AutoGyro RotorSport CALIDUS Pilot'S Handbook Manual Download

Page: 23 / 101

Document number RSUK0060

Page 23 of 101 Page issue 5.1, dated 10.06.14

If an IVO-prop in-flight variable pitch propeller is fitted in combination with a 914UL
turbocharged engine the following placard is fitted adjacent to the manifold pressure
gauge or combined engine rpm/manifold pressure gauge, as applicable.

Max manifold pressure (take off):

39.9in Hg

Max continuous manifold pressure:

35.4in Hg

Summary of Contents for RotorSport CALIDUS

Page 1: ...age issue 4 dated 01 07 13 Pilots Handbook Gyroplane Type CALIDUS UK spec only RotorSport UK Ltd Poplar Farm Prolley Moor Wentnor Bishops Castle SY9 5EJ Company Reg No 5486550 Phone 44 0 1588 650769 Fax 44 0 1588 650769 Email info rotorsport org Approval number DAI 9917 06 ...

Page 2: ... 8 4m Rotor System II TOPP blue end caps only NB all types have silver spacers clamp profiles Propeller type HTC 1 73m ground adjustable propeller or IVO prop DL3 68 in flight variable pitch propeller NOTE This autogyro may be operated only under adherence to the operation limits and the information contained in this manual The manual should be carried on board the aircraft The manual is not a rep...

Page 3: ...8 3 EMERGENCY PROCEDURE 3 1 Introduction 24 3 2 Engine failure 24 3 3 Engine start in the flight 25 3 4 Abandoning the aircraft 25 3 5 Smoke and fire 25 3 6 Gliding flight forced landings 26 3 7 Precautionary landings 26 3 8 Loss of control 27 3 9 Engine shutdown 27 3 10 PIO reduced rotor rpm 27 3 11 Vibration 28 3 12 Other equipment failure 29 3 13 Canopy open in flight 30 3 14 Loss of vision 30 ...

Page 4: ... MAINTENANCE 7 1 Introduction 87 7 2 Regular maintenance requirements 87 7 3 Repairs 88 7 4 Ground handling road transport 88 7 5 Cleaning and care 90 7 6 Winter operation 90 8 EQUIPMENT 8 1 Minimum equipment 92 8 2 Additional equipment 92 9 IVO PROP IN FLIGHT VARIABLE PITCH PROPELLER OPTION 93 9 1 Introduction 93 9 2 Function 93 9 3 Control 93 9 4 Manifold Absolute Pressure Indications 94 9 5 Cir...

Page 5: ...ued ISSUE NUMBER DATE INSERTED BY ISSUE NUMBER DATE INSERTED BY Initial _______ ________ 11 1 14 01 11 12 2 12 09 11 13 3 02 04 12 14 4 01 07 13 Superceded Not Published 15 5 1 10 06 14 16 6 12 04 16 17 7 18 8 19 9 20 10 21 Issue Change summary 4 Warning on Binx nuts p38 different rpm gauges p62 nitrogen filled tyres p64 and pressures clarified in Checklist 5hr greasing added p39 40 ATR833 audio s...

Page 6: ... Page 24 2 12 9 11 Page 74 5 1 10 06 14 Page 25 2 12 9 11 Page 75 5 1 10 06 14 Page 26 2 12 9 11 Page 76 4 01 07 13 Page 27 2 12 9 11 Page 77 4 01 07 13 Page 28 2 12 9 11 Page 78 2 12 9 11 Page 29 2 12 9 11 Page 79 2 12 9 11 Page 30 6 12 04 16 Page 80 2 12 9 11 Page 31 6 12 04 16 Page 81 2 12 9 11 Page 32 6 12 04 16 Page 82 2 12 9 11 Page 33 6 12 04 16 Page 83 2 12 9 11 Page 34 6 12 04 16 Page 84 ...

Page 7: ...gulated in the Airworthiness Approval Notification AAN29266 issued by the Civil Aviation Authority CAA It has been shown to comply with the requirements of BCAR Section T issue 3 and is considered as a factory built aircraft It is supplied by RotorSport UK Ltd The aircraft is equipped and permitted for daytime VFR flight only 1 3 EXPLANATIONS AND SENSIBLE SAFETY MEASURES The manual is not a replac...

Page 8: ... take no responsibility for your decision to fly This aircraft is operated under a Permit to Fly not a certificate of airworthiness This means that it is only allowed to be used for recreation or flight training where allowed It also means that the aircraft has not been certified to any international standard and that the components used in the aircraft are not necessarily certified parts Whilst t...

