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G 4-2 - Trixy Aviation

1. 13 EMERGENCY PROCEDURES 106 13 1 Introduction 106 13 2 Engine failure 107 13 3 Engine startup during flight 107 13 4 Smoke and fire 108 13 5 Gliding 108 13 6 Emergency landing 108 13 7 Rescue system 109 13 8 Miscellaneous emergency procedures 109 Flight and operation manual G 4 2 Revision 3 0 09 04 2013 7 1 GENERAL 1 1 Introduction This manual contains information which is necessary to operate the gyrocopter efficiently and safely according to German regulations as well as information from the manufacturer The maintenance manual contains all the necessary information instructions and documents required for proper maintenance To fly this gyrocopter a pilot s license according to the rules and regulations of the country it is to be flown in is required Before flight it is important that the pilot be instructed about the features and characteristics of the gyrocopter during a thorough familiarization in an authorized flight school The registration of the gyrocopter is obligatory in almost all countries It is the responsibility of the operator to get and follow the valid rules in the country it is intended to fly in Further laws like the acquisition of third party liability insurance are to be observed as well It is obligatory to read the entire manual and all documents provided by the manufacturer to get accustomed with every detail of the gyrocopter and the installed equipment 1 2 Registra
2. Flight and operation manual G 4 2 Revision 3 0 09 04 2013 108 c Landing with defective undercarriage or flat tire Regular approach Land with high angle of attack and minimum speed slow the gyrocopter down with the rotor and hold direction with the rudder After successful landing the engine is to be shut down immediately putting the switches for MAG1 MAG2 and master switch in OFF position d Landing with engine power Look for emergency landing field and prepare landing accordingly Pay attention to wind direction and speed and if possible land against the wind and up hill e Landing without engine power Look for emergency landing field and prepare landing accordingly Pay attention to wind direction and speed and if possible land against the wind and up hill 13 7 Rescue system Because the gyrocopter is equipped with a rotor system which is constantly in autorotation during flight no further rescue system is installed For this reason it is important to look after the entire rotor system including the rotor head with special care 13 8 Miscellaneous emergency procedures 13 8 1 Loss of manouverability Try to reach a large landing field by using the possibly remaining rudder and changing altitude with engine power Fly wide and flat turns Land against the wind direction if possible 13 8 2 Loss of maneuverability around pitch axis The air speed to maintain horizontal flight will vary dep
3. 5 3 Weighing report Serial No 001 11 Registration D MTRX Clor Orange Metallic Operator Rainer Farrag MTOW 500 kg Empty weight including accessories 272 kg Maximum payload 178 kg CG in X direction 2320 mm Name Date Signature Maximum take off weight with Rotax 912 ULS 500 kg Maximum take off weight with Rotax 914 UL 530 kg Maximum take off weight with Trixy 912 TI 560 kg Minimum load on front seat 65 kg Maximum load on front seat 125 kg Empty CG limitation in X direction 2250 2400 mm Flight CG limitation in X direction 1900 2200 mm Warning Any change which has effect on the mass and or center of gravity must be noted in section 5 4 empty mass alteration and this must be considered by the pilot in command The neglancy may have fatal consequences Flight and operation manual G 4 2 Revision 3 0 09 04 2013 52 5 4 Empty weight alteration Any change which has effect on the mass and or center of gravity must be noted in this section Such changes may only be excuted and documented by an authorized aviation work shop The oprator of the gyrocopter is responsible for keeping the documents up to date The pilot in command must consider the valid and current weights and CG Equipment added kg Equipment removed kg Weight kg New empty weight kg New center of gravity in X direction mm Date Signature Stamp of specialized company Equipment added kg Equipment removed kg Weight kg New empty
4. Checking the oil is very important 1 2 3 4 Both ignition circuits turned off Remove the cap of the oil container Turn the engine at the propeller in rotation tirection aproximately 8 10 revolutions until flushing sound can be heard The oil level is measured while the gyrocopter is level and should not be lower than the middle of the flat area of the dip stick It should not be higher tha 1 Pressure regulator 2 Oil pressure sensor 3 Oil pump 4 Oil container 5 Oil radiator 6 Oil filter 7 Vent hose 8 Oil temperature sensor Warning both ignition circuits must be turned off before the engine is turned by hand to check the oil level There is a risk of severe injury and or death if this is ignored Note In case of engine damage due to low oil level all manufacturer warranties are void Flight and operation manual G 4 2 Revision 3 0 09 04 2013 90 9 5 Cooling system To check the level of the engine coolant it is important to not only check the reservoir but also every now and then to check the level of the expansion container 4 The radiator 2 must be checked for clean surfaces and no leaks 9 6 Ignition system The two independent Zandtolge 1 4 2 3 magnetos on the generator paides A stator 1 each supply one of AIEEE ei the 2 ignition circuits The energy is saved in condensers in the electrical module 2 At the time of ignition 2 of the 4 transducers 3 initiate the d
5. must be adhered to 3 13 Descent v Use engine throttle to maintain 100 km h 110 km h in case of rain or turbulence v Adjust trim pressure for descent v Request landing permission if required v Enter traffic pattern if required and check engine instruments Flight and operation manual G 4 2 Revision 3 0 09 04 2013 37 3 14 Before touchdown check Check all systems Land against the wind if possible Approach with 100 110 km h not under 90 km h Adjust trim pressure Landing lights ANNA A 3 1 o Go around procedure Full throttle Adjust trim pressure Set speed for best ascent rate 90 110 km h Check engine instruments Minimum safe altitude reached Engine settings as required KN NANA 3 16 Touchdown v Reduce speed shortly before touching ground reduce engine power and land softly on the main gear v Keep the stick pulled back all the way toward body and reduce speed using the rotor until standing still Warning If the gyrocopter starts to roll backwards in case of strong head wind the brakes are not to be used to stop under any circumstances Instead use the engine throttle and add power v When rotor speed is below 150 RPM the control stick should be brought into the front middle position to reduce the risk of damage to the rotor and empennage Slow the rotor down and push the stick all the way forward v Incase of side wind position the rotor as required Flight and operat
6. only Any navigational information is provided for reference only The pilot takes all responsibility and risk associated with the use of this device Press OK to agree and continue Serial 8019 Version 2 2 SVN 7197 Princess The warning window also displays the serial No of the software at the bottom of the window Pushing the rotating knob 2 in is the confirmation OK and this would enable the unit to continue the start process The second window allows the user to select a pilot name from a list which can be set in the setting menu Confirming the name of the selected pilot with the rotating knob 2 push in will make the curser drop down into the box for setting QNH Select Pilot EVA a QFE altitude 885 feet Rotating the rotating knob 2 will change the QNH setting and pushing it in will confirm the setting and then the main display 1 is on Flight and operation manual G 4 2 Revision 3 0 09 04 2013 79 The first main display 1 Indicated air speed 3 Engine RPM UPM x1000 5 Rotor RPM 7 Oil temperature 9 Fuel pressure 11 Cirsuit current 13 Fuel consumption l h 15 Range km 17 Fuel gauge 19 Vertical speed indicator 21 Altitude indicator 23 Current position 2 True air speed 4 Manifold pressure 6 CHT 2x 8 Oil pressure 10 Circuit voltage 12 Turn coordinator 14 Average consumption l h 16 Endurance h 18 G Meter acceleration 20 QNH 22 GP
7. 04 2013 86 Flight and operation manual G 4 2 Revision 3 0 09 04 2013 87 9 POWER PLANTS 9 1 Introduction A 4 stroke engine of the type Rotax 912 ULS or Rotax 914 UL serves as a power plant These engines are developed and certified for use in ultra light gyrocopters however they are not certified for general aviation For this reason an engine failure must always be considered and the flight rout must be chosen so that a safe landing is always possible Warning Maintenance work and checks are to be carried out in regular intervals acording to maintenance protocols e g engine oil change every 50 h sparkplug replacement after 200 h Note Pure water may never be used as engine coolant only the mandatory mixture with 50 antifreeze BASF GL48 and 50 distilled water Air filter K amp N Lifetime cotton filter is to be used It is to be cleaned and oiled or replaced depending on the condition In case of disregard to the maintenance instructions the manufacturer warranties are void Flight and operation manual G 4 2 Revision 3 0 09 04 2013 88 9 2 Triebwerkansichten Side view Direction of rotation Top view Front view Zyl 1 Zyl 3 9 3 Power plant 1 Propeller hub 2 Vacuum pump not used 3 Engine serial number 4 Carburetors 5 Electric starter 6 Reservoir for coolant 7 Exhaust manifold 8 External general optional Flight and operation manual G 4 2 Revision 3 0 09 04 2013 89 9 4 Oil system
8. 2 5 Center of gravity 24 2 6 Admissible maneuvers 24 2 7 G forces 24 2 8 Minimum crew 24 2 9 Operating modes 24 2 10 Fuel 24 2 11 Operation fluids 25 2 12 Limitation labels 26 3 NORMAL OPERATION 28 3 1 Introduction 28 3 2 Periodic inspection 28 3 3 Pre flight check 31 3 4 Pre startup check 35 3 5 Operating procedures with external power source 35 3 6 Engine startup 35 3 7 Pre taxi check 35 3 8 Check during taxying 35 3 9 Preparation for take off and pre rotation 36 3 10 Take off 37 Flight and operation manual G 4 2 Revision 3 0 09 04 2013 4 37 3 11 Climb 3 12 Cruise 37 3 13 Descent 37 3 14 Pre landing check 38 3 15 Go around procedure 38 3 16 Touchdown 38 3 17 Post landing check 39 3 18 Engine shut down 39 3 19 Securing the gyrocopter 39 3 20 Mounting and removing the rotor 40 3 21 Handling the rotor system 40 3 22 Propeller 44 4 FLIGHT PERFORMANCE 46 4 1 Introduction 46 4 2 Performance data 46 4 3 Influence through rain and insects 47 4 4 Max ascertained cross wind 47 4 5 Noise data 47 4 6 Tire pressure 47 4 7 Service ceiling 47 4 8 Torque specifications 48 4 9 Battery and generator 49 4 10 Altitude and pace diagram 49 5 WEIGHTS AND CENTER OF GRAVITY 50 5 1 Introduction 50 5 2 Weighing procedure 51 5 3 Weighing report 52 5 4 Empty mass alteration 53 5 5 Determining the center of gravi
9. Put on the washer and tighten the crown nut hand tight then secure it with the safety split pin The main bolt must be rotatable by hand NO Flight and operation manual G 4 2 Revision 3 0 09 04 2013 43 3 22 Propeller The gyrocopter G 4 2 is delivered with a ground adjustable propeller as a standard In flight adjustable prop is optional Warning It is recommended to read and follow the instructions given in the manufacturer s manual of engine and propeller Note In case of mishandling or wrong operation of the propeller and or the engine the warranties for for the propeller and or engine will be void Flight and operation manual G 4 2 Revision 3 0 09 04 2013 44 Flight and operation manual G 4 2 Revision 3 0 09 04 2013 45 4 FLIGHT PERFORMANCE 4 1 Introduction The following data has been collected during test flights It is only valid when the gyrocopter rotor propeller and engine are in an immaculate condition the propeller and the rotor are clean and the pilot disposes over average flying skills The performances listed here are under standard conditions sea level 1013 mbar 15 C no wind take off weight 450 kg and smooth runway with short turf in good condition Higher airports higher temperatures higher humidity and lower atmospheric pressure can dramatically affect the performance data 4 2 Performance data Speeds Minimum speed VSo 40 km h Manouver speed VA 100 km h Most economical
