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DYNALI HELICOPTER COMPANY 101, avenue Thomas Edison,1402 - Thines BELGIQUE Tel : +32 (0) 67 55 29 98 Fax : +32 (0) 67 84 05 31 [email protected] ______________________________________________________________________ FLIGHT MANUAL DYNALI H3 EASYFLYER Microlight Helicopter S/N : ______________________ Registration : _______________ Ref. DYNH3/01/01/T01 Copyright © by Dynali Helicopter Company, Thines, Belgium

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  • DYNALI HELICOPTER COMPANY 101, avenue Thomas Edison,1402 - Thines BELGIQUE

    Tel : +32 (0) 67 55 29 98 Fax : +32 (0) 67 84 05 31 [email protected]

    ______________________________________________________________________

    FLIGHT MANUAL

    DYNALI H3 EASYFLYER

    Microlight Helicopter

    S/N : ______________________

    Registration : _______________

    Ref. DYNH3/01/01/T01

    Copyright by Dynali Helicopter Company, Thines, Belgium

  • FLIGHT MANUAL EDITION N1 DYNALI H3 EASYFLYER NOVEMBER 2013

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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 : +32 (0) 67 55 29 98 FAX : +32 (0) 67 84 05 31 E-MAIL : [email protected]

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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 March 2013 01/03/13 J. Tonet Edition 01 November 2013 15/11/13 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

    2 VIEWS AND DIMENSIONS ....................................................................................................10 3 LIMITS IN USE .......................................................................................................................11

    3.1 LIMITS IN WEIGHT.....................................................................................................................11 3.2 BALANCE LIMITS .......................................................................................................................11 3.3 SPEED LIMITS............................................................................................................................12 3.4 LOAD FACTOR LIMITS ..............................................................................................................12 3.5 AUTHORISED OPERATION.......................................................................................................13 3.6 LIMITS ENGINE AND ROTOR RPM...........................................................................................14 3.7 TRANSMISSION LIMITS.............................................................................................................15 3.8 NOISE LEVEL .............................................................................................................................15 3.9 PLACARDS .................................................................................................................................16

    4 EMERGENCY PROCEDURES...............................................................................................17 4.1 ENGINE FAILURE GENERAL ..................................................................................................17 4.2 ENGINE FAILURE ABOVE 500FT..............................................................................................17 4.3 ENGINE FAILURE AT LOW ALTITUDE .................................. ERREUR ! SIGNET NON DEFINI. 4.4 ENGINE FAILURE AT LOW ALTITUDE AND LOW SPEED ......................................................17 4.5 PROCEDURE FOR ENGINE RE-START ................................ ERREUR ! SIGNET NON DEFINI. 4.6. GOVERNOR FAILURE ..............................................................................................................18 4.6 FORCED DITCHING WITHOUT ENGINE POWER....................................................................18 4.7 FORCED LANDING UNDER POWER ........................................................................................18 4.8 REAR TRANSMISSION OR REAR ROTOR FAILURE IN TRANSITION....................................18 4.9 REAR TRANSMISSION OR REAR ROTOR FAILURE IN HOVERING FLIGHT ........................19 4.10 ENGINE FIRE ON START-UP ..................................................................................................19 4.11 ENGINE FIRE IN FLIGHT .........................................................................................................19 4.12 ALARM AND WARNING LIGHTS .............................................................................................19

    5 NORMAL PRE-FLIGHT AND CHECK-OUT PROCEDURES .................................................21 5.1 PRE-FLIGHT INSPECTION ........................................................................................................21

    5.1.1 TARMAC AND ENVIRONMENT.................................................................................................................................21 5.1.2 AIRFRAME..................................................................................................................................................................21 5.1.3 CABIN INTERIOR .......................................................................................................................................................22

    5.2 STARTUP....................................................................................................................................22 5.3 TAKE OFF...................................................................................................................................23 5.4 CRUISE.......................................................................................................................................23 5.5 APPROACH AND LANDING.......................................................................................................23 5.6 AUTOROTATION........................................................................................................................24 5.7 ENGINE SHUT DOWN PROCEDURE........................................................................................24 5.8 CHECKOUT ................................................................................................................................25

    6 PERFORMANCE ....................................................................................................................26 6.1 GENERAL ...................................................................................................................................26 6.2 ALTITUDE DENSITY DIAGRAMME ...........................................................................................26 6.3 DIAGRAMME : HOVER IN GROUND EFFECT ..........................................................................27 6.4 DIAGRAMME : HOVER OUTSIDE GROUND EFFECT..............................................................28 6.5 DIAGRAMME HEIGHT/ AIRSPEED............................................................................................29 6.6 ENGINE PERFORMANCE DIAGRAMME...................................................................................30

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    7 WEIGHT AND BALANCE SHEET ..........................................................................................31

    7.1 EMPTY WEIGHT ET BALANCE .................................................................................................31 7.2 PROCEDURE FOR WEIGHING EMPTY ....................................................................................31

    7.2.1 PREPARATION OF THE AIRCRAFT .........................................................................................................................31 7.2.2 METHOD TO DETERMINE EMPTY C.G. POSITION.................................................................................................31

    7.3 CALCULATION OF WEIGHT AND BALANCE............................................................................32 7.4 INDIVIDUAL WEIGHT SHEET....................................................................................................33 7.5 LATERAL BALANCE...................................................................................................................34

    8 SYSTEMS...............................................................................................................................35 8.1 GENERAL ...................................................................................................................................35 8.2 AIRFRAME..................................................................................................................................35 8.3 UNDERCARRIAGE.....................................................................................................................35 8.4 MAIN ROTOR .............................................................................................................................35 8.5 REAR (ANTI-TORQUE) ROTOR ................................................................................................36 8.6 TRANSMISSIONS.......................................................................................................................36 8.7 ENGINE.......................................................................................................................................37 8.8 FLIGHT CONTROLS...................................................................................................................37 8.9 ENGINE CLUTCH DRIVE BELTS.........................................................................................38 8.10 FUEL CIRCUIT..........................................................................................................................38

    9 HANDLING AND MAINTENANCE..........................................................................................39 9.1 GENERAL ...................................................................................................................................39 9.2 OBLIGATORY DOCUMENTS.....................................................................................................39 9.3 MAINTENANCE ..........................................................................................................................40 9.4 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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    1 GENERAL

    1.1 DESCRIPTION

    The Dynali H3 EasyFlyer is a microlight two-seat 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 912S which develops 100 HP (Rotax Turbo with 115 HP as an option, 10kg). Its structure is based on a stainless steel frame. The cabin cell is in carbon and the canopy in Perspex. The fuel tank can hold 60 litres. The fuel consumption at maximum power is 15L/h. In the standard version, the machine is equipped with 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..................................................................................7,11 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.....................................................................................8 V-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 ........................................................................................2,9/1 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. Engine............................................................................ Rotax 912S / Rotax Turbo Capacity ...................................................................................1350 cm / 1211cm3 Maximum power..............................................................................100CV / 115CV Cooling................................................................................................ .liquid, oil, air

    1.2.5 FUEL

    Regular fuel................................................................................ SP 95 or 98, UL91 Occasional fuel ...............................................................................AVGAS 100 LL Hourly consumption: ......................................................................................15 L/h Total fuel capacity : ...........................................................................................60 L Usable fuel capacity:.........................................................................................60 L Non usable capacity :..........................................................................................0 L Low level warning light........................................................................................5 L

