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FLIGHT MANUAL            

DYNALI HELICOPTER COMPANY

              Edition N°3  

DYNALI H2S                                                                                                        January 2012 
__________________________________________________________________________________ 
 

 

14

 

 

1.1.

 

 CHARACTERISTICS AND PERFORMANCE 

Dimensions 

Main rotor  - Diameter ................................................................................... 7,16 m 
Number of blades  ................................................................................................. 2 
Anti-torque rotor - Diameter ............................................................................ 0,8 m 
Number of blades  ................................................................................................. 8 
Fuselage length ............................................................................................ 6,23 m 
Overall length (including reach of main rotor) ............................................... 7,95 m 
Height............................................................................................................ 2,58 m 
Undercarriage width ....................................................................................  2,00 m 
Cabin interior width ....................................................................................... 1,45 m 

 

Power plant  

Engine........................................................................................... Subaru DS EJ25 
Capacity  ................................................................................................... 2500 cm

³

 

Max power output ........................................................................................ 180 HP 
Hourly fuel consumption ................................................................................ 27 L/h 
Total fuel capacity ............................................................................................. 90 L 
Useable fuel capacity..................................................................................... 87,5 L 
Unusable fuel capacity..................................................................................... 2,5 L 

 

Performance 

Autonomy at 27L/h.................................................................. ...................... 03h10 
Practical useable ceiling ..................................3500 / 4000 m ........ 11500/13150 ft 
VNE.......................................................................... 190 km/h ...................... 102 kt 
Cruising speed ............................................... 140 à 165 km/h ............... 75 to 90 kt 
Rate of climb (dependent on payload) …150 to 300m/min……...500 to 1000ft/min 

 

1.2.

 

 DESCRIPTIVE DATA

 

Main rotor  

Semi-rigid type, on teetering hinge, without

 

trailing articulations

.

 

Number of blades................................................................................................... 2 
Diameter ....................................................................................................... 7,12 m  
Constant blade chord.................................................................................. 0,195 m 
Blade tortion......................................................................................................... 6° 
Blade mass ..................................................................................................... 12 kg 
Blade tip speed at 100% of nominal capacity ....................... 735 km/h at 530 RPM 

 

Rear or anti-torque rotor  

Rigid type, no flapping articulations, fully housed 
Number of blades................................................................................................... 8 
Diameter  .................................................................................................... 0,840 m 
Surface area of disc ...................................................................................0,554 m

²

 

Constant blade chord.................................................................................. 0,055 m 
Blade twisting....................................................................................................... 5° 
Mass of blade.................................................................................................... 78 g 
Blade tip speed at 100% of nominal capacity ..................... 608 km/h at 3833 RPM 

Содержание H2S

Страница 1: ...0 rue de la science 1400 Nivelles Belgique Tel 32 0 67 55 29 98 Fax 32 0 67 84 05 31 Mail info dynali com _________________________________________________________________________ FLIGHT MANUAL Kit helicopter Ref DYNH2S 01 01 T01 ...

Страница 2: ...y Nivelles Belgium This document is protected by copyright All associated rights in particular those of translation reprinting web transmission reproduction by photo mechanical or similar means and storing in data processing facilities in whole or part are reserved Dynali Helicopter Company 10 Rue de la Science 1400 Nivelles Belgium Tel 32 0 67 55 29 98 Fax 32 0 67 84 05 31 E mail info dynali com ...

Страница 3: ...ight manual is dependent on the punctuality with which it is updated The signature of the person responsible for the assembly of the kit provides a guarantee of updates for himself and for other users The composition of the manual is given in the list of current pages RECORD OF REVISIONS REVISIONS INCORPORATED number dated on by signature 00 Original Edition January 2009 01 July 2010 02 January 20...

Страница 4: ...at all pilots must constantly bear in mind A helicopter is by its nature a capricious and unstable machine which is subject to both the laws of the air and of physics Furthermore its mechanical components comprise a total chain which is both complex and precise It requires care and maintenance Please study carefully the specific characteristics and the recommendations which follow These are derive...

Страница 5: ...t Speed both in climb and cruise at over 60kts always above VPM In the event of a reduction in rotor RPM lower the collective immediately and increase fuel flow Auto rotation training should be undertaken over a known surface and under favourable conditions mass light headwind temperature If you are flying solo and unless you are undergoing instruction by a Dynali H2S qualified instructor limit au...