10. RPM 5500 RPM 5800 RPM max 135 C min 50 C max 130 C EN228 Super min 95 octane or EN228 Super plus min 98 octane AVGAS 100 LL ASTM D910 SAE 10W 40 API SG or higher E g Oil Shell Advance VSX4 115 HP 5800 RPM 100 HP 5500 RPM 5500 RPM 5800 RPM max 135 C min 50 C max 130 C EN228 Super min 95 octane or EN228 Super plus min 98 octane AVGAS 100 LL ASTM D910 SAE 10W 40 API SG or higher E g Oil Shell Advance VSX4 130 HP 5800 RPM 113 HP 5500 RPM 5500 RPM 5800 RPM max 135 C min 50 C max 130 C EN228 Super min 95 octane or EN228 Super plus min 98 octane AVGAS 100 LL ASTM D910 SAE 10W 40 API SG or higher E g Oil Shell Advance VSX4 Flight and operation manual G 4 2 Revision 3 0 09 04 2013 22 Also see engine manuals Further data can be found in the provided engine manuals Warning The engine may not be started without the propeller in place or it could suffer damage due to over revving Warning With the propeller in place the engine RPM may never pass the maximum permissible value or severe damage could be the consequence 2 4 Weights The maximum take off weight MTOW with Rotax 912 ULS is 500 kg The maximum take off weight MTOW with Rotax 914 UL is 530 kg The maximum take off weight MTOW with Trixy 912 TI is 560 kg This weight includes empty weight of the gyrocopter pilots weight fuel and luggage The pay load MTOW mi
11. a higher amount of unflyable fuel because of the aircraft s attitude Low nose attitude may cause the engine to fail during certain maneuvers due to a lack of fuel flow Warning If a landing must be made with low fuel remaining it must be done with a low sink rate and a raised nose The engine manufacturer recommends unleaded gasoline 95 Octane as fuel AVGAS 100LL can also be used Due to a lower risk of vapor bubble build up during very hot conditions and freezing during very low temperatures AVGAS 100LL should be preferred during these times Every time after fueling the fuel must be checked for no water content Open the drain under the aircraft and take a sample of fuel to check it for no water content In case no layering between water and fuel can be seen it is to be checked whether only water or fuel is contained in the tank If in doubt draining should be continued until only pure fuel is in the tank s of the gyrocopter In case of prolonged operation more than 30 with AVGAS 100LL the condition of the sparkplugs must be checked every 25 hours due to the danger of lead buildup on the electrodes The engine manufacturer also demands an additional check of the power plant every 50 hours in case of prolonged operation with this type of fuel When fueling it is to be made certain that only clean fuel free of water be supplied In case of doubts a funnel with an integrated filter should be used when fueling 2 11 Operatio
12. up time v Let engine run at 1800 RPM for 2 minutes then at 2500 RPM until oil temperature reaches 50 C Warning It is obligatory to follow the instructions for the propeller see section 3 22 in this book and the proprller manual provided by the manufacturer Note To start the engine when it is cold the choke must be fully pulled up and the throttle in the idle position or the choke is rendered useless If the engine does not fire up wait 20 seconds before attempting to start again so the battery and starter motor do not overheat The engine temperature should be checked and the use of the choke reconsidered Flight and operation manual G 4 2 Revision 3 0 09 04 2013 34 3 7 Before taxi check KN NANA NNRNRN SN Close and lock canopy Adjust ventilation as desired Cabin heater as desired optional Auxiliary fuel pump optional check for function and then off Check fuel level Adjust altimeter Turn on and adjust radio optional Turn on and adjust transponder optional Check if ELT is functioning optional Landing lights and optional Nav Strobes as desired Check compass heading Warning Turns at slow speeds only and with caution due to danger of tipping Warning Caution when taxying onto uneven ground otherwise severe damage to landing gear and rotor system may occur 3 8 Check during taxying NN Adjust trim nose heavy to keep the stick in a forward position Surrounding area is fre
13. 15 42 0 The following information is displayed on the upper edge of the screen Wind direction and speed ground speed air space No of Satellites in sight current time and remaining flight time to destination Navigational information is displayed on the lower edge of the screen A transparent window will appear on the lower left corner of screen once the engine is running CHT 2 X oil temperature oil pressure fuel pressure voltage V current A engine RPM range and rotor RPM range Traffic awareness ADS B and Flarm if installed will be displayed on the moving map in this display Turning the rotating knob 2 will result in zooming in or out in the moving map Turning the rotating knob 1 will toggle between the 5 main displays Flight and operation manual G 4 2 Revision 3 0 09 04 2013 82 The third main display the flight training screen This display is designed for flight schools to teach student pilots in their initial training It displays conventional instruments and does not contain any navigation data This is suitable for VFR instruction with paper flight charts This screen can be locked with a password so that the student cannot chose a different display An additional small display may be installed with the optional traffic awareness system to enhance flight safety Pitch trim Roll trim Tail Nose Left Right MANEFOLD l 208 30 S ENGINE TIME FLIGHT LLLI 100 60 42 4 13 3 7 8 Current Ran
14. Flight and operation manual Trixy Aviation G 4 2 Flight and operation manual G 4 2 Revision 3 0 09 04 2013 Flight and operation manual for Gyrocopter G 4 2 Individual gyrocopter data here This manual is to be carried along when operating the gyrocopter The extent and state of revision of this manual may be obtained from the index and the revision index The Gyrocopter G 4 2 may only be operated in accordance with the instructions and within the operating limits included in this manual This manual does not substitute a theoretical or practical instruction to operate this gyrocopter Revision 3 0 Date issued 09 04 2013 Flight and operation manual G 4 2 Revision 3 0 09 04 2013 2 REVISIONS TO THE FLIGHT OPERATIONS MANUAL No Description Page Date Signature __ OOU Flight and operation manual G 4 2 Revision 3 0 09 04 2013 3 INDEX 1 GENERAL 8 1 1 Introduction 8 1 2 Registration and certification basis 8 1 3 Performance data and operating procedure 8 1 4 Warnings and precautions 8 1 5 Three side views 12 1 6 Description 14 1 7 Technical data 14 1 8 Rotor 14 1 9 Propeller 14 1 10 Power plant 15 1 11 Abbreviations and terminology 18 2 OPERATING LIMITS 20 2 1 Introduction 20 2 2 Flight speeds 21 2 3 Engine limits 22 2 4 Weights 23
15. S moving map 24 Electronic compass More information such as coordinates of current position current time and ground speed are also displayed on this screen Flight and operation manual G 4 2 Revision 3 0 09 04 2013 80 Nesis II displays warnings whenever a value oil pressure CHT max air speed min rotor RPM gets out of the set limits The illustration below shows a Fuel Low warning When connected to the transceiver and set for audio warnings the NESIS II will also announce audio warnings in the head set The user may enable or disable any of the warnings in the setting list of warnings Audio beep or voice warnings may also be enabled or disabled in the same list The range limits for each warning are predefined and cannot be changed by the user in the unit i j LICL B 223 D 53 8 km 0 pi 1 Y 4 AIRSPEED ee 9 Ml oe bi sane X ALTITUDE km h 507 SVG A Umas s et y ee Viz ENGINE MANIFOLD x 1000 6 far 3 gt VARIO 30_ y x f E a ee D E 4 x N 20 a j ACCELERATION z i A 0 4 10 1 2 Bie VY rotor RPM arse x PA a 8 ee s Di tir ein ais 0 15 Turning the rotating knob 2 will result in Zooming in or out in the moving map Turning the rotating knob 1 will toggle between the 5 main displays Flight and operation manual G 4 2 Revision 3 0 09 04 2013 81 The second main display the navigation screen CH O Bear 185 km Track 005 T 0 07 26 E
16. air speed The static pressure is measured at the left side of the cabin and is attached to EMSIS NESIS through a hose Flight and operation manual G 4 2 Revision 3 0 09 04 2013 73 7 GLASS COCKPIT 7 1 Introduction The Mini Glascockpit EMSIS is specially designed for the Model Liberty und the Glascockpit NESIS II is specially designed for the Model Princess by Kanardia These units are directly connected to the board electrical circuit through the Nav switch They are connected to the Pitot tube at the nose of the gyrocopter through a hose They are also connected to the static pressure port at the left side of the cabin through a hose See chapter 6 11 EMSIS EMSIS NESIS II Warning This manual includes only a brief description of EMSIS and NESIS The pilot must read the operation manual of the unit in the units manual and get familiarized with the operation instructions befor flight 7 2 Description EMSIS The standard equipment of the Model Liberty includes one Mini Glass Cockpit EMSIS which includes the following Instruments air speed indicator altimeter vertical speed indicator G Meter acceleration CHT 2x oil temperature oil pressure fuel gauge fuel pressure hour meter and other useful functions Engine RPM and Rotor RPM are displayed in a separate instrument A second EMSIS is optionally available for GPS navigation in Liberty NESIS II The standard equipment of the Model Prin
17. ake function check 46 Luggage only soft objects stowed 47 Luggage compartments correctly loaded check 48 Canopy glass optional tightly installed check 49 Rear seat belts fastened and locked OK 50 No free objects lying on the floor check 51 Key is removed from the canopy lock check 52 Main electric switch ON 53 Landing and Navigation lights check 54 Switches for lights fan and cabin heating OFF 55 Auxiliary fuel pump Option Function check 56 Auxiliary fuel pump switch and main switch OFF 57 MTOW check 58 Board documents and flight charts on board present Warning This manual does not replace a theoretical or practical training to operate this gyrocopter Disregard to this may result in death or severe injury It is the responsibility of the pilot to cunduct a visual inspection prior to every flight The necessary expertise to do this is aquired during the pilot training course special details will be instructed during the familiarization with this gyrocopter Flight and operation manual G 4 2 Revision 3 0 09 04 2013 32 3 4 Before engine start check Passenger briefing Passenger secured Loose objects aboard secured Rotor free rotor securing bag removed Stick moves freely in all directions Embark and fasten seatbelt Parking break set Wind checked Propeller area clear Main instrument glass cockpit turned on Set pilots name QNH and amount of fuel KN NNN N NNN 3 5 Operating procedures with external power
18. amage the propeller or the empennage 7 The rotor system may not be laid down on a dirty or rough surface since the blades may get damaged or scratched It is best to place it on two jacks placed under the center of each blade 3 21 2 Dismantling the rotor system 1 To dismantle the rotor system lay it upside down on two jacks or a clean surface 2 The 4 outer locknuts which secure the rotor blade must be removed from one rotor blade while the fitted bolt on the lower side of the blade must be countered with a wrench 3 All the fitted bolts can now be removed without using any force by gently wobbling the rotor blade up and down to keep the screws from canting Carefully pull the rotor blade out away from the rotor hub Repeat steps 2 4 for the second rotor blade The rotor hub itself and its screws may not be dismantled Rotor blades and rotor hub should only be stored and transported in bubble wrap or similar material to avoid damage and scratch NDIA Flight and operation manual G 4 2 Revision 3 0 09 04 2013 41 3 21 3 Assembling the rotor system 1 2 The rotor blades and the rotor hub are labeled with red and black dots Carefully position the first rotor blade with the appropriate marking in the correct side of the rotor hub with the flat side facing down Gently wiggle the blade up and down while doing so to avoid canting the blade Now carefully and forceless slide the screws in from the top while gently