    1.2.6 ENGINE COOLING AND LUBRICATION

    Engine coolant Glycol diluted at 50% Quantity........................................................................................................ 6L max

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    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 ........................................................................................ hypod SAE 75 to 90 Capacity ...........................................................................................................0,5 L

    Oil RTG

    Type ....................................................................................... hypod SAE 75 to 90 Capacity ........................................................................................................ 125 ml

    Spark plugs

    Type ...............NGK BPR8E (Rotax 912S) or DENSO X27 EPR U9 (Rotax Turbo) Spark electrode distance ...................................................................0,6 to 0,7 mm Cylinder compression ratio Rotax 912S...............................................................11 Cylinder compression ratio Rotax Turbo................................................................9

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    VIEWS AND DIMENSIONS

    Airframe length................................................................................................6,2 m Maximum Length (including main rotor).............................................................8 m Height .............................................................................................................2,5 m Height on wheels .........................................................................................2,61 m Interior width cabin........................................................................................1,30 m Width of undercarriage..................................................................................1,65 m

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    2 LIMITS IN USE

    2.1 LIMITS IN WEIGHT

    Maximum takeoff weight at sea level ............................................................ 450 kg Standard empty weight ................................................................................. 280 kg Maximum empty weight ................................................................................ 283 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 100HP output. GENERAL RULE : always keep 1inHg (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) .................................... 125 kg 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 140 km/h Yellow arc (Vmax to VNE) ............................................ from 140 km/h to 155 km/h Red arc (above VNE)................................................................................ 155 km/h Maximum crosswind limit ............................................................................ 35 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 Rgime 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 95 C High temperature caution range ..........................................................95 to 106 C Maximum ......................................................................................................106 C

    Engine oil pressure

    Low oil pressure warning light.......................................................................1,5 bar

    Main transmission oil temperature

    Normal range ...................................................................................60C to 120 C Caution range ................................................................................120C to 135 C Maximum ......................................................................................................135 C

    Fual type

    Regular fuel.................................................... automobile gasoline 95 or 98 octane Occasional fuel .............................................................. AVGAS 100 LL or Ethanol

    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: 125 KG MAX TAKEOFF WEIGHT: 450 KG MINIMUIM WEIGHT FOR SOLO PILOT : 50 KG

    VMAX :160 KM/H VNE : 190 KM/H

    FUEL : SP98/SP95

    STARTER

    MAGNETO

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    3 EMERGENCY 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 : Si le Quick Stop nest plus possible, atterrir gliss en non-drapage par rapport au sol.

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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 5L 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

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    4 NORMAL PRE-FLIGHT AND CHECK-OUT PROCEDURES

    4.1 PRE-FLIGHT INSPECTION

    4.1.1 TARMAC AND ENVIRONMENT

    1. Sweater/jacket or pollution, check that nothing can be sucked into the rotors. 2. No human or animal presence closer than 20m. 3. Wind speed and direction. 4. Obstacles and clearance in departure zones.

    4.1.2 AIRFRAME

    1. Remove the parking strap from rear facing rotor. 2. Undercarriage : wheels removed or locked. 3. Fuel tank : check level, filler cap closed, selector opened, filters, leaks. 4. Horizontal pitch rod : enough clearance from the landing skids. 5. Carburetors : check the springs (throttle, choke), ducts properly fixed, filters. 6. Carburetors tanks : check proper fixing and and no leaks or cracks. 7. Exhaust : 2 x 3 springs and hooks. 8. Radiator and fans : check for grass or debris and check for leaks. 9. Check for oil, coolant or fuel leaks on and below engine and transmissions. 10. Check drive pulley for signs of wear 11. Check pitot tube facing forward. 12. Check condition of drive belts and check that no foreign objects can obstruct

    them. 13. Juboflex : no deformation. 14. Rotor blades : check along full length. 15. Horizontal stabiliser : check no objects left lying there and carefully check

    attachments. Check the vertical stabilisers. 16. Rear transmission gearbox : check for leaks and oil level. 17. Rear rotor blades : check appearance. 18. Check the water level in the water expansion tank. 19. Rotax Turbo : check all metallic hoses (a leak can cause engine fire). 20. Do complete walk around check and observe everything

    N.B : If a maintenance operation has been performed, check.

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    4.1.3 CABIN INTERIOR

    21. Check for fuel smell. 22. Pedal lines straight. It is normal to feel a point of resistance in the pedal

    movement when stopped (but not at operating RPM). 23. No loose objects. 24. Empty seat : seatbelt fastened, not impeding collective. 25. Instrument panel : check the zeros. 26. Controls free and full travel of all 5 controls. 27. Check that when left hand collective is fully lowered, the central collective is

    against the lower stop (to guarantee autorotation). 28. Check maximum manifold pressure and atmospheric pressure. 29. Throttle in idle position. 30. Controls are not installed on the passenger side. 31. Doors are locked.

    4.2 STARTUP

    Belts Attached Doors Closed and latched Ignition switch ON Governor switch ON LOW RPM switch ON Clutch with OFF Fuel Verified and calculated Balance Verified and calculated Throttle Full - idle Contact ON Warnings Alight (charge, press, low RPM) Breakers Pushed in Pedals Check travel Cyclic plate Test movement 3cm Surroundings Clear Starter START at 2200 2500 RPM Ignition light Not alight Oil pressure 1,5 bars minimum Rotors Engage clutch after 30 sec RPM Increase to 300 rotor RPM Engine block Wait for 70C before takeoff RPM Increase to 5400RPM (100%) Warning low RPM Off Freewheel Check de-synchronisation RPM/rotor Instruments Checked Governor ON (green LED) Surroundings Clear

    Note : in very cold climatic conditions, the engine should be run up with rotors turning at 100% to heat the reduction and other bearings, before takeoff.

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    4.3 TAKE OFF

    Vibrations None Holding in hover Check RPM Stable Balance Checked Controls Normal, free and no shimmy T Min 70C Oil pressure Min 1,5 bar Controls Normal, free and no shimmy Transition Control trajectory Take-off Minimum 70km/h before climb

    4.4 CRUISE

    Collective Adjust Cyclic Do not let go Instruments / Alarms Regular visual check (green) External safety Permanent vigilance Altitude Min. 500ft Airspeed 100 to 140km/h RPM Monitor

    4.5 APPROACH AND LANDING

    Where possible, always opt for an upwind approach and check wind direction during your study of planned landing zone.

    POWER MANAGEMENT

    Reminders : climb configuration: power : 100%, airspeed 80 km/h (possibility 106% if necessary for a few seconds) Configuration for level flight: up to maximum continuous power Configuration for descent : power on demand (in relation to descent plan chosen) 90km/h airspeed on approach).

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    4.6 AUTOROTATION

    This is the most common safety measure that must be taken naturally. It is strongly advised to learn to perform this operation as often as possible, in order for it to become completely reflexive.

