Pipistrel Sinus 503 Скачать руководство пользователя страница 87

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SINUS motorglider

www.pipistrel.si

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SINUS motorglider

www.pipistrel.si

REV. 0

Appendix

Myth: I can fully deflect the controls
below maneuvering speed!

WRONG! BELIEVE THIS AND DIE!

The wing structure in light planes is usually certified to take +3.8 G’s, -1.52 G’s (plus a certain safety

factor). Put more load on the wing than that and you should consider yourself dead.

But here is the nice part: Below a certain speed, the wing simply cannot put out a full 3.8 G’s of lift! It

will

stall

first! This speed is called

Maneuvering Speed

Maneuvering Speed is defined as the maximum speed the plane can be flying at and still

stall

before the

wing breaks

no matter how much you pull back on the stick. If you are going

slower

than the

and you pull the stick all the way back, the wing will stall

without braking physically

If you are going

faster

than the

and you pull the stick all the way back, the wing can put out

much lift

that it can be expected to

break

. Therefore people think they can deflect the stick as much

as they desire below Maneuvering Speed and stay alive.

Wrong! The Maneuvering Speed is based on pulling back on the stick, not pushing it forward!

Note what was said above: The Va is defined as how fast you can fly and not be able to put out more

than 3.8 G’s of lift. But while the plane is certified for

positive 3.8 G’s

, it is only certified for a

nega-

tive G-load of 1.52 G’s!

In other words,

you can fail the wing

in the negative direction

by pushing

forward

on the stick well

below the Va!

Few pilots know this.

Also, for airliners, certification basis require that the rudder can be fully deflected below

Maneuvering Speed, but only if the plane is not in a sideslip of any kind! (e.g. crab method of ap-

proach) Does this make sense at all? Why would you need to fully deflect the rudder if not to

re-establish rightened flight?

In a wonderfully-timed accident shortly after Sept. 11

, 2001 of which everybody thought might be

an act of terrorism, an Airbus

pilot stomped the rudder

in wake turbulence while the plane was

a considerable sideslip

. The

combined loads

of the

sideslip

and the

deflected rudder

took the

vertical stabilizator to it’s

critical load

. A very simple numerical analysis based on the black box con-

firmed this. The airplane lost it’s vertical stabilizator in flight and you know the rest.

Also, if you are at your

maximum allowable g-limit

(e.g. 3.8) and you

deflect the ailerons

even

slightly

, you are actually asking for

more lift from one wing than the allowable limit!

Therefore combined elevator and aileron deflections can break the plane, even if the elevator

is positive only!

SO, WHEN YOU THINK THAT YOU CAN DO AS YOU PLEASE WITH THE CONTROLS BELOW

MANEUVERING SPEED, YOU ARE WRONG!

Please reconsider this myth and also look at the Vg diagram and the aircraft’s limitations to prove it

to yourself.

Содержание Sinus 503

Страница 1: ...t is mandatory to designate those specific parts of this manual that regard the aircraft you own This booklet MUST be present inside the cockpit at all times Should you be selling the aircraft make sure this manual is handed over to the new owner This is the original manual of Pipistrel d o o Ajdovscina Should third party translations to other languages contain any inconsistencies Pipistrel d o o ...

Страница 2: ...r www pipistrel si REV 0 Sinus model Serial number Date of manufacture Aircraft empty weight kg Fuel weight Available cargo weight Installed appliances included in aircraft empty weight Date and place of issue Ajdovščina ...

Страница 3: ...uthority Signature Stamp Original date of Approval This aircraft is to be operated in compliance with information and limitations contained herein The original English Language edition of this manual has been approved as operating instruction according to Pravilnik o ultralahkih letalnih napravah of Republic of Slovenia Approval of translation has been done by best knowledge and judgement Pipistre...

Страница 4: ...below All revised pages should be clearly designated in the upper right corner of the page also any changes in page content should be clearly visible e g marked with a bold black vertical line Name of revision Reason for Revision Revision no date Description Affected pages Approval signature Original Rev 0 15 April 2006 First original release ...

Страница 5: ...5 SINUS motorglider www pipistrel si REV 0 ...

Страница 6: ...6 SINUS motorglider www pipistrel si REV 0 This page is intentionally left blank ...