19. and side of the main EMSIS unit in the instrument panel Flight and operation manual G 4 2 Revision 3 0 09 04 2013 76 A21m AMSL_ A BURG AUF IPPE a Soh Taufkirchen EMSIS 4 Flight and operation manual G 4 2 Revision 3 0 09 04 2013 77 Nesis II is a modern Glass Cockpit which is operated by 8 push buttons and 2 rotating knobs The knobs may be also pushed in for additional functions All buttons are labeled in 2 rows A quick push ona button will open a window related to the subject listed on the upper row of the button Pushing the button for 3 seconds will open a window related to the lower label Data downloads and updates uploads can be excuted via USB Stick on the frame of the unit A Mini USB is also available on the unit s frame 5 main displays are available in NESIS II The upper rotating knub will change the the main display The operation manual is delivered with every gyrocopter equipped with this unit 11 3 s 8 5 9 6 10 7 12 2 1 Rotating knob 1 2 Rotating knob 2 3 QNH button 4 NEAR WPT button 5 ROUTE BRWS button 6 LOG LEGEND button 7 HDG ALT button 8 VOLUME BRIGHT button 9 USER button 10 ALARM SETUP button 11 Mini USB 12 USB The screen of the unit illuminates after switching the unit on and the orientation process runs for a few seconds in the background and then the following warnig is displayed Warning This instrument may be used under VFR visual flying rules
20. cess includes one Glass Cockpit which includes the following instruments and functions air speed indicator altimeter vertical speed indicator G Meter acceleration GPS moving map electronic compass engine RPM CHT 2x oil temperature oil pressure fuel gauge fuel pressure fuel computer rotor RPM hour meter OAT flight planner data recorder and much more An optional traffic awareness system ADS B and FLARM may be coupled to NESIS and displays the position of other aircrafts on the moving map NESIS II funktioniert auch im Model Princess als Bildschirm f r eine optionale Bordkamera Flight and operation manual G 4 2 Revision 3 0 09 04 2013 75 7 3 Operation EMSIS is a modern Mini Glass Cockpit which is operated by 5 push buttons A Mini USB is also available for Software Updates The operation manual is delivered with every gyrocopter equipped with this unit The main display shows air speed indicator altimeter QNH vertical speed indicator nick trim position oil pressure oil temperature CHT 2x fuel gauge voltage and hour meter OAT is optional Personal preferences can be set in the setting mode a 7 a EAE 1364 n Emsis Settings 0 Ne Layout 30 l 30 inHg i a Engine Tank Pitch 7 ee ne T Airspeed OP Oil T i Units cHT 46 12 1v 13c 595 5 h Service EMSIS EMSIS An optional Mini Glass Cockpit may be also installed for GPS navigation on the right h
21. cognized through a thorough pre flight inspection For this reason proper care should be taken to be able to avoid crash risks Power plant Check for fluid leaks oil coolant and fuel Check oil level according to engine manual Check lubrication and fuel system hoses for leakages Check electrical connections sparkplug plugs gas and choke pull cables for proper condition Crank the engine by hand watch proper direction to check for any unusual sounds difficult movement and good compression SSS lt S Propeller v Check propeller blades for cleanliness and damages v Propeller blades are properly attached to the hub Spinner is properly attached to the hub v Propeller is properly attached to the engine flange Rotor v Check Titer bolt and safety splint pin Flight and operation manual G 4 2 Revision 3 0 09 04 2013 28 v All hub bolts are in place v No deformation or surface damage Check wear of the rotor brake pad Rotorhead Check pre rotator gears for wear v Check main bearing for ease of motion v Bendix gear axes lubricated and free rotatable v Check safety splint pins for proper seating Rotor control rod Check push rods for proper attachment and wear Check bell crank for ease of motion and wear v Control stick also in back if available is freely movable and has no play in all directions Rudder v Check pedals and cables for free movement and cables for abrasions v Rudder and stabilizers p
22. copter with nose wheel steering Stainless steel frame welded in gas shielded process Two seats in tandem configuration inside an open cabin Liberty or inside an enclosed cabin made of carbon fiber composite with removable hard top Princess Main undercarriage strut equipped with hydraulic brakes Rotor made of extruded aluminum profile Rotor head steering with push rods for 2 heads tilt head or swash plate head Rudder steering with steel wires Rudder and stabilizers made from CFC 1 7 Technical data Length 4 90 m Width 1 85m Heigh 2 80 m Empty weight 265 310 kg Load capacity 190 280 kg Max Take off weight 500 560 kg as motorized Tank capacity 34 68 as equipped 1 8 Rotor Air foil NACA 8H12 Manufacturer Averso Aviation Rotor diameter 8 4 m 8 6 m as equipped Rotor surface area 55 4 m 58 0 m Specific load of rotor surface area 10 1 kg m 9 65 kg m Recommended overhaul exchange 500 h 1000 h 1 9 Propeller 3 types Type 3B FC Windspoon left Manufacturer DUC www duc helices com No of blades 3 Diameter 173 cm Blade material Fiber reinforced plastic Pitch adjustment Ground adjustable Recommended overhaul exchange 800 h Flight and operation manual G 4 2 Revision 3 0 09 04 2013 14 Type Manufacturer No of blades Diameter Blade material Pitch adjustment Recommended overhaul Type Manufacturer No of blades Diameter Blade ma
23. cruising speed 120 km h Maximum permissible speed VNE 167 km h Take off distance Take off ground roll 50 200 m Take off ground roll over 15 m obstacle 300 m Depending on wind speed and weight Touch down distance Touch down ground roll with brakes 0 30 m Touch down ground roll over 15 m obstacle 150 m Depending on wind speed and weight Climb performance One seated 380 kg TOW 6 m s at 100 km h Two seated 450 kg TOW 4 m s at 100 km h Maximum endurance With 1 tank and TOW 450 kg 240 km at economical speed of 120 km h at rotor speed of 370 RPM Endurance with lighter weight is much higher Flight and operation manual G 4 2 Revision 3 0 09 04 2013 46 4 3 Influence of rain amp insects on flight performance In case of a constant loss of power in horizontal flight at constant speed a dirty rotor for e g because of insects may be the reason This may go so far that horizontal flight is no longer possible even with full engine power For this reason the rotor is always to be kept clean The gyrocopter G 4 2 is designed for VFR flights only However flying through heavy rain moisture may reduce and performance performance beside the possibility that electronic equipment may suffer some damage 4 4 Demonstrated maximum crosswind component The maximum demonstrated crosswind is 35 km h 4 5 Noise data G 4 2 complies with the noise abundance regulations in Germany whic
24. e Request permission to taxi if necessary Taxi at a brisk walking speed Do not push pedals unless the aircraft is moving Activate breaks check for effectiveness Continue taxiing at low speed and monitor engine instruments Watch rotor blades strait forward while taxiing Taxi slowly into turns due to risk of tipping Flight and operation manual G 4 2 Revision 3 0 09 04 2013 35 3 9 Preparation for take off and pre rotation Warning Take off direction should be against the wind if possible The maximum crosswind during take off is 35 km h Insure the rotor control stick position while pre rotation otherwise severe damage may be caused Attention During pre rotation the control stick must be held in the forward center position until a minimum of 180 RPM has ben reached otherwise a collision between the rotor and empennage may occur v Hold stick in front center position v Hold break engaged Check engine instruments v Check ignition circuits at 3000 RPM The speed drop should be no more than 150 RPM when turning off one of the circuits v Throttle back to idle position v Request take off permission if required v Line up against the wind on the runway and engage the brakes v Rotor area free v Adjust trim nose heavy to keep the stick in a forward position v Hold the stick in the forward middle position v Quickly but gently push pre rotator pedal forward with foot v Maintain engine RPM at 2500 3000 RPM with t
25. e flown from the front seat and the seat belts in the back must be fastened so they cannot catch on the co pilot s stick if installed in case that the rear seat is not occupied Both seats are equipped with 4 point seat belts which are attached directly to the frame 6 7 Luggage compartments Warning Hard or sharp edged objects may damage the structure of the gyrocopter in turbulent conditions This may have fatal consequences Warning the lugage must be secured in the lugage compartments prior to every flight Flight and operation manual G 4 2 Revision 3 0 09 04 2013 64 G 4 2 is equipped with two luggage compartments under the back seat The maximum load is 5 kg per compartment Hard or sharp edged objects may not be stowed in these compartments 6 8 Doors windows and exits The G 4 2 canopy is attached to the left side of the cabin in flying direction through hinges and has a locking mechanism on the right side The canopy is uncovered above in standard version A windshield of unbreakable PMMA is attached to the front part of the canopy in the standard version Optionally a removable unbreakable PMMA cover fitted in a carbon fiber reinforced frame and equipped with 2 Snap On vents may be used This glass cover is to be installed and secured on the ground as required Embarkation or disembarkation is on the right side of the gyrocopter Glass is to be cleaned only with water and a soft cloth Do not use cleaners with so
26. e made if the oil pressure drops to 0 13 8 7 Rotor icing If more engine power is required to keep the altitude during horizontal flight ice buildup on the rotor may be the cause This can go so far that horizontal flight even with full engine power is no longer possible In this case an altitude with warmer dry air could be higher must be considered or a safety landing must be performed Flight and operation manual G 4 2 Revision 3 0 09 04 2013 111 Flight and operation manual G 4 2 Revision 3 0 09 04 2013 112 Flight and operation manual G 4 2 Revision 3 0 09 04 2013 113 photo stern press V r s 2012 The content of this manual including text pictures and drawings is not to copy without the written permission of Trixy Aviation GmbH
27. ection OK 09 Mounts of the main gear strut right OK 10 Open engine compartment look for damage check 11 Engine cowling and hinges right side check 12 Engine compartment locks check 13 Tank filler cap and hoses right tight 14 Oil level check 15 Engine hoses and wiring right side tight 16 sparkplug caps right side tight 17 Coolant level check 18 Pre rotator drive OK 19 Fuel free from water check 20 Fuel level visual inspection noted 21 Frame welds in engine compartment OK 22 Propeller undamaged tight blade position check 23 Rudder cable tension OK 24 Empennage rudder cable connections tight OK 25 Engine cowling and hinges left side check 26 Engine hoses and wiring left side tight 27 Sparkplug caps left side tight 28 Exhaust system tight 30 Engine cowling closed properly OK 31 Wheel brake left bolts and mounts OK 32 Tire pressure left visual inspection OK 33 Mounts of the main gear strut left OK 34 Vertical rotor control rods secure with no play OK 35 Rotor head moves freely bolts tight 36 Head main bolts are secured check 37 Rotor blades clean and undamaged check 38 Cabin glass clean and undamaged OK 39 Windshield clean and undamaged OK Flight and operation manual G 4 2 Revision 3 0 09 04 2013 31 39 Static air intake free and clean OK 7 40 Windshield undamaged and clean OK 41 Landing lights undamaged and clean OK 42 Pitot tube free and clean check 43 Rotor free OK 44 Throttle rods and wire free moving OK 45 Wheel br
