Aerospool WT9 Dynamic LSA Ciub S Flight Manual Download | Manualshive

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Summary of Contents for WT9 Dynamic LSA Ciub S

Page 1: ...l aerospool sk wwwaerospool sk FLIGUT MANUAL FOR THE LIGHT SPORT AIRPLANE WT9 Dynamic LSA Ciub MTOW 550kg Type WT9 Dynamic LSA Model Ciub S Seiial No DY 361 2010 LSA Registiation L k flate of Issue 01...

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Page 3: ...serted 1 2 3 2 1 2 3 3 08 12 03 08 12 03 2 3 3 2 22 09 04 22 09 04 3 7 2 7 8 9 10 01 10 06 01 10 06 4 2 4 5 7 2 5 7 9 15 01 07 15 01 07 4 1 3 4 12 5 4 7 2 7 11 12 5 7 7 12 17 08 10 17 08 10 5 1 1 4 21...

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Page 5: ...5 12 09 2011 7 4 01 12 2001 Appr 2 6 05 10 2009 7 5 28 11 2007 Appr 2 7 12 09 2011 7 6 01 12 2001 Appr 2 8 01 12 2001 7 7 01 10 2006 7 8 01 10 2006 3 Appr 3 1 01 12 2001 7 9 01 10 2006 Appr 3 2 22 09...

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Page 7: ...TABLE OF CONTENTS GENERAL LIM ITATIONS EMERGENCY PROCEDURES NORMAL PROCEDURES PERFORMANCE WEIGHT AND BALANCE I EQUIPMENT LIST AIRCRAFT AND SYSTEMS DESCRIPTION AIRCRAFT HANDLING SERVICING AND MAINTENA...

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Page 9: ...acturer 1 2 Certification basis F 2245 Standard Specification for Design and Performance of a Light Sport Airplane 1 3 Warnings cautions and notes The following definitions apply to wamings cautions a...

Page 10: ...in flight electricaly adjustable propeller and the following type and model is approved Woodcomp R 2000 D 1 4 2 Technical data Wing span 9 00 m Wingarea 10 3m2 tD Wing aspect ratio 7 82 Length 6 4 m H...

Page 11: ...I 0 3 cD 3 PODr___ 0 D...

Page 12: ...r 0 Cl z CJD 0 IF...

Page 13: ...ions instrument markings and basic placards necessaiy for safe operation of the airplane its engine standard systems and equipment Ihe limitations included in this section and in Section 9 have beeri...

Page 14: ...ded positive Normal Operating Range Lower limit is 70 230 43 143 37 124 maximum weight 1 1 VSI at most forward c g Gieen aic with flaps Upper limit is VRA YelIow arc 230 280 143 174 124 150 Manoeuvres...

Page 15: ...P1 ciassification SF or SG high performance 4 stroke motor cycle oils are recommended If using aircrafi engine oil then only blended one 3 0 litre 2 0 litre max 0 1 l h WARNING Never use AVGAS LB 95 w...

Page 16: ...8 28 28 29 5 29 5 gauge EMS D 1000 Ehau c 250 300 800 250 300 880 temperature EMS D 1000 800 880 Fuel flow meter LPH EMSD 1000 upto 25 25 Fuet reserve litre Red light annunciator will be illunilitated...

Page 17: ...imit is valid for en route weight at maximum crew weight forward centre ofgravity limit is valid for minimum pilot weight 70 kg and minimum capacity ofthe fuel tanks Example to check the centre ofgrav...

Page 18: ...d 0 WARNING JFR flights and flights in icing conditions are prohibited for flight operations the following minimum equipment must be installed Magnetic compass Sensitive barometric altimeter Airspeed...

Page 19: ...G on board the ultralight aircraft Maximum towing cable bad is 3 000 N Ifthe strength oftow cable is more than 3000 N a weak link must by used Maximum weight oftowed glider is 750 kg Maximum weight of...

Page 20: ...rn allowed filling of the fueJ tanks in litres Baggage I Crew weight kg weight kg 160 170 180 190 200 210 220 230 240 0 full 99 85 71 57 43 29 15 1 5 full 92 78 64 50 36 22 8 0 JO 99 85 71 57 43 29 15...

Page 21: ...scnibed in this section should be considered and applied as necessary to correct the problem 3 2 Engine fallure 3 2 1 Engine failure at take off tun 1 Throffte lever set to idle position 2 Ignition bo...

Page 22: ...5 Choke ifthe engine is already in operating temperature start the engine without choke 6 Throttle lever at cold engine set to idle position at warm engine slightly open 7 Ignition both circuits swit...