Страница 6: ...s reduced by half Accidents are always the consequence of an accumulation of circumstances All possible sources of failures must be studied with an instructor OTHER RISK FACTORS With a heavy payload limitations are more restricted Wind shifts and other aerial phenomena must be taken into account The vortex danger descending too fast and catching up with your own turbulence The rotor operates in tu...

Страница 7: ...ast possible power To be learned by heart In case of engine failure lower the collective to the limit use the left pedal to avoid a yaw to the right attain safe speed as quickly as possible and a trajectory which will bring you to a safe landing spot During descent take care to manage your rotor RPM Flare out to stationary position followed by applying pitch control input one or several times to s...

Страница 8: ..._____________________________________________________________ 8 To avoid doubt when to increase or decrease fuel flow MORE FINGERS MORE FUEL meaning the side of the throttle grip where the four fingers are placed LESS FINGERS LESS FUEL meaning the side of the throttle grip where the thumb is placed ...

Страница 9: ...LIMITS ON THE DS25 ENGINE 22 2 10 LIMITS RELATING TO OIL 22 2 11 LIMITS RELATING TO FUEL 23 2 12 MARKINGS ON ENGINE INSTRUMENTS 23 2 13 MASS AND BALANCING LIMITS 24 2 14 LIMITS ON IN FLIGHT MANŒUVRES 24 2 15 LIMITATIONS ON TAKEOFF 25 2 16 LIMITATIONS ON LANDING ON SLOPES 26 2 17 LIMITATIONS ON LOAD FACTORS 26 2 18 LIMITATIONS IN CASE OF FAILURE OF GOVERNOR 27 2 19 COCKPIT PLACARDS 27 CHAPTER 3 EME...

Страница 10: ...CT 46 5 5 CEILING FOR HOVER OUTSIDE GROUND EFFECT 47 5 6 DISTANCE ALTITUDE RATIO USING AUTOROTATION 48 5 7 HEIGHT SPEED DIAGRAM 49 5 8 NOISE LEVEL 50 CHAPTER 6 MASS AND BALANCE 51 6 1 GENERAL 52 6 2 MASS AND BALANCE 52 6 3 HELICOPTER LOADSHEET 58 6 4 LATERAL BALANCING 59 CHAPTER 7 SYSTEMS 61 7 1 GENERAL 62 7 2 CABIN SHELL 62 7 3 UNDERCARRIAGE 62 7 4 MAIN ROTOR 62 7 5 REAR TURBINE OR ANTI TORQUE RO...

Страница 11: ...___________________________________________ 11 CHAPTER 1 GENERAL 1 1 CHARACTERISTICS AND PERFORMANCE 1 2 DESCRIPTIVE DATA 1 3 ABREVIATIONS AND DEFINITIONS MISCELLANEOUS 1 4 ABREVIATIONS AND DEFINITIONS PERFORMANCE 1 5 ABREVIATIONS AND DEFINITIONS MASS AND BALANCING 1 6 ABREVIATIONS AND DEFINITIONS CONVERSION TABLES ...

Страница 12: ...FLIGHT MANUAL DYNALI HELICOPTER COMPANY Edition N 3 DYNALI H2S January 2012 __________________________________________________________________________________ 12 ...

Страница 13: ...4 Generator charge indicator 5 Low RPM indicator 6 Low Fuel indicator 7 Engine Rotor dual RPM 8 Chip detector MTG 9 Chip detector RTG 10 FAN 1 11 FAN 2 12 Vertical speed indicator 13 Altimeter 14 External T 15 Coolant liquid T 16 Free swtich 17 Free switch 18 Free switch 19 Free switch 20 Transponder 21 Free fuse 22 Free fuse 23 Instruments 24 Engine 25 Fuel pump 1 26 Fuel pump 2 27 Fan 1 28 Fan 2...

Страница 14: ...l capacity 87 5 L Unusable fuel capacity 2 5 L Performance Autonomy at 27L h 03h10 Practical useable ceiling 3500 4000 m 11500 13150 ft VNE 190 km h 102 kt Cruising speed 140 à 165 km h 75 to 90 kt Rate of climb dependent on payload 150 to 300m min 500 to 1000ft min 1 2 DESCRIPTIVE DATA Main rotor Semi rigid type on teetering hinge without trailing articulations Number of blades 2 Diameter 7 12 m ...