Page 9: ...tabilizer engine cowlings and body Engine four stroke flat four Rotax 912 ULS or optional Rotax 914 UL Three blade ground adjustable 1 73m diameter HTC or Three blade variable pitch propeller 68inch diameter IVO prop TECHNICAL DATA see also fig 1 Rotor diameter 8 4 Rotorsystem II either standard variant red end caps or TOPP variant blue end caps Length 4 77m Height 2 74m Width 1 72m Rotor blade pr...

Page 10: ...Copyright of RotorSport UK Ltd Document number RSUK0060 Page 10 of 101 Page issue 1 dated 14 01 11 1 5 PICTORIAL VIEWS OF THE CALIDUS figure 1 dimensions in mm ...

Page 11: ...Copyright of RotorSport UK Ltd Document number RSUK0060 Page 11 of 101 Page issue 1 dated 14 01 11 Front quarter view Rear quarter view ...

Page 12: ...Copyright of RotorSport UK Ltd Document number RSUK0060 Page 12 of 101 Page issue 1 dated 14 01 11 View from the side Example cockpit view Centre blank panel for customer GPS fitment ...

Page 13: ...Copyright of RotorSport UK Ltd Document number RSUK0060 Page 13 of 101 Page issue 2 dated 12 9 11 Intentionally blank ...

Page 14: ...ided 6 2 Loading Limitations Maximum Total Weight Authorised 500kg Maximum Empty Weight 311 6 kg 914UL 309Kg 912ULS Maximum Pilot Weight front seat 125 kg Minimum Pilot Weight front seat 65 kg Maximum Occupant Weight rear seat 120 kg Front seat occupants under 65 kg in weight must carry suitable ballast 6 3 Engine Limitations Maximum take off max 5 minutes 5800 rpm Max continuous 5500 rpm Max CHT ...

Page 15: ...r exceeded Operating in excess of this is dangerous as this area is the safety margin to the maximum design speed 2 3 AIRSPEED INDICATOR MARKS Green range normal range from 30 80mph Yellow range caution especially nearing Vne from 0 to 30mph and from 80 to 90 mph Red line VNE at 90 mph or 120mph if SB 039 incorporated or 120mph if SB 039 incorporated and Rotor System II TOPP rotor variant fitted b...

Page 16: ...auges are marked with these values internally Range Maximum value Unit of measurement Engine RPM Green 1600 5500 Amber 5500 5800 5min red line 5800 rpm Oil temperature 50 130 130 max C Cylinder head temperature to 135 135 max C Oil pressure 0 8bar min to 3 500 rpm 1 5bar min above 3 500rpm Normal range 2 5bar 7 cold weather starting Bar 2 7 WEIGHT BALANCE The maximum take off weight MTOW of the Ca...

Page 17: ...t occupants under 65kg body weight must carry ballast Remember Fuel loading permissible is 500kg minus occupant weight minus aircraft empty weight minus any baggage or items added to the aircraft since weighed Aircraft empty weight is placarded Mogas nominal density is 0 72kg ltr check for the type of fuel used Example 500Kg 275Kg empty wt 90Kg rear seat occupant 90Kg pilot 10Kg rear seat luggage ...

Page 18: ...s clean and water free 2 Always use a filter when refuelling preferably with a water trap 3 Ensure the aircraft keyswitch is OFF before commencing refuelling 4 Ensure filler cap properly closed latch flush to surface after refuelling 5 Ensure that an earthing cable is connected where one is available Before flight use the water drain point under the keel to ensure the fuel is water free 2 9 GENERA...

Page 19: ...ed CG Range Limits Gyroplane refer to Pilots Handbook data Airspeed Limitations Maximum Indicated Airspeed Vne 90mph Other Limitations This aircraft shall be flown by day and under Visual Flight Rules only Smoking in the aircraft is prohibited OCCUPANT WARNING This aircraft has not been certificated to an International Requirement L R Roll Trim Front seat back straps limit stops must be fitted if ...

Page 20: ... not annotated on panel Pressure gauge placard unless panel annotated Fuel capacity 75 ltrs Preferred fuel EN228 MOGAS super or super plus AVGAS 100LL permissible Coolant Header Tank Filled with 50 50 water antifreeze Oil tank Capacity 3 ltrs Use Shell VSX or equivalent Motorcycle oil SF or SG Continuously lit Low Volt lamp indicates electrical demand exceeds supply and the battery is being draine...