Page 23: ...emergency landing The optimum gliding performance is with retracted wing flaps and with stopped propeller In case ofengine failure it is necessary to maintain the following optimum speeds for given c...

Page 24: ...at the desired touch down spot will be immediately after passing the edge ofthe selected landing field 0 7 After touch down apply heavy breaking till stopped ground loop ifnecessary 8 When the airplan...

Page 25: ...is a danger ofpartial cockpit canopy latching or non locking The canopy is equipped with a lock on the upper rear section ofthe ftame and it is secured by the lock lever shot backwards The lock pin i...

Page 26: ...eck the cockpit canopy latching and locking by canopy frame and red ring 0 P0 sition 6 Ciose the leif ventilation sliding window on cockpit canopy 7 Adjust flight airspeed to cruising speed 0 WARN1NG...

Page 27: ...ion and the wing root is approx 100 mm Fig 3 Connect the hoses ftom the Pitot static tube and prepare and adjust the wing fuel tank hoses connect the wiring for fuel tank conductive connection ans pos...

Page 28: ...tape ftap Safety pin No 3 at the rear spar with the security I Date 01 12 09 Rev 0 Appr I c c WARNING Afier rigging ofthe wings check for correct operation and security ofthe aileron control pins and...

Page 29: ...l out the flxation pins for connection ofthe wing spar end with the wing central panel and the auxiliary rear pin 5 Pull out the wing along its longitudinal axis so that there is a distance between th...

Page 30: ...rfaces for full and ftee movement 6 All surfaces ofthe airplane for cracks nicks or any visible damage 7 Power plant and propeller 8 Check fuel oil coolant liquid fig 6 Walkaround inspection Date 01 1...

Page 31: ...ening for blockage Leading edges without damage clean Ailerons check for fteedom of movement and security Flaps without play check hinges for security 3 Fuselage Surface without damage Static pressure...

Page 32: ...he engine attachment itito the rubber engine mants check coolant level and oil level check attachment of carburettors check electric system state state ofthe holder hoses check condition and integrity...

Page 33: ...rd cockpit controls see also fig 9 on page 7 3 1 Control stick 2 Rudder pedals 3 Elevator mm control lever 4 Brake control lever 5 Wing flaps control lever 6 Pocket 7 Headset socket Ijack 8 Seat and s...

Page 34: ...position check setting and check up ofthe value function check adjust and lock function check shut and latched set on parking position switched on switch to 1 position select Ieft tank switch on and e...

Page 35: ...th only one ignition circuit must not exceed 300 r p m Max difference 120 r p m of speed by use ofeither circuit A or B 2 Throttle response short full throttle ground test speed must not exceed 5800 r...

Page 36: ...h readings increase airspeed and reduce engine power sening 4 5 8 Cruise The range of cruising speeds is from 140 to 230 km h in accordance with the engine speed setting from 4000 to 5200 r p m Ihe ec...

Page 37: ...1 Fuel pump switched on 2 Approach speed 110 120 km h according to the weight 3 Wing flaps as required flaps down at speed below 140 km h 4 Elevator trim adjust as required 5 Begin levelling out at h...

Page 38: ...nts avionics switch off 2 Propeller set minimum pitch take off position 3 Throttle idling tums 4 Ignition switch off the first circuit and D afier 2 3 s switch off the second circuit 5 Master switch s...

Page 39: ...imum never position 3 required for the field length Although the crab or combination method of drift correction may be used the wing low method gives the best control After touchdown hold a straight c...

Page 40: ......

Page 41: ...lse data 5 5 5 1 Introduction Section 5 provides approved data for airspeed calibration stall speed and take off perforrnance and non approved additional information The data in the charts has been co...

Page 42: ...y 75 252 Non paved grass 86 264 5 2 3 Landing distance The data is valid for following conditions Fl 0 m MSL Temperature t 15 C Wing flaps position 35 landing run is braked Surface of the Landtng dist...

Page 43: ...d has the quadrate running The power consurnption and also the fuel consumption increases with square of the airspeed The flight altitude is another factor which effects the fuel consumption because t...

Page 44: ...1773 1795 1811 1827 1851 1893 The table is valid for flight altitude 1000 m MSA take offperformance 73 5 kW the total usable quantity of frie in the tanks is 120 litres 5 3 3 Balked landing climb The...

Page 45: ...ance The maximum demonstrated crosswind speed for take off and landing is 6 mls according to the airworthiness requirements 5 3 5 Nolse data The maximum noise data 56 7 dB A was measured during the fl...

