Voyageur II Instruction Manual
Contents
1. GMP accessories and instrumentation CF section 2 06 2 08 DTA MAUT EN VOYAGEUR II Edition June 2005 Section 2 01 Illustrations and dimensions 2 50 1 40 4 172 182 _____ MAUT EN VOYAGEUR II Edition June 2005 Section 2 02 a e Accessories Definition Comments Spats for rear wheels 6 Front fairing Requires wheel spats Skirt with integrated satchels requires front fairing Front bag requires front fairing Simple skirt requires front fairing Parachute GRS 3 450 out of container with attachments for 582 Parachute GRS 3 450 out of container with attachments for 912 912S Dual nose wheel steering controls Dual foot throttle controls Rear Seat Dual ignition controls Towing Kit Hang glider or Banner specify 582 or 912 912S Altimeter 3 hand barometric subscale 280mm Analogue Air Speed indicator 57mm or 80mm Variometer analogue 57mm Pedestal Compass with mount on front bar Compass panel mount 80mm Radio VHF Icom ICA3 Case for radio VHF ICOM ICA3 Antenna whip granted Intercom Lynx external power or Alphatec requires an auxiliary battery radio Filter tyoe Lynx with 2 outlets type RCA requires an auxiliary battery Battery 12V 7A for radio or strobe require a battery bracket Becker Radio Becker Transponder Mode C type Becker radio Becker transponder requires console XXL Voyageur Strobe flash light requires an auxiliary2. INSTRUCTION MANUAL Dynamic VOYAGEUR II AIRFRAME SECTION 0 PREAMBLE Symbols GO DANGER Identifies an instruction which if not observed can cause damage having fatal consequences y ATTENTION Identifies a significant instruction which if not followed can cause very serious damage Reminder Note Underlines a useful instruction which must be observed for the proper use and operation of this COMBO airframe GMP Group Motor Propeller CF see Warning The information and the descriptions contained in this Handbook correspond to the current design That is the airframe as specified at the time of this publication It is in no case exhaustive DTA improves its production constantly and reserves the right to modify the specification the drawing the characteristics the model and or the equipment in the interests of Quality Assurance without incurring obligation The specifications are given in the metric system Note DTA SARL a limited liability company will not be held responsible for errors in translation The original and reference version of this document is in the French language and held by DTA SARL Copyright Details French Version DTA SARL France 2005 English Version DTA ULM Australia Australia 2005 No unauthorized copying of this document can be done with out consent written or verbal of DTA SARL France MAUT EN VOYAGEUR II Edition June 2005 Section 0 02 Sia Page Index
3. remove the windshield 6 screws turn remove the 25 front strut M6 bolt remove the M10 locking bolt from the mast lower the mast bring the trike base s nose wheel to the wing control bar place the two parts of the wing s hang cube around the keel between the centring rings engage the trike base s parking brake the toothed brake lever raise the wing by making it swivel on the control bar centre and stabilize it slip the metal plates on both sides of the wing s hang cube position tighten and secure the M10 hang bolt position the security cable gt make a complete turn around the keel tube pass the cable under the tensioning cables and through the loop of the transverse bars ote the safety cable does not make a turn of the kingpost 1 screw without tightening the M10 wing nut of the wing safety cable no washer secure Pre Flight the Wing CF Wing User s Manual grip the wing by the control bar raise the wing holding it horizontal 2 slip the mast into its housing on the trike frame replace the mast s M10 locking bolt 3 firmly tighten the wing nut and secure place the 25 front strut tighten the M6 bolt and secure front fairing gt place the windscreen and screw the 6 screws 4 turn 4 fold back the back seat Pre Flight the trike frame CF following pages Detaching the Wing Follow the wing attachment procedure in reverse Refolding the wing oee the User s manual for the wing MAUT EN VOY
4. then R for 5 seconds then return the key to BOTH 11 The thermostat installed in the liquid coolant circuit allows the engine to come to running temperature quickly The water radiator is situated at the back under the airframe avoid prolonged stationary engine operation so as not to cause overheating It is recommended that the coolant temperature not exceed 80 C on the coolant temperature gauge If conducting a fully loaded ground run it is advisable that the engine be run for 2 minutes at 3000 rpm to avoid the formation of vapour in the cylinder head follow up by a period of about 10 seconds at 2000 rpm In winter it may be necessary to partially occlude the airflow through the radiator MAUT EN VOYAGEUR II Edition June 2005 Section 3 06 e 912 and 912S Motors 1 Fill the fuel tank Fuel CF Rotax Users Manuel Replace the fuel cap 2 Turn the key on CF above the discharge and oil pressure indicator lamps will come on For the Flydat the discharge indicator lamp will come on and Flydat activates Then to activate the auxiliary electric fuel pump for at least 30 seconds to fill the carburettors bowls 3 Visually verify that both the carburettor butterfly valves are closed This can be accomplished by several movements of the hand throttle lever then foot throttle pedal this will let you verify the correct operation of carburettor butterfly valves A start up with the butterflies wedged in the full throttl
5. Cantileve vertical mast with wing incidence angle limiter and no front strut Large all moving foot pedals Front wheel with suspension brake and polyester mudguard Aerodynamically profiled rear landing gear struts 2 positions adjustable front fork For your security Airframeand rigid passenger support frame constructed with stainless steel TIG welded Engine mount and rear axles 4130 aircraft grade steel Front and rear bucket ergonomic seats carbon composite 6 plys 600x6 aviation tyres Powerful brakes on all 3 wheels Parking brake on all 3 wheels Foot and hand throttles hand throttle protected by pilot seat Oleopneumatic rear landing gear suspension Key ignition For your comfort Forward tilting seats for better passenger access and refueling Ergonomic seats with removable padded seat covers blue or black colours Easy raising of the wing due to specially placed pivot point and mast geometry Padded passenger headrest blue or black Rear passenger footrest Documen t pouch in rear passenger seat Delivery with Rotax toolkit spare fuses butterfly nuts hyper syphon fueling Large capacity Voyageur side bags bue or black 20 litres detachable with carry handles GMP Enngine mount 4130 aircrtaft grade steel TIG welved 75 litres injection moulded fuel tank with fuel gauge Rubber mounted polyester instrument console for integrate radio Ignition swithes engine kill swith starter by key Fuel gauge Instrument console cover blue or black
