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Dyn'Aéro MCR ULC ECOLIGHT HB-WAZ, Aircraft Flight Manual

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Dyn'Aéro MCR ULC ECOLIGHT HB-WAZ Aircraft Flight Manual Download Page 52

 

                                                                       19, rue de l’Aviation, F21121 Darois, FRANCE                                         Ed.2 2009/06/2 

NEXNO0901                              MCR ULC 

Ecolight - 

Flight Manual                                    Page 

50

/

67

 

9.  S

UPPLEMENTARY SYSTEMS AND EQUIPMENTS

 

9.1.  I

NTRODUCTION

 

 

This section presents the appropriate supplementary elements to safely and properly use the 

aircraft with the following optional systems and equipment that are not delivered with the standard 
aircraft (list to be completed by the assembler). 

9.2.  L

IST OF THE SUPPLÉMENTARY SYSTEMS AND EQUIPMENTS

 

Date 

Document N°  

Title of the supplementary element  

  

 

 

 

 

 

 

 

 

 

 

 

 

 

9.3.  S

UPPLEMENTARY ELEMENTS DESCRIPTIONS

 

Tow winch: See Manual: Flug- und Betriebsanweisung für die Schleppseil- 
                                        Einziehwinde mit Kappvorrichtung  
Further Instructions for Handling of the Winch and Glider towing will be developed and added in the 
AFM after the initial flight testing. 
 

Summary of Contents for MCR ULC ECOLIGHT HB-WAZ

Page 1: ... 19 RUE DE L AVIATION F21121 DAROIS FRANCE TEL 33 0 3 80 35 60 62 FAX 33 0 3 80 35 60 63 contact dynaero fr Ref N EX NO 09 01 MCR ULC ECOLIGHT Aircraft Flight Manual 3rd Edition 2009 08 20 ...

Page 2: ...19 rue de l Aviation F21121 Darois FRANCE Ed 2 2009 06 2 NEXNO0901 MCR ULC Ecolight Flight Manual Page 2 67 PAGE INTENTIONNALLY LEFT BLANK ...

Page 3: ...T ALWAYS BE USED IN ACCORDANCE WITH THE INFORMATION AND LIMITATIONS CONTAINED IN THIS DOCUMENT THE USER IS RESPONSIBLE FOR THE USE OF THE AIRCRAFT ENSURING THAT IT COMPLIES WITH REGULATIONS AND INFORMING ANY PASSENGER OF THE LIMITATIONS OF THE AIRCRAFT WITH RESPECT TO ITS AIRWORTHINESS LIMITATIONS BUILDERS DYN AERO FRANCE ...

Page 4: ...19 rue de l Aviation F21121 Darois FRANCE Ed 2 2009 06 2 NEXNO0901 MCR ULC Ecolight Flight Manual Page 4 67 PAGE INTENTIONNALLY LEFT BLANK ...

Page 5: ...E AIRCRAFT HB WAZ S N 363 0 1 REGISTRATION OF THE REVISIONS All amendments to this document must be entered in the table below except weighing data and all cases of approved sections aimed and approved by the Authority responsible for Airworthiness Revision N Affected section Affected pages Date Approval Date Date of insertion Signed ...

Page 6: ...13 2 6 MISCELLANEOUS INSTRUMENT MARKINGS 13 2 7 WEIGHT 13 2 8 CENTRE OF GRAVITY 14 2 9 APPROVED MANOEUVRES 14 2 10 MANOEUVRING LOAD FACTOR 14 2 11 FLIGHT CREW 15 2 12 KINDS OF OPERATION 15 2 13 FUEL 15 2 14 MAXIMUM NUMBER OF SEATS 15 2 15 OTHER LIMITATIONS 16 2 16 PLACARDS 16 3 EMERGENCY PROCEDURES 19 3 1 INTRODUCTION 19 3 2 ENGINE FAILURE 19 3 3 AIR START 20 3 4 SMOKE AND FIRE 20 3 5 GLIDE 21 3 6...