Page 21: ... stick either type of stick grip L roll and R Roll only if roll trim system fitted Fuel cut off valve Interlock placard unless engraved on panel Placard above switch where fitted for Airbox GPS adjacent to Nav sw Off placard is fitted below the switch Where a Flymap L GPS has been fitted with an AHRS unit the following placard must be affixed adjacent to the Flymap GPS Off On Fuel cut off valve Pr...

Page 22: ...are placed high on the tail fin and are 60cm long 30cm high This has been accepted as best practice compliance to CAP523 the CAA standard for aircraft registration Alternative markings and position of markings is acceptable provided they comply with this standard Note that all placards must have the same units of measure as the instruments COMPASS DEVIATION For N 30 60 Set For E 120 150 Set For S ...

Page 23: ...rop in flight variable pitch propeller is fitted in combination with a 914UL turbocharged engine the following placard is fitted adjacent to the manifold pressure gauge or combined engine rpm manifold pressure gauge as applicable Max manifold pressure take off 39 9in Hg Max continuous manifold pressure 35 4in Hg ...

Page 24: ...hecked the aircraft will pick up speed in the descent and roll level The correct response is to gently pull the nose up to the airspeed and attitude required for the considered emergency landing In case of failure of the engine the following actions are recommended Taxying before take off maintain directional control brake and stop where safe Immediately after take off land immediately ahead In fl...

Page 25: ...nts should follow a path in line with the nose of the aircraft with heads as low as possible to minimise the risk of being struck by either the rotor or the propeller Occupants should be briefed before flight on emergency evacuation procedures including Actions to be taken in the event of a forced landing Operation of the seat harness Disconnection of any intercom leads or other connections to the...

Page 26: ...ne off airflow over the rudder surface reduces as airspeed drops to the point where there is limited directional control so take care at very low airspeeds The best glide speed is 60mph The height distance ratio with engine on tickover at maxTOW is approximately 1 4 400 feet of forward movement for every 100 feet of height With the engine stopped the ratio is approximately 1 3 If there is sufficie...

Page 27: ...the fuel supply valve It will take about 20 to 30secs min for this method to stop the engine Alternatively in an emergency fully close the choke wait a few seconds and open the throttle suddenly This normally chokes the engine and causes it to stop but is not guaranteed If the engine does not stop close the throttle 3 10 WHAT TO DO IN THE EVENT OF PITCH OSCILLATION OR ROTOR RPM REDUCTION DUE TO LO...

Page 28: ...ult has developed either through an impact loose luggage bird strike etc passing through the propeller or by some mechanical failure In the event the pilot should make a precautionary landing for evaluation Propeller damage may also be evident from a change in noise level Upon landing carefully check the propeller for damage loose bolts or evidence of mechanical failure within the prop or engine E...

Page 29: ... judgement of the best engine rpm to maintain to match the desired flight speed and payload Altimeter failure In a gyroplane it is reasonably easy to judge height If in controlled airspace ensure the controlling authority is informed to prevent traffic conflict Otherwise continue to a safe landing using navigational skills to avoid potential collisions Compass failure Resort to map aided by GPS if...

Page 30: ...ward vision may occur through a birdstrike or unexpected canopy icing eg freezing rain Immediately ensure the aircraft is in a safe attitude by reference to the side view using if required the emergency viewing hatch on the left of the pilot If at a safe height slow the aircraft to 50mph and using a hand through the hatch clear if possible the viewing obstruction If this is impossible then the air...

Page 31: ...tographs are from the MT series as the upper rotor head and rotor attachment is identical The rotor blades spacer extrusion and hub are provided with numbers to define the installation direction By matching these numbers put the blades into the hub Fit the 6 bolts per blade fitted with thin 9mm washers through the hub and blade assembly from the top and fit an 8mm thin washer and M8 nyloc on the l...

Page 32: ...y causing rotor to make tail or propeller contact The tower used with a RotorSystem II rotor is 40mm higher than that used on earlier aircraft It is good practice to fit one blade to the hub bar first with the nuts loose and then the second blade taking care that the blades are supported at the natural angle to each other of around 4degrees Three trestles are ideal for this with the middle trestle...

Page 33: ...or in the head 7 Grease the bolt via the grease nipple where fitted 8 Ensure the rotor teeters to the stops freely Removal of the rotors is the reverse of the above noting 1 Ensure the rotor and parking brakes are fully on before starting the process 2 Remove the rear seat cushion and place a suitably strong box in its place to stand on whilst lifting the rotor into position 3 Ensure the relations...

Page 34: ...Copyright of RotorSport UK Ltd Document number RSUK0060 Page 34 of 101 Page issue 6 dated 12 04 16 Views of orange end cap rotor system View of rotor bottom ...