    Autorotation should be practiced from an altitude of 100m o above and an airspeed de 100km/h :

    - Initiate at a safe altitude. - Check clear below, forward and left and right. - Lower collective to lower stop. - Reduce throttle. - Reach and maintain airspeed of 90-100km/h. - Manage rotor RPM during descent - Approaching the ground, start to flare by acting on the cyclic without touching

    the collective. - Maintain heading to ensure that on impact with the ground there is no sideways

    movement. - In completing flare (when the tail is about to sink) flatten our (in non sliding

    mode) and start to provide lift with the collective without causing the machine to climb.

    4.7 ENGINE SHUT DOWN PROCEDURE

    After touchdown Immediately lower collective to stop position

    Throttle Immediately to idle Cyclic Neutral Pedals Neutral RPM Idle for 1 minute T Wait for significant drop Avionics Off Contacts OFF one after the other

    On shut down do not brake the rotor by using the collective. When left free, the wind can cause the rotor to swing over to head height. Any movement of persons below the rotor disc during shutdown is extremely dangerous. The pilot must survey the aircrafts surroundings and hold the cyclic to prevent the rotor swinging over.

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    4.8 CHECKOUT

    Having shut down the engine, watch the time that it takes for the rotor to stop. Get in the habit of placing your hand on the main and rear transmissions and checking the thermal label (tell-a-temp) on them. If the fuel level is low, lower the tail to check the LOW FUEL level sensor. Keep the fuel selectors opened to test the carburetors waterproofing. WARNING :

    - If the collective lever is too free, it is too sensitive. - If the collective frictions are too tightened, there are vibrations and shymmi. - If the cyclic stick is too free, it is too sensitive. - If the cyclic frictions are too tightened, control if difficult - For autorotation, adjust to have 516 RPM, solo pilot at 90km/h

    (refer to assembly manual)

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    5 PERFORMANCE

    5.1 GENERAL

    Performance data given in this chapter result from measurements made in standard atmosphere and at maximum takeoff weight. WARNING : Always keep at least 1 inHG (MAP) in relation to atmospheric pressure. Reminder : flight is authorised with atmospheric temperatures between 10C and +35C (For conditions outside this range please consult Dynali Reminder : the maximum altitude in cruise is 10 000ft Warning : information regarding performance indicated in this chapter was obtained under optimal flight conditions, Performance shown under other conditions may vary substantially from this.

    5.2 ALTITUDE DENSITY DIAGRAMME

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    5.3 DIAGRAMME : HOVER IN GROUND EFFECT

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    5.4 DIAGRAMME : HOVER OUTSIDE GROUND EFFECT

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    5.5 DIAGRAMME HEIGHT/ AIRSPEED

    Hard but smooth surface, Light wind - Power at 104%

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    5.6 ENGINE PERFORMANCE DIAGRAMME

    Please refer to Rotax 912S or Rotax Turbo engine manuals to find performance curves.

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    6 WEIGHT AND BALANCE SHEET

    6.1 EMPTY WEIGHT ET BALANCE

    The empty weight of a Dynali H3 EasyFlyer helicopter includes : - basic flight equipment, - engine oil, transmission gearbox oils, - coolant liquid, - The quantity of unusable fuel. The empty weight and the empty C.G. must be measured for each Dynali H3 EasyFlyer helicopter, once assembly is completed. The empty weight may not in any case (except for options) exceed the standard reference empty weight as indicated in this manual. Standard empty weight .280 kg Maximum takeoff weight ......450 kg Standard payload...170 kg Datum..defined as vertically from main rotor mast Forward balance limit in relation to datum...136 mm Aft balance limit in relation to datum....-136 mm

    6.2 PROCEDURE FOR WEIGHING EMPTY

    6.2.1 Preparation of the aircraft

    - Purge the fuel, - Check oil levels, - Check that all equipment included in the basic configuration are correctly

    installed, - Check the cleanliness of the aircraft and remove any foreign body,

    6.2.2 Method to determine empty C.G. position

    - Place a water level on the rotor mast, - Suspend the helicopter from a spring balance and hang on the rear rotor

    protection with a weight balance, place on a 80cm-high support, - Adjust the spring balance to keep the rotor mast vertical, - Read the spring balance value (A) and the weight balance value (B), - The center of gravity is located at X = B / (A+B) * 3884mm, behind the mast.

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    6.3 CALCULATION OF WEIGHT AND BALANCE

    The aircraft may only be used within the limits of weight and balance described in paragraph 2.8 Any additional load exceeding these limits may lead to an insufficient amplitude in the flight controls. For each part of a helicopter there is an associated weight expressed in kilos and a moment in relation to the datum point (the rotor mast) expressed in kg*m. This moment corresponds to the weight of the part multiplied by the distance from the centre of gravity of the part by reference to the datum. Before each flight you should : - Check that the position of the C.G. of your Dynali H3 EasyFlyer, as it will be on takeoff, is within the fore and aft balance limits. - Ensure that the takeoff weight of your Dynali H3 EasyFlyer does not exceed the maximum authorised takeoff weight 450 kg. These two conditions are met if the point defined by the takeoff weight and the position of the C.G. are within the range of the longitudinal CG (see figure showing longitudinal balance range). If either of these conditions is not met, you must cancel the flight. Under these circumstances, think of the possibility of carrying less fuel or a lighter passenger. The table below sums up the weights and distances from the datum and the moment associated with the various parts of the helicopter and its payload. Item Weight (kg) Distance % datum

    (mm) Moment (kg.mm)

    Standard empty weight 280 -136 -38000 Passenger Mpax 606 Mpax x 606 Useable fuel (0.7 kg/l) Mfuel -170 Mfuel x 170

    The solo pilot must weigh at least 50 kg. Below this weight the rear balance limit is exceeded. Below this weight, ballast must be added to maintain an equivalent of 50 kg. minimum on the passenger seat.. The maximum weight of the solo pilot is 125kg. THE SOLO PILOT MUST IMPERATIVELY TAKE THE LEFT HAND SEAT !

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    6.4 INDIVIDUAL WEIGHT SHEET

    INDIVIDUAL WEIGHT SHEET (to be completed and retained in this manual) DYNALI HS

    DYNALI H3 EASYFLYER DATE N AIRFRAME (s/n) REGISTRATION

    OWNER NAME ADDRESS

    PLACE OF WEIGHING

    METHOD OF WEIGHING (specify : spring balance, scales, other),

    EMPTY WEIGHT The empty weight is the weight of a Dynali H3 helicopter empty but including the basic on-board equipment, - full engine oil - coolant liquid

    kg POSITION EMPTY CG % DATUM* at .. mm in front of wheel axles = ......... mm rear of axis of rotor mast

    *Datum = axis of rotor mast

    mm NOTES The empty CG measured at mm aft of the mast axis, i.e., forward of**, aligned with**, aft of** the standard CG of the H3 (located at 136 mm behind the mast axis) * *delete where not applicable

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    6.5 LATERAL BALANCE

    The Dynali H3 EasyFlyer is equipped with dual controls. Apart from solo flights, for which the pilot must be in the left hand seat, the Dynali H3 may be flown from the left or the right hand seat. In order to guarantee the easy piloting of the aircraft, the left hand side must always be heavier than the right hand side.