Page 7: ... PLANT 42 7 10 FUEL SYSTEM 43 7 11 ELECTRICAL SYSTEM 44 7 12 PITOT AND STATIC PRESSURE SYSTEMS 46 7 13 MISCELLANEOUS EQUIPMENT 46 7 14 AVIONICS 46 8 AEROPLANE HANDLING SERVICING AND MAINTENANCE 48 8 1 INTRODUCTION 48 8 2 RIGGING AND DERIGGING 48 8 3 AIRCRAFT MAINTENANCE SCHEDULE 49 8 4 AIRCRAFT MODIFICATIONS AND REPAIRS 49 8 5 GROUND HANDLING 49 8 6 CLEANING AND TREATMENT 49 9 SUPPLEMENTARY SYSTEM...

Page 8: ...n F21121 Darois FRANCE Ed 2 2009 06 2 NEXNO0901 MCR ULC Ecolight Flight Manual Page 8 67 10 8 CARE AND MAINTENANCE 54 10 9 PLACARDS 54 11 SUPPLEMENT EDIATEC FLARM ECW 100 55 12 SUPPLEMENT TOW CABLE RETRACTOR WINCH TOST 62 ...

Page 9: ...raft was approved by ____________________________________ Category of Airworthiness ECOLIGHT Basis of acceptance LTF UL 2003 Noise certification basis ICAO Annex 16 Chapter 10 1 3 WARNINGS CAUTIONS AND NOTES The following definitions apply to Warnings Alarms Notes used in the flight manual WARNING Means that a failure to observe the corresponding procedures will lead to an immediate or important d...

Page 10: ...ing tail 2 seats Carbon structure Engine From Rotax 912 to 914 Only 914 will be described here each other engine 912 and 912S will be added as soon as it equips an aircraft Propeller Dyn Aero Prop two three blades fix or variable pitch Span 8 62 m Wing surface 8 31 m Aspect ratio 9 02 Wing loading 54 5 kg m Cabin width 1 12 m Fuel capacity 72 l Overall Length 5 53 m Height 1 53 m MAC 22 40 1 5 THR...

Page 11: ...tions except in calm air and then only with great cautions VA Manoeuvring speed 180 km h Do not apply abrupt or full range control deflections beyond this speed because under certain conditions the Aircraft might be exposed to excessive loads VFE Maximum speed allowed with flaps extended 140 km h Do not exceed this Velocity with Flaps Extended Note The maximum speed of the safety parachute deploym...

Page 12: ...tes 39 9 Hg 1350 hPa Continuous 35 4 Hg 1200 hPa Engine RPM Maximum Take off max 5 minutes 5800 RPM Continuous 5500 RPM Cylinder Head Temperature Maximum 135 C Oil Temperature Maximum 130 C Oil pressure Minimum 0 8 Bar Maximum 7 Bars Fuel pressure Minimum 0 15 Bar Maximum 0 35 Bar Octane grade of fuel Automotive Gasoline unleaded min 95 RON or AVGAS 100LL Oil quality Motorcycle oil of a registered...

Page 13: ...r model 3 S N 328 only RPM 0 to 1500 1500 to 1800 1800 to 5500 5500 to 5800 5800 Oil temperature C 50 C 50 to 90 C 90 to 110 C 110 to 130 C 130 C Cylinder Head C 60 C 60 to 80 C 80 to 110 C 110 to 135 C 135 C Temperature Manifold pressure In HG 0 to 35 4 in Hg 35 4 39 9 in Hg 39 9 in Hg Oil Pressure Bar 0 8 Bars 0 8 to 2 Bars 2 to 5 Bars 5 to 7 Bars 7 Bars 2 6 MISCELLANEOUS INSTRUMENT MARKINGS Fue...

Page 14: ... M A C M A C 960 mm reference datum 13 5 mm ahead of left wing leading edge 2 9 APPROVED MANOEUVRES NORMAL CATEGORY AEROBATIC FLIGHT IS PROHIBITED INTENTIONAL SPINS ARE PROHIBITED 2 10 MANOEUVRING LOAD FACTOR 4 2 g 2 0 0 g with flaps down 225 250 275 300 325 350 375 400 425 450 475 500 20 25 30 35 40 mass kg of MAC Centre of Gravity range with parachute without parachute ...