Страница 15: ... gear Reduction ratio rear transmission box N transmission shaft N rear rotor 1 2 Reduction ratio N engine N main rotor 9 83 1 N rear rotor N main rotor 7 09 1 Power plant Engine Subaru DS EJ25 Horizontally opposed flat 4 cylinders 4 stroke Electronic injection Liquid cooled Dry sump separate oil tank Cylinder capacity 2500 cm Maximum power output 180 HP Engine RPM at maximum power 5300 RPM Fuel R...

Страница 16: ... relative to the air in which the aircraft is flying Expressed in kilometers per hour or knots km h kts VNE Maximum safe speed Above this speed the aircraft will exceed its mechanical design limits Expressed in kilometres per hour or knots km h kts Vy ou Vpm Speed providing maximum power Speed which gives the optimum rate of climb Speed expressed in kilometers per hour or knots km h kts Rate of cl...

Страница 17: ...the axis of the main rotor as the datum Station Distance from the datum point to the centre of gravity of a component C G Centre of gravity Point from which the helicopter would balance if suspended Balancing Horizontal distance from the CG of the component concerned in relation to the datum point Balancing limits Distance limits from the CG for which use of the helicopter may be operated at a giv...

Страница 18: ...t 1852 m Statute Mile SM 1 SM 1609 m inch in 1 in 0 0254 m foot plur feet ft 1 ft 12 in 0 3048 m yard yd 1 yd 3 ft 0 9144 m Speed knot kts 1 kt 1 NM h 1 852 km h feet minute ft min 100 ft min 0 508 m s Weight kilogram kg 1 kg 2 2 lbs pound lbs 1 lb 0 454 kg Volume litre l 1 l 1 055 qt 0 264 USG millilitre ml 1 ml 0 001 l quart qt 1 qt 0 25 USG 0 9475 l US Gallon USG 1 USG 4 qts 0 833 ImpG 3 79 l I...

Страница 19: ...IRSPEED INDICATOR 2 6 LIMITS AND RELATIONSHIP BETWEEN ROTOR AND ENGINE REVS 2 7 MARKINGS ON ROTOR AND ENGINE REVS COUNTERS 2 8 VIBRATIONS AND HARMONICS 2 9 LIMITS ON THE DS25 ENGINE 2 10 LIMITS RELATING TO OIL 2 11 LIMITS RELATING TO FUEL 2 12 MARKINGS ON ENGINE INSTRUMENTS 2 13 MASS AND BALANCING LIMITS 2 14 LIMITS ON IN FLIGHT MANŒUVRES 2 15 LIMITATIONS ON TAKEOFF 2 16 LIMITATIONS ON LANDING ON ...

Страница 20: ... normal operation 2 3 ENVIRONMENTAL LIMITS Temperature Limits The Dynali H2S may be operated between 15 C and 45 C except in icing or super cooling conditions Wind limits Start up in steady wind Headwind 35 kts Crosswind 25 kts Tailwind 15 kts Start up in gusting wind Headwind 20 to 30 kts Crosswind 15 kts Tailwind 15 kts Note Always try to startup facing into the wind this is almost always possib...

Страница 21: ... ROTOR SPEEDS LIMITS ON ROTOR ENGINE OUTPUT ROTOR ENGINE RPM RPM Nominal output 100 530 5300 Low RPM with power 92 496 4960 Max RPM with power 5 min max 106 571 5710 Low RPM freewheel flight 92 500 0 Maxi RPM freewheel flight 112 600 0 Maximum rotor rate 112 600 RPM Maximum engine rate over speed limiter operates 106 5800 RPM 2 7 MARKINGS ON ROTOR AND ENGINE REV COUNTERS Rotor Rev Counter Rotor En...

Страница 22: ...e may differ from the indications provided for information purposes only in this flight manual Climatic conditions for engine start Minimum temperature 15 C Maximum temperature 45 C Output Maximum engine output engine speed limiter operates 106 5710 RPM Temperature of cooling fluid Caution range 70 to 75 C Nominal range 75 to 95 C Caution range 95 to 106 C Maximum 106 C Engine oil pressure Red war...