Страница 7: ...S motorglider www pipistrel si REV 0 Table of contents General Limitations Emergency procedures Normal procedures Performance Weight and balance Aircraft and systems on board Handling and maintenance Appendix ...

Страница 8: ...8 SINUS motorglider www pipistrel si REV 0 This page is intentionally left blank ...

Страница 9: ...9 SINUS motorglider www pipistrel si REV 0 Introduction Certification basis Notes and remarks Technical data Aircraft projections General General ...

Страница 10: ...ider is certified at URSZP according to the standards of the Republic of Slovenia and the Type Certificate no __AT ULN 01__ dated 09 07 1999 as an Ultralight aircraft see attachments for copies of certificates Notes and remarks Safety definitions used in the manual WARNING Disregarding the following instructions leads to severe deterioration of flight safety and hazardous situations including such...

Страница 11: ...11 SINUS motorglider www pipistrel si REV 0 Aircraft projections General ...

Страница 12: ...12 SINUS motorglider www pipistrel si REV 0 This page is intentionally left blank ...

Страница 13: ... 0 Introduction Operational velocities Engine fuel oil Weight limits Centre of gravity limits Manoeuvre limits G load factors Cockpit crew Types of operations Minimum equipment list Other restrictions Warning placecards Limitations Limitarions ...

Страница 14: ...e extended Lower end is defined as 110 of VS stall speed in landing configuration at MTOM up per end of speed range is limited by VFE see above green arc 66 141 36 76 Speed range of normal operation Lower end is defined as 110 of VS1 stall speed at MTOM with flaps in neutral position upper end is limited by VRA see above yellow arc 141 220 76 119 Manouvre the aircraft with great caution in calm ai...

Страница 15: ...0 135 260 140 270 146 280 151 0 3000 6000 9000 12000 15000 18000 21000 24000 27000 30000 1000 2000 3000 4000 5000 6000 7000 8000 9000 km h kts pressure altitude Indicated AirSpeed IAS m ft TAS 225 km h 122 kts TAS 250 km h 135 kts The graph below shows which indicated airspeed IAS must be maintained to keep the true air speed TAS constant Note that true airspeed TAS is constant along the entire se...

Страница 16: ...verything under AKI 87 everything under AKI 87 leaded or 100LL recommended oil super 2 stroke API TC super 2 stroke API TC API SJ SAE 10W 50 Engine life is reduced Should you be forced to used this kind of fuel change of engine oil every 50 flight hours is crucial Please consult the manufacturer on which type of oil to use IMPORTANT Two stroke engines should be powered only by fuel complying with ...

Страница 17: ...g 450 472 5 kg 450 472 5 kg fuel capacity 2 x 30 l 2 x 30 l 2 x 30 l max fuel weight allowable 45 6 kg 45 6 kg 45 6 kg minimum cockpit crew weight no limit no limit no limit maximum cockpit crew weight 180 kg 180 kg 180 kg joint parachute rescue sys and luggage weight 15 kg 16 kg 18 kg WARNING Should one of the above listed values be exceeded others MUST be reduced in order to keep MTOM below 450 ...

Страница 18: ...f stalls not below 150 meters 500 feet above ground level Power on and off lazy eights not below 150 meters 500 feet above ground level Steep turns with a maximum bank of 60 and initial speed of 160 km h 85 kts Chandelle maneuver not below 150 meters 500 feet above ground level Intended spin at most 180 in actual spinning manoeuvre G load factors max positive wing load 4 G max negative wing load 2...

Страница 19: ...r face freezing to the airframe Minimum equipment list Airspeed indicator Altimeter Compass Tachometer RPM Other restrictions Due to flight safety reasons it is forbidden to fly in heavy rainfalls fly during thunderstorm activity fly in a blizzard fly according to instrumental flight rules IFR or attempt to fly in zero visibility condi tions IMC fly when outside air temperature OAT reaches 40 C or...

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Страница 21: ...otorglider www pipistrel si REV 0 Introduction Stall recovery Spin recovery Engine failure Landing out Engine fire Smoke in cockpit Carburator icing Flutter Exceeding VNE Emergencyprocedures Emergency procedures ...