Page 15: ... Minimum flight crew is one pilot Two people onboard maximum 2 12 KINDS OF OPERATION VFR DAY 2 13 FUEL For S N 326 328 389 For S N 349 351 362 363 Total fuel 73 L 81 L Usable fuel 72 L 80 L Unusable fuel 1 L 1 L Fuel Octane grade approved Unleaded Automotive Gasoline min 95 RON or avgas 100LL 2 14 MAXIMUM NUMBER OF SEATS Two ...

Page 16: ... 16 PLACARDS Minimum 3 cm high placard ECOLIGHT AIRCRAFT must be placed next to each cabin opening 2 16 1 Flight limitations and airworthiness placards Sized 100 20mm and so that both pilots can easily read it the following placard Sized 75 35 and so that both pilots can easily read it the following placard ID Plate 100 50mm 100 50mm Inox HB XXX Height 15mm Depth 1mm In the back frame of the lugga...

Page 17: ...e paragraph 2 5 1 2 16 4 Control system markings Each control system other than main flight control systems is marked in order to explain its function and operation mode This is an overview of the markings you should have on your aircraft if it is equipped with the corresponding device It includes lights switches breakers handles and levers markings ...

Page 18: ...n luggage compartment MTOW 472 5 kg or 450 kg w o parachute Fuel tank filler To be stuck around the fuel hole filler Either with 72 or 80 L depending on the aircraft S N Inside diameter 80 mm Oil tank filler To be stuck on the hidden side of the oil filler door Water tank filler To be stuck on the hidden side of the coolant filler door Placards and Markings for Aerotow See section 10 ...

Page 19: ...rcraft engine or other systems is very rare However should an emergency occur the procedures described in this section of the manual should be adopted 3 2 ENGINE FAILURE 3 2 1 Engine failure on take off run If there is enough runway length remaining Fully reduce power and apply brakes If there is insufficient runway length remaining Fully reduce power Brake hard Fuel valve closed Magnetos OFF Mast...

Page 20: ... a forced landing 3 3 2 Dive restart If the altitude is sufficient to attempt to restart the engine minimum altitude lost 1500 feet Nose dive as explained Airspeed 250 km h Fuel valve open Electric pump on Throttle setting 1 2 Magnetos BOTH If the motor does not start plan to make a forced landing 3 4 SMOKE AND FIRE 3 4 1 Fire on engine start Continue starting the engine or leave it running if it ...

Page 21: ...ventilation to eliminate the smoke In case of an electrical fire recognised by the smell of burning insulation Reduce cabin ventilation Master off Charge breaker pulled LAND QUICKLY 3 5 GLIDE Recommended air speed 134 km h Flaps 0 Glide ratio 16 3 6 LANDING EMERGENCIES 3 6 1 Planned forced landing with engine stopped Choose a suitable site and report your position by radio Best glide ratio airspee...

Page 22: ... the situations that can justify the use of the safety parachute within the best conditions If necessary Minimum altitude of parachute deployment 200m 656 ft above flight surface Maximum speed of parachute deployment 270 km h Safety pin removed Engine off Pilot and copilot check safety harness attaches Parachute handle take with full hand and pull firmly Pilot and copilot protect faces and group m...

Page 23: ... be possible Monitor oil pressure The orange caution lamp of TCU turbo control unit is blinking Limited flying operation as possibly wastegate does not close any more NOTE A minimum performance of approx 66 kW remains available Any exceeding of the max admissible operating limits and or blinking of orange caution lamp must be recorded by the pilot in the logbook stating the duration exact time and...

Page 24: ... duration exact time and duration of switching off 3 9 7 Red boost lamp of TCU permanently illuminating The maximum admissible boost pressure was exceeded Reduce speed and boost pressure manually to be within the operating limits Limited flying operation as boost pressure control is no more or insufficiently possible ATTENTION The boost pressure will not be reduced automatically In case of exceedi...