Страница 23: ... when there remains less than 10L of usable fuel or less than 20 minutes flying time before engine failure 2 12 MARKINGS ON ENGINE INSTRUMENTS Intake manifold pressure Green zone 20 to 29 5 in Hg Note as from 29 5 inHg manifold pressure in standard atmosphere at sea level the engine supplies maximum power and there is therefore a greater reserve of power should the unexpected occur Rotor rev count...

Страница 24: ...on IFR flight is prohibited with CNSK2 registration Aerobatics are prohibited Flight in icing or snowing conditions is prohibited Maximum altitude density for operation is 4000 m Transport capability 2 persons on board including pilot Solo flight the pilot must use the left hand seat Safety belts must be fastened both on an empty seat and on the pilotʼs seat Flight with one or both doors removed i...

Страница 25: ...because the rotor is exercising a pull Take care always to take off gently making sure that the skids leave the ground vertically There is a moment of risk during takeoff If the pilot fears a suction effect on the skids frost mud entangling vegetation he must take care to takeoff with first the left skid As soon as this detaches from the ground the pilot brings the cyclic back to the centre positi...

Страница 26: ...ravity is lower than the axis of its teetering hinge Furthermore under a low or negative load factor the helicopter is still pushed laterally by the tail rotor and rolls over even faster on account of its low mass Mast bumping only occurs on twin rotor blade helicopters It occurs when the load factor moves from a level of 1G towards 0G It is initiated as from 0 5G Mast bumping starts with a loss o...

Страница 27: ...LOT IN LEFT HAND SEAT THE HEAVIER OCCUPANT IN THE LEFT HAND SEAT MINIMUM MASS FOR SOLO PILOT 60 kg see Flight Manual MAXIMUM MASS FOR SOLO PILOT WITHOUT BALLAST 135 kg MAXIMUM TAKEOFF WEIGHT 700 kg VFR flight in daylight authorised Night flight and IFR flight prohibited Flight in icing conditions prohibited Warning this helicopter does not meet the conditions required for the issuance of a normal ...

Страница 28: ...mits VNE Altitudes below 1000 m 3000ft VNE with or without power 190 km h 102 kts Altitudes from 1000 to 1500 m 3000ft to 4500 ft VNE with or without power 180 km h 97 kts Above 1500 m 4500ft VNE decreases by12 km h 6 kts per 1000 m 3000 ft Flight with 1 or 2 doors removed is authorised Maximum speed 150 km h 80kts Doors may be opened in flight at or below 30 km h 16kts ...

Страница 29: ...T 3 4 ENGINE FAILURE AT LOW ALTITUDE 3 5 ENGINE FAILURE AT LOW ALTITUDE AND LOW SPEED 3 6 FAILURE OF GOVERNOR 3 7 BEST AERODYNAMIC EFFICIENCY DURING AUTOROTATION 3 8 ENGINE RE START PROCEDURE 3 9 EMERGENCY DITCHING WITHOUT POWER 3 10 EMERGENCY DITCHING WITH POWER 3 11 REAR TRANSMISSION OR ROTOR FAILURE DURING TRANSITION 3 12 REAR TRANSMISSION OR ROTOR FAILTURE DURING HOVER 3 13 ENGINE FIRE DURING ...

Страница 30: ...ine failure see the height speed diagram every possibility of succeeding in an auto rotation landing in the first case Altitude gives you time during which you can retain control of your manœuvres This time also enables you if things go wrong to select a better landing ground A FLARE PROVIDES THE GREATEST AMOUNT OF AUTO ROTATIVE ENERGY Auto rotation procedure see Chapter 4 3 2 ENGINE FAILURE GENER...

Страница 31: ...collective is lowered in order to avoid excess engine speed Note The H2S is equipped with a limiter for high motor RPM Do not hesitate to give full throttle if you are worried about the governor failure which has just occurred as by doing this you will retain full power rotor RPM The only inconvenience of this is that the noise of the high RPM setting is characteristic as it is linked to the injec...

Страница 32: ...tric vertical stabiliser will ensure maintenance in the axis of the fuselage Initiate auto rotation immediately then adjust power Maintain 110 km h 60 kts so that the steering effect of the tail remains effective Reduce throttle and slightly increase the collective Hold the cyclic to the right in order to limit the drift On final throttle to idle and sliding landing under auto rotation 3 12 FAILUR...