Page 46: ...fthree weighing machines located below the lefi and right mai11 wheels and below the nose wheel The airplane position for weighing has to be parallel with the horizontal plane which passes through the...

Page 47: ...crew passenger weight with Condition Aircraft in the range from maximum fuel of 100 5 litres to minimum fuel of 7 litres 0 Date 01 12 09 Rev 0 Date Empty weight kg Ernpty moment kgm C G Position Max b...

Page 48: ...stant from DP mm Moment M G Distant Empty airplane Empty Weight G 309 0 kg Empty Moment M 67262 0 kgmm Crew Gcrew kg 720 mm kgmm fuel Gfuel kg 240 mm kgmm Baggage Gbag kg 1100 mm kgmm Total weight G1...

Page 49: ...nents Ignition Switch Fuel indicator Tachometer Oil temperature indicator and Oil pressure indicator Coolant temperature indicator Additional eguiDment Master Switch ofthe electrical system with fuses...

Page 50: ...ration of the airplane and its systems Refer to Section 9 Supplements for details ofoptional systems and equipment D 7 2 Airfiame WT9 Dynamic LSA Ciub S is a single engine aircraft controlled aerodyna...

Page 51: ...tabilizer and elevator The stabilizer consists of sandw h shells from advanced composite material The stabilizer is fixed at the fin The width of the horizontal tail unit is 2 4 m the same width as th...

Page 52: ...iojack in 16 12 V Stage Socket 17 Throttle Lever I 8 Rescue system lever 19 Oil Cooler flap Lever 20 Carburettor preheating Confrol 21 Cabin venting 22 Cahin heating 23 Fuel selector 24 Choke Lever 25...

Page 53: ...FueI Reserve 11 lOASocketl2V The main wheels ofthe model CIub S are mounted on spring Jegs which are attached to the lefi and to the right outside ofthe wing central panel The nose wheel leg is affach...

Page 54: ...Doors windows and exits The cockpit canopy consists of one part The Perspex canopy is glued on the composite frame The canopy is attached to the nose section ofthe fuselage by pins which make it possi...

Page 55: ...nt for the coolmg system 50 antifteeze concentrate with additives against corrosion and 50 pure water is used The coolant must be renewed eveiy two years Refer to the Operator s Manual for ROTAX 912 U...

Page 56: ...wing the attachrnent screws connecting the cooler to the cowling face side then unscrew the attachment screws connecting the cowling to the firewalt border Propelier DUC Swirl is the three blades on g...

Page 57: ...v i CJD CJD I 00...

Page 58: ...rJD 1 0 L u z JD Cl...

Page 59: ...kpit below the instrument panel then through the fuel filter mto the engine fttel pump into the carburettor Ihe unconsumed fuel is supplied back through return piping into the leif tank The vent pipe...

Page 60: ...ights flash 7 C litters each tank the following procedure is recommended Select the right tank and use this tank until all the fuel is exhausted Change back to the left tank should now have slightly m...

Page 61: ...in the airplane radios and intercom This equipment must be connected with the headphones and with the antenna Ihe airplane might be equipped with other instruments such as GPS transponder board compu...

Page 62: ...against dust All engine intakes vents the fuel vents and pitot static system should be covered before long term airplane parking or storing due to contamination by foreign objects insects birds The ex...

Page 63: ...ve filter mat unroll and check it for metal chips foreign matter contamination and abrasion This check is important as it allows conclusions regarding the condition of the engine and gives information...

Page 64: ...battery if need be cleaning 5 Power plant visually check the hoses for condition damage leaks attachment and security the rubber flange of the air filter for cracks Visually check exhaust system for...

Page 65: ...st every 2 years Check condition ofthe bearings ofthe nose wheel clean and lubricate if need be at least twice per year Lubricate Main and rear spar pins The axle of the nose wheel leg Guid tube ofthe...

Page 66: ...ecessary transportation in the road CAUTION The airpfane is equipped with mooring eyes which are screwed into the threaded hubs on the wing lower surface located approx half way along the wing It is a...

Page 67: ...ded Cover a part of radiator face by a duralumin sheet or drawing paper of appropriate dimensions insert it between the radiator and the bottom engine cowling Cover the oil cooler face or a part ofthe...

Page 68: ...erate the airplane when equipped with various optional systems and equipment not provided with the standard airplane NOTE Additional individual equipment in accordance with a customer s request will i...

Page 69: ...I WT9 Dynamic LSA Ciub S FLIGHT MANUAL Section 9 Page 9 2 I 9 3 Supptements inserted For operation and handling with inserted supplements see corresponding Operation manual Date 01 12 09 Rev 0...

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