    SOLO PILOT MUS BE IN LEFT HAND SEAT MINIMUM WEIGHT IN SOLO : 50 KG TWO PEOPLE ON BOARD: PLACE HEAVIER PERSON IN LEFT HAND SEAT

    SOLO PILOT Maximum weight of solo pilot without ballast in right hand seat : 125 kg 125kg on the left corresponds to the limit of travel of the cyclic acceptable on the right to maintain the manoeuverability. Above 125 kg in the left hand seat, add ballast in the right hand seat corresponding to the weight of the pilot relative to 125 kg TWO PEOPLE ON BOARD The condition for balancing the aircraft to compensate for the thrust of the tail rotor is 13 kg more on the left hand seat (**) so that the rotor mast is vertical in hover. However the aircraft remains maneuverable, although listing. See Chapter 6, 6.3 (**) This explains the obligation for the solo pilot to take the left hand seat.

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    7 SYSTEMS

    7.1 GENERAL

    The purpose of this chapter is to introduce the pilot who has not assembled his Dynali H3 EasyFlyer to the various systems forming part of this helicopter. Further information can be found in the assembly manual. We advise all pilots to read through this in order to better understand the design and mechanics of the Dynali H3 EasyFlyer.

    7.2 AIRFRAME

    The Dynali H3 EasyFlyer a two seater single engine helicopter with a single main rotor of mainly metal construction and equipped with landing skids. The basic protective structure of the airframe is in welded tubular stainless steel tubes to provide maximum passive safety for the crew. The tail of the Dynali H3 EasyFlyer is made of aluminium tubing. Carbon external fairing in carbon is included but has no structural role. The fire partition is built of carbon fibre.

    7.3 UNDERCARRIAGE

    The undercarriage is made of aluminium and stainless steel tubing. It is of shock absorbing design with two legs designed for progressive deformation on each side (passive safety). The two black balls located in the front are necessary to avoid vibration. They also provide protection in the case of landing on uneven surfaces such a ploughed fields. The two central tubes of the skids (that bond left and right side) can bend in a curve, giving some flexibility to the undercarriage. Deformation of the central tubes can not exceed 17mm.

    7.4 MAIN ROTOR

    The blades are made of extruded high resistance aluminium. As a safety precaution, their service life is provisionally limited to 500h. A mark is traced on the upper side of the blade to check for possible permanent elongation of the aluminium. They are held by stainless steel sheets and aluminium blade roots. Four stop bearings with oblique contact allow for the blade root to oscillate to set the pitch. They are over-dimensioned and can support excess speed up to 600RPM. These bearings oscillate very little and the bearing balls, over the long term can make traces in their seating, causing shimmy in the cyclic pitch control. They should be replaced as soon as the shymmi can be strongly felt.

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    The ball joints of the blade rods have a little play ; they should be greased with traditional grease. The seven bolts and the two blade screws are set in position on a template. Dismounting them may cause misalignment.

    7.5 REAR (ANTI-TORQUE) ROTOR

    The rear rotor is equipped with four blades in order to keep a small diameter which provides for a greater degree of safety. The four blades are composed of carbon, held by blade roots which are not articulated. The blade roots are held in nylon bearings which rapidly develop play. This play does not affect the performance as the nylon bearings are held by stop bearings with flat rollers. In operation, the centrifugal force maintains the roots firmly in place which press uniformly on the whold crown of the bearings. Only the rollers of these bearings must be greased and all surplus grease is immediately evacuated by the 1kg of centrifugal force. The rollers dry and sometime corrode rapidly but no intervention is required as long as the pedals do not show stiffness. All that has to be done then is to dismantle, clean with gasoline and grease the corroded rollers without necessarily changing them.

    7.6 TRANSMISSIONS

    A drive pulley is bolted directly onto the transmission shaft at the exit to the engine. Eight vee belts transfer the movement to the upper pulley which houses the two freewheels. The shaft transmits the movement forward to the main rotor via the main transmission and to the rear rotor via a flector joint and then the rear transmission. The belts occasionally slap. This makes a metallic sound but is not damaging. The carbon fairing amplifies all mechanical noises. The long shaft which drives the rear rotor is supported by seven intermediate bearings in the tail tube. The main transmission gearbox (MTG) contains conic gearing with spiral teeth providing a single stage of reduction with splash lubrication. The large upper bearing in the main transmission gearbox may leak a little. This is not a problem as all precautions have been taken : sponge clean and watch the oil level. No intervention is required as long as the lip of the bearing flange fills up clearly. The conical spiral gearing of the main transmission gearbox is a part that wears out rapidly. The gearbox should be emptied regularly to filter the oil or renew it and also the caliper of the iron fillings on the magnetic plug should be surveyed. Every 400h, the main transmission gearbox should be exchanged for a new part in order to replace the conical gear and the bearings. The method to control the level can be found in chapter 303 of this assembly manual.

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    The rear transmission gearbox (RTG) also has a pair of conic gears with spiral teeth and splash lubrication. The entry and exit shafts are of stainless steel. It does not present any problem of wear.

    7.7 ENGINE

    Engine Rotax 912S / Rotax Turbo Cylinder capacity : 1350 cm / 1211cm3 Power : 100 CV / 115CV Exhaust : Dynali Rotax are one of the best engines in the world. However, Rotax does not guarantee its engines when thse are used in rotary wing aircraft. Precaution : the air vents on the carburetors must be well held as if they are pinched or blocked, large amounts of fuel leak through the air filters. Check the carburetor supports and the rubber hoses which may sometimes tear. Sensitive to green fuels, thanol destroys the carburetors. Some brands of fuel generate engine Knock and then destruction of the pistons in a very short time.

    7.8 FLIGHT CONTROLS

    Standard equipment includes dual controls. The cyclic on the passenger side can be folded away. The rules only allow dual control during training flights with instructor. All controls operate through control rods with ball joint endings. The flight controls of the Dynali H3 EasyFlyer operate in the same manner as those of most other helicopters. The cyclic and the collective control the pitch of each blade via the cyclic plate. Warning : the controls are very sensitive, this being why we recommend frictions on the three controls. Fully unscrew and re-screw 11 threads the lateral frictions and 6 threads the pitch friction. The collective is also of the classical type with a throttle twist grip. A correlator activates the throttle in relation to the collective position but a fine adjustment is still necessary using a servo-motor called a governor. The governor operates on the pilots throttle control and gathers its information from the probe of the rotor rev-counter. The friction of the collective lever is set by the degree of tightening of its attachment bolt. Takeoff with a failed governor is possible but the pilot must control the throttle himself to maintain 100% rotor RPM until after landing. The pedals act on the pitch variator lever of the rear rotor through two teleflex cables. Note : The teleflex cables do not bear any particular stress. A system of counter rotating pinions neutralises the pushing effort on the pedals.

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    7.9 ENGINE CLUTCH DRIVE BELTS

    The engine is mounted on shock blocks and suspended by a two rods which act as a clutch by lowering or raising the engine. The tension in the drive belts is provided by the two suspending rods and an electric jack which moves them. Dynali exhaust pipes are positioned on each side of the engine, these are not interconnected.

    7.10 FUEL CIRCUIT

    Each carburettor is fed directly by gravity. The two fuel taps each have a filter. It is advised to keep both fuel taps permanently open to observe the condition of the fuel circuit and the carburetor needles. The central tank has a capacity of 56L of gasoline.