28. ely not reached This can be compensated for by covering a part of the radiator The oil temperature in turn will most probably reach the required 80 C because a thermostat is built into the oil circuit The Bowden cables are to be checked for icing and proper daily wetting with oil Flight and operation manual G 4 2 Revision 3 0 09 04 2013 99 11 6 Operation with closed cabin and cabin heat G 4 2 can be equipped with the optional removable cabin glass Cabin heat is also available as an option It is indicated that the cabin glass must be mounted and secured properly when it is installed on the ground The cabin heating system consists of a heat exchanger and a fan Engine coolant be is used to heat the cabin when allowed to path through the heat exchanger which is installed under the pilot seat A ball valve is installed on the coolant plumbing in the engine compartment to shut off the flow to the heat exchanger in the cabin when the heating system is not used i e summer operations Flight and operation manual G 4 2 Revision 3 0 09 04 2013 100 Flight and operation manual G 4 2 Revision 3 0 09 04 2013 101 12 APENDIX 12 1 Introduction This section contains explanations related to the safe use of installed auxiliary equipment and the use of the gyrocopter 12 2 Minimum equipment The legal documents of the gyrocopter Airworthiness certificate registration radio license must always be on board Personal
29. ending on the CG position Steer course with side rudder pedals Control speed and altitude with engine power Flight and operation manual G 4 2 Revision 3 0 09 04 2013 109 13 8 3 Loss of maneuverability of yaw axis Control course and speed by pitching and rolling Control altitude with engine power 13 8 4 Loss of maneuverability of banking Hold course with side rudders land straight ahead Control altitude with engine power 13 8 5 GEN light The normal electric circuit voltage is around 13 2 V The glass cockpit NESIS II displays a warning once the circuit voltage drops below 12 V The display of the glass cockpit darkens at a voltage around 10 V However the unit continues to operate with a voltage as low as 6 5 V The generator light lamp is used to check the generator If the LED stays on constantly during flight the battery is no longer charged If this occurs all electrical loads beside the glass cockpit the transceiver and the transponder are to be turned off 1 All external units connected to the board net OFF 2 Landing light OFF 3 Navigation light OFF 4 Windshield fan OFF 5 Cabin heat fan OFF If the voltage continues to drop down the pilot must plan a normal landing in the closest airfield and must be ready for a safety landing if he cannot reach an air field At a voltage of 12 V or lower the pilot must consider a safety landing A sudden drop of the electrical circuit will cause all electro
30. evision 3 0 09 04 2013 98 11 4 Maintenance and care The regular care and cleaning the power plant propeller rotor system control systems and frame are important for flight safety This must be executed in intervals depending on weather and use The rotor system is to be cleaned after every flight Grime on the rotor may be removed by clear water and eventually with cleaning additives To do so let grime soak and then flush with plenty of clear water Special care must be taken when cleaning glass Do not use fuel solvents or insect remover to clean glass surfaces under any circumstances The unbreakable material will develop small cracks and will be ruined After cleaning with water make sure all wet parts can dry easily 11 5 Winter operation The cooling system for the cylinder heads of the engine is filled with a water anti freeze mixture which will not freeze in temperatures as low as 18 C Prior to temperatures reaching freezing levels the anti freeze mixture must be analyzed to confirm the freezing level If the temperature drops below the indicated value the anti freeze mixture must either be drained or exchanged with pure anti freeze to guarantee that the liquid will not freeze Due to aging and the dropping anti corrosive properties the coolant must be exchanged every 2 years Further information may be found in the engine s manual During winter operation the operating temperatures for the cylinder heads are most lik
31. exhaust pipe ventilation pipe and air filter against dirt and moist air Flight and operation manual G 4 2 Revision 3 0 09 04 2013 92 Flight and operation manual G 4 2 Revision 3 0 09 04 2013 93 10 Propeller The G 4 2 are factory equiped with a high performance propeller DUC Windspoon which may be adjusted on the ground or an in flight adjustable propeller Neuform CL3 V 70 IP R2 Warning it is recommended to read and follow the instructions given in the manuals of the propeller and the engine Note In case of mishandling or incorrect operation of the propeller the warranties of the propeller and or engine will be void Flight and operation manual G 4 2 Revision 3 0 09 04 2013 94 Flight and operation manual G 4 2 Revision 3 0 09 04 2013 95 11 HANDLING MAINTENANCE AND CARE This section contains recommendations of the manufacturer about the correct handling of the gyrocopter on the ground and about maintenance and care which must be performed to retain the performance and reliability of the gyrocopter The regular care and cleanliness of the powertrain propeller rotor system undercarriage control systems and cowling is the first prerequisite for operating safety It is to be performed in adapted intervals depending on weather conditions and use To avoid the gyrocopter from getting dusty it is recommended to cover it with the optional tarp If no hangar is available it is recommended to store the gy
32. form safety outside landing 13 3 Engine re start during flight Proceed start up as described in section 3 6 with 30 seconds warm up phase until full power can be demanded from the engine Flight and operation manual G 4 2 Revision 3 0 09 04 2013 107 13 4 Smoke and Fire The following procedures are recommended in case of engine smoke or fire Fire at the engine on the ground no direct fire disembark the gyrocopter quickly but safely Fire at the engine during start no direct fire Fly flat turns land as practical even if this was against the wind Fire at the engine during flight no direct fire Emergency landing disembark the gyrocopter quickly Im Flug h her als 100 m Emergency landing leave gyrocopter quickly 13 5 Gliding The speed for best gliding is 100 km h Glide ratio with engine idle 1 4 Glide ratio with engine off 1 3 13 6 Emergency landing a Emergency landing An emergency landing is when an emergency situation occurs during flight which makes an immediate landing necessary e g Fire on board heavy damage or malfunction of the gyrocopter engine failure life threatening condition of the pilot or passenger b Safety landing A safety landing is when the pilot decides to land to avoid an impending emergency situation which has not yet occured e g unexpectet meteorological conditions which do not permit a continued flight unusual behavior of the engine or the pilot got sick
33. ge Fuel fl 18 0 h 254 km i B y i A Average Endur m 25 C CHT Oil Oil Fuel Volt Cur 144Vh 2 20 Warnings will be also displayed on this screen Turning the rotating knob 1 will toggle between the 5 main displays if this screen was not locked with a password Flight and operation manual G 4 2 Revision 3 0 09 04 2013 83 The fourth main display the modern instrument screen This screen is the glass cockpit modern instrumentation display The indicated air speed is displayed on a vertical scale with a dial containing the IAS in numbers The true air speed is indicated at the bottom of the vertical scale The altitude is indicated on a vertical scale on the right side of the moving map with a dial containing the altitude in numbers The vertical speed is indicated on a vertical scale on the right side of the altitude scale The G meter is indicating the acceleration in a white window below the Vertical speed indicator Engine RPM Rotor RPM and manifold pressure are indicated left of the engine data at the left bottom corner of the display IASkm h 320 330 340 350 NMBMPO 20 30 40 50 feet 1 29 3025 i a RAN Sa 7 S AI OR 115 100 4 2 Engine Rotor CHT Oil Oil Fuel Volt Cur Traffic awareness ADS B and Flarm if installed will be displayed on the moving map in this display Turning the rotating knob 2 will result in Zooming in or out in the moving map Turning the rotating knob 1 will toggle between the 5 main disp
34. gh turbulences as this may lead to damage to the main structure as well as uncontrollable flight conditions To operate the aircraft with care on uneven ground and to maintain it accordingly To regularly conduct the checks described in section 3 Operating Procedures before to every flight Flight and operation manual G 4 2 Revision 3 0 09 04 2013 9 Flight and operation manual G 4 2 Revision 3 0 09 04 2013 10 Note Disregard of the instructions contained int his manual will lead to loss of warranty Two models of the series G 4 2 are available Liberty and Princess Liberty is an entry level model which is basically designed to operate with an open cabin This model however can be converted with an optional kit into a gyrocopter to fly with a closed cabin Princess is the top model which is basically designed to operate with a closed cabin This model however can be converted with an optional kit into a gyrocopter to fly with an open cabin Flight and operation manual G 4 2 Revision 3 0 09 04 2013 11 i j 1 5 Side view top view and front view 2 models Note The three sides view is not drawn to scale The model Liberty Flight and operation manual G 4 2 Revision 3 0 09 04 2013 12 a ae Note The three sides view is not drawn to scale The model Princess p Flight and operation manual G 4 2 Revision 3 0 09 04 2013 13 1 6 Description Gyro
35. gine s manufacturer 11 1 3 Daily check The daily check must be done prior to every flight or the first flight of the day if several flights are made as instructed in section 3 3 11 1 4 25 hour check As instructed by the engine s and propellers manufacturers a check of these parts is to be carried out after every 25 hours To keep the gyrocopter manufacturer s warranty the maintenance must be done by an authorized workshop and be loged into the maintenance manual 11 1 5 50 hour check As instructed by the engine manufacturer a check of the powerplant is to be carried out every 50 hours To keep the gyrocopter manufacturer s warranty the maintenance must be done by an authorized workshop and be loged into the maintenance manual 11 1 6 100 hour check As instructed by the engine s and propellers manufacturers a check of these parts is to be carried out every 100 hours To keep the gyrocopter manufacturer s warranty the maintenance must be done by an authorized workshop and be loged into the maintenance manual Flight and operation manual G 4 2 Revision 3 0 09 04 2013 97 11 2 Repairs The operator of the gyrocopter must insure that only original parts are exchanged and documented by an authorized work shop after consulting the manufacturer Only original spare parts may be used Malfunctions which may have been caused by weaknesses in construction are to be reported to the manufacturer by the enclosed for
36. gravity must be within the following limits In X direction between 1900 mm and 2200 mm The pilots mass must be between 65 and 125 kg The valid MTOF must be observed The CG is calculated by the pilot in command in the following table for help see example above Flight and operation manual G 4 2 Revision 3 0 09 04 2013 55 Weight in kg Xin mm X Moment G 4 2 R RT leer Use last valid data Pilot 1190 Co Pilot 1950 Luggage 1880 Fuel weight 2215 Summ CG at take off The last valid empty weight and last valid CG must be taken over from the weighing report section 5 3 and or from the last valid entry in section 5 5 The maximum take off weight may not exceed 450 kg The CG must be between 1963 mm and 2127 mm in X direction The following specifications are to be considered for the empty qyrocopter The CG must be between 2250 mm and 2400 mm in X direction Flight and operation manual G 4 2 Revision 3 0 09 04 2013 56 Flight and operation manual G 4 2 Revision 3 0 09 04 2013 57 6 SYSTEMS DESCRIPTION 6 1 Introduction This section contains descriptions and operating instructions for the gyrocopter and its systems Instructions for the use of auxiliary equipment can be found in the operating manual of the equipment s manufacturer 6 2 Gyrocopter description G 4 2 is a gyrocopter with 2 seats in tandem configuration The model Liberty is designed for operatio