Страница 33: ... ignition of the engine is linked to the battery and operates independently of the alternator Reduce power to avoid the activation of the cooling fans and land safely as soon as possible Orange low fuel level warning light Low fuel This warning lights up when there remains only 10 L of usable fuel The engine will run dry after approximately 20 minutes operation at nominal power ACTION YOU MUST LAN...

Страница 34: ..._____________________________________________________________________ 34 In normal operation the engine oil pressure should remain between 1 5 and 5 bar The warning lights up if the oil pressure falls below 2 bar Action you should land without undue urgency or precipitation within 5 minutes ...

Страница 35: ..._________________________________________________________ 35 CHAPTER 4 NORMAL PROCEDURES 4 1 NORMAL OPERATING SPEED 4 2 PREFLIGHT INSPECTION AND CHECKS 4 3 CHECKLISTS WARNINGS 4 4 ENGINE START 4 5 TAKEOFF 4 6 CRUISE 4 7 APPROACH AND LANDING 4 8 AUTOROTATION 4 9 ENGINE SHUTDOWN PROCEDURE 4 10 CHECK OUT ...

Страница 36: ...les takeoff flight path clear Airframe 1 Remove parking strap on rear facing main rotor blade 2 Undercarriage wheels removed or failing that locked 3 Fuel tanks check fuel level equal on both sides check fuel tank caps closed 4 Radiator and fans check for grass or debris 5 Check underside of engine main transmission and generally on the ground under the helicopter for signs of leaked oil fuel or c...

Страница 37: ...re taking off and transitioning with caution The principle of takeoff is the same as for an aeroplane Think about the ambient conditions the fuel level and load as well as the aerological conditions wind speed and direction Check the terrain and possible obstacles Decide in advance on the best takeoff route Start out from the end of the field if necessary to provide room for acceleration Intellige...

Страница 38: ... clear Starter START engage to 800RPM Temptrature coolant liq Wait until 50 C RPM Increase to 3500RPM Temperature coolant liq Wait until 70 C RPM Increase to 5400RPM Light low RPM Check OFF Free Wheel Check by decreasing suddenly RPM Instruments Checked Area Clear Note in very cold climatic conditions at least three minutes should be spent on the ground with rotors turning at 100 to warm up the re...

Страница 39: ...Altitude Min 500ft Speed 80 to 90kts RPM Monitor 4 7 APPROACH AND LANDING Always opt for an approach into the wind and check the direction of this while studying the landing site POWER MANAGEMENT Reminders climb parameters power 100 speed 100 km h 55 kts possibility of 108 if necessary for a few seconds Level flight parameters maximum continuous power setting 23 à 25 in PA and 165 km h 90 kts Flig...

Страница 40: ... and hold up the aircraft using the collective but without causing the aircraft to climb Accept that the progressive application of the collective results in a regular but slow loss of altitude Accept the lighting up of the low RPM warning light Accept the sounding of the low RPM warning siren At around 30cm 1ft from the ground estimated height which can vary by 20cm continue to apply the collecti...

Страница 41: ...he collective At low revs the wind can cause the rotor blades to swing down to head height All movement of personnel under the rotor circumference at standstill is extremely dangerous It must be prohibited in the case where boarding or disembarking of a passenger is necessary while the rotor is turning instruct your passengers to move away to the front of the helicopter and keep very low e g landi...

Страница 42: ...___________________________________________ 42 CHAPTER 5 PERFORMANCES 5 1 GENERAL 5 2 CALIBRATION OF AIRSPEED INDICATOR 5 3 ALTITUDE DENSITY TABLE 5 4 CEILING FOR HOVER IN GROUND EFFECT 5 5 CEILING FOR HOVER OUTSIDE GROUND EFFECT 5 6 DISTANCE ALTITUDE RATIO USING AUTOROTATION 5 7 HEIGHT SPEED DIAGRAM 5 8 NOISE LEVEL ...

Страница 43: ...osswinds and tail winds of up to 35 kts at a mass of 700 kg on the ground VNE 190 km h 102 kts VFR flight authorised IFR flight prohibited for use under CNSK2 certification Night flying prohibited for use under CNSK2 certification Flight in icing conditions prohibited Emergency Auto rotation see 4 10 Use maximum revs in the range with power 100 during takeoff and climb out if necessary 108 limited...