Page 35: ...Copyright of RotorSport UK Ltd Document number RSUK0060 Page 35 of 101 Page issue 6 dated 12 04 16 View of orange cap rotor installed Top view of rotor installed ...

Page 36: ...This is adjustable by turning the lower adjustment knob anticlockwise for less or clockwise for more damping with 6 position notches The position may be adjusted to suit the pilot requirements A stiffer setting will reduce vibration but give a heavier feel to the aircraft handling good for long distance cruising A light setting will increase vibration but give a light feel to the aircraft great fo...

Page 37: ... Ltd Document number RSUK0060 Page 37 of 101 Page issue 6 dated 12 04 16 Additional views below show the differences between the original and RotorSystem II construction Section view of rotor head with RotorSystem II parts shown ...

Page 38: ...Copyright of RotorSport UK Ltd Document number RSUK0060 Page 38 of 101 Page issue 6 dated 12 04 16 Old rotor head assy Rotorsystem II head assy View of RotorSystem II fitted rotor blades not installed ...

Page 39: ...sue 6 dated 12 04 16 WARNING under MC 227 low profile metal lock nuts known as Binx nuts replace nyloc nuts for attachment of the teeter block to the hub bars These two nut types must not be interchanged For further information see AMM RSUK0061 Binx low profile self locking nuts ...

Page 40: ...here fitted Inspect condition and security of fiberglass enclosure A4 Landing Gear Inspect that extension appears normal Inspect tyres for proper inflation Main wheels 1 5 to 2 2bar Nose wheel 1 5 to 1 8bar damage and creep Inspect brake installation for external evidence of leaks and correct fluid level and for damage and security Inspect brake disc securing screws 4 each are secure Inspect that ...

Page 41: ... mechanism Op C pre rotator brake works with panel switch switched to BRAKE A11 Tail assembly Op C condition and security check surface for delamination check cables for fraying and secure connection to rudder check nico clamp for security check horizontal stabiliser and fins for security and any sign of damage from heavy tail down landings Op C check rudder bearings for security and operation Ins...

Page 42: ...ol elements functions and operation are as follows Check list before starting 1 Safety belts on and secure including pilot shoulder strap link to rear attachment 2 Headsets secure 3 Parking brake on Item function Status Operation Main switch 9 key OFF Turn anticlockwise ON Position centre START Turn fully clockwise spring return to centre Throttle 4 CLOSED IDLE Pull to the rear FULL POWER Push for...

Page 43: ... a load shedding relay when the lamp is lit Check that it goes off when the engine is run up to 4 000rpm If is doesn t then do not fly investigate as the alternator will be unable to maintain the aircraft electrical requirement Note that if there is insufficient voltage this load shedding relay will stop ancillary services from working ie 12v socket and lights whether or not the engine is running ...

Page 44: ...Be careful not to keep the brakes engaged for a long taxy with the choke on the choke idle rpm is higher and the resultant thrust increases the brake loads and can lead to brake fade on a long taxy Intermittently apply the brake instead WARNING Excessive idle rpm on long distances will cause brake pad fade and possible pad damage Idle rpm should be approx 1600 WARNING Taxiing with the canopy fully...

Page 45: ...enerally longer than the RotorSport MTseries due to the shorter nose length and more aft CG meaning there is less moment arm of the forward structure holding the nose down whilst accelerating the rotor Hence an aft CG a heavier passenger or full fuel will result in a longer take off run than a heavy pilot with lower fuel load The heavier rotor also requires more energy to accelerate to flight spee...

Page 46: ...ficiently reduced or engine rpm increased to increase alternator output then after a short delay the lamp will go out and the automatically switched loads will be restored If the lamp fails to extinguish and if the aircraft is powered by a Rotax 914UL expedite an immediate precautionary landing as the aircraft may have only minutes of battery power remaining to power the electric fuel pump and eng...

Page 47: ... the leverage increases the pressure in the system which could exceed allowable pressure 10bar the slow moving rotor blades will have reduced clearance to the tail Do not taxy with the rotors parked across the aircraft The advancing blade will try to lift and the retreating blade will be stalled leading to a significant load pushing the stick to the left Park into wind to ensure the canopy is not ...

Page 48: ...ow air pressure will change performance data SPEEDS Minimum speed Vmin 30mph 914UL or lightly loaded 912ULS 35mph for 912ULS MTOW Manoeuvre speed VA 80mph Cruising speed up to 80 mph with orange cap rotor system or up to 110mph with RotorSystem II red end caps or TOPP variant with blue end caps Permissible maximum speed VNE 90mph with orange cap rotor system or 120mph with RotorSystem II red end c...