37. h limit a maximum of 68 dB A at the time of its certification 4 6 Tire pressure Main landing gear 3 0 Bar Nose wheel 2 5 Bar 4 7 Service ceiling The service ceiling defines the altitude at which the maximum rate of climb of an aircraft is 0 5 m s with maximum continuous engine power and MTOW The service ceiling with Rotax 912 ULS is 8 000 ft approx 2450 m The service ceiling with Rotax 914 UL is 10 000 ft approx 3050 m The service ceiling with Rotax 912 ULS is 12 000 ft approx 3660 m 4 8 Bolt tightening torques All bolts and nuts are to be tightened to the torques indicated in the maintenance manual In case of doubts the mechanic or maintenance company must contact the manufacturer of the gyrocopter Engine bolts must be tightened to the engine manufacturer s specifications Flight and operation manual G 4 2 Revision 3 0 09 04 2013 47 4 9 Battery generator 4 10 Altitude Air speed Diagram The altitude Airs peed diagram indicates the air speed IAS at a certain altitude at which a safe landing is still possible amp m 5 3 lt q HAUA a A a Air speed IAS in km h Flight and operation manual G 4 2 Revision 3 0 09 04 2013 48 Flight and operation manual G 4 2 Revision 3 0 09 04 2013 49 5 WEIGHTS AND CENTER OF GRAVITY 5 1 Introduction This section contains the maximum load procedure to weigh the gyrocopter current empty mass and empty moment of mass and the method
38. he throttle lever v Build up rotor speed of 200 220 RPM with the throttle and pedal v Release the pre rotator pedal and put feet on both rudder pedals v Pull the rotor control stick back towards body all the way v Incase of crosswind turn rotor sideways as required v Release brake v Push throttle forward until engine reaches maximum power v Adjust trim as required Warning Before accelerating make sure the stick is pulled back all the way towards your body It is life threatening to start acceleration with the stick forward Flight and operation manual G 4 2 Revision 3 0 09 04 2013 36 3 10 Take off Accelerate with full throttle Hold direction using rudder pedals Briefly check engine instruments Climb speed is 90 110 km h IAS As soon as nose wheel leaves the ground push stick forward gently and take off flat on the main gear NNN A 3 11 Climb Adjust trim pressure for comfortable control stick Check engine instruments Landing lights Minimum safe altitude reached Engine power as required also see engine manual 3 12 Cruise Adjust trim pressure as desired for confortable cruise Check engine instruments Auxiliary fuel pump optional off unless needed Adjust engine to cruising speed 80 160 km h at 4000 5500 RPM Periodically check engine instruments and fuel ANNAN NN The permissible maximum speed VNE is 167 km h may never be exceeded During strong turbulences the maneuver speed VA 100 km h
39. ht tank and is connected with the glass cockpit The fuel quantity will show a maximum capacity of 34 with one tank or 68 with two tanks installed The 912 ULS engine is equipped with a mechanical fuel pump An electric auxiliary pump is optional It may be turned on off by a switch in the cockpit in case of fuel pressure loss Flight and operation manual G 4 2 Revision 3 0 09 04 2013 66 67 Revision 3 0 09 04 2013 Flight and operation manual G 4 2 6 10 Electric wiring diagram 3 z lt i i Lz i eS e 335 Fa t jesa 3 oo oh i 3 wh 1 T S S A T S o s _I T a gS gt t 25 5 i 2 H pa lt __ gt 4 J a i j L x E ao Li a ee Fs J 7 m a zi Tii r E s i i p z j gt gt t bs 3 L4 3 be ihe bay e U man saree Flight and operation manual G 4 2 Revision 3 0 09 04 2013 68 69 Revision 3 0 09 04 2013 Flight and operation manual G 4 2 Feng Maan Flight and operation manual G 4 2 Revision 3 0 09 04 2013 70 Flight and operation manual G 4 2 Revision 3 0 09 04 2013 Ja 6 11 Dynamic and static pressure system G 4 2 is equipped with static pressure and dynamic pressure systems The dynamic pressure is taken from the Pitot tube at the nose and guided to the NESIS glass cockpit with a hose The dynamic pressure is required to determine the
40. ial permit is obtained or interstate agreements are in existence Flight and operation manual G 4 2 Revision 3 0 09 04 2013 20 2 2 Flight velocities The data printed here are indicated air speeds IAS and refer to the original mount location of the Pitot tube in the center of the fuselage s nose Vne 167 km h maximum permissible speed Va 100 km h maneuver speed Vx 90 km h speed of best angle of climb Vy 100 km h speed of best ascent rate VCrusie 160 km h maximum cruise speed VApproach 90 km h minimum recommended approach speed Vso 40 km h minimum speed Vcross wind 35 km h maximum permissible crosswind during take off Flight and operation manual G 4 2 Revision 3 0 09 04 2013 21 2 3 Engine limitations Rotax 912 ULS Take off output Recommended continuous output Max Allowed cont power setting Max Allowed take off RPM Cylinder head temperature Oil temperature Fuel quality Alternative fuel Oil type Rotax 914 UL Take off output Recommended continuous output Max Allowed cont power setting Max Allowed take off RPM Cylinder head temperature Oil temperature Fuel quality Alternative fuel Oil type Rotax 912 TI Take off output Recommended continuous output Max Allowed cont power setting Max Allowed take off RPM Cylinder head temperature Oil temperature Fuel quality Alternative fuel Oil type 100 HP 5800 RPM 95 HP 5500
41. ion manual G 4 2 Revision 3 0 09 04 2013 38 3 17 After landing check ANN KN Shes AON a After complete landing push the stick all the way forward In case of strong wind bank rotor against the wind as required Engage rotor brake and push stick all the way forward Taxi with adjusted throttle in a brisk walking speed use wheel brakes if required Initiate turns at low speed using pedals due to risk of tipping Turn off cabin heat optional Adjust ventilation as required Landing lights Secure gyrocopter against rolling with parking brake when at parking position Set rotor brake to park position and secure Warning Taxi with caution and at low speed when turning due to the high risk of tipping Warning The cabin may only be opened when the gyrocopter and rotor are standing still 3 18 Engine shut down NN AA Lights radios and transponder if available OFF Engine RPM to idle Note flight times and turn off main instrument glas cockpit Both ignition switches to OFF Master switch OFF Warning The gyrocopter may not be exited untill the parking break is engaged and both rotor and prop are standing still 3 19 Securing the gyrocopter SNN AN Adjust ventilation as required Attach rotor bag and secure the rotor Hardtop as required Close and lock cabin Flight and operation manual G 4 2 Revision 3 0 09 04 2013 39 3 20 Installing and uninstalling the rotor To transpo
42. ischarge of the condensers via the main coil of the dual ignition transformers 4 The fi sensor 5 is designated for Z ndkreis B the RPM signal l 4 Fee pe mannna T l rt ata T i H a Flight and operation manual G 4 2 Revision 3 0 09 04 2013 91 9 7 Fuel system See section 6 9 for the fuel system 9 8 Power plant maintenance All checks are to be performed according to the maintenance manual of ROTAX newest revision issue Prior to every flight an oil level coolant level and ignition wiring check must be done by the pilot in command Warning The disregard of this information may lead to injury or death Only qualified technicians authorized by ROTAX which have been trained on this engine are permitted to undertake repairs and maintenance work 1 In extreme climates and in case of prolonged standstill the following is suggested to avoid corrosion of valve guides 2 The engine must be running until all temperatures are stable for 5 minutes oil temperature between 50 C and 70 C 3 Shut the engine down and let it cool off 4 Change the oil 5 Let engine run with increased idle speed and with the air filters removed squirt approx 30 cm of preservation oil into the carburetor then shut the engine down 6 Drain the carburetor floater chamber and wet all carburetor joints with engine oil 7 When engine is cold close off all openings
43. lays Flight and operation manual G 4 2 Revision 3 0 09 04 2013 84 The fifth main display the setting screen The user can set in this screen the desired personal settings Downloads and uploads of data are also activated in this screen More information about the operation and the proper use of the unit is found in the separated manual of NESIS Flight and operation manual G 4 2 Revision 3 0 09 04 2013 85 8 TRANSCEIVER TRANSPONDER amp ELT 8 1 Introduction The standard configuration does not include transceiver transponder or ELT The wiring and circuit breakers for this equipment are partially included in the standard version These are options to be ordered directly from the gyrocopter manufacturer and will factory installed 8 2 TRANSCEIVR It is left up to the operator of the gyrocopter to select the type of transceiver to be installed Trixy Aviation will deliver the manual of the radio separately if it is installed in the factory 8 3 Transponder It is left up to the operator of the gyrocopter to select the type of transponder to be installed Trixy Aviation will deliver the manual of the transponder separately if it is installed in the factory 8 4 ELT It is left up to the operator of the gyrocopter to select the desired ELT type to be installed Trixy Aviation will deliver the manual of the ELT separately if it is installed in the factory Flight and operation manual G 4 2 Revision 3 0 09
44. ls of the series G 4 2 12 4 List of supplements Date No Description of supplement Flight and operation manual G 4 2 Revision 3 0 09 04 2013 103 12 5 Incident accident and technical defect report Type of aircraft Serial no Year Model Call sign Engine no Manufacturer Operator Hours flown until damage engine cabin Pilot experience on type hours Description of the damage Description of the incident accident or technical defect Reported by Name Address Phone Fax Date Signature Please send to Trixy Aviation GmbH Eschbuehel 10 F A 6850 Dornbirn Austria info trixyaviation com Flight and operation manual G 4 2 Revision 3 0 09 04 2013 104 Flight and operation manual G 4 2 Revision 3 0 09 04 2013 105 13 EMERGENCY PROCEDURES 13 1 Introduction This section contains checklists and procedures to overcome emergency situations Emergencies due to failure of the gyrocopter or the power plant are extremely seldom as long as a careful pre flight inspection and proper maintenance are undertaken In case an emergency still arises the fundamental guidelines stated in this section should be applied to overcome the emergency As alredy stated earlyer in section 1 2 UL power plants are not certified to aeronautical standards due to the high costs Experience has shown that for this reason above all power plant defects may arise Always be aler
45. lvents The glass must be replaced if it shows cracks or is badly scratched Flight and operation manual G 4 2 Revision 3 0 09 04 2013 65 a 6 9 Fuel system G 4 2 is equipped with one anti explosive tank 34 volume at the right side of the passenger seat in standard configuration Optional auxiliary tank 34 volume may be installed on the left side of the seat In this case both tanks are connected through a hose and both feed the engine simultaneously The tank s is filled from the right side The fuel flow from the right tank to the left tank is rather slow Fast fueling may fill the right tank while the left tank may stay partly filled Slow fueling is recommended when equipped with 2 tanks Wait for 3 minutes before checking the fuel quantity in the tanks A fuel drain with a shut off valve is installed under the frame in front of the main gear strut to check the fuel A transparent hose with markings is also delivered with the gyrocopter to visually inspect the fuel quality as well as the quantity For this purpose the hose is to be attached to the drain valve at one end The other end of the hose is to be held beside the tank filling opening at the middle position The shut off valve is then to be opened and fuel flows from the drain into the hose where the fuel quality can be inspected The fuel quantity may be visually checked with the help of the markings on the hose A standard electronic fuel gage installed in the rig