6. RON 90 or AVGAS 100 LL Radiator coolant antigel anti corrosion for Al block Engine oil SL adapted according to climatic zone oil motor bike 4 stroke semi synth API SG or SG Electric prime pump for the fuel system STD Maximum power output maximum revolutions 59 6 kW at 5800 rom Duration in minutes at maximum power 5 min at 5800 rpm Continuous power revolutions continuous power 58 kW at 5500 rom Maximum governed speed not to be exceed 5800 rom Mini idle 1400 rpm Fuel consumption at 7596 continuous power 16 2 L h Cooling fluid radiator expansion bottle recovery system SID Cooling oils reservoir and radiator STD Cylinder Head Temperature in degree Celsius max 150 optimal 807 100 Oil Temperature in degree Celsius min 50 max 140 optimal 90 110 Oil Pressure in bar min 1 5 bar max 7 bar optimal 2 5 bar Exhaust Gas Temperature EGT in degree Celsius Max 650 optimal 500 7 620 Stainless Exhaust STD Exhaust Silencer Intake Silencer D Electric starter SID Integrated gearbox i 2 27 or 2 43 STD i 22 27 Gearbox Torque limiter Option Propeller Duc three bladed F300 SID Propeller Arplast Three bladed Option Voltage regulator with condenser 22000 MF STD Ignition switches engine kill switch starter by key SID Battery with power switch for the instrumentation SID Fused electric circuit protection SID Tachometer STD analogue Hour meter STD analogue Cylinder Head Temperature Indicator STD analogue O
7. SECTION SECTION 0 SECTION 1 SECTION 2 SECTION 3 SECTION 4 SECTION 5 SECTION 6 DESIGNATION PREAMBLE oymbols Warning PAGE INDEX GENERAL Reminder of Regulations Safety Amateur Construction Description Addresses CARACTERISTIQUES PERFORMANCES Dimensions Illustrations with dimensions Accessories Options Carrying Capacity Calculation Weight Limitations Flight envelope GMP 2 stroke Rotax 582 DCDI 2V GMP 4 stroke Rotax 912 UL GMP 4 stroke Rotax 912 ULSFR Noise Level Over flight Height USE Attaching detaching the wing on the airframe Illustrations Adjustments Pre flight Checks Use of the aircraft Use of the tricycle otarting Rotax 582 motors Starting Rotax 912 and 912S motors Pre take off check Take off Cruising Landing End of flight EMERGENCY PROCEDURES Engine failure Other emergencies Use of a parachute OTHER USES Loads Parachutist Towing GUARANTEES TRANSFER Guarantee Card Transfer of Ownership Card ULM delivery report specimen Card Quality Control 2 09 3 01 3 02 3 03 3 04 3 05 3 06 3 07 3 08 3 09 6 01 6 02 6 03 6 04 DATE UPDATED JUNE 05 JUNE 05 JUNE 05 JUNE 05 JUNE 05 JUNE 05 JUNE 05 MAUT EN VOYAGEUR II Edition June 2005 Section 0 03 SECTION 1 GENERAL This user s manual is supplemented by a Maintenance Handbook and the maintenanc
8. bar Exhaust Gas Temperature EGT in degree Celsius Stainless Exhaust Exhaust Silencer Intake Silencer Electric starter Integrated gearbox i 2 27 or 2 43 Gearbox Torque limiter Propeller Duc three bladed F300 Propeller Arplast Three bladed Voltage regulator with condenser 22000 MF Ignition switches engine kill switch starter by key Battery with power switch for the instrumentation Fused electric circuit protection Tachometer Hour meter Cylinder Head Temperature Indicator Oil Pressure Gauge Oil Temperature Gauge Exhaust Gas Temperature EGT Charge and Oil Pressure warning lights Intake temperature gauge Digital replacement of Analogue instrumentation Carburettor heat intake pre heat by exhaust Carburettor heat intake pre heat by liquid cooling circuit Thermostat on water coolant circuit Thermostat on oil circuit Engine Cap Rotax 912 ULSFR A stroke 4 cyl 1352 cm 10 511 left counter clockwise SID Maximum drop 300 rpm 12V 240W 2 Bing carburettors min RON 90 or AVGAS 100 LL Anti freeze anti corrosion for Al block oil motor bike 4 stroke semi synthetic API SG SG SID 73 5 kW at 5800 rpm 5 min at 5800 rpm 59 kW at 5250 rpm 5800 rpm 1400 rpm 18 2 L h SID SID max 150 optimal 80 100 min 50 max 140 optimal 90 110 min 1 5 bar max 7 bar optimal 2 5 bar Max 650 optimal 500 7 620 SID STD STD i 22 43 Option STD Option STD STD STD STD STD analo
9. battery Oil injection Rotax 582 Cylinder Head Temperature CHT in degrees Celsius Rotax 582 Exhaust Gas Temperature EGT in degrees Celsius Rotax 582 Intake Temperature Rotax 912 912S Carburettor heat intake pre heat by exhaust Rotax 912 and 912S Carburettor heat intake pre heat by liquid cooling circuit Rotax 912 and 912S Thermostat on the liquid coolant circuit Rotax 912 and 912S Torque limiter Rotax 912 Landing lights Hella Xenon Parking Cover according to motor and fairing Control bar sleeves Fuselage Yellow Colour RAL 1028 Options Definition Comment Electric fuel priming pump replaces the manual pump Rotax 582 with starter Electric starter E type gearbox replaces C type Rotax 582 Propeller Arplast three blade replaces DUC F300 three blade Rotax 582 912 912S Propeller Arplast four blade replaces DUC F300 three blade Rotax 582 reduction i 3 47 becomes i 4 Rotax Flydat replaces the standard analog instrumentation Rotax 912 et 912S Console XXL replaces STD console Inertia reel three point seatbelt mount plate replaces passenger and or pilot X Large Satchels Cape to Cape Ill replaces Voyageur STD satchels MAUT EN VOYAGEUR II Edition June 2005 Section 2 03 Carrying Capacity Calculation quide with the following options and accessories Motor gearbox 1 1 ac 912 ms Empty weight Voyageur ll Kg 142 167 pq E po Carb Heat exhaust type 91
10. between the rev drop of both circuits L and R should not exceed more than 120 rpm Turn the key to L for 5 seconds then R for 5 seconds then return the key to BOTH 12 The installation of the optional thermostats three different options on the coolant circuit on the oil circuit or both will allow a faster rise in engine temperature As the water and oil radiators are placed at the rear avoid prolonged stationary operation of the engine as it may cause engine overheating Note it is advised that a Cylinder Head Temperature of greater than 115 never be exceeded If conducting a fully loaded ground run it is advisable that the engine be run for 30 seconds at 3000 rpm to avoid the formation of vapour in the cylinder head follow up by a period of about 10 seconds at 2000 rpm In winter it may be necessary to partially occlude the airflow through the radiator s Note the oil pressure must stabilize in less than 10 seconds An unstable oil pressure oscillating between 1 and 3 bars for example is sign of air in the oil lubrication circuit gt Turn off the engine immediately The propeller should not be hand turned in a direction opposite to its normal rotation direction MAUT EN VOYAGEUR II Edition June 2005 Section 3 07 THE PRE TAKEOFF CHECK This check is carried out at the holding point The PRE TAKEOFF CHECK is an important procedure which should NEVER be overlooked It is a vital moment concentrate on the