Page 49: ...ularly when lightly laden with maximum power that you do not lose further rpm and rest on the engine power alone Rotor RPM should not drop below 280rpm in flight There is also a meter recording the rotor bearing temperature Land and investigate if there is any significant rise over the ambient temperature 5 2 FURTHER DATA RANGES The range depends on the fuel consumption which is proportionally lar...

Page 50: ... the flown speed IAS at which a safe landing is considered possible at max all up weight 8 4m rotors following engine failure Engine failures whilst flying at heights and speeds to the left of the graph line may prove fatal for the pilot and passenger Height velocity diagram 0 50 100 150 200 250 300 350 400 450 500 550 600 0 10 20 30 40 50 60 70 80 90 100 Speed in mph Height in ft ...

Page 51: ...uel tank is manufactured from fire resistant GRP with a fireproof covering Fuel pipe is fire resistant fabric strengthened rubber hose The canopy consists of Plexiglass The pilot enclosure and wheel spats consist of GRP or CRP composite material 6 2 Controls Rotor The rotor head control is via a normal cyclic type stick for the pilot connected to the rotor head via a tube in tube based keel assemb...

Page 52: ...ck grip To ensure that operating clearances to instrument panel and seats are maintained the alternative installation is supplied as a pre wired stick grip assembly Its placarding is the same in content but positioned differently MTOsport installation is shown below PTT Trim 4 axis movement Pre rotator engage Placards fitment if pitch trim only Placard fitment if pitch roll trim fitted ...

Page 53: ... pull out The limit stops fitted to the pilot seat adjustment straps may also be removed Note Stick changes must be noted in the aircraft logbook and dual inspected and the strap limit stops MUST be refitted with the stick to ensure the rear stick forward movement is not obstructed View of strap limit stop stops fitted comprise 2 washers screw and nylock nut per strap View of the two rear stick at...

Page 54: ...dals are an option fit item for instructional use Note that the rudder is fitted with a trim tab This is normally biased to the left and may be adjusted by the operator to trim the aircraft for straight flight at a desired speed feet off the pedals Adjusting it to the left will biase the rudder to the right and vice versa Trim tab fitted to the rudder Throttle The front cockpit is fitted with a th...

Page 55: ...le The unit may be removed but removal or refitment must be noted in the aircraft logbook and must be dual inspected The unit may also be fitted with a brake lever to operate the mainwheel brakes via a Bowden cable to the front seat throttle cluster Again this may be removed with the appropriate tools and replacement parts and noted in the aircraft logbook with a dual inspection The rear cockpit m...

Page 56: ... Magneto switches Headset jack plugs and power supply Rear seat headset mounting with instructor kill switch option fitted Throttle Brake Rear seat throttle and brake instructor pack When fitted the rear instructor stick carries the same features as the pilots stick PTT pre rotate and trim functions ...

Page 57: ...cker switch LEDs 35 Variable pitch prop circuit breaker 36 Fan on warning when lit 37 Canopy unlocked warning lamp 38 Avionics switch turns on radio transponder 39 GPS antenna GPS 40 option not shown switch to turn on off Airbox GPS adjacent to Nav sw Note items 29 34 35 not yet released in the UK market Note also that the different sized GPS units require that some items such as warning lamps may...

Page 58: ...f lit 26 Low Volt red When lit indicates that the battery voltage has dropped below 11 8v and that the load shedding relay has disconnected the 12v socket strobes and landing lamps Placard on panel advises operator to reduce electrical load or make a precautionary landing 27 Fire warning when lit red Pulse red three times on system start up Flashes red rapidly when the engine bay fire warning cabl...

Page 59: ...Copyright of RotorSport UK Ltd Document number RSUK0060 Page 59 of 101 Page issue 2 dated 12 09 11 Standard GPSmap panel option Flymap F7 installation no antenna required ...

Page 60: ...Copyright of RotorSport UK Ltd Document number RSUK0060 Page 60 of 101 Page issue 2 dated 12 09 11 Analogue panel standard ...

Page 61: ...HRS manual from Stauff Systec GmbH manual ref 500 408 and must always be considered secondary to the primary dial type flight instruments Refer to the operator manual for device setup and GPS integration WARNING The Flymap AHRS unit is not certified as an aviation sensor Therefore under no circumstances may it be relied upon for flight information not even as a backup device Non compliance with th...

Page 62: ...Copyright of RotorSport UK Ltd Document number RSUK0060 Page 62 of 101 Page issue 3 dated 02 04 12 Airbox Foresight GPS installation with additional on off switch 39 GPS antenna View of AVmap panel ...