Page 25: ...age in the airbox Reduce speed and boost pressure manually the be within the operating limits Limited flying operation as this may indicate that boost pressure control is no more or insufficiently possible and may affect engine performance In case of blinking of the orange caution lamp of TCU this has to be recorded by the pilot in the logbook starting the duration exact time and extent of exceedi...

Page 26: ... section 4 2 DAILY INSPECTION 1 CABIN Seats adjusted locked Safety harness attachments checked Primary wing attachment pins in place safety pinned Front wing fixings in place secure Rear wing fixings in place secure Controls free Magneto contacts off cut Master switch on Fuel level checked Fuel filler cap in place locked Master switch off Documentation all present and correct Weight and balance in...

Page 27: ...riage brakes tyre inflation checked 6 ENGINE COWLS Cowl fixing screws checked Air vents clean unobstructed Propeller spinner screws checked no play or looseness Propeller clean good condition Oil level checked Fuel drain Check for absence of water and impurities operate and check Exhaust pipe fixings checked Fuel tank air vent beneath fuselage clean unobstructed Manually turn the engine until you ...

Page 28: ...o another one may harm the system Therefore the battery has to be fully charged before flying 4 4 2 Cold engine start ROTAX Master on Function Test TCU 2 lamps illuminated 1 2 sec checked Fuel valve check function open Electric fuel pump on Throttle setting idle Choke pull fully Propeller area clear Magneto contacts BOTH Starter operate when ready As soon as the motor starts Choke push RPM 1 600 r...

Page 29: ...400 checked Throttle 2 000 rpm 4 4 6 Pre take off checks Magneto contacts BOTH Controls full and free Cabin canopy harness checked Oil pressure and temperature within green sector Trim checked Altimeter checked Fuel valve open Fuel quantity checked Electric fuel pump on Flaps Check full extension and set to take off position Compass checked 4 4 7 Take off RPM at full throttle 5 500 rpm checked MP ...

Page 30: ...inimum rpm 2 400 rpm 4 4 11 Approach Cabin harness tight Electric fuel pump on Flaps under 140 km h extended Altimeter set 4 4 12 Final Flaps 30 Park Brakes off Airspeed 85 km h 4 4 13 Go Around Airspeed 85 km h Flaps retracted Climb airspeed 120 km h 4 4 14 Post landing checks Flaps retracted Electric fuel pump off 4 4 15 Engine Stop Parking brake on Avionic switch off Strobe light off Magneto 2 ...

Page 31: ...tandardised air speeds stall speeds take off performance and supplementary non approved information The information given in the diagrams was obtained from flight tests with an aircraft and an engine in good condition and in the hands of an average pilot 5 2 APPROVED DATA 5 2 1 Airspeed indicator system calibration 100 120 140 160 180 200 220 240 100 120 140 160 180 200 220 240 IAS km h CAS km h ...

Page 32: ...e Pressure Ground over Ground Over Ground over Ground over Ground over Altitude Run 15 m Run 715 m Run 15 m Run 15 m Run 15 m obstacle obstacle obstacle obstacle obstacle feets m m m M m m m m M m 0 138 206 149 221 160 235 169 248 178 260 2000 166 252 181 275 195 296 208 317 221 337 4000 200 307 219 338 237 369 255 399 272 429 6000 240 373 264 414 288 456 311 467 333 539 8000 290 454 321 509 351 5...

Page 33: ...un 15 m obstacle obstacle obstacle obstacle obstacle feet m m m M m m m m M m 0 208 430 225 459 240 485 255 510 268 533 2000 250 526 272 569 294 611 314 652 333 691 4000 300 640 329 701 357 761 384 821 410 879 6000 361 776 398 858 433 941 468 1023 502 1104 8000 436 946 483 1055 528 1165 573 1275 617 1386 Flaps position 30 For every knot of headwind reduce distances by 1 For every 2 knots of tailwi...

Page 34: ... 3h 10 9000 31 5000 208 242 20 3h 10 Power setting 55 Altitude Power IAS TAS Fuel flow Endurance ft MF RPM km h km h l h without res 6000 28 4300 195 217 16 4h 00 9000 28 4300 195 227 16 4h 00 5 3 2 Effect of rain and insects on aircraft performance flying and handling qualities Decrease the performances by 4 5 3 3 Cross wind demonstrated performances 35 km h 5 3 4 Noise data This airplane is cert...