11. failure Engine failure on takeoff if an minimum altitude of 100 m could not be obtained immediately pull the Q control bar in gain and maintain a speed close to 80 km h while seeking a place to land immediately in front to you IT IS IMPERATIVE THAT CORRECT GLIDE SPEED BE ATTAINED AND MAINTAINED DO NOT TURN BACK TO THE RUNWAY Engine failure in flight adopt a glide speed of approximately 70 km h preferably with a tail wind As a careful pilot you should always fly in a cone of flight of safety at sufficient altitude with an understanding of the orientation of the wind It is not enough to simply land on the area you have chosen do NOT forget to take into account the possible obstacles that you could discover only at the last minute eg power lines ditches etc and ground related or and mechanical turbulence that may occur Check that your seat belt and that of the passenger is securely fastened The final approach should be made preferably into the wind With the onset of night the approach should be with the sun at the rear if possible Your aircraft will be quiet check that there is nobody on the ground Make a short landing run if possible If you have time you can try to start the engine again whilst in flight Verify that the problem is not from a memory lapse choke lever actuated icing ignition switches off Remember even if the engine starts again remains in the cone of flight safety and land on the area initially
12. plate on the lap section of the belt If the inertia reel is not used a safety pin makes it possible to secure the seatbelt blade to the inertia reel Fastening the Satchels There are four 4 straps with buckles connect each side satchel to the airframe after clipping the buckle the loose length of strap must be securely fasten to a higher section of the strap Note each satchel can be loaded to a maximum of 4 kg Note the satchels disturb the air flow on the radiator and can increase the coolant temperature by a few degrees Fuel tank is an injection moulded tank holding 75 litres and has a fuel quantity gauge There is no fuel cock on the standard model There is NO purge valve The manual pump delivered with the machine makes it possible to purge the bottom of the tank Instrument Power this relates to only those aircraft fitted with an electric starter or 7Ah battery Check that the ignition key is in the OFF position before actuating the electric circuit power switch This switch is protected by a missile type red switch cover The circuit is enabled by toggling the switch forward The electric starter can not be engaged if the Power Circuit is live It is preferable to leave the switch in the ON position as long as the engine is running 5 Note the electric circuit has a condenser After switching the power circuit to the OFF position the discharge of this condenser takes a few seconds during which time the starter can still
13. the propeller and finally that there is nobody in the propeller arc 5 Actuate the choke except when the engine is warm 6 Ensure that the hand throttle control lever is in the closed position 7 The Start gt e Hand start Stand in front of the wing control bar which will be resting against the pilot seat Turn the ignition key to the BOTH position Ensure that you are able to carry out an emergency engine stop if necessary Gentle draw the starter cord until some resistance is felt then pull the start cord very vigorously e Electric starter Sit in the front seat turn the ignition key to the BOTH position CF above then turn the key to the START in order to engage the electric starter Let the key return to the BOTH position Note the starter should not be engaged for more than 10 seconds at a time after which an uninterrupted cooling period of two minutes should be observed 8 Bring the engine to about 2500 rpm and close the choke as soon as possible Make sure that the hand L gt start cord is fully rewound and that the hand start handle is secure against the pulley 9 Keep the engine at 2500 rpm 10 The ignition check is carried out at 3500 rpm the engine revolution drop on only one of the two ignition circuits should not drop by more than 300 rpm the difference between the rev drop of both circuits L and R should not exceed more than 120 rpm Turn the key to L for 5 seconds
14. would be grateful to you if you agree to return the document below to the following address DTA SARL A rodrome de Mont limar Anc ne 26200 MONTELIMAR France T l 433 0 4 75 01 20 83 Fax 33 0 4 75 51 36 72 Former owner Name UE ee SS O Post Zip Code and at DTA Microlight trike base wing Year of issue of 1st Identification Card Number of hours pace a T ea Wing DYNAMIC 1699 DYNAMICI6 480 Seain DYNAMIC 15 99 DYNAMIC 15 430 DYNAMIC 450 Other Demo gnum UPTETT 17777 E cross out incorrect choice See the Identification Card and or cover of your Handbooks New owner Name REIS S PosuZipCodeandCiy Geuy a_i 2 snss n ans Munn MAUT EN VOYAGEUR II Edition June 2005 Section 6 02 DTA ULM DELIVERY STATEMENT Wing DYNAMIC 15 430 16 430 450 Serial N Lnguasskzcuzis deti E kisRi iai Trike Frame COMBO EVOLUTION FEELING VOYAGEUR II Serial N eee7II Motor 503 582 GearboxC E 912 912S Serial N sgmEesS Nr the UNCC FS IOI NC ala we B MOREM ld Em hesidngal EE eee iiia es abide ad rri re c dert QURE nati auteni adero Testify e that the aircraft ULM delivered by ou cece cece cece eee e neces Hm the Distributor is in conformity with the Purchase order e that the commissioning tests of this aircraft ULM was carried out in my presence e tha
15. 2 5 090 NENNEN SERE Coolant circuit thermostat 912 5 060 aC ae NE MEA included NEN CERNI p pu NEN PEE un EE ENT ee Option front strut for cantilever mast EE RE O c NENNEN VERE T 9 py p rs E Alimeter 8hand 8 80mm NENNEN RENE d NENNEN NENNEN pep gu EK Intercom Lynx external mount 060 eS Ses pou y EE RENE NENNEN ea p NENNEN MNT NENNEN EE Landimgligt HellaXenon 1 090 d MEN NENNEN Emptyweigh p Maximum Takeoff Weight NENNEN ERN Carrying Capacity 1 NENNEN MAUT EN VOYAGEUR II Edition June 2005 Section 2 04 DIT Empty weight The empty weight indicated is that of a standard machine complete in flying condition without options flight instrumentation toolkit documents or fuel Shown on the Weight Card given with the machine at the time of the delivery the empty weight indicated is that of the referred machine with the accessories and options defined in the Delivery order and or the final Invoice without toolkit documents and fuel Weight Limits and COG For your safety in all the configurations the maximum empty weight will be lower than DYNAMIC 450 260 kg DYNAMIC 16 430 240 kg DYNAMIC 15 430 240 kg CF WING MANUEL E loads should be carried as close to the COG of the aircraft as possible i e around the back seat The Maximum Take Off Weight MTOW of each wi