Page 63: ...sibility to ensure the compass is not affected New items Under modification MC 218 a new design of rpm gauge was introduced engine rpm and rotor rpm and may be supplied as spares or with new aircraft They are visually and functionally similar to the earlier gauges but carry out a full sweep of the gauge face as a self test feature when powered up by the aircraft master switch Under modification MC...

Page 64: ...age 64 of 101 Page issue 2 dated 12 09 11 Rear and front seat lockers The push button locks the doors in place The rear seat lockers are part covered by the seat cushion and all are accessible in flight They are locked closed by the single sprung push button ...

Page 65: ...wners may wish to consider its use in older aircraft it is available from a number of UK tyre specialists To denote nitrogen filling green valve caps are used Arrangement nose gear wheel and main landing gear The main landing gear consists of a GRP bow which is fastened to the airframe The lower end carries the wheels which are braked with hydraulic brakes The nose gear wheel sits in a fork pivoti...

Page 66: ...he same number of holes from the rearmost position 6 6 ENGINE The engine provided is either a 4 stroke Rotax 912 or 914 This engine is appropriate for the market and is in use on many other similar aircraft but possesses no certification Engine failures occur with more regularity on uncertified engines so always plan your route and fly in such a way that an emergency landing is safely possible To ...

Page 67: ...els are air cooled Note that a thermostat is fitted to allow faster warm up and better temperature control Air cleaners to be replaced or cleaned according to the manufacturers recommendation Fig 10 engine 1 Engine serial number 2 Carburettor 3 Propeller gearbox 4 Electric starter 5 Coolant filler cap with overpressure 6 Exhaust manifold Rear end view 1 2 3 4 Thermostat Radiator Header tank Overfl...

Page 68: ...efore flight oil reservoir is item 1 The oil level is measured in aircraft level attitude and should reach between the marks on the dipstick Before checking turn the engine by the propeller approx 8 10 revolutions in normal direction of rotation until you clearly hear the oil gurgle in the tank take the tank filler cap off first to hear it better Switch ignition off first To get to the tank remove...

Page 69: ...for better control of the oil temperature see the line diagram below Only the oil tank is accessible without removing the upper engine cover other than visual checks through the cooling apertures To remove the engine cover undo all the camlok fasteners around the edge of the cowl Pull the four around the rear mast cowl out as far as possible Then wiggle the cowl to detach from the lower cowls and ...

Page 70: ...Copyright of RotorSport UK Ltd Document number RSUK0060 Page 70 of 101 Page issue 2 dated 12 09 11 Undo these camlok fasteners all the way around the upper cowl View with cowl removed Heater box ...

Page 71: ...finger over the vent hole in the overflow bottle to stop it draining back into the system REMARK Since the exhaust and its attachment are exposed to high loads by temperature and thermal expansion these should be frequently checked 6 7 FUEL SYSTEM The fuel system is under the rear seat and has a capacity of 39 ltr in the left tank and 36 ltrs in the right The tank is ventilated by a ventilation li...

Page 72: ...al expansion of the fuel Remember that the two tanks are connected via a crossover tube such that the tanks do not fill at the same rate Always wait 5mins to allow fuel levels to settle before confirming the fuel content Principle sketch fuel system 912S The engine mechanical pump is backed up with an electrical fuel pump located between the fuel tanks fed after the fuel cut off tap Left main tank...

Page 73: ...o showing water drain point The fuel feed passes from the fuel tank to a fuel shut off valve located on the rear face of the enclosure and remotely operated by a tap on the front forward face of the rear seat left side Ensure this fuel cock is fully open before flight It is there to allow the fuel supply system to be closed for instance during a fire in the air Left main tank Right optional tank F...

Page 74: ...ional items such as GPS units all draw a significant amount of current The amount will depend on individual circumstances Engine current availability and usage Calidus gyroplane Peak Amperage Peak Wattage Average Amperage Average Wattage Item Engine and engine systems inc one elect fuel pumps 912ULS Average assumes elect pump off 5A 60W 2A 24W Engine and engine systems inc two elect fuel pumps 914...

Page 75: ...er equipment failure or excessive electrical energy demand versus available alternator energy noting that the electrical supply from the alternator is dependent on engine rpm as shown in the supply graphs in the Rotax engine handbooks If by pilot intervention the electrical load is sufficiently reduced or engine rpm increased to increase alternator output then after a short delay the lamp will go ...