Страница 44: ...FLIGHT MANUAL DYNALI HELICOPTER COMPANY Edition N 3 DYNALI H2S January 2012 __________________________________________________________________________________ 44 5 2 CALIBRATION OF AIRSPEED INDICATOR ...

Страница 45: ...FLIGHT MANUAL DYNALI HELICOPTER COMPANY Edition N 3 DYNALI H2S January 2012 __________________________________________________________________________________ 45 5 3 ALTITUDE DENSITY TABLE ...

Страница 46: ...FLIGHT MANUAL DYNALI HELICOPTER COMPANY Edition N 3 DYNALI H2S January 2012 __________________________________________________________________________________ 46 5 4 HOVER CEILING IN GROUND EFFECT ...

Страница 47: ...FLIGHT MANUAL DYNALI HELICOPTER COMPANY Edition N 3 DYNALI H2S January 2012 __________________________________________________________________________________ 47 5 5 HOVER CEILING OUTSIDE GROUND EFFECT ...

Страница 48: ..._________________________________________________________ 48 5 6 DISTANCE ALTITUDE RATIO UNDER AUTO ROTATION This table has been established starting from hover outside ground effect at 1000 2000 and 3000 m at the FE local FE of Maubeuge 3280 65 and 9843 ft wind not measured but very light below 5 kts ...

Страница 49: ...FLIGHT MANUAL DYNALI HELICOPTER COMPANY Edition N 3 DYNALI H2S January 2012 __________________________________________________________________________________ 49 5 7 HEIGHT SPEED DIAGRAMME ...

Страница 50: ...__ 50 5 8 NOISE LEVEL Noise levels determined under conditions set by article 6 of the decree of 19 02 1987 chapter 8 and appendix 4 of the second part of appendix 16 are as follows Recording conditions unobstructed zone free no background noise REFERENCE MEASUREMENT POINTS NOISE LEVELS EPNDB NOISE LIMITS EPNDB Takeoff 71 82 Approach 73 82 Overflight 69 82 ...

Страница 51: ...OMPANY Edition N 3 DYNALI H2S January 2012 __________________________________________________________________________________ 51 CHAPTER 6 MASS AND BALANCE 6 1 GENERAL 6 2 MASS AND BALANCE 6 3 HELICOPTER LOADSHEET 6 4 LATERAL BALANCING ...

Страница 52: ...long as the maximum takeoff weight of 700 kg is not exceeded EMPTY WEIGHT Empty weight is the mass of a Dynali H2S helicopter empty but including basic on board equipment engine oil engine coolant the various lubricants the unusable quantity of fuel 2 5L The empty weight as well as the empty C G must be measured for each H2S helicopter once assembly is complete There will be slight differences in ...

Страница 53: ... longitudinal axis Hold the helicopter with the mast vertical in balance on the bar A spirit level is placed on the receiving pulley this being perpendicular to the mast The virtual junction of the axis of the mast and the skids is 190mm forward of the axis of the attachment of the rear wheel measure the distance between the bar and the axle of the rear wheels Normally 75 mm A simple subtraction w...

Страница 54: ... should verify that the position of the C G of your Dynali H2S at the moment of takeoff is within the fore and aft balance limits You must also make sure that the takeoff weight of your Dynali H2S does not exceed the authorised Maximum Takeoff Weight of 700 kg These two conditions are met if the point defined by the takeoff weight and the position of the C G are within the area for longitudinal ba...

Страница 55: ...ples are reflected in the longitudinal balance graph Example 1 for balance calculation 1 passenger 27L of fuel doors removed Mass kg Distance datum mm Moment kg mm Empty weight 465 115 53475 Left hand passenger Put the heavier person on the left 83 575 47870 Right hand passenger 575 0 Usable fuel d 0 7 kg l max 90L 60 kg 27L 19 175 3307 5 Baggage max 26 kg 0 0 0 TOTAL 575 2300 CG for this configur...

Страница 56: ... DYNALI HELICOPTER COMPANY Edition N 3 DYNALI H2S January 2012 __________________________________________________________________________________ 56 Position of the centres of gravity of the various parts of the H2S ...