16. AGEUR II Edition June 2005 Section 3 01 Sia Power switch MAUT EN VOYAGEUR II Edition June 2005 Section 3 02 DIV m lt a Adjustments Trike Base e 2 positions of the front forks are possible This modification requires the removal of the instrument console e he front seat can be rolled slightly forward by unscrewing the support plugs 10 mm at the maximum It is then necessary that a counter nut be installed Wing e CF Wing Maintenance and Instruction Manual Pre Flight a thorough and methodically pre flight must be conducted before each flight Wing CF Wing Maintenance and Instruction Manual Trike Base Wing nuts tight and secured by the safety pin e M10 wing hang bolt e M10 wing safety cable e M6 front strut sleeve e M10 Mast frame locking bolt Visually check the airworthiness and establish the serviceability of e the mast and the trike base e the fairing of the trike base the windscreen the front removable bag the side satchels NOTE ensure the side satchels and the front bag are closed e the fork the nose wheel and the front suspension NOTE move the machine several revolutions of the wheel in order to check for the absence of suspicious noises e the console and the electrical wire harness loom to the engine e sparkplugs regulator starter relay battery e front and rear seats e seat belts passed through the loops on the seat covers Note for solo flight gt
17. Rotation of propeller Aircraft ULM viewed from behind PTO Double electronic ignition Ignition check at 3500 rpm max difference between circuit 1 and 2 120 rpm Integrated alternator Number of carburettors or electronic injectors Fuel adapted according to climatic zone or conditions 2 stroke oil injected or mixed and rotary valve Proportion oil in mixture advised semi synthetic 50 1 fuel oil mix Separate lubricating system Gear box Oil Radiator coolant Manual priming pump for the fuel system Electric priming pump for the fuel system Maximum power output maximum revolutions Duration in minutes at maximum power Continuous power revolutions continuous power Maximum governed speed not to be exceed Idle Fuel Consumption at 75 continuous power Cooling fluid radiator expansion bottle recovery system Vanne thermostat on water circuit Cylinder Head Temperature CHT in degree Celsius Liquid Coolant Temperature in degree Celsius Exhaust Gas Temperature EGT in degree Celsius Exhaust Steel high temperature paint coating Exhaust stainless Steel Exhaust Silencer Intake Silencer Pull start Electric starter Gear box type B i 2 58 Gear box type C i 3 47 Gear box type Ci 4 Gear box with electric starter type E i 3 47 or 4 Propeller Duc three bladed F300 Propeller Arplast three bladed or four bladed Regulator 3 phases with 2200 MF condenser Ignition switches engine kill switch
18. UM PUdIBeoc sicud iuba dI SIMI A a EUN EIN MEI PRO SS RN E ERE ERU dient eee naa REPRE HEUREUSE DRE R Post Zip Code CMY cS SOUN sae reer net ten ee tera det S MM MM EE yE I jojo N edP IN MOUS Ol Mo A T Encountered problem schema photograph if possible MAUT EN VOYAGEUR II Edition June 2005 Section 6 04 OTs
19. be engaged Note the ignition switch and the light switches are independent of the instrument power switch GO After use remove the ignition key to avoid accidental starting of the aircraft AUSTRALIA It is a Federal Regulation that all Aircraft be disabled when not in use The use of a propeller lock is advised Ignition Switches Light Switches e he keyed ignition switch controls both ignition circuits as well as the electric starter this carried out using a keyed ignition switch by selecting OFF L R BOTH START CF Instrument Power MAUT EN VOYAGEUR II Edition June 2005 Section 3 05 Starting the engine refer to the engine manufacturer s Users Manual e 582 Motors E Fill the fuel tank Fuel Mix Ratio CF Rotax Users Manuel Replace the fuel cap 2 Use the manual prime pump or option auxiliary electric prime pump to fill the carburettor bowls 3 Verify the full movement of the hand and foot throttles verify the correct operation of both carburettor barrels You should hear both carburettor barrels closing together GO Start up at full throttle can cause the aircraft to become uncontrollable and is very dangerous 4 Ensure easy access to the ignition kill switches verify that both the hand and foot throttles are in the idle position verify that the machine can not move park brake engaged and hold the aircraft if necessary Verify that nothing can be sucked into
20. by key Ignition switches engine kill switch starter by key Battery with power switch for the instrumentation Fused electric circuit protection Tachometer Hour meter Water Temperature Gauge Cylinder Head Temperature CHT Exhaust Gas Temperature EGT Rotax 582 DCDI 2V 2 stroke 2 cyl 580 7 cm Clockwise SID maximum drop 300 rpm 12V 155W 2 Bing carburettors min RON 90 or AVGAS 100LL ASTM CEC STD class API TC 2 096 O API GL5 SAE 85W 140 EP Anti freeze anti corrosion for AL block STD Option 48 kW at 6500 rom 6800 rpm 2000 rpm 20 L h STD STD Max 150 optimal 110 130 Max 80 min 65 Max 650 optimal 500 620 STD Option STD STD STD Option Option STD Option Option STD Option STD STD Option Option radio strobe electric starter STD STD analogue STD analogue STD analogue Option Option Manufacturer Data also see the Rotax Maintenance amp Users Handbooks MAUT EN VOYAGEUR II Edition June 2005 Section 2 06 Make type cycle Rotax 912 UL 4 stroke Number of cylinders 4 cyl 1211 cm Compression ratio 9 0 1 Direction of propeller rotation from rear rotation in reverse direction prohibited left counter clockwise Dual ignition STD Ignition check at 4000 rom maximum difference between 1 and 2 120 rom Maximum drop 300 rpm Integrated alternator 12V 240W Number of carburettors 2 Bing carburettors Fuel adapted according to climatic zone min
21. considered so as to determine the possible origin of the engine failure BEFORE continuing the flight NOTE In most countries any accident or any incident affecting or which can affect the safety of an aircraft on the ground or in that country s airspace MUST be declared by the pilot in command to the relevant Authorities Within the accident or any incident report is a specific declaration as to if the accident or the incident caused damage to the aircraft and or injury to people It is often a punishable offence to NOT declare any accident or any incident affecting or which can affect the safety of an aircraft Other Emergencies Propeller Breakage improperly fastened helmets a GPS a camera are some of the many projectiles likely to pass through the propeller arc All removable objects taken on board must be securely fastened to the airframe The helmet clasp the seat GO belt and the seat belt shoulder harness strap are to be checked during the PRE TAKEOFF check The vibration caused by the breakage of or damage to a propeller blade s is extremely violent Reduce power immediately If the vibration does not seem to endanger the engine the carburettors becoming detached or the occupants land safely before cutting the engine Otherwise switch the ignitions to the OFF position immediately Then verify the state of the sail wing before making any other decision Fire on board maintain your airspeed and land as fast as possible S