Page 76: ...and the compressor relay Automotive Inst panel Rotax regulator 25A Charging circuit from regulator to battery aircraft supply Automotive 25A fuse located between the 30A fuse and the cockpit supply Engine bay fuse box above left fuel tank on rear face of enclosure or engine bearer Starter 80A 100A under mod SB 042 Primary supply from battery to starter solenoid starter and from starter solenoid to...

Page 77: ...3 may be fitted approval no EASA 21O 0193 This radio has audio in capability e g warning tones from GPS devices and a miniature jack socket may be provided for connection positioned to the left of the instrument panel Transponder Option fit is a Funkwerk TRT800H Mode S transponder The antenna protrudes under the body under the front seat Read the user manual for operational instructions and take c...

Page 78: ...craft are an approved package modification or other installations require CAA RSUK approval 6 11 NAVIGATION AND STROBE LIGHTS These lights where fitted may not conform to the relevant ANO They are not intended for use as approved night flight equipment Two options are supplied 1 Airworld Skyflash system with or without navigation lamps fitted either side of the body or 2 Aveoflash system either on...

Page 79: ...re hand fitted to individual aircraft and should not be changed between aircraft The canopy is hinged on the LH port side of the aircraft and locked by a single detented lever on the RH side of the aircraft When open the canopy is restrained by a webbing strap on the rear LH side When closing the canopy is guided on to the enclosure by means of two tapered spigots on the enclosure and mating holes...

Page 80: ...e Bungee fitting on canopy frame nut cover removed To remove replace a canopy without damage it is necessary to use a helper although there is no heavy lifting involved To remove 1 With the aid of the helper to take the weight of the canopy remove the restraint strap from the rear enclosure mounting by removing the M6 nyloc nut The nut will be covered with a protective dome which is a push fit 2 C...

Page 81: ...ective pivots and the tapered location spigots engaged 2 With the helper manipulating the canopy fit the hinge pins with nylon and steel washers through the pivots 3 At each hinge position fit the nyloc nut with steel washer under and tighten progressively until all slack has been taken out of the hinge movement Do not tighten so that the hinge is under strain 4 Fit the two safety clips by pushing...

Page 82: ... detent action The degree of detent is factory set so that if canopies are interchanged no adjustment is necessary The detent force must be large enough to avoid erroneous opening but small enough to enable ready release from both outside the aircraft and inside by either pilot or passenger The detent force assessed as the peak force of the over centre action may be measured by means of a force ga...

Page 83: ...aced again at about 95mm radius and the load maintained at 90º to the handle When the detent occurs the tension loop invariably slides off the handle but the maximum value will be recorded Measured as above the locking force should be 30 40N equivalent to 2 85 3 8Nm or 3 4Kg but may be 50 higher with brand new parts not yet run in With the semi open canopy the forces must be measured on the interi...

Page 84: ...t to 3 8 5 7Nm or 3 3 4 9Kg For detent locking force use a small wire loop placed at the handle s bend point effective radius 75mm Max force here 38 50N equivalent to 2 85 3 8Nm or 3 9 5 1Kg but may be 50 higher with brand new parts not yet run in The average locking release force may be adjusted by selective assembly of different sizes of brass bush on the locking pin and or shims fitted under th...

Page 85: ...ly valve operated by a pull knob on the instrument panel Temperature is controlled by mixing this air with the cooler air coming through the front vents Because the warm air is not circulating around the hot exhaust there is no risk of carbon monoxide entering the cabin Alternatively under MC 259 a radiator matrix is installed in the nose of the aircraft with a heater fan This unit takes hot water...

Page 86: ...d 12 09 11 APPROVED MODIFICATIONS For confirmation of all modifications permissible in the UK contact RotorSport UK Ltd or reference the RotorSport website Alternatively the aircraft TADS issued by the CAA lists all approved modifications for the type and is available from the CAA website ...

Page 87: ...Copyright of RotorSport UK Ltd Document number RSUK0060 Page 87 of 101 Page issue 2 dated 12 09 11 Intentionally blank ...

Page 88: ...ity sun and wind and the manufacturers will take no responsibility for the safety margins eroded by such actions In strong sunlight the interior of the cabin will get very hot This is detrimental to the aircraft so either leave the canopy slightly open bearing in mind wind direction and propeller wash or cover with a reflective canopy to reflect the sun s rays Dark coloured aircraft are particular...

Page 89: ...rmation 7 4 GROUND HANDLING ROAD TRANSPORT Aircraft are generally exposed to larger loads on the ground than in air especially in road transport Since the structure is designed for air use this can induce a safety risk Hard landings and rough ground especially potholes all induce high accelerations on the autogyro framework as does being bounced around on the back of a road trailer Therefore avoid...