Страница 57: ...______ 57 Calculation of balance for your H2S Mass weight kg Distance datum mm Moment kg mm Empty weight Left hand passenger Put the heavier person on the left 575 Right hand passenger 575 Usable fuel 0 7 kg l max 90L 60 kg L 175 Baggage max 26 kg 0 0 TOTAL CG in this configuration Mom Tot Tot weight If the doors are removed subtract 6kg and 3450kg mm ...

Страница 58: ...fy hoist spring balance other WEIGHED EMPTY WEIGHT The empty weight of a Dynali H2S helicopter empty but including basic on board equipment the two doors 2 x 3 kg 6 kg full engine oil engine coolant the various lubricants the quantity of unusable fuel 2 5L kg POSITION OF THE CG EMPTY DATUM at mm forward of the wheel axles 190 mm mm mm rear of the axis of the rotor mast Datum axis of the rotor mast...

Страница 59: ... Minimum weight of solo pilot 60 kg Maximum weight of solo pilot without ballast in right hand seat 110 kg 110kg on the left limit of acceptable cyclic movement to the right to maintain operational manoeuvrability Above 110 kg in the left hand seat add ballast in the right hand seat corresponding to the surplus weight of the pilot over and above 110 kg Maximum weight of solo pilot 135 kg TWO MAN C...

Страница 60: ..._______________________________________________________________________ 60 CHAPTER 7 SYSTEMS 7 1 GENERAL 7 2 CABIN SHELL 7 3 UNDERCARRIAGE 7 4 MAIN ROTOR 7 5 REAR TURBINE OR ANTI TORQUE ROTOR 7 6 TRANSMISSIONS 7 7 ENGINE 7 8 FLIGHT CONTROLS 7 9 ENGINE CLUTCH DRIVE BELTS 7 10 FUEL CIRCUIT ...

Страница 61: ...e is made of aluminium tubes it is of the energy absorbing type with two legs on each side passive safety 7 4 MAIN ROTOR When still the blade roots withdraw in their bearings on their spindles to the limit The overhanging mass of the blades creates a high level of force on the blade roots The blades are made of composite materials glass fibre carbon aeronautical resin The blades are held by alumin...

Страница 62: ... IMPORTANT MAINTENANCE OF THIS HIGH LEVEL IS DESIGNED TO AVOID CAVITATION 7 7 ENGINE Subaru DS EJ25 engine Stroke 2500 cm3 Power 180HP Motor structure Subaru Electronic injection MOTEC Exhaust Dynali 7 8 FLIGHT CONTROLS Standard equipment includes dual controls The cyclic on the passenger side can be removed All controls are activated via shafts with maintenance free ball joint ends The flight con...

Страница 63: ... through two teleflex cables Note the control cables are not submitted to any special strain a system of contra rotating pinions neutralises the thrust efforts 7 9 ENGINE CLUTCH DRIVE BELTS The H2S has an automatic centrifugal clutch The drive belt tension is regulated by a floating tension spring In the receiving pulley there are two free wheels 7 10 FUEL CIRCUIT The fuel is supplied to the injec...

Страница 64: ..._________________________________________________________ 64 CHAPTER 8 HANDLING AND MAINTENANCE 8 1 GENERAL 8 2 REQUIRED DOCUMENTS 8 3 MAINTENANCE 8 4 MODIFICATIONS TO THE HELICOPTER 8 5 MANŒUVRES ON THE GROUND 8 6 PARKING AND TIEING DOWN 8 7 MAINTENANCE AND PROCEDURES 8 8 MAINTENANCE AND SERVICE LIFE ...

Страница 65: ...is info dynali com www dynali com The official regulations stipulate that the responsibility and the maintenance of a helicopter sold in kit form lies exclusively with assembler owner operator of this helicopter He must ensure that all maintenance is performed in compliance with the maintenance manual All limitations procedures safety procedures service lifetimes and maintenance conditions set out...

Страница 66: ...icopter Company declines all responsibility for any modification of the kit undertaken outside the above framework 8 5 MANEUVRES ON THE GROUND PRECAUTION climbing onto the undercarriage and step onto any part of the structure in stainless steel to examine the rotor On skids the helicopter is manoeuvred on the ground on its retractable wheels Manœuvre using the tail better hold better overall view ...

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