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    8 HANDLING AND MAINTENANCE

    8.1 GENERAL

    This chapter describes the recommended procedures for the handling and maintenance of the Dynali H3 Easyflyer helicopter. Any person designated by the assembler of the kit or the new owner is authorised to perform maintenance operations, under the authority of the owner. We ask that each new owner contacts us and remains in close contact with Dynali or his local official distributor in order to receive the latest service bulletins concerning the Dynali H3 EasyFlyer. In the event of sale of his helicopter, the original assembler should inform the new owner of the manuals that he requires and suggest that he contact Dynali or the authorised distributor. Furthermore, the internet site www.dynali.com regularly shows new information made available to everybody. Under the regularions, the responsibility for the maintenance of a micro-might helicopter lies exclusively with the assembler / proprietor / operator of the helicopter. He must ensure that servicing is performed in compliance with the Maintenance Manual and the recommendations of Dynali SPRL. All limits, procedures, safety practices, part life cycles and total time expiry life cycles shown in the present manual are considered as mandatory.

    8.2 OBLIGATORY DOCUMENTS

    The following documents must be permanently left aboard the aircraft :

    1. Airworthiness Certificate 2. Registration Certificate 3. Radio operation certificate (if the helicopter has a radio) 4. Insurance Certificate 5. Weight sheet 6. Checklists 7. Flight manual

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    8.3 MAINTENANCE

    All maintenance work must be noted in the appropriate log book which must contain, at the least, the following information :

    - Date of performance of the work. - Number of hours flight logged. - Description of the work and remarks. - Name of the technician. - Superviser signature. - Telephone contact with Dynali Helicopter Company which is always possible, if

    any doubt subsists if there is any doubt concerning the work.

    8.4 MAINTENANCE AND PROCEDURES

    Dynali SPRL requires that the following inspections should be made :

    1) Daily inspections described in 4.1. 2) Every 10h. The pilot may perform this after having followed a training course

    with an authorised distributor. 3) Every 50h. The pilot may perform this after having followed a training course

    with an authorised distributor. 4) Every 100h. The pilot may perform this after having followed a training course

    with an authorised distributor. 5) Every 250h. The pilot may perform this after having followed a training course

    with an authorised distributor 6) Every 500h. This operation must be performed by an authorised distributor. 7) Every 1000h. This operation must be performed by an authorised distributor. 8) Every 2000h. This operation must be performed by an authorised distributor.

    Dynali SPRL recommends a full inspection of the machine every 12 months. This must be performed by an authorised distributor. Furthermore as from the 50th hour, the operation to be undertaken is, in fact, a series of operations. For example, after 2000 hours, all the maintenance operations included in the 10, 25, 50, 100, 250, 500, 1000 and 2000h. checks must be performed.

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    MAINTENANCE TRACKING SHEET Machine :

    Registration Serial N Delivery date Observations

    Owner :

    Name First name Address Telephone

    Maintenance calendar:

    Machine hours Comments 25 50 75

    100 125 150 175 200 225 250 275 300 325 350 375 400 425 450

    etc.

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    10 HOURS SERVICE

    The following service procedure must be performed after every 10 hours flight

    !"#$%&'()&&CANOPY Check the hinges, the pitot tube the canopy and the wool thread &CABIN SHELL Check the rear attachments and the sealing tape &ROTOR Check the rotor blades, the blade tips, check absence of leaks at

    the blade roots, the free swing over of the blades and the swing over stop on the nylon ring Test the free movement of the pitch rods

    &CYCLIC PLATE Test ball joints

    Check the bellows Test the free movement of the control rods

    &DOUBLE SCISSORS Check for cracks on the drive collar

    Check that the ball joint extensions are not bent &

    ENGINE Check absence of leaks under engine Check the 3 springs on the carburettors (fuel, choke, attachment) Check attachment of air vent tube Check attachment of air filters Check for leaks in drain dishes Check for cracks in drain dishes Check the 2 x 4 exhaust springs Check no cracks on exhaust

    &

    RADIATOR Check no leaks on panels Check attachment lugs collars and rivets Check for leaks in water and oil hoses

    &FUEL TANK Check that bottom of tank is dry

    Check that taps are not open Check that there is no water in the filters

    &MAIN TRANSMISSION Check that there are no oil leaks

    Check the thermal tabs &

    TRANSMISSION SHAFT Check the bearings Check that there is no play Check that there is no leak of grease Check the three blocking collars (pulley and support bearings) Check the rubber sleeve

    &BELTS AND PULLEYS Check the state of the drive belts

    Check the wear of the pulleys &

    FLECTOR Check the state of the flector &TAIL TUBE Check the attachment of the tail tube

    Check the attachment plates Check attachment ball-joints for the support struts Check attachments for the teleflexes Check the upper strut attachments

    &TAIL STABILISER Check attachment collars

    Check support struts Check stabiliser

    &TAIL ROTOR SURROUND

    Check attachment lugs Check for cracks in collar

    &REAR ROTOR TRANSMISSION GEARBOX

    Check thermal tag Check oil level Check for oil leaks Check the six lugs of the variator and the lock-wire Check state of teleflex Manually check the travel of the mechanism

    &REAR ROTOR BLADES Check for cracks and chipping &OIL LEVEL Check &WATER LEVEL Check level in the expansion tank &

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    25 HOURS SERVICE

    The following service procedure must be performed after every 25 hours flight

    !"#$%&'()&&& Part N Designation Operation OK 1 000 MAGNETIC CHIP DETECTOR Check operation and clean. &2 220 VENTRAL SAFETY BELT Check Loctite 638 in the buckles &2 312 CARBURETORS Synchronise carburetors (the 2

    butterfly axles horizontal with wide open throttle)

    &1 205115 COMPRESSION PLUG M45x1,5 Chek &1 205120 NUT M45x1,5 Check condition and check tightened &2 207500 ROCKER ARM BEARING Swing over the rotor and check the

    absence of jerks &

    2 209040 FRICTION WASHERS NYLON Check condition and check free. &1 216020 JUBOFLEX Check &1 220950 FINISHING JOINT Check &1 304360 MAIN TRANSMISSION SHAFT Check, test vertically, check no play

    where is connects to the MTG entry shaft.

    &8 304450 GATES QUAD POWER DRIVE BELT Check tension and belts alignment.

    Service life +/- 100h. &

    2 304520 SUPPORT BEARING STOPPER Check play, clean, grease. &2 304550 KEY SCREW M8x24,5 Check, grease if needed, re-tight is

    necessary. &

    2 304590 BELT GUIDE RIGHT Check (cracks are possible). &1 305045 PLASTIC SHEET COVER Check wear on the mast. &1 305100 MAST STOP TUBE Check it turns with difficulty (must

    keep contact with the upper bearing) &

    1 306010 SCISSORS GUIDE Check no deformation &1 307010 PAIR OF BLADES Check bonding at blade tip &1 309070 ATTACHMENT OF COLLECTIVE

    BRACER Check &

    1 309270 SANDOW TRIM GAZ Check carefully &1 312300 RADIATOR WATER/OIL Check and clean the grille &2 312301 OIL CONNECTOR D12 Check. If any leaking, replace 2x2 o-

    rings. &

    2 312440 RADIATOR PIPE If water leakage replace o-ring &2 314510 FUEL TANK ATTACHMENT COLLAR Check no cracks &2 315210 END BALL JOINT M10 Check &1 315270 MAIN TAIL COLLAR Check &1 315400 TAIL TUBE Check &4 315401 CURVED ATTACHMENT PLATE Check &1 319315 TAIL SURROUND COLLAR Check for possible cracks &2 320450 LEFT INTERIOR LATCH Check for possible deformation &2 320820 CABIN TWISTED STRIP Check &2 320900 SEAT Check inflation of cushion &&&&&&&

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    50 HOURS SERVICE

    The following service procedure must be performed after every 50 hours flight

    !"#$%&'()&&& Part N Dsignation Opration OK 1 000 MAGNETIC CHIP DETECTOR Check operation &1 317 REAR TRANSMISSION GEARBOX Check small pinion teeth &2 202020 SHOCK BLOCK (SILENTBLOC) Check condition and deformation &1 203170 MAGNETIC CHIP DETECTOR Check and clean &1 203410 CONIC GEARING Check play (alternate movements of

    the flector). Note the play in the grooves of the main transmission shaft.