Page 35: ...t and balance calculation procedures and a complete list of the equipment available on the aircraft are included in last section of this Chapter 6 2 WEIGHT BALANCE REGISTRATION AND LOADING ENVELOPE 6 2 1 Loading envelope M A C 960 mm Reference datum 13 5 mm ahead of left wing leading edge 225 250 275 300 325 350 375 400 425 450 475 500 20 25 30 35 40 mass kg of MAC Centre of Gravity range with par...

Page 36: ...e actual empty weight and moment arm of the Aircraft Also update if possible the actual moment arms of movable weight by weighing your Aircraft refer to MBENOPP Weighing procedure Calculation method Note movable weights in fill above chart Compute total mass Multiply weights and corresponding moment arms and note the results in Moment column Compute the moment sum Divide the moment sum by the tota...

Page 37: ...Weight Arm Moment kg m mkg kg m kg Initial basic empty weight record 292 0 200 58 4 Examples Far forward C G one light pilot fuel Weight kg Arm m Moment kgm Empty Weight 292 0 2 58 4 Pilot 70 0 7 49 Passenger 0 0 7 0 Baggage 0 1 15 0 Fuel 56 0 02 1 1 Total 418 108 5 Far rearward C G heavy crew max luggage and near empty tanks Weight kg Arm m Moment kgm Empty Weight 292 0 2 58 4 Pilot 78 0 7 55 Pas...

Page 38: ...m Bord d attaque moyen avg leading edge Cote droit Coté gauche Géometrie mm D1 627 mm D1 mm D2 522 mm D2 517 Pesée TRAIN PRINCIPAL Main L G ROUE GAUCHE L ROUE DROITE R TOTAL 1 Masse à vide Empty 78 111 113 5 302 5 kg Centrage Calcul masse maxi 65 203 7 203 7 472 5 37 8 VOIR EGALEMENT DEVIS DE CENTRAGE page 2 4 Visa Norbert LEOTTE INVENTAIRE DETAILLE page 3 4 PHOTO TABLEAU DE BORD page 4 4 immatric...

Page 39: ...ote 70 0 700 49 0 0 0 Copilote 68 0 700 47 6 Bagage 5 1 150 5 8 Essence avant 27 0 020 0 5 Masse totale 472 5 kg Somme des moments 171 6 kg m Somme moments Masse totale 0 363 m 37 8 Ref BA moyen voilure annexe à la fiche de pesée p 250 300 350 400 450 0 2 0 22 0 24 0 26 0 28 0 3 0 32 0 34 0 36 0 38 0 4 Masse Kg Bras de levier m Limites de centrage Dyn Aéro 29 04 2009 ...

Page 40: ...nwheel Dyn Aéro ZMAEQ5W00 Brakes hydraulic Dyn Aéro ZMAEQ9Q00 C Electrical Systems 12V Voltage regulator Dyn Aéro ZMAEL4P00 Batterie Dyn Aéro ZMAEMB800 Batterie relay Dyn Aéro ZMAEM4200 Starter relay Dyn Aéro ZMAEM1400 Flap electric motor Dyn Aéro ZMAEQJ800 Elevator trim motor Dyn Aéro ZMAEQ9R00 Fuse Breakers ETA Switches ETA Strobe lights Dyn Aéro ZMAIN7A00 D Instruments Air speed indicator Winte...

Page 41: ...s Pilot Operation Handbook V1 0 G Auxiliary Equipment Tow winch Dyn Aéro ZMAEQWA00 H Avionics Autopilot Com Dyn Aéro ZMAIN2G00 Com Antenna Dyn Aéro ZMAINR000 Transponder Mode S Dyn Aéro ZMAIN5L00 Transponder Antenna Dyn Aéro ZMAINRX00 J Fuel System Maintank 80 l Dyn Aéro Fuel gauges Dyn Aéro ZMAIN6700 Fuel selector Dyn Aéro ZMAEQF700 Fuel gascolator AC2 10564 Main fuel pump Dyn Aéro ZMAEM0400 Aux ...