Page 90: ...the metal walls 100mm high This prevents scuffing of the wheel spats when loading protects the tyre side walls and limits sideways movement of the aircraft during the journey The aircraft CG is just forward of the mainwheels balanced over the trailer axles for good weight distribution For normal road transport the rotors are removed The nose wheel is tied forwards to prevent the aircraft moving ba...

Page 91: ...xiglass cleaning sprays such as Plexus with soft lint free cloths to polish and finish the surface inside and out Read and follow the product instructions A good quality polish helps protect the surface finish and reduce surface friction Use of RainX or other proprietary rain repellent compound will help rain drops wash away when flying in rain Read the instructions and ensure the compound is suit...

Page 92: ...very two years Read the engine manual for the manufacturer s recommendations During winter flying operation the necessary operating temperature for oil and cooling agent may not be reached It is important that the oil temperature reaches higher than 80 C to prevent engine interior corrosion from condensation so if necessary carefully blank off a portion of the oil cooler and monitor the temperatur...

Page 93: ...uipment Use of a Mode S transponder in certain designated airspace is mandatory Flight without a transponder or with an unserviceable transponder is only permitted outside of those airspaces ATTENTION Take care when installing additional equipment in case it changes the magnetic field of the aircraft and hence the compass accuracy 8 2 ADDITIONAL EQUIPMENT Various options are available from RotorSp...

Page 94: ...eller hub drives a spool which twists each torque tube simultaneously The propeller has two internal pitch limit stops mechanically limiting the pitch angle at the pre determined FINE and COARSE limits NB These are different for 912ULS and 914UL engine applications These pre determined limits ensure that the aircraft will still climb at a minimum rate of 250fpm in the full COARSE setting and will ...

Page 95: ... direction for at least 1 second Indication can only be reset by switching the master switch temporarily to OFF and then back to ON In order to avoid pilot distraction indication of a possible defect is retriggered after another activation of the rocker switch 9 4 MANIFOLD ABSOLUTE PRESSURE INDICATIONS The analogue manifold absolute pressure gauge MAP has perimeter markings to show normal warning ...

Page 96: ... FINE steady on To adjust the propeller to a COARSER setting use the following procedure Adjust propeller pitch and throttle to match engine RPM and manifold pressure according to the power setting table below ROTAX 912 ULS Power setting Engine RPM MAP Fuel flow ltr h Max TOP 5800 27 5 27 Max MCP 5500 27 26 75 MCP 5000 26 20 65 MCP 4800 26 18 55 MCP 4300 24 14 ROTAX 914 UL Power setting Engine RPM...

Page 97: ...f keep the propeller at full FINE Monitor the engine RPM to ensure that the high RPM time limit specified by Rotax is not exceeded It is the pilot s responsibility to ensure that the recommended time limit is not exceeded Cruise When the aircraft in the climb phase reaches the required cruising level level out and adjust the throttle to the desired power level manifold pressure Then select the COA...

Page 98: ...function giving the following scenarios 1 Propeller runs to fully coarse and stops RPM will decrease and MAP will rise Reduce power if needed to stay within MAP limits Probable cause jammed or internally failed rocker switch Continue flight with careful monitoring or if in any doubt make a precautionary landing WARNING The climb rate will be reduced to 250fpm minimum At fully coarse the engine wil...

Page 99: ...use internal mechanical failure This will result in significant warning vibration Reduce power and assess vibration with consideration of a precautionary landing If necessary turn off engine make immediate precautionary landing 5 Loss of blade This will result in severe vibration Switch engine off and land immediately 6 Loss of blade tip This will result in significant vibration Switch engine off ...

Page 100: ...If the new owner does not register then they will not be automatically updated which may lead to unsafe flight or an un airworthy aircraft Return this form to RotorSport UK Ltd Poplar Farm Prolley Moor Wentnor Bishops Castle Shropshire SY9 5EJ Or email info rotorsport org or fax 01588 650769 Aircraft type Aircraft serial No Aircraft Registration No Aircraft Engine No Logbook Aircraft hours Logbook...

Page 101: ... action is investigated and if needed supplied back to the customer s The information given is stored on a computer and is only used within RotorSport UK for the above purpose Return this form to RotorSport UK Ltd Poplar Farm Prolley Moor Wentnor Bishops Castle Shropshire SY9 5EJ Or email info rotorsport org or fax 01588 650769 Aircraft type Aircraft serial No Aircraft Registration No Aircraft Eng...

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