46. m No welding on the frame is permitted without authorization of the manufacturer Note Repairs may onle be carried out by authorized personell by the manufacturer Only original spare parts may be used Exchanging parts require the written consent of the manufacturer 11 3 Ground handling and road transportation Experience has shown that aircrafts are generally exposed to higher stress on the ground than in the air Through this higher stress on the ground it is more likely to cause severe damage to the aircraft and reduce flight safety This is especially the case with lightly built ULs The gyrocopter s frame is exposed to extreme stress by high G forces through hard landings and taxying on uneven terrain and pot holes For this reason unnecessary road transport should be avoided For transportation drain the fuel tanks and wrap the entire gyrocopter e g with bubble wrap to keep it safe The rotor blades must be packaged with special care because the smallest damage alredy forces the replacement of the entire rotor system In case of road transport on an open trailer the rotor system must be removed as instructed in section 3 21 and all parts must be secured to the trailer by belts The gyrocopter manufacturer also offers enclosed trailers in which the rotor may be left installed during the transportation Such trailers are called mobile hangar and they may also be equipped as a caravan Flight and operation manual G 4 2 R
47. manual G 4 2 Revision 3 0 09 04 2013 58 6 3 Steering systems Rudder steering The rudder controls are conventional pedals and steel wires A set of pedals adjustable for more comfort in the nose of the cabin are connected to the nose wheel control via rods The steel wires controlling the rudder are attached to the nose wheel controls and lead back to the rudder inside the frame Optionally a second set of pedals may be installed for the co pilot which is also connected to the set of pedals in the front via rods This way the rudder can be controlled from both seats Throttle and wheel brake control unit The throttle and the choke are on the left side of the pilots seat The throttle lever is connected to the carburetors via cable controls whereby the back position is idle and the forward position is full power An engine cold start requires choke control For this purpose the choke lever must be pulled all the way back towards the throttle and the throttle is sat to idle After starting the engine a short warm up phase should follow before returning the chocke lever all the way to the forward position Optionally a throttle lever can be mounted left of the co pilot s seat and is then connected to the front throttle lever via rods Flight and operation manual G 4 2 Revision 3 0 09 04 2013 59 Rotor steering The rotor head is controlled by the control stick in front of the pilot s seat The stick
48. moves control rods under the seats These are linked by a fork to 2 vertical rods which connects to the rotor head The limitations for pitch and roll are in the rotor head A change of position of the control stick directly affects the gyrocopter s attitude in the air Vigorous movement of the stick is strictly prohibited The proper way to handle the control X stick is learned during the corresponding course in a flight training school Furthermore the PTT and trim buttons are located on the stick A co pilot control stick is optional and is directly attached to the rods under the seats in the cabin Trimming Electrical operated rack and pinion triming device is installed under the rear seat It is connected to the control rods under the seat through spring coil Actuating the trim button on the control stick trims the gyrocopter for fast to the front or slow flight to the back Optional trim button for the co pilot may also be installed Rotor brake The rotor is slowed down and stopped by a brake which is mounted in the rotor head With the control stick pushed all the way forward the brake pad is pressed on the rotating gear disk in the rotor head and slows the rotor It is absolutely prohibited to activate the rotor brake during flight The rotor brake is only actuated after landing Flight and operation manual G 4 2 Revision 3 0 09 04 2013 60 Hydraulic wheel brakes The hydraulic wheel brake
49. n alternator status indicator 18 Aircraft ID 19 Compass magnetic compass 20 ELT remote control optional 21 Booster reset switch Rotax 914 UL engine only 22 Booster warning lights Rotax 914 UL engine only 23 Controller for constant speed propeller optional OONoOOIRWNM gt Flight and operation manual G 4 2 Revision 3 0 09 04 2013 63 6 5 Undercarriage The undercarriage is made up of the main landing gear with tire size 4 00 6 and the nose wheel with tire size 3 50 4 The main landing gear consists of a fiber reinforced composite strut which is attached to the frame at its middle The tips carry the main wheels which are equipped with hydraulic brakes The nose wheel is held inside a stainless steel fork The fork may be rotated inside a steel holder welded in the front part of the steel frame The nose gear construction is connected through rods to the pedals The main landing gear and the nose wheel are maintenance free The main wheel bearings are to be checked and the front wheel shaft may be greased as a part of the regular maintenance The tires must be changed when in bad condition worn down tread or visible damage The main wheel bolts on the strut must be checked prior to every flight 6 6 Seats and seat belts All seats are made of carbon fiber composite They are appropriately re enforced and are attached to the frame Thus the pilots mass is directly loaded on the frame The gyrocopter must b
50. n fluids Engine oil SAE 10W 40 oil quality API SG E g Shell Advance Ultra 4 or higher Brake fluid DOT 4 or BERINGER Brake fluid Flight and operation manual G 4 2 Revision 3 0 09 04 2013 25 The instructions of the engine manufacturer are to be checked in the engine service manual When using AVGAS as a main fuel alternative engine oil according to the engine manuals must be used For further information please check the engine manuals 2 12 Operation limit labels To be found left of the pilot s seat in the cockpit or the pilot s field of vision Only daytime VFR flights are permitted Aerobatics prohibited Low G maneuvers prohibited Flight under icing conditions prohibited MTOW kg Empty Weight Max PayLoad For further information see the manual Flight and operation manual G 4 2 Revision 3 0 09 04 2013 26 Flight and operation manual G 4 2 Revision 3 0 09 04 2013 27 3 NORMAL OPERATION 3 1 Introduction Section 3 of this manual contains check lists and operating instructions for standard operations Warning It is recommended to read the operation manuals from the engine and propeller manufacturers and to follow the instructions contained in those manuals These informations complete the statements made to engine and propeller in this manual Note In case of misuse or mishandling all warranties are void 3 2 Periodic inspections Almost all technical faults can be found and re
51. n with an open cabin The cabin can be enclosed with an optional kit The model Princess is designed for operation with an enclosed cabin The cabin can be converted with an optional kit for open operation The light canopy is made of carbon fiber composite and opens around hinges on the left side of the cabin It is lockable and may optionally be equipped with removable cabin glass Consequently the gyrocopter can be flown with open or closed cabin The cabin is also made of carbon fiber composite The model Liberty is equipped with a simple windshield made of PC The model Princess is equipped with an integrated windshield in the canopy made of formed unbreakable PMMA material The engine cowling consists of 6 parts made of reinforced carbon fiber The upper parts of the cowling are hinged for easy access to the engine and accessories The gyrocopters frame is made of special stainless steel and is welded under gas shield The empennage structure is made of carbon fiber composite The power plant is attached to the back of the mast via a steel tube ring and 4 vibration dampeners The rotor blades are made of extruded aluminum The main gear strut is made of GFC CFC for flexibility The nose wheel suspension consists of a stainless steel fork and axles which are welded and mounted steerable inside a steel guide at the front edge of the frame The fuel tank is made of rubber fabric in an anti explosive construction Flight and operation
52. nic units in the panel to drop off In such a case the pilot must initiate a safety landing or an emergency landing The pilot should reset all circuit breakers in the panel If this solves the problem the pilot must plan a normal landing in the closest air field The pilot must keep an eye on the voltage and remain alert for a safety or emergency landing A drop of the electrical circuit should not cause the engine type Rotax 912 ULS to quit However the engines of type Rotax 914 UL and Trixy 912 TI are equipped with electrical fuel pumps A breakage of the board net will cause these those engines to quit Flight and operation manual G 4 2 Revision 3 0 09 04 2013 110 The transceivers of type Funkwerk ATR500 or ATR833 indicate also low voltage A blinking B in the upper left display indicates battery voltage lower than 10 5 V Warningg A fault in the board circuit of Type G 4 2 equipped with Rotax 914 UL or Trixy 912 TI may cause the engine to quit Those 2 engine types are equipped with electrical fuel pumps and the shortage of electrical power supply leads to fuel starvation within seconds 13 8 6 Engine instruments oil pressure CHT oil temperature If the indicator is outside of the green range of the instruments the instrument must be monitored closely When the indicator leaves the yellow range of the instrument a safety landing should be performed otherwise the engine may fail A safety landing should also b
53. nus the empty weight of the aircraft including all optional equipment If additional equipment is installed in the gyrocopter which adds to the empty weight the pay load will be reduces It is the pilot s responsibility to assure that the MTOW is not exceeded The maximum permissible range for the center of gravity must not be exceeded The center of gravity range and the empty weight are to be found in section 5 of this manual as well as in the gyrocopter registration documents The reference point for the CG datum is the leading edge of the Pitot tube while the cabin floor is horizontal Pilot s weight The pilot s weight is extremely important for safe flight Max Pilot s weight 125 kg Min Pilot s weight 65 kg Pilots weighing less than 65 kg must carry a belt with weights around their waste All weight combinations of pilot co pilot fuel and luggage are only permissible under consideration of the MTOW Flight and operation manual G 4 2 Revision 3 0 09 04 2013 23 Luggage weight The G 4 2 is equipped with 2 luggage compartments under the passenger seat Only soft luggage may be stowed in these compartments The luggage compartments may not be laden beyond 5 kg each 10 kg total This must be considered in the MTOW of 450 kg Warning Stowing hard and or sharp edged luggage in the compartments is not permitted Doing so may cause damage to the gyrocopter and could lead to a crash during turbulent condition
