IFR flight is prohibited.
-Aerobatic flight is prohibited.
-Flight in icing or supercooling conditions is prohibited.
-Maximum altitude density for operation is 10 000 ft.
-Load capacity is for maximum of two persons including pilot.
-In solo flight the pilot must be in the left hand seat.
-Flight with lateral perspex canopy panels removed is authorised.
-Tight turns authorised if machine remains within recommended speed, load
factor and weight limits.
-Dual controls authorised.
-The maximum lateral banking in flight is 66° (+2,5G). Beyond that angle, rotor
dynamic stall can occur.
-Slope landing : maximum 8° front, 4° lateral.
N.B :
In most countries the law prohibits flight with dual controls except in training flights accompanied
by a qualified instructor on board. Without an instructor it is necessary to remove the cyclic stick
on the passenger side.

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2.6 LIMITS ENGINE AND ROTOR RPM
RPM LIMITS ROTOR / ENGINE
%
ROTOR
RPM
ENGINE
RPM
Low RPM under power
93
480
5100
Low RPM under power
(ALARM)
96
500
5300
Max RPM under power
100
516
5500
Low RPM freewheel
106
540
5800
Max RPM freewheel
109
565
6000
Maximum rotor RPM ....................................................................109 % -565 RPM
Maximum engine RPM...............................................................106 % -5800 RPM
Régime minimal du rotor.................................................................93% -480 RPM
Instrument indications :
Tachometer
Rotor
Rotor
%
Engine
Tachometer
Engine
[RPM]
[RPM]
Red line
480
93
5100
Yellow arc
500
96
5300
516
100
5500
Green arc
Green arc
530
103
5650
Yellow arc
Yellow arc
540
106
5800
Red line
Red arc
Red line
565
109
6000

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2.7 TRANSMISSION LIMITS
Engine limits as found in the Rotax manual or its appendices take priority over information
provided in this manual for information purposes.
Climatic conditions for engine start-up
Minimum temperature ....................................................................................-15 °C
Maximum temperature ....................................................................................40 °C
Engine block temperature
Low temperature caution range .............................................................60 to 75 °C
Normal range .......................................................................................75 to 100 °C
High temperature caution range ........................................................100 to 110 °C
Maximum ......................................................................................................110 °C
Engine oil pressure
Low oil pressure warning light..........................................................................1bar
Main transmission oil temperature
Normal range ...................................................................................60°C to 110 °C
Caution range ................................................................................ 110°C to 125°C
Maximum ......................................................................................................125°C
Fual type
Regular fuel.................................................. automobile gasoline 95 to 100 octane
Occasional fuel ................................................................................AVGAS 100 LL
N.B : Green fuels are prohibited such as Ethanol. Some fuels induce knock in the cylinders and can
cause piston destruction instantly. Be careful.
2.8 NOISE LEVEL
Measurement conditions : unobstructed area, no background noise.
REFERENCE MEASUREMENT POINT
NOISE LEVEL
(EPNDB)
Takeoff
71
Approach
73
Overflight
69

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2.9 PLACARDS
In view of pilot and passenger:
SOLO PILOT IN LEFT HAND SEAT
HEAVIER OCCUPANT IN LEFT HAND SEAT
N.B : Nonetheless if the pilot in the right hand seat weighs up to 20 kg more than the passenger in the
left hand seat the helicopter remains perfectly controllable.
MAXIMUM WEIGHT FOR SOLO PILOT:125KG
MAX TAKEOFF WEIGHT:450KG
MINIMUIM WEIGHT FOR SOLO PILOT : 50 KG
VMAX :145 KM/H
VNE : 155 KM/H
FUEL : SP98/SP95
STARTER
MAGNETO