    &2 204371 O-RING D30 (MAIN SHAFT) Check + move aside to check

    condition of brass ring (304310) &

    1 205080 ROTOR TILT STOP RING Check tilt stop movement &8 206030 BAR BEARING 626-2RS Check condition and play &2 206353 BALL JOINT SALKB 10F (LEFT) Grease &2 206354 BALL JOINT SAKB 10F (RIGHT) Grease &1 210122 CABLE THIMBLE Check that the cable can not slide

    out of the cable thimble. &

    1 210132 THREADED CABLE TIGHTENER Check that the cable tightener is tight

    &1 210360 TOOTHED DRIVE BELT Check tension &4 218220 STOP BEARING 51104 Check and grease if necessary &6 218430 NYLON CUP ATTACHMENT TELEFLEX Check screws are tightened &1 219030 HORIZONTAL STABILISER Check for cracks in the attachment

    lugs and collars. Check the nylon supports

    &2 219085 AFTERWARD COLLAR STABILISER Check &1 220520 NYLON WASHER Check & 303010 ORION OIL SAE 75/90 Drain and filter &1 305030 STOP BEARING 7208-B-2RS Check condition and grease if

    necessary. &

    1 306140 BELLOWS 3 FOLD Inspect and check for cracks &1 309070 ATTACHMENT TAB FOR COLLECTIVE

    STIFFENER Check &

    2 310120 DOUBLE THROTTLE / CHOKE CABLE Check that the cables move freely in the sleeves

    &1 319080 FORWARD COLLAR STABILISER Check &2 319420 VERTICAL STABILISER Check &&&&&&&&&&&&&

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    100 HOURS SERVICE

    The following service procedure must be performed after every 100 hours flight

    !"#$%&!'(()!!! Part N Dsignation Opration OK 8 312 SPARK PLUGS Replace !1 312 ENGINE OIL FILTER Replace !4 312 SYNTHETIC MOTORBIKE RACING OIL Drain and replace !1 301000 UNDERCARRIAGE Inspect and check welds !1 301100 COMPLETE LANDING GEAR Inspect, check welds, and wear of

    the skids !

    1 307010 PAIR OF BLADES Check for the 1000mm mark on the upper wing surface. 1mm tolerance is accepted

    !4 311060 LEFT FOOT PEDAL Check welds !1 318100 REAR ROTOR HUB Check for possible cracks !2 320800 VENTRAL SAFETY BELT + BUCKLES Check for wear of strap !2 320810 ATTACHMENT BUCKLES Check buckles for wear !!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!

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    250 HOURS SERVICE

    The following service procedure must be performed after every 250 hours flight

    !"#$%&!'()*!!! Part N Designation Opeeration OK 1 000006 STAINLESS STEEL LOCKWIRE Replace !4 213 SWITCH ON/OFF 250V Replace !2 220 SEAT VELCRO Check attachment of seats !1 312 ENGINE REDUCER Check for possible wear !6 312 GLYCOL COOLANT (1L) Drain and Replace !1 312 THERMO SWITCH FAN SENSOR Replace !2 314 FUEL TANK STRAP Check and replace if worn !1 203410 CONIC GEARING Inspect !1 203470 SHAFT SMALL PINION Inspect !2 204330 FREE WHEEL TFS Inspect !1 205080 SWING OVER STOP RING Inspect !2 206353 LEFT BALL JOINT SALKB 10F Inspect !2 206354 RIGHT BALL JOINT OTULE SALKB 10F Inspect !6 212090 EXHAUST SPRING Replace !7 216050 REAR TRANSMISSION SHAFT

    SUPPORT BEARING Inspect via the orifices below the tube

    !7 216060 BEARING 6002 2RS C3 Replace !7 216065 CONICAL SLEEVE Replace !1 217250 OIL SAE 80W90 Drain and replace !2 218020 BEARING 61806 2RS Replace !1 218030 SMOOTH RING PCM Replace !4 218190 STOP PELLET Replace !4 218200 MUSHROOM BUSHING Replace !4 218220 STOP BEARING Replace !6 218350 VARIATOR GUIDE STUD Replace !2 218400 TELEFLEX 33C Disconnect and check !4 218410 TELEFLEX ATTACHMENT Check !1 301000 TUBULAR CHASSIS H3 Inspect welds !1 302010 ENGINE MOUNTS Inspect !1 303010 ORION SAE 75W90 OIL (main and rear

    transmissions) Replace !

    1 304310 BRASS RING Inspect !1 304320 O-RING (BRASS RING) Replace !1 304360 MAIN TRANSMISSION SHAFT Inspect and check for wear in

    grooves, clean and grease. !

    2 304371 O-RING (MAIN TRANSMISSION SHAFT) Replace !1 304560 O-RING (SHAFT ENTRY TO MTG) Replace !1 305070 ROTOR MAST AND ROTOR HEAD Inspect !1 306140 BELLOWS 3 FOLD Replace !1 306300 CENTRAL BALL JOINT GEH 40 TX3GE Replace !1 309200 THROTTLE AXIS Inspect !1 309270 SANDOW TRIM THROTTLE Replace !1 310100 GAS CORRELATOR Inspect !2 312090 EXHAUST HOOK Check wear !1 312300 RADIATOR WATER/OIL Replace !