22. e handbooks specific to the wing the engine and the parachute if necessary These handbooks define the conditions of use as well as the requirements to maintain the airworthiness of this aircraft The Pilot in Command PIC will use this aircraft ULM for sport leisure and air work only is responsible for the state of airworthiness of the aircraft ULM which he pilots js holder of a valid current certificate and or license necessary to the particular activity an endorsement for this type of aircraft will abide by the Regulations and Rules pertaining to Aviation in the country of use and or registration will conform to the recommendations stated in the Maintenance and Instruction manuals relating to this aircraft ULM relating to amongst other things the flight envelope the flight and weight limitations and maintenance requirements will make sure that the aircraft ULM is used in conformity with its identification card and that it has not been modified it is forbidden to modify a whole or a part of the elements composing the aircraft or to add elements by modifying the estimate of weight Will check that the identification registration card is valid and that the identification markings a minimal height of 50 cm for France attached to the under surface of the aerofoil are easily readable will observe the elementary rules of flight safety a thorough PRE FLIGHT PRE TAKEOFF PRE LANDING and PRE MANOEVER procedur
23. e position can GO cause the aircraft to become uncontrollable and is very dangerous 4 Ensure easy access to the ignition kill switches verify that both the hand and foot throttles are in the idle position verify that the machine can not move park brake engaged and hold the aircraft if necessary Verify that nothing can be sucked into the propeller and finally that there is nobody in the propeller arc 5 Actuate the choke except when the engine is warm 6 Position the hand throttle lever a nearly closed position no more than 10 open 7 Sit in the front seat turn the ignition key to the START position in order to engage the starter Note the electric starter should not be engaged for more than 10 seconds after which a cooling period of two minutes should be observed 8 Set the engine revolutions to 2000 rpm The electrical discharge indicator lamp as well as the oil pressure indicator lamp must go out For the Flydat refer to the Flydat Instruction Manual o The oil pressure must become stable within 2 to 4 second between 1 5 6 bars 10 Close the choke gradually then visually check that the choke butterflies have returned to the off position Let the engine idle at up to 2500 rpm until oil temperature gauge indicates 60 C 11 The ignition check should be carried out at 3500 rpm the engine revolution drop on only one of the two ignition circuits should not drop by more than 300 rpm the difference
24. e rope connecting the parachute to the Airframe could be entangled in the propeller The nose down attitude will be even more significant Before impact adopt the safety position Note before starting a flight remove the parachute release safety pin The parachute release procedure must be explained to the passenger GO The parachute release safety pin must be reinstalled after the landing and before leaving the aircraft Note the installation of a parachute is an option Installation of a parachute CF Voyageur II Maintenance Manuel MANE EN VOYAGEUR II Section 3 06 Appendices Safety pin Parachute MAUT EN VOYAGEUR II Edition June 2005 Section 4 02 DTA SECTION 5 OTHER USES Load carriage Reconnaissance Equipment Surveillance Line Inspection The load must be situated close to the back seat those places nearest to the centre of gravity of the aircraft accounting for the MTOW maximum takeoff weight indicated for the wing used The freedom of movement of the wing must be unhindered in particular take care that no load blocks or rubs on the back longitudinal cables The attachment of a video or still camera on the wing tip is acceptable with the proviso that a weight limit of 1 5 kg be observed and that a counter weight of equal weight is mounted in a similar position on the opposite wing tip The wing s inertia will be greatly increased Dropping of parachutists The parachutist must be
25. ensuing flight and carry out the final flight checks A good pre takeoff checklist should include the following Visually check the hang bolt particular the installation and security of the three safety pins at the top of the mast hang bracket safety cable etc and on the wing the tensions of the battens and dive sticks the closing of the under surface inspection hatches the security and presence of the nose cap the installation of the safety pins for the tensioning levers at the nose of the wing and the back of the keel Helmets and seat belts including the optional inertia reel shoulder harness for the pilot and passenger and than all luggage is firmly fastened and secured Ensure full movement of the front steering assembly that the parking brake is not engaged and of the full and free movement of the control bar in both the pitch and roll directions Check both ignition circuits CF Starting the engine and check that the ignition key is in the BOTH position Apply power until just prior to the brake being unable to hold the aircraft There should be NO propeller vibration at all Verity that the volume of fuel carried is adequate reserve for the intended flight The volume of unusable fuel is approximately one 1 litre It is not recommended that even a very short flight should be undertaken with less than 10 litres of fuel Check the Flight Instruments Altimeter ASI etc the engine instruments according t
26. es and fly always with reference to the CONE OF FLIGHT SAFETY etc This document was drawn up in accordance with the current French Regulations relating to ultra microlight ULM aircraft Note Be aware of the Regulations regarding the maintenance of Microlight ULM aircraft and the responsibilities of the Pilot in Command and or owner of a Microlight ULM in the country of registration of the Aircraft DTA SARL will NOT be held responsible Be aware that the ULM in France are not subject to certification Safety Our aircraft ULM are delivered as standard without flight instrumentation We recommend the installation of an altimeter in feet an Air Speed Indicator in the unit of speed measurement of the country of registration and a compass Check with the National Regulatory bodies of the country of use to ascertain the minimum required instrumentation The information given by the instrumentation can be erroneous The engine can break down The movement GO of air by nature is unpredictable It can be sudden and violent and thus compromise the safety of the aircraft To pilot an aircraft ULM is an activity which can involve dangers and which requires adequate training MAUT EN VOYAGEUR II Edition June 2005 Section 1 01 Case of Amateur Construction The DTA Voyageur II airframe with its various motor combinations can be equipped with other weight shift delta wings When manufactured by other than DTA