54. of calculation to determine the flight mass and center of gravity as well as a list of all installed equipment when the gyrocopter was weighed before leaving the manufacturing plant Note The manufacturer must be informed about all alterations and the installation of additional equipment otherwise the warranty may be void Flight and operation manual G 4 2 Revision 3 0 09 04 2013 50 5 2 Weighing procedure The G 4 2 is delivered ready to fly with all installations and additional equipment and accessories The empty weight and the CG are indicated in this manual see section 5 3 To determine the weight of the gyrocopter it is placed on 3 certified scales one scale under each wheel The indicated weights are then added together The mass moments in X directions must be calculated and then divided by the total weight to determine the center of gravity The table in section 5 5 is necessary to determine the center of gravity It contains the weights and the CG of the gyrocopter as well as the CG of occupants luggage fuel and all equipment in the instrument panel The determination of the CG is important and must be done by the pilot in command prior to every flight The permissible CG limits must consider The maximum take off weight must be observed The gyrocopter s operator is responsible to keep the correct and current data in the operating manual Flight and operation manual G 4 2 Revision 3 0 09 04 2013 51
55. optional Circuit breakers Main Switch Mag 1 ignition circuit switch 1 Mag 2 ignition circuit switch 2 Auxiliary Fuel Pump optional Avionics Switch Transceiver Transponder and EMSIS Landing Light Switch optional Navigation Light Switch optional Heating set Switch optional Defroster Fan Switch optional Start Switch engine starter GEN alternator status Indicator Aircraft ID Magnetic compass ELT optional Booster reset switch Rotax 914 UL engine only Booster warning lights Rotax 914 UL engine only Controller for constant speed propeller optional Engine and Rotor RPM Flight and operation manual G 4 2 Revision 3 0 09 04 2013 62 Type PRINCESS The standard princess panel is designed as shown in the illustration below It contains all instruments GPS navigation circuit breakers and switches as well as optional electronic devices Mechanical Air Speed Indicator NESIS glass cockpit main instrument Mechanical Altimeter Transceiver optional Transponder optional Circuit breakers Master switch Mag 1 switch ignition circuit switch 1 Mag 2 switch ignition circuit switch 2 10 Electric Fuel Pump switch optional 11 Avionic master switch optional 12 Ldg Lt switch landing light 13 Nav Lt switch optional navigation and strobe light 14 Heating fan switch optional 15 Ventilation Fan switch 16 Start switch engine starter 17 Ge
56. pilot equipment may include headset with microphone head cover during open operation and sun glasses Proper clothing during winter operation with open cabin or closed cabin without cabin heat must be considered It is recommended to wear an apropriate helmet during operation with open cabin This counts for the pilot and for the passenger co pilot The gyrocopter equipment includes e Safety belts 2 x 4 point belt systems e Type label e Data label and checklist these must be mounted clearly visible To be carried on board e Flight manual Registration certificate Proof or insurance Noise certificate Flight log book Weight and balance report valid for 48 months Avionic inspection protocol valid for 12 24 months Airworthiness certificate Flight and operation manual G 4 2 Revision 3 0 09 04 2013 102 Minimum instrumentation required by law in Germany 1 airspeed indicator 1 altimeter 1 compass Engine instruments 1 rotor RPM gauge 1 fuel gauge G 4 2 is equipped with a mini glass cockpit EMSIS or a glass cockpit NESIS II in the standard configuration It contains the minimum required instrumentation by law and much more In agreement with the registration office the gyrocopter is additionally equipped with a mechanical airspeed indicator an altimeter and a magnetic compass 12 3 Possible optional equipment See the list of accessories on the website of Trixy Aviation www trixyaviation com for both mode
57. ransmission Steel exhaust system 2 mufflers Electric 12V 0 6 kW Alternating current with external Rectifier 12V 20A DC 1 11 Abbreviations and Terminology Velocities IAS CAS TAS Vne Vso Vx Vy VA VCruise Atmosphare ISA OAT PA DA Indicated Airspeed All data in this manual refers to indicated airspeed and does not consider instrument fluctuations Calibrated Airspeed Indicated airspeed corrected to the value of variation related to the construction True Airspeed True speed of the gyrocopter in smooth air and corrected for air density V never exceed Highest permissible IAS which must never be exceeded Minimum horizontal flight speed IAS Speed for steepest possible angle of ascent best ascent angle Speed for best ascent best ascent rate Maneuvering speed Maximum cruising speed International Standard Atmosphere Outside Air Temperature Pressure Altitude Density Altitude Weight and Center of Gravity MTOW Empty Wt CG CGRP Max take off weight Empty weight weight of the empty gyrocopter with full oil container unusable fuel and engine coolant Center of Gravity Reference point for center of gravity datum Flight and operation manual G 4 2 Revision 3 0 09 04 2013 18 Flight and operation manual G 4 2 Revision 3 0 09 04 2013 19 1 OPERATING LIMITATIONS 2 1 Introduction Section 2 contains the operating limits and indicating labels which are necessa
58. rocopter in the optional trailer Openings to the engine fuel system and Pitot tube should be closed off after flights insects birds and such Grime on the gyrocopter may be removed by clean water and eventually with cleaning additives The parking place of the gyrocopter should be dry and protected from sunlight and wind If the gyrocopter is constantly stored outdoors and is exposed to sun wind and rain it will age and corrode quickly 11 1 Maintenance instructions All mandatory inspections e g annual inspections required by low in the country where the gyrocopter is registered must be done and documented in time All other checks and maintenance works are to be performed as instructed in the maintenance manual by authorized aviation service shops Note If the maintenance instructions are not fulfilled all manufacturer warranties are void Flight and operation manual G 4 2 Revision 3 0 09 04 2013 96 11 1 1 Frame propeller and rotor At 500 hours the frame propeller and rotor must be inspected by the manufacturer or an authorized workshop The necessary maintenance work through the course of the TBO is non destructive and will not necessarily lead to exchange of the parts if no damages are found 11 1 2 Engine The power plant must be maintained with the procedures and intervals as written in the engine s manual A complete overhaul TBO must be carried out at 2000 hours at the latest as instructed by the en
59. roperly mounted and not damaged Check end stops with relieved nose wheel v Rudder hinges secure and without play Frame v Check all frame parts for deformations or cracks v Check seat shell and holding fixture for proper seating Undercarriage v Check tire pressures and condition y Check mounts and proper seating of main undercarriage Nose wheel v Lift nose wheel and check for freedom of movement v Check welds linkage and wheel fork for proper seating Wheel brakes Check for function v Check brake fluid level Check wear of brake pads Flight and operation manual G 4 2 Revision 3 0 09 04 2013 29 Pre rotator v Check pulley and belt for wear v As soon as a gentle engagement of the pre rotating mechanism is not possible apply silicon spray to the inside of the belt v Driveshaft is straight and without play Check the gear box for mounts and rotation without play Check clutch lever and the wire system for play Bowden cable v Gas choke and rudder cables move freely and a slightly wetted with oil to prevent freezing Flight and operation manual G 4 2 Revision 3 0 09 04 2013 30 3 3 Pre flight check 01 Both Magneto switches off 02 Master switch off 03 Nose wheel tire pressure visual inspection OK 04 Bolts of the front steering stick OK 05 Bolts of the back steering stick optional OK 06 Canopy hinges and locking system OK 07 Wheel brake right bolts and mounts OK 08 Tire pressure right visual insp
60. rt or store the gyrocopter with minimal space requirements the rotor may be dismounted This must be done with the help of a second instructed person at least to avoid damage to the rotor system or the gyrocopter Warning The instructions of how to handle the rotor system must be followed In case of mishandling the rotorsystem may be damaged and may not be used for flight without inspection by an authorized aviation service work shop 3 21 Handling the rotor system The mounted rotor system is either to be removed by at least two persons at the center of gravity of the blades approximately 2 5 m from the middle or at the center of gravity middle of the entire rotor system Note In case of mishandling of the rotor system all warranties are void Flight and operation manual G 4 2 Revision 3 0 09 04 2013 40 3 21 1 Uninstalling the rotor 1 The gyrocopter must be secured against rolling off with the parking brake on plain ground and the rotor centered lengthwise 2 Standing on a ladder remove the safety split pin and the Titer bolt nut 3 The Titer bolt is to be removed by hand not using a hammer or using force If required wobble the rotor lengthwise to make sure the bolt doesn t cant 4 An instructed person must hold the rotor at the back side of the gyrocopter 5 Lift the rotor system vertically out of the hub with care 6 Remove the rotor system from the gyrocopter off to one side taking care not to d
61. ry for safe operation of the gyrocopter including the power plant standard systems and equipment It contains the tested operating limits which have been recorded during testing as well as those which were mathematically calculated and tested in practical tests The gyrocopter G 4 2 is not designed for aerobatic flight Turns are limited to 60 angle Flights under icing conditions i a high humidity and air temperature lower than 10 C are not permitted It is not allowed to fly during extreme gusty winds or in wind velocities exceeding 72 km h 20 m s 40 knots All the safe weights have been tested in trials according to the construction regulations for ultra light gyrocopters during the type certification process However this does not mean that higher forces are not to be expected especially when operating the gyrocopter on very uneven terrain For this reason it is especially important to maintain it with great care and to exchange the parts that were exposed to extreme and or unusual loads Warning To operate the gyrocopter it is required that the pilot has undergone a professional training and is in possession of a proper pilot s license besides the familiarization process on this specific model Note This gyrocopter does not comply to the rules and regulations of the International Civil Aviation Organization ICAO For this reason it is not permissible to participate in international air traffic unless a spec
62. s 2 5 Center of gravity The center of gravity and the reference point can be found in section 5 of this manual and in the gyrocopter registration documents 2 6 Permissible maneuvers UL gyrocopters are constructed to withstand and fly maneuvers with more than 0 3 G and less than 3 G Warning All aerobatic manouvers are PROHIBITED Flying a turn with more than a 60 angle is PROHIBITED All manouvers which may lead to a partially or completely unburdened state are PROHIBITED Slipping is only permitted if the pilot is trained accordingly and is to be performed with care Extreme slipping is PROHIBITED 2 7 G forces Max Permissible G forces 3 0 G Min continuous permissible G forces 1 0 G Min permissible G forces 0 3 G Negative G forces are not permitted 2 8 Minimum crew One pilot in the front seat The pilot must weigh 65 kg 125 kg Pilots weighing less than 65 kg must wear waste harness with ballast weight 2 9 Operating modes It is only permitted to operate the gyrocopter during day time in VFR conditions unless otherwise permitted by the local authorities Flight and operation manual G 4 2 Revision 3 0 09 04 2013 24 2 10 Fuel Total tank content 34 optional 68 with auxiliary tank Flyable content 32 5 65 with auxiliary tank Fuel quality EN 228 Super min 95 Octane EN 228 Super plus min 98 Octane Alternatively AVGAS 100 LL ASTM D910 Warning A heavy pilot must consider