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3EMERGENCY PROCEDURES
3.1 ENGINE FAILURE–GENERAL
-EVERY PILOT MUST BE PERFECTLY TRAINED FOR AUTOROTATION.
-A loss of power may be caused by a failure of engine or transmission.
-A change in the noise level, a yawing movement or a loss of revolutions (RPM)
may indicate an engine failure.
-A transmission failure may be indicated by an unusual noise, vibrations or
serious yawing. In all events, autorotation should be initiated.
-When hearing weird noise, shock, alert, lower the collective stick and perform.
3.2 ENGINE FAILURE ABOVE 500FT
-Lower the collective completely and immediately to initiate autorotation.
-Cut the throttle and push the left pedal down.
-Maintain the speed around 100km/h.
-Use collective to maintain rotor RPM.
-Select landing point facing into wind.
-Approaching the ground, act on the cyclic stick to flare and reduce rate of
descent WITHOUT RISING THE COLLECTIVE STICK.
-At around 10ft,push the cyclic forward to bring the machine to horizontal and
raise the collective to halt the descent.
-Preferably land into the wind.
WARNING : the first “hold” is necessary to brake the rate of descent. A rotor can only
support +2.5 to +3G ; beyond this limit, the helicopter risks “passing through” the
flare, i.e. that the rate of descent is not sufficiently attenuated and the machine
impacts on the ground.
3.3 ENGINE FAILURE AT LOW ALTITUDE AND LOW SPEED
-Left pedal down
-Above 5ft, slightly lower collective.
-Use collective to cushion contact with the ground
N.B : If the Quick Stop isnʼt possible, land sliding.

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3.4 GOVERNOR FAILURE
If there is a failure of the governor in flight, use the throttle to maintain rotor RPM manually
and land using an average angle approach. The throttle control must be used to ensure full
power and RPM. The pilots must be trained to control the throttle manually.
3.5 FORCED DITCHING WITHOUT ENGINE POWER
-Autorotation procedure until contact with water.
-Lay the helicopter down on the left as soon as contact has been made with
water in order to stop the rotation of the rear rotor.
-Detach the safety belts and evacuate the cabin rapidly as soon as the rotor has
completely stopped turning.
3.6 FORCED LANDING UNDER POWER
-Move into hover over the water,
-Unbolt the doors and release safety belts
-Evacuate the passenger
-Fully cut the engine and left pedal down.
-Slow rate of descent by pulling on the cyclic.
-Lay the helicopter down on the left hand side in order to stop the rotor blades to
the rear.
-Leave the machine as soon as the rotor has stopped.
3.7 REAR TRANSMISSION OR REAR ROTOR FAILURE IN
TRANSITION
-Sudden yaw to the left that cannot be controlled with the right pedal if the
airspeed is below 100km/km/h. Above 100km/h the vertical stabilisers remain
efficient enough to maintain heading +/- 25%.
-Initiate autorotation immediately and then adjust power.
-Maintain 110 km/h to maintain so that the vertical stabilisers assist in keeping
heading.
-Close throttle to idle and slightly increase collective. Hold the cyclic to the right
to limit sideslip.
-On final, throttle to idle and sliding landing under autorotation.

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3.8 REAR TRANSMISSION OR REAR ROTOR FAILURE IN
HOVERING FLIGHT
-Sudden yaw to the left that cannot be controlled with the right pedal.
-Keep machine horizontal and raise collective to cushion impact.
-Cut the throttle immediately.
3.9 ENGINE FIRE ON START-UP
-Cut engine and evacuate.
-Extinguish the fire with an extinguisher, a fire hose, or a woollen blanket, sand
or earth.
3.10 ENGINE FIRE IN FLIGHT
-Rapid descent under autorotation.
-Land under power if possible.
-If engine is operating, open the throttle and make a normal landing.
3.11 ALARM AND WARNING LIGHTS
Red lights Low RPM rotor + audio alarm at 92%
Action : lower the collective and twist the throttle handle through the governor to recover rotor
RPM immediately.
Several situations should be considered :
-In hovering flight, lower the collective and open wide the throttle.
-At altitude, with a sufficient margin, you can fully lower the collective, open wide
the throttle to recover the rotor RPM and pick up speed.
In any case you should not follow your initially planned approach if you have a Low RPM
warning.
Red charging light
If the alternator fails, the engine continues running but you should land as soon as possible
as the fans may cease operating.

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Orange warning light Low Fuel
This warning will light up when there are 7L of fuel remaining. The engine will run dry after
about 20 minutes of operation at nominal power.
Action : you should land within 5 minutes : no emergency.
Orange warning filings detector main transmission
This warning lights up if metallic particles are detected in the main transmission gearbox.
Action : you should land within 5 minutes : no emergency
Orange warning light rear transmission
This warning lights up if metallic particles are detected in the rear transmission gearbox.
Action : you should land within 5 minutes : no emergency