27. fuel level gauge on the instrument console A landing MUST take place before the remaining fuel volume decreases to less than 5 litres Landing When flying in conditions conducive to icing see above the throttle reduction should be gradually in order to enable the detection of the start of carburettor icing The approach in calm weather should be carried out at 1 3 of Vso that is close to 80 km h Factors such as altitude the temperature the load the atmospheric instability wind conditions are some of the many factors which would suggest an increased approach speed End of the flight e ROTAX 582 Motor Let the engine run at 3000rpm for 2 minutes to facilitate even cooling this should be followed by a short period of 10 seconds at idle before shutting down e 912 and 912S Motors Let the engine run at 3000 rpm for 30 seconds to facilitate even cooling before shutting down For any engine equipped with an electric starter switch the Instrument Power switch to the OFF position and to remove the key of the keyed ignition GO For any Aircraft equipped with a pyrotechnic parachute BRS secure the parachute safety pin Secure the park brake secure the aircraft wing and if possible park the aircraft out of direct sunlight NOTE after engine shutdown the muffler can retain heat capable of causing burns for ten minutes MAUT VOYAGEUR II Edition June 2005 Section 3 09 Z SECTION 4 EMERGENCY PROCEDURES Engine
28. gue STD analogue STD analogue STD analogue STD analogue Option STD Option Option Option Option Option Option STD Manufacturer Data also see the Rotax Maintenance amp Users Handbook MAUT EN VOYAGEUR II Edition June 2005 Section 2 08 Motor Rotax 582 DCDI 2V Rotax 582 DCDI 2V Rotax 912 UL Rotax 912 ULSFR Gearbox C or E C or E Noise Level Reduction Propeller Lm noise level ratio p Max weight Lr corrected max power DUC F300 ou 3 47 Arplast 70 dB 70 dB 3Blade Arplast 4 4 Blade 69 dB 69 dB DUC F300 ou 2 27 Arplast 3 71 dB 71 dB Blade DUC F300 ou 2 43 Arplast 3 70 dB 70 dB Blade Height of pass 150 m 150 m 150 m 150 m Minimum Height of pass for a noise on the ground of 65 dB 253 m 228 m 280 m 253 m Noise perceived on the ground Lh emitted when the aircraft flies at the height h with maximum weight and power calculated according to the figures above by applying the formula Lh Lr 22 Log h H MAUT EN VOYAGEUR II Edition June 2005 Section 2 09 OTA SECTION 3 USE Wing Assembly CF Wing Users Manuel Attachment of wing on the fuselage Note for all the bolts assembled with wing nuts the washer is placed under the wing nut A safety pin makes it possible to secure these nuts s Z 9 9 99 09 0o 0o 0o 0 0 eo Wing facing into wind nose placed on the ground Hock the rear seat forward front fairing gt
29. il Pressure Gauge STD analogue Oil Temperature Gauge STD analogue Exhaust Gas Temperature EGT Option Charge and Oil Pressure warning lights STD Intake temperature gauge Option Digital replacement of Analogue instrumentation Option Carburettor heat intake pre heat by exhaust Option Carburettor heat intake pre heat by liquid cooling circuit Option Thermostat on water coolant circuit Option Thermostat on oil circuit Option Manufacturer Data also see the Rotax Maintenance Handbook amp Users Handbook MAUT EN VOYAGEUR II Edition June 2005 Section 2 07 Make type cycle Number of cylinders Compression ratio Direction of propeller rotation from rear rotation in reverse direction prohibited Twin ignition Ignition check at 4000 rpm maximum difference between 1 and 2 120 rpm Integrated alternator Number of carburettors or electronic injectors Fuel adapted according to climatic zone Radiator coolant Engine oil 3L adapted according to climatic zone Electric prime pump for the fuel system Maximum power output maximum revolutions Duration in minutes at maximum power Continuous power revolutions continuous power Maximum governed speed not to be exceed Mini idle Fuel consumption at 7596 continuous power Cooling fluid radiator expansion bottle recovery system Cooling oils reservoir and radiator Cylinder Head Temperature in degree Celsius Oil Temperature in degree Celsius Oil Pressure in
30. ively impact the behavior Q Caution badly attached powerful motors the presence of badly designed or poorly positioned fairing can of the aircraft and make it uncontrolable Description Fuselage weight shift pendulum two seat tandem Aerofoil flexible delta wing models DYNAMIC 15 430 DYNAMIC 16 430 DYNAMIC 450 Motor 2 stroke water cooled ROTAX 582 D C D l 2V 4 stroke water oil cooled ROTAX 912UL 4 stroke water oil cooled ROTAX 912 ULSFR Manufacturers Address Fuselage and Wing D T A SARL A rodrome F 26200 MONTELIMAR T l 04 75 01 20 83 Fax 04 7551 3672 dta um wanadoo fr Motors ROTAX A 4623 GUNSKIRCHEN AUSTRIA imported by MAD 11 bd Albert 1 98000 MONACO T l 00 377 93 30 17 40 Fax 00 377 93 30 17 60 MAUT EN VOYAGEUR II Edition June 2005 Section 1 02 E SECTION 2 TECHNICAL CARACTERISTICS PERFORMANCE Dimensions Model Overall Lengt of Lenght of Width of VOYAGEURII lenght with Wingspan bari NUS airframe airframe airframe rdg i TES tas DYNAMIC range wing g bare faired bare g g Rotax 582C 2 58 3 02 1 95 2 00 DYNAMIC 15 430 3 00 9 80 3 60 196 kg DYNAMIC16 430 3 00 10 30 3 60 196 kg DYNAMIC 450 3 00 10 20 3 60 201 kg Rotax 912UL 2 65 2 95 1 95 2 00 DYNAMIC 15 430 3 00 9 80 3 60 221 kg DYNAMIC 450 3 00 10 20 3 60 226 kg Rotax 912ULSFR 2 65 2 95 1 95 2 00 DYNAMIC 15 430 3 00 9 80 3 60 224 kg DYNAMIC 450 3 00 10 20 3 60 229 kg Airframe with aerodynamic profiles powder coated white
31. ng should ALWAYS be taken into account The side satchels located on both sides of the back seat can carry 2 x 4 kg The document pocket located at the rear the seat cover of the pilot seat can carry 2 kg The front bag front fairing configuration can carry 3 kg To maintain the fuselage s in flight balance the front seat in all adjusted positions should carry a minimum of 50 kg and a maximum of 110 kg The aircraft should NEVER be flown solo from the rear seat Load Limits Operational Load Limits for the Voyageur fuselage e in flight 4g O 2gin gusts at 472 5 kg e onthe ground 3g at 472 5kg Operational Load Limits of the Voyageur Aircraft ULM CF WING MANUEL MAUT DYN EN Air Speed at MTOW CF WING MANUEL Flight Envelope Limitations CF WING MANUEL e Maximum Angle of Bank 60 e Maximum Pitch 45 The observance of this flight envelope is imperative This Aircraft ULM is NOT designed for aerobatic flight Flight manoeuvres which result in negative load factors are completely prohibited GO Tow release operations are authorized only by a progressive increase in pitch idling engine in straight and level flight nose down at an minimum altitude of 500 meters Beyond the limits bank 60 pitch 45 loss of stability or control structural failure or tumbling can occur MAUT EN VOYAGEUR II Edition June 2005 Section 2 05 Power Unit GMP Brand type cycle A number of cylinders