Page 42: ...rs consist of wood carbon sandwich construction with foam ribs glued to a carbon fibre sheet serving as wing skin The ailerons and flaps are constructed the same way The wing fuselage connection is made with six bolts The two main bolts hold both wings in the spar tunnel Each wing has two fixings one on the leading and one on the trailing edge 7 2 3 Tail plane The Rudder and Elevator are built the...

Page 43: ...eed indicator P Electric Fuel pump switch B EFIS Dynon D10A Q Master switch C Slip Indicator R Flash Switch D Altimeter S Ignition switch E Oil Pressure and Hour meter to the left T Fligt Time Counter F Low voltage warning lamp U FLARM ECW100 G Boost warning lamp V VSI H TCU caution lamp and Fuel pressure warning light to the right W Flaps switch I Winch X Parachute handle J Compass Y Oil temperat...

Page 44: ...date different body sizes the back can be adjusted in height and secured with spring loaded pins Harness are 4 points type 7 7 BAGGAGE COMPARTMENT The baggage compartment is located behind the 2 seats Secure baggage s and respect weight balance Max shelf load is 15 kg 7 8 CANOPY 7 8 1 Lock and unlock CANOPY from inside The CANOPY is locked by pulling the levers on each side of the fuselage To unlo...

Page 45: ...nel System From the tank to the carburetors the fuel takes the following way see next picture Tank Shut off Valve Gascolator Electric auxilary pump Electrical main pump float chamber of carburetors Before the carburetor a return line leads to the top of the tank and a pressure switch is installed Ventilation and overflow The tank ventilation is on the front top of the tank 7 10 1 Fuel schema 7 10 ...

Page 46: ...gauge in the cockpit 7 10 4 Fuel pressure A fuel pressure probe is installed forward the carburetors 7 11 ELECTRICAL SYSTEM 7 11 1 Electric schematic with circuit protection 7 11 1 1 Alte rnator Voltage regulator Ignition GEN 22000uF Regulator G G L C R B 1A 25A 14V BUS Master switch 3A x2 Batt 12V 3A IS BOX Starter shilded shilded Master Relay Start Relay Magnetos selector Fuel Pump 1 5A 1uF 100V...

Page 47: ...ue de l Aviation F21121 Darois FRANCE Ed 2 2009 06 2 NEXNO0901 MCR ULC Ecolight Flight Manual Page 45 67 7 11 1 2 Ele ctrical components diagram 7 11 1 3 TC U electric diagram RPM Ftc 1A Flight Time Counter ...

Page 48: ...t switch UP BUS 14V 5A Nose down Relays 2x left right Flaps switch Down Nose UP 15A Flaps 7 12 PITOT AND STATIC PRESSURE SYSTEMS The total pressure is measured below the left wing The static pressure is measured by the two static holes one on each side of the fuselage behind the seats 7 13 MISCELLANEOUS EQUIPMENT N A 7 14 AVIONICS See schema Electrical components diagram For details Manual Filser ...

Page 49: ...viation F21121 Darois FRANCE Ed 2 2009 06 2 NEXNO0901 MCR ULC Ecolight Flight Manual Page 47 67 Manual EDIATec ECW100 and FOCA approved AFM Supplement included Manual of the Tow Cable Retractable Winch TOST included ...

Page 50: ...st be applied 8 2 RIGGING AND DERIGGING Wings assembly keep ready the two bolts and the security pins and a screw driver keep ready all 4 fittings Insert right wing first Right wing spar goes in front of left wing spar Support right wing Mount flaps control bar and secure Insert left wing with same procedure as above Support left wing Insert bolts through both spars and secure with pins back of sp...

Page 51: ...e all modification or repair which can change the aircraft Airworthiness 8 5 GROUND HANDLING Towing The aircraft is most easily maneuverd by pulling it by its propeller near the center Parking Parking brake on off for hangaring Canopy locked Canopy cover advised Main landing gear wheels choked 8 5 1 Ground fixing Wing attach fittings using 6 mm diameter captive nut can also be installed 8 6 CLEANI...