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    500 HOURS SERVICE

    The following service procedure must be performed after every 500 hours flight

    2 312302 ATTACHMENT PLATE FOR OIL CONNECTOR

    Replace !4 312310 ATTACHMENT PLATE FOR RADIATOR Replace !1 314330 LOW FUEL PROBE Check ! 314331 ADJUSTMENT WASHER Check !2 315210 END BALL JOINT M10 Replace !1 318100 HUB FOR BLADE REAR ROTOR Inspect !!!!!!!!!"#$%&!'(()!!! Part N Designation Operation OK 1 OIL ATF + Slick 50 PTFE Drain and replace !1 000 FLEXIBLE TRANSPARENT SLEEVE D5 Replace !1 000 FLEXIBLE TRANSPARENT SLEEVE D6 Replace !1 000 FLEXIBLE TRANSPARENT SLEEVE D8 Replace !4 000 RIGID NYLON SLEEVE Replace !1 217 REAR TRANSMSSION GEARBOX Replace !1 203340 SPACER (BOTTOM OF MAST) Replace !2 204330 FREEWHEEL TFS Replace !2 206353 BALL JOINT SALKB 10F LEFT Replace !2 206354 BALL JOINT SALKB 10F RIGHT Replace !2 207500 BEARING DE BALANCIER NKXR 35Z Replace !1 208120 BALL JOINT SAKAC 10M Replace !3 208130 BALL JOINT SAKAC 8M (CONTROL RODS) Replace !1 208130 BALL JOINT SAKAC 8M (CHASSIS) Replace !2 209290 BALL JOINT SAKAC 6M Replace !1 209350 BALL JOINT SAKAC 8M Replace !3 209350 BALL JOINT SAKAC 8M (UPPER) Replace !1 210009 ATTACHMENT PLUG THROTTLE/MTG Check !1 210360 DRIVE BELT Replace !4 211010 SUPPORT BEARING FOR PEDALS Inspect, check play and grease !1 216020 JUBOFLEX (FLECTOR JOINT) Check !3 217020 BEARING ICOS D1804 Replace !1 217030 BEARING 6205 Replace !1 217080 PROPELLOR SHAFT AND PINIONS Replace !1 217300 THERMAL TAG Replace !4 218250 TAIL ROTOR BLADE ROOT Replace !1 219085 REAR COLLAR HORIZONTAL TAIL Replace !1 302000 ROTAX 912S ENGINE Inspect !8 304450 GATES DRIVE BELTS SPA1000 Replace !1 307010 PAIR OF BLADES Replace !

    2 312302 ATTACHMENT PLATE FOR OIL CONNECTOR

    Replace !4 312310 ATTACHMENT PLATE FOR RADIATOR Replace !1 314330 LOW FUEL PROBE Check ! 314331 ADJUSTMENT WASHER Check !2 315210 END BALL JOINT M10 Replace !1 318100 HUB FOR BLADE REAR ROTOR Inspect !!!!!!!!!"#$%&!'(()!!! Part N Designation Operation OK 1 OIL ATF + Slick 50 PTFE Drain and replace !1 000 FLEXIBLE TRANSPARENT SLEEVE D5 Replace !1 000 FLEXIBLE TRANSPARENT SLEEVE D6 Replace !1 000 FLEXIBLE TRANSPARENT SLEEVE D8 Replace !4 000 RIGID NYLON SLEEVE Replace !1 217 REAR TRANSMSSION GEARBOX Replace !1 203340 SPACER (BOTTOM OF MAST) Replace !2 204330 FREEWHEEL TFS Replace !2 206353 BALL JOINT SALKB 10F LEFT Replace !2 206354 BALL JOINT SALKB 10F RIGHT Replace !2 207500 BEARING DE BALANCIER NKXR 35Z Replace !1 208120 BALL JOINT SAKAC 10M Replace !3 208130 BALL JOINT SAKAC 8M (CONTROL RODS) Replace !1 208130 BALL JOINT SAKAC 8M (CHASSIS) Replace !2 209290 BALL JOINT SAKAC 6M Replace !1 209350 BALL JOINT SAKAC 8M Replace !3 209350 BALL JOINT SAKAC 8M (UPPER) Replace !1 210009 ATTACHMENT PLUG THROTTLE/MTG Check !1 210360 DRIVE BELT Replace !4 211010 SUPPORT BEARING FOR PEDALS Inspect, check play and grease !1 216020 JUBOFLEX (FLECTOR JOINT) Check !3 217020 BEARING ICOS D1804 Replace !1 217030 BEARING 6205 Replace !1 217080 PROPELLOR SHAFT AND PINIONS Replace !1 217300 THERMAL TAG Replace !4 218250 TAIL ROTOR BLADE ROOT Replace !1 219085 REAR COLLAR HORIZONTAL TAIL Replace !1 302000 ROTAX 912S ENGINE Inspect !8 304450 GATES DRIVE BELTS SPA1000 Replace !1 307010 PAIR OF BLADES Replace !

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    1000 HOURS SERVICE

    The following service procedure must be performed after every 1000 hours flight

    1 309345 BALL JOINT SAKAC 10Mc16 Replace !1 310010 ATTACHMENT PLUG CHOKE/MTG Check !1 319080 FRONT COLLAR HORIZONTAL TAIL Replace !2 319420 VERTICAL STABILISER Replace !!!!!!!!!!!!!!!!!!!!"#$%&!'((()!!! Part N Dsignation Opration OK 1 000 GATES HEATER D25 Replace !1 000 GATES MULTICARBURANT D8 Replace !1 000 GATES MULTICARBURANT D12 Replace !4 000 NYLON HOSE ROOT Replace !1 000105 RIGID NYLON SLEEVE L2000 Replace !1 213 RED CHARGING LIGHT Replace !3 213 ORANGE WARNING TRANSMISSIONS /

    LOW FUEL Replace !

    2 213 GREEN LIGHT FANS Replace !1 213 WARNING LIGHT & KLAXON LOW RPM Replace !1 213 SOCKET LIGHT & KLAXON LOW RPM Replace !1 213 INVERSOR SWITCH CLUTCH Replace !2 213 AUTOMATIC BREAKER 5A Replace !2 213 AUTOMATIC BREAKER 25A Replace !2 213 RELAY 40A FANS Replace !1 213 CONDENSATEUR 22000 F Replace !1 312 ALTERNATOR VOLTAGE REGULATOR Replace !1 000400 PROBE T EXT Replace !2 202020 ENGINE SHOCK BLOCK Replace !2 202020 SHOCK ABSORBER (SILENTBLOC) Replace !4 205020 SLEEVE SCREW Replace !2 205090 BEARING RING IR 30/35/30 Replace !8 206030 STRIP BEARING 626 2RS Drain and replace !

    1 309345 BALL JOINT SAKAC 10Mc16 Replace !1 310010 ATTACHMENT PLUG CHOKE/MTG Check !1 319080 FRONT COLLAR HORIZONTAL TAIL Replace !2 319420 VERTICAL STABILISER Replace !!!!!!!!!!!!!!!!!!!!"#$%&!'((()!!! Part N Dsignation Opration OK 1 000 GATES HEATER D25 Replace !1 000 GATES MULTICARBURANT D8 Replace !1 000 GATES MULTICARBURANT D12 Replace !4 000 NYLON HOSE ROOT Replace !1 000105 RIGID NYLON SLEEVE L2000 Replace !1 213 RED CHARGING LIGHT Replace !3 213 ORANGE WARNING TRANSMISSIONS /

    LOW FUEL Replace !

    2 213 GREEN LIGHT FANS Replace !1 213 WARNING LIGHT & KLAXON LOW RPM Replace !1 213 SOCKET LIGHT & KLAXON LOW RPM Replace !1 213 INVERSOR SWITCH CLUTCH Replace !2 213 AUTOMATIC BREAKER 5A Replace !2 213 AUTOMATIC BREAKER 25A Replace !2 213 RELAY 40A FANS Replace !1 213 CONDENSATEUR 22000 F Replace !1 312 ALTERNATOR VOLTAGE REGULATOR Replace !1 000400 PROBE T EXT Replace !2 202020 ENGINE SHOCK BLOCK Replace !2 202020 SHOCK ABSORBER (SILENTBLOC) Replace !4 205020 SLEEVE SCREW Replace !2 205090 BEARING RING IR 30/35/30 Replace !8 206030 STRIP BEARING 626 2RS Drain and replace !