32. o purge the fuel tank GO Verify that there is FULL and FREE movement of the wing and nothing hinders the wing Use of the tricycle Throttle Pedal when you depress the top of the right pedal forwards the tension exerted on the accelerator cable increases the engine speed and conversely Throttle Control lever when you push the throttle control lever forwards the tension exerted on the accelerator cable increases the engine speed and conversely Choke Lever located on the left side of the base beam between the front seat and the instrument console Chokes are opened by pushing the lever forward Carburettor Heat Lever located on the right side of the base beam between the front seat and instrument console it is differentiated by a yellow marking The carburettor heat is activated by pushing the lever forward If activated always open completely Ground Direction Control when you exert pressure on the right hand side pedal the front steering assembly the wheel turns towards the left So the aircraft ULM moves towards the left and conversely Because of the low stability of this type of machine Powered Ground movement is completely prohibited without the wing attached Note the geometry of the rear wheel axle unit is such that when the tricycle is moved backwards the shock absorbers can be compressed slightly Some forward movement will return them to their initial position Braking all 3 wheels are braked The brake is act
33. o the type of engine oil pressure and temperature cylinder head temperature liquid coolant temperature electrical discharge light extinguished etc NOTE BRS parachute Remove the safety pin Check outside other aircraft traffic the direction of the wind vvv v Verify the correct operation and channel selection of the radio Takeoff e ROTAX 582 Motor Align the aircraft track with that of the runway before increasing the power gradually It is recommended that full power is used during climb out after takeoff Co incidentally a reduction of power causes the fuel oil mixture to be reduced and must be avoided Avoid any quick power reduction or engine shutdown below 150 m altitude e ROTAX 912 and 912S Motors Align the aircraft track with that of the runway before increasing the power gradually 75 power is generally sufficient for pilot only operations Full power is necessary with pilot and passenger or in the case single seat operations when conditions dictate short takeoff areas at altitude heavy load Full power can be sustained for only three minutes Carefully watch the oil pressure and the oil and cylinder head temperatures Avoid any quick power reduction or engine shutdown below 150 m altitude gt No takeoff should be undertaken with a fuel quantity less than 10 litres MAUT EN VOYAGEUR II Edition June 2005 Section 3 08 Cruising e ROTAX 582 Motor According to the load and indica
34. onditions of use of the aircraft given to the purchaser at the time of purchase Not respecting or obeying or infringing the provisions of the Civil Aviation Code of the country in which the aircraft is registered or being flown and the related texts which as a consequence result in an accident or incident exonerates DTA SARL of any guaranteed with respect to the infringing aircraft operator or the aircraft Fair wear and tear of maintenance items are not covered by this guarantee Any modification of the aircraft by the purchaser as well as the replacement of parts by parts not being of DTA origin will involve the forfeiture of the guarantee of DTA SARL unless the replacement has first been approved in writing by DTA SARL The guarantee is limited to the replacement or repair in the workshops of DTA SARL or by a DTA SARL approved workshop The guarantee covering the engine and its accessories the propeller that equipment not built by DTA SARL are covered by the conditions and guarantee by the manufacturers of those products The obligations of DTA SARL stated above constitute the limit of the guarantee MAUT EN VOYAGEUR II Edition June 2005 Section 6 01 Sia Transfer of Ownership We hope that you are fully satisfied with your DTA Microlight and that it enables you to enjoy many hours of flying pleasure In the event of a transfer of ownership or of a second hand purchase and in order to carry out follow up DTA SARL
35. provided the characteristics of the wing weight limitations hang bracket characteristics control bar clearance keel length motor combination etc are compatible with the DTA airframe under consideration The position of the propeller axis requires wings with short keels It is necessary to maintain a minimum distance of 10 cm between the wing structure wing and the propeller blade tip this clearance MUST be in the full range if motion of the Control Bar The characteristics of the Voyageur ll airframe with its various motor combinations accessories and options must also be compatible with limitations imposed by the manufacturer of the wing France in accordance with the Law of 23 September 98 amended by the decree of May 15 2001 the assembler of a wing and a tricycle of different manufacturing origins is considered to be the manufacturer of the aircraft ULM and consequently must ask for a Carte d identification provisoire d ULM in order to carry out the flight tests and to lodge with the Directeur de l Aviation Civile a Dossier Technique de Construction Amateur Australia This aircraft has been accepted as a complete aircraft Alteration or modification is NOT allowed AU CAR 95 32 Worldwide please check with you Regulatory Authority E The amateur builder will assume ALL responsibilities related to any modifications and the flight testing cause interactions between the wing and the airframe which can abruptly and negat
36. seated in the back seat in NO case in the front seat Jump Procedure cut engine best glide soeed make a gentle turn The parachutist jumps to the outside of the turn It is imperative that this procedure be practiced on the ground Glider hang glider or banner towin It is essential the tow release mechanism is able to quickly release the glider or banner even under tension load A weak link rated at 40daN MUST be installed between the Tug aircraft and the glider or banner NOTE BE AWARE THAT EACH COUNTRY HAS ITS OWN RULES AND REGULATIONS REGARDING WHAT CONSITUTES RECREATIONAL AVIATION AND WHAT CONSTITUTES AIRWORK THERE ARE OFTEN LISCENCING REQUIRMENTS FOR THE TWO DIFFERENT ACTIVITIES IT IS IMPERATIVE THAT EACH OWNER PILOT BE AWARE OF THE RULES AND REGULATIONS PERTAINING TO THE OPERATIONS THEY INTEND TO CARRY OUT DTA DOES NOT CONDONE ANY UNLAWFUL AERIAL ACTIVITY MAUT VOYAGEUR II Edition June 2005 Section 5 01 SECTION 6 GUARANTEES TRANSFER Guarantee The Guarantee of DTA SARL a limited liability company on the airframe trike base and the wing is limited to a duration of one 1 year starting from the date on the invoice of the aircraft During delivery the delivery document MUST be filled out and signed by the customer The guarantee only applies within the framework of aircraft usage which conforms to the instructions appearing in the User s manuals or any technical document stating the c