Page 52: ...l systems and equipment that are not delivered with the standard aircraft list to be completed by the assembler 9 2 LIST OF THE SUPPLÉMENTARY SYSTEMS AND EQUIPMENTS Date Document N Title of the supplementary element 9 3 SUPPLEMENTARY ELEMENTS DESCRIPTIONS Tow winch See Manual Flug und Betriebsanweisung für die Schleppseil Einziehwinde mit Kappvorrichtung Further Instructions for Handling of the Wi...

Page 53: ...00 N The length of the rope should be between 35 m and 60 m Mass of Gliders Gliders up to 820 kg MTOW are permitted with one person in the towplane Gliders up to 650 kg MTOW are permitted with two persons in the towplane instruction Towingspeed Flaps Setting Modern plastic gliders are best towed at 110 km h and flaps retracted or T O position Water loaded gliders in turbulent air should be towed a...

Page 54: ...the aircraft 10 5 NORMAL PROCEDURES Pre flight Inspection Aerotow The aircraft might lift off before the glider It is mandatory for the aircraft pilot to accelerate close to the ground until the glider is well above its minimal speed and not to initiate the climb earlier 10 6 PERFORMANCES Take off Take off distance s1 rolling distance s0 distance over the 15 m obstacle on a level shortcut and dry ...

Page 55: ...50 400 450 500 550 600 650 700 750 800 820 Towplane Glider Weight kg 770 820 870 920 970 1020 1070 1120 1170 1220 1240 Vz m s 3 4 3 2 3 0 2 9 2 7 2 6 2 5 2 4 2 3 2 2 2 1 At T ISA 23 C and Zp 450m Glider Weight kg 350 400 450 500 550 600 650 700 750 800 820 Towplane Glider Weight kg 770 820 870 920 970 1020 1070 1120 1170 1220 1240 Vz m s 2 8 2 6 2 4 2 3 2 2 2 1 2 0 1 9 1 8 1 7 1 7 10 7 AIRCRAFT AN...

Page 56: ...CE For a detailed description see the Operating Manual for the TOST Cable Retractor Winch in the annex of this manual 10 9 PLACARDS Sized 100 40mm and in sight of crew Winch command 13 18mm 13 40mm near the green light for Cable in and close to the button retraction Rope cutter 100 18mm along the cutter handle Either in black or red ...

Page 57: ...CE Ed 2 2009 06 2 NEXNO0901 MCR ULC Ecolight Flight Manual Page 55 67 11 SUPPLEMENT EDIATEC FLARM ECW 100 This document is up to date on November 2008 Nonetheless it is provided for information only and any new amendment should be considered ...

Page 58: ...19 rue de l Aviation F21121 Darois FRANCE Ed 2 2009 06 2 NEXNO0901 MCR ULC Ecolight Flight Manual Page 56 67 ...

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Page 60: ...19 rue de l Aviation F21121 Darois FRANCE Ed 2 2009 06 2 NEXNO0901 MCR ULC Ecolight Flight Manual Page 58 67 ...

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Page 63: ...19 rue de l Aviation F21121 Darois FRANCE Ed 2 2009 06 2 NEXNO0901 MCR ULC Ecolight Flight Manual Page 61 67 ...

Page 64: ...06 2 NEXNO0901 MCR ULC Ecolight Flight Manual Page 62 67 12 SUPPLEMENT TOW CABLE RETRACTOR WINCH TOST This document is up to date on November 2008 Nonetheless it is provided for information only and any new amendment should be considered MCR ULC Ecolight ...

Page 65: ...19 rue de l Aviation F21121 Darois FRANCE Ed 2 2009 06 2 NEXNO0901 MCR ULC Ecolight Flight Manual Page 63 67 ...

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Page 69: ...19 rue de l Aviation F21121 Darois FRANCE Ed 2 2009 06 2 NEXNO0901 MCR ULC Ecolight Flight Manual Page 67 67 ...

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