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    2000 HOURS SERVICE

    Contact the manufacturer for information concerning the 2 000 hour check procedures.

    1 208040 INTER BEARING SPACER Replace !2 208050 BEARING 608 2RS Replace !1 208100 LEFT PITCH BELLCRANK (WITH

    TIGHTENED BEARING) Replace !

    1 208105 RIGHT PITCH BELLCRANK (WITH TIGHTENED BEARING)

    Replace !2 208160 BEARING 6000 2RS Replace !1 208170 INTER BEARING SPACER Replace !1 213207 CONTACT KEY 40A Replace !1 213460 RPM ROTOR SENSOR Replace !7 216050 REAR TRANSMISSION SHAFT

    SUPPORT Replace !

    7 216060 BEARING 6002 2RS Replace !7 216065 SPLIT CONIC SOCKET Replace !1 218010 REAR ROTOR ROTATING VARIATOR Replace !4 218240 BLADE ROOT WELL Replace !4 218250 BLADE ROOT Replace !1 219060 SUPPORT FOR TAIL SURROUND Check !1 304360 MAIN TRANSMISSION SHAFT Replace !1 305030 STOP BEARING 7208-B-2RS Replace !1 305070 ROTOR MAST AND ROTOR HEAD Replace !2 306090 BALL JOINT SAKAC 8M Replace !2 310120 THROTTLE / CHOKE / CABLE Replace !1 312060 COLLAR OIL TANK Replace !4 312303 O-RING D12 Replace !1 312410 FAN PANEL Replace !2 312445 O-RING D30 Replace !1 312510 GATES HOSE D25 L630 (UPPER FORWARD) Replace !1 312512 GATES HOSE D25 L675 (BAS/ARRIRE) Replace !2 312515 HOSE SPRING D25 L300 Replace !1 312720 WATER TANK 0,5L ROTAX Replace !2 314030 CARBURETOR COLLECTOR Replace !2 314040 CARBURERTOR COLLECTOR

    ATTACHMENT PLUG Replace !

    1 314330 LOW FUEL SENSOR Replace ! 314331 ADJUSTEMENT SPACER Replace !1 314500 FUEL TANK Replace !2 314550 FUEL SELECTOR Replace !1 314560 FUEL LEVEL PROBE Replace !2 315210 END BALL JOINT M10 Replace !2 315211 SPACER D10 Replace !1 319055 TAIL ROTOR SURROUND Check !1 319315 TAIL SURROUND COLLAR Check !!

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    ADDITIONAL ADVISES - Keep up your speed and never remain hanging on your engine, it may fail. - Never fly in a helicopter which is not adjusted for autorotation. - To keep in training, descend as often as possible in autorotation, stopping short of the ground. - Always watch your MAP. This instrument will tell you the reserve power available ; before initiating any manuver, check that you have at least 1" inHg MAP in reserve. - Do not continue with a landing if the LOW RPM warning is alight. - Check that the engine runs smoothly at idle. - The throttle sandow cord must be kept in good condition. WARNING : SOLO PILOT LEFT HAND SEAT. MANOEUVRES CLOSE TO GROUND AND TAKEOFFS AND LANDINGS SHOULD BE PERFORMED WITH THE GOVERNOR SET AT 5800 TO PROVIDE MORE POWER. IF YOU HAVE, IN CLIMB OR ON FINAL, EXCEEDED THE AVAILABLE POWER, THE ROTOR WILL LOSE RPM. THE WORST REACTION IS TO FURTHER RAISE THE COLLECTIVE, WHICH WILL EVEN FURTHER REDUCE THE RPM. THE CORRECT REACTION IS TO LOWER THE COLLECTIVE AND OPEN THE THROTTLE TO THE LIMIT (THE GOVERNOR WILL DO THIS), THEN ALLOW THE HELICOPTER TO LOSE A LITTLE MORE HEIGHT WHILE AWAITING FOR THE RPM TO INCREASE. Special precautions : Take the time to get to know your H3 ; carrying a passenger increases the difficulty of managing the power. 30 hours of solo flight is recommended for beginners and 5 hours for experienced pilots before carrying a passenger.

    Beware of any stiffening in the controls ; cyclic plate, freezing or hardening of the grease on the mast. Rapid complete blockage can occur in these cases. In the pedals, the grease hardens in the stop bearings of the rear rotor blades. Never force the controls but fix the problem.

    Manuvering on the ground ; at the rear rotor, do not force the blades as doing so may mis-align them. Do not use force on the rear rotor surround. The manoeuvering wheels should only be used on hard and smooth ground. The machine should not be moved by pushing on the canopy or the tail stabiliser.

    Parking ; restrain the rotor blades which flap in the wind. The shocks leave traces of impacts on the balls in the bearings.

    Transporting the helicopter on a trailer ; without main rotor blades or support the rearward blade. Possibly, on a short trip, let the blades hang and prevent flapping by using straps left fairly loose.

    Flight in hard weather condition : heavy rain may damage main rotor blades.

    Turbo : takeoff or landing in long grass absolutely prohibited on account of fire risk.

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    WARRANTY

    - Although your H3 will have been flight tested, these tests are of limited duration and it is possible that minor adjustments may be required during the first few flight hours following release of the machine. The user must ensure that these adjustments are made.

    - Estimated service life of parts is not a guarantee that certain parts may not show wear earlier than predicted.

    - The helicopter is supposed to be used according to the manual and within its flight envelope.

    - There may never be more than two persons on board.

    - The pilot is understood to be capable of landing with engine out. He is understood to avoid all use outside the recognized flight envelope.

    - Dual controls should be removed if there is not an instructor giving training on board.

    - Warranty of 2 years or 200 hours and :

    - This warranty only covers parts. - The warranty does only covers parts which are assembled in the rules of the art

    and subject to normal usage. - The warranty does only covers parts that have been serviced logically and in

    compliance with the maintenance manual. - The warranty does not cover the use of the helicopter in destructive environments

    which may cause premature wear (sand, airborne salt, heavy rain, hail or other). - The warranty does not cover any use in extreme conditions, these including excess

    RPM, heavy landings, overload, road or water transport in poor conditions or heavy manuvres on the ground. The handling wheels can only be used on hard and smooth ground. No force may be used on the canopy or the tail-plane.

    - To benefit from the warranty, (and for his own safety) the user has the obligation of keeping up to date the AIRCRAFT LOGBOOK, indicating the flight hours, comments and all technical operations regarding regular maintenance and/or repairs.

    - The warranty will not apply to the consequential damage where a part is found to be defective and continued use causes further damage (e.g. fuel or coolant leak, overheating of engine or transmission, slipping drive belts, noise in a bearing unusual vibration, etc).

    - The engine is not covered by the warranty.

    - The H3 will evolve over time and improvements will certainly be incorporated. Incorporation of such improvements is not covered by warranty and will be subject to acceptance of an estimate.

    - Regarding the after sales service, solution of technical problems will be invoiced if the cause of the problem is due to a factor not related to the original assembly of the helicopter or arises from inappropriate use or lack of vigilance on the part of the user.