37. t indications relating to Wing tests and Trike tests are in conformity with what the instruments indicate e that have received the DIA SARL Users and Maintenance Handbooks specific to the trike base the engine the wing and the parachute if necessary have read the documentation have accepted and understood the instructions the recommendations and the prohibitions stated in these documents e taken note that the empty weight of the delivered Aircraft Is Kg the MTOW Maximum Take Off Weight is Kg is able to carry Kg Signature of Purchaser eeseeeeenneee B7 m Signature of Witness eeeeeee Print Witness Name J RII MAUT EN VOYAGEUR II Edition June 2005 Section 6 03 DIT Quality Control Card We are very attentive to the comments and remarks of our users and clients We endeavour to constantly improve our products The maintenance of the quality of our manufacture is an abiding concern Many procedural checks have been installed at each stage of manufacture and assembly of your aircraft so that it is in conformity with our stringent quality requirements Nevertheless if you encounter a problem while using your machine no matter what we would appreciate if you would fill out this card and return it as soon as possible We can try to remedy your problem as fast as possible MESRINE ETE UU
38. ted speed straight and level flight can be maintained between 50 and 100 power Avoid rapid and brutal changes in power which generate quick fluctuations in temperature and overly stress the gearbox Although not common carburettor icing can occur with two stroke engines at cruise speed when the atmospheric temperature is between 10 and 10 and that the relative humidity is high e ROTAX 912 and 912S Motors According to the load and indicated speed straight and level flight can be maintained between 40 and 75 of the power Avoid rapid and brutal changes in power which generate quick fluctuations in temperature and overly stress the gearbox Carburettor icing can occur even at cruising speed when the atmospheric temperature is between 10 and 10 and that the relative humidity is high Symptoms include a gradual decrease in engine speed and running DO NOT decrease the throttle but to increase to FULL POWER to allow the carburettors to swallow the ice particles forming in the carburettors then return the throttle to the desired position Option carburettor de icing by exhaust preheat push the carb heat lever fully forward remember all or nothing The power loss fully open will be approximately 300 rpm Option carburettor de icing by heat scavenge from the liquid coolant with this option the warmed air intake is always on The translucent fuel tank carries 75 litres and is equipped with an analogue
39. the rear seat belt must be locked and roller buckles it not used must be secured by the safety pin connected to the body of the roller Hear foot rests fuel tank gt fuel cap secured the fuel line to the engine and that the fuel breather is functioning the fuel filter the hand or electric priming pump the fuel pump the carburettors the air filter s the intake silencer 582 the throttles hand foot double command and the choke cables and sheaths the suspension tie rods and links the ball joints the axle assembly and the rear tyres the suspension arms with their oil and air shock absorbers make Fournal s the wheel spats the motor cap 912 9125 the engine bracket the mounts the engine the radiator s security and free of blockage radiator hoses for both the oil and water the exhaust system springs mounts EGT probe security etc the propeller damage general airworthy state MAUT EN VOYAGEUR II Edition June 2005 Section 3 03 Sia Check the security of the plugs and the levels in e the radiator of overflow container e the oil injection tank if installed 2 temps e the rotary valve lubricating oil reservoir bottle 582 e the oil reservoir 912 912S e the fuel tank sufficient for flight reserve E Note check that the fuel filter and the fuel tank is free of any trace of water or other impurities and also A manual fuel pump is provided with each machine to make it possible t
40. uated by the forward depression of the left pedal A toothed rack enables the setting of the park brake It is set manually and is released by rocking the pedal forwards Seats the front seat rocks forward facilitating passenger access It rests on its frame on two adjustable plugs In its normal upright position forward movement is restricted by the seat belt The rear seat rocks forwards making it possible to remove the wing In its normal upright position forward movement is restricted by the seat belt L The front seat must carry a pilot of greater than 55 kg and lower than 110 kg Pilot and passenger apparel sport or walking shoes ensure good purchase of the feet on the pedals Helmet with visor or safety goggles in good condition clean and without scratches warm clothing not loose fitting gloves if necessary Pay particular attention that scarves and or long hair do not come in contact with the engine or the propeller Being Seating the engine must be turned off when being seated in the rear position take care not to catch your foot in the hand throttle control cable Seat Belts the seatbelts must be positioned at the level of the hips and tightened firmly They must be slipped through the loops located on the seat covers MAUT EN VOYAGEUR II Edition June 2005 Section 3 04 3 Point Seat belts the blade of the shoulder belt must be located exactly on the nipple receptacle located on the adjustable
41. witch the ignitions off before landing Emergency landing ask your passenger to adopt the safety position head lowered onto the arms leaning forward Parachute Use the parachute is the final resort it is designed to save lives or to reduce the chance of serious wounds to the occupants of the aircraft during an emergency These emergencies could include a collision in flight a total loss of control of the aircraft a structural failure or the pilot becoming unconscious without the possibility of the passenger being able to control fly the aircraft There are other circumstances for example an engine failure above a forest and the pilot in command does not believe that an emergency landing can be carried out without serious injury to the occupants MAUT EN VOYAGEUR II Edition June 2005 Section 4 01 Z As far as possible the engine should be stopped before releasing the parachute The parachute release handle is positioned between the front seat and the instrument console on the base beam between the legs of the person in the front seat Although difficult the release handle can be reached from the back seat The release handle is pulled upward CF The parachute manufacturer s Handbook This parachute release sequence should be explained by the pilot to the passenger before flight After a normal opening the aircraft will have a strong nose down attitude If the engine could not be stopped it is possible that the wir
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