63. s are regulated by pulling the brake lever which is installed on the throttle control lever The hydraulic brake acts on both main gear wheels at the same time When standing still the wheel brake is to be fixed with the locking button parking brake Optional brake lever is installed for the co pilot on the back throttle control lever and is directly connected to the pilot s brake lever Nose wheel steering The nose wheel is controlled by the pedals for the side rudder via rods Pre rotator control To pre rotate start the rotor the pilot must push a pedal which pulls a wire to actuate a belt clutch drive shafts and a bendix gear The control stick must be kept in the front quarter position with the trim in the most forward position to avoid collision between the rotor blades and the empennage To deactivate the pre rotation process the pedal must be released A slide pre rotator slide pedal type may be used in older models see picture in 6 3 Steering systems Flight and operation manual G 4 2 Revision 3 0 09 04 2013 61 6 4 Instrument panel Type LIBERTY The standard Liberty panel is designed das shown in the illustration below It includes all the necessary instruments and may optionally be equipped with a second Mini Glascockpit EMSIS for GPS navigation CONBDaARwO Nh gt Mechanical Air Speed indicator EMSIS II A Standard B GPS optional Mechanical Altimeter Transceiver optional Transponder
64. source When charging the battery with an external charger it is recommended to use one for iron phosphate While charging the battery must be disconnected from the on board circuit and connected to the charger with the correct polarity The circuit voltage is 12V The battery is to be exchanged if the voltage drops under 8 V 3 6 Start up When the engine is started a person who is authorized and trained to operate the gyrocopter must be in the pilots seat The function of the controls in the cockpit can be found in section 7 of this book Warning This manual does not replace a theoretical or practical training to operate this gyrocopter Disregard to this may result in death or severe injury Only trained and authorized persons e g flight technician and pilots may start the engine Warning The propeller area must be clear with some distance There is a high risk of severe injury and death Flight and operation manual G 4 2 Revision 3 0 09 04 2013 33 Engine start check v Parking break set OK v Throttle idle v Master switch ON v Alternator indicator illuminated Choke for cold engine pulled up v Choke for warm engine pushed down v Propeller area clear v Ignition switches Mag 1 and Mag 2 ON v Lift starter switch until engine fires up max 20 seconds v Avionic switch right after engine starts ON v Check oil pressure immediately after start min 1 5 bar v Choke required push down after short warm
65. st system Starter Generator Type Manufacturer Recommended overhaul Performance RPM Continuous output Torque RPM Nr of cylinders type Displacement Cooling system Lubrication Fuel Electric 12V 0 6 kW Alternating current with external Rectifier 12V 20A DC 914 UL Rotax www rotax aircraft engines com 2000 h 115 HP 5800 RPM 100 HP 5500 RPM 128 Nm 5500 RPM 4 opposed 1211 cms Liquid Air cooling Oil in separate tank Regular unleaded min 95 octane Aviation fuel AVGAS 100 LL 1 electric Pump optional 2 electric pump2 2 CD carburetors 20 4 I h at 75 Dual solid state magnetos Via integrated transmission Steel exhaust system 2 mufflers Electric 12V 0 6 kW Alternating current with external Rectifier 12V 20A DC 912 Tl Trixy Aviation www trixyaviation com 2000 h 130 HP 5800 RPM 113 HP 5500 RPM 145 Nm 5500 RPM 4 opposed 1211 cms Liquid Air cooling Oil in separate tank Regular unleaded min 95 octane Flight and operation manual G 4 2 Revision 3 0 09 04 2013 16 Alternative fuel Fuel supply Fuel air mixture Consumption at performance Ignition Propeller drive Exhaust system Starter Generator Revision 3 0 09 04 2013 17 Flight and operation manual G 4 2 Aviation fuel AVGAS 100 LL 1 electric Pump optional 2 electric pump2 2 CD carburetors 23 0 I h at 75 Dual solid state magnetos Via integrated t
66. ted Always fly so that an outside landing is possible at all times Warning This manual is no substitute for proper theoretical or practical instruction for the operation of this gyrocopter Warning The disregard to the instructions given in this manual may have fatal or life threatening consequences Flight and operation manual G 4 2 Revision 3 0 09 04 2013 106 13 2 Engine failure The following is recommended in case of engine failure During start prior to take off Abort take off procedure hold direction apply brakes while braking the control stick should remain pulled all the way back to assist in the brakeing process The stick must be pusched forward if the rotor is rotating at or below 180 RPM During start after take off land straight ahead 80 m after take off If possible land straight ahead otherwise fly a flat turn and according to wind situation land in the opposite direction During flight with altitude above 100 m look for suitable emergency landing field and prepare for landing consider the wind direction and speed land against the wind or up hill Tree landing or high vegetation Consider top of vagatation as runway flare and land with minimal speed During initial contact with vegetation hold control stick very tight Engine rough loss or power Consider possible carburator icing Change altitude to a lavel where no icing conditions exist Consider fuel pump failiure If required per
67. terial Pitch adjustment Recommended overhaul 1 10 Power plant 3 types Type Manufacturer Recommended overhaul Performance RPM Continuous output Torque RPM Nr of cylinders type Displacement Cooling system Lubrication Fuel Alternative fuel Fuel supply Fuel air mixture Consumption at performance Ignition Propeller drive Exhaust system CL3 V 70 IP R2 Neuform www neuform composites de 3 170 cm Fiber reinforced plastic Adjustable in flight 1000 h TXL3 V 70 R2 Neuform www neuform composites de 3 170 cm Fiber reinforced plastic Adjustable in flight 1000 h 912 ULS Rotax www rotax aircraft engines com 2000 h 100 HP 5800 RPM 95 HP 5500 RPM 107 Nm 5500 RPM 4 opposed 1352 cms Liquid Air cooling Oil in separate tank Regular unleaded min 95 octane Aviation fuel AVGAS 100 LL 1 mechanic Pump optional 1 Electric booster pump 2 CD carburetors 16 5 I h at 75 Dual solid state magnetos Via integrated transmission Steel exhaust system 2 mufflers Flight and operation manual G 4 2 Revision 3 0 09 04 2013 15 Starter Generator Type Manufacturer Recommended overhaul Performance RPM Continuous output Torque RPM Nr of cylinders type Displacement Cooling system Lubrication Fuel Alternative fuel Fuel supply Fuel air mixture Consumption at performance Ignition Propeller drive Exhau
68. tion and certification basis The statutory basis for the operation of an ultra light gyrocopter ULG is regulated in air traffic laws Details are to be obtained from associated documents All rules and regulations contained in these documents must be obeyed The G 4 2 is constructed manufactured and tested according to the construction regulations for ultra light gyrocopters BUT 2001 and Nfl Il 18 09 dated 12 02 2009 and is registered under the identification number 61218 by the responsible German authority DAeC 1 3 Performance data and operating procedure The performance data and operating procedures mentioned in this manual have been determined during the type certification process of this gyrocopter 1 4 Warnings and precautions The following definitions are used for warnings precautions and notes in this manual Flight and operation manual G 4 2 Revision 3 0 09 04 2013 8 Warning means that the disregard of the corresponding procedure leads to an immediate or major reduction of flight safety Note attends to special issues which are not in direct relation to flight safety but are important or unusual Precautionary measures It is highly recommended To regularly read the flight safety briefs in publications e g Aviation magazines aviators pocket calendar notifications for airmen notifications of the official authorities publications from Trixy Aviation etc Not to conduct flights during hi
69. tiy 55 6 SYSTEM DESCRIPTION 58 6 1 Introduction 58 6 2 Gyrocopter explanation 58 6 3 Control system 59 6 4 Instrument panel 62 6 5 Drive train 64 6 6 Seats and seat belts 64 6 7 Luggage compartments 65 Flight and operation manual G 4 2 Revision 3 0 09 04 2013 6 8 Doors windows and exits 66 6 9 Fuel system 68 6 10 Electrical system 72 6 11 Dynamic and static pressure 72 7 GLASS COCKPIT 74 7 1 Introduction 74 7 2 Explanation 75 7 3 Operation 76 8 TRANSCEIVER TRANSPONDER amp ELT 86 8 1 Introduction 86 8 2 Two way radio 86 8 3 Transponder 86 8 4 ELT 86 9 POWER PLANT 88 9 1 Introduction 88 9 2 Engine views 89 9 3 Engine legend 89 9 4 Oil system 90 9 5 Cooling system 91 9 6 Ignition system 91 9 7 Fuel system 92 9 8 Drivetrain maintenance 92 10 PROPELLER 94 11 HANDING MAINTENANCE AND CARE 96 11 1 Maintenance instructions 96 11 2 Repairs 98 11 3 Ground handling and road transport 98 11 4 Maintenance and care operations 99 11 5 Winter operation 99 11 6 Operation with closed cabin and cabin heat 100 12 HANDBUCHERGANZUNGEN 102 12 1 Introduction 102 12 2 Minimum equipment 102 12 3 Optional auxiliary equipment 103 12 4 _ List of installed optional equipment 103 12 5 Reporting damages and accidents 104 Flight and operation manual G 4 2 Revision 3 0 09 04 2013 6
70. weight kg New center of gravity in X direction mm Date Signature Stamp of specialized company Flight and operation manual G 4 2 Revision 3 0 09 04 2013 53 Equipment added kg Equipment removed kg Weight kg New empty weight kg New center of gravity in X direction mm Date Signature Stamp of specialized company Equipment added kg Equipment removed kg Weight kg New empty weight kg New center of gravity in X direction mm Date Signature Stamp of specialized company Equipment added kg Equipment removed kg Weight kg New empty weight kg New center of gravity in X direction mm Date Signature Stamp of specialized company Flight and operation manual G 4 2 Revision 3 0 09 04 2013 54 5 5 Determining the center of gravity Explanation Hereafter is an example see weighing report in section 5 3 Weight in kg Xinmm X Moment Empty weight 272 2320 631040 Pilot 80 1190 95200 Co Pilot 73 1950 142350 Luggage 5 1950 9750 Fuel 20 2215 44300 Summ 450 922640 CG 922640 450 2050 cm from datum The empty mass of the gyrocopter is 272 kg last valid The center of gravity is located 2320 mm from the Pitot tube s leading edge in X direction The X Moment 272 2320 631040 Sum of all weights 450 kg Sum of all X moments 922290 The CG of the loaded gyrocopter in X direction is calculated 922290 450 2050 mm Warning The center of
71. wiggling the blade up and down Slide the washers onto the screws and screw the locknuts on tightening them lightly Afterwards tighten all screws with a torque wrench starting from the inside and finishing with the outer one Repeat steps 2 5 for the second rotor blade Warning A life threatening condition may arise if the rotorsystem is mishandled Note In case the rotor system is mishandled all warranties for the rotor system are void 3 21 4 Installing the rotor 1 The gyrocopter must be secured against rolling off with the parking brake on plain ground and the titer tower centered lengthwise Check mounting direction The titer tower and rotor hub are each marked with colored dots on both sides Lift the rotor blade with an instructed person one at the back and one just behind the rotor hub in flight direction Bring the rotor system closer to the gyrocopter from one side paying attention not to damage the propeller or the empennage Standing on a ladder settle the rotor hub centered into the titer tower Flight and operation manual G 4 2 Revision 3 0 09 04 2013 42 The second person may now release the rotor system Push the main bolt back in from either side with the flat hand Check mounting direction The titer tower and rotor hub are each engraved with corresponding letters on both sides 8 If the main bolt cannot be pushed in the rotor is to be gently wobbled lengthwise with the other hand 9

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