Страница 22: ...ablish rightened flight by itself usually after having spinned for a mere 90 WARNING Keep the control stick centred along its lateral axis no aileron deflections throughout the recovery phase Do not attempt to stop the aircraft from spinning using ailerons instead of rudder WARNING After having stopped spinning recovering from the dive must be performed using gentle stick movements pull rather tha...

Страница 23: ...uel valves 2 Master switch OFF key in full left position 3 Approach and land with extreme caution maintaining proper airspeed 4 After having landed abandon the aircraft immediately The landing out manoeuvre MUST be preformed with regard to all normal flight parameters Engine fire Engine fire on ground This phenomenon is very rare in the field of Ultralight aviation However coming across engine fir...

Страница 24: ...bility of carburator icing is increased by planes equipped with two stroke engines using a separate oil injection unit and four stroke engines The carburator air intake in Sinus ultralight motorglider is preheated running over the water cooling radiator before entering the carburators Therefore the possibility of carburator icing is slight Should you be suspecting carburator icing to take place de...

Страница 25: ...SINUS motorglider www pipistrel si REV 0 Introduction Assembling and disassembling the aircraft Daily check up Preflight check up Normal procedures and recommended speeds Normalprocedures Normal procedures ...

Страница 26: ...have fitted into adequate fuselage fittings prop erly At the same time the person holding the wingtip must start with slight circular move ments 1cm each direction in order to assure a tight fit of the wing and its adequate bushings As this is done the person at the wingtip must remain in positon holding the wing whereas the other two move over to the other wing half lift it and bring it closer to...

Страница 27: ...pins yet Once the fuel tanks are empty disconnect the fuel hoses inside the cockpit as well Make sure you tape the end attached to the wing not to spill any eventual leftover fuel over the fuselage or glass surfaces as substantial damage may occur Two people must now lift the wingtips one wingtip each and the person in the cock pit remove the main spar pins one by one smoothly Forcing pins out of ...

Страница 28: ...g the following procedure To fit the horizon tal tail surfaces first set the trim handle inside the cockpit to full forward position Make sure the pins their holes and bushings have been cleaned and greased Lift the joint stabilizer and elevator and slide them into position by pushing them backwards while the elevator is deflected DOWN fully Now use the enclosed T key to push the security screw do...

Страница 29: ...h both nuts tightened check full rudder deflections for smooth unobstructed movement Detaching the rudder Deflect the rudder to one side fully and unscrew the nut of the bolt with which the rudder is at tached to the bottom hinge This is the bolt located in between the central bolt axis of rotation and the bolt holding the metal ropes DO NOT touch these two bolts unscrew the nut of the middle bolt...

Страница 30: ... the damage MUST be repaired prior to engine start up Disobeying this instruc tions may result in serious further damage to the plane and crew including injury and loss of life Schematic of preflight check up 12 1 2 3 4 5 6 7 8 9 10 11 13 14 15 16 17 18 19 20 21 22 1 Engine engine cover 8 Right wing trailing edge 15 Hor tail surfaces left 2 Gascolator 9 Right spoiler 16 Fuselage continued left 3 S...

Страница 31: ... pollution and intercept fuel with a canister Spinner Spinner no mechanical damage e g cracks impact spots screws tightened Bolts and nuts secured Propeller Hub and blades no mechanical damage e g cracks both immaculately clean Bolts and nuts secured VARIO propeller smooth unobstructed movement along propeller pitch Undercarriage wheels Bolts fastened Landing gear strut no mechanical damage e g cr...

Страница 32: ...s Hinges no free play in any direction Central securing screw on top or the horizontal stabilizer fastened and secured Self adhesive tape covering the gap between horizontal and vertical tail surfaces in position Elevator smooth and unobstructed up down movement no side to side free play Vertical tail surfaces Vertical fin bottom part no cracks impact spots or paint separations along main chord Su...

Страница 33: ...d headset perform radio check Injection oil quantity optional oil injection pump sufficient for the planned flight duration Battery some models firmly in position check water level if not dry version joints clean with wires connected Emergency parachute release handle optional safety pin removed Make sure unobstructed access is provided Normal procedures and recommended speeds To enter the cabin f...

Страница 34: ...e 20 seconds to make mixture richer Engine warm up procedure A two stroke engine should be warmed up at 3500 RPM a four stroke however at 2500 RPM up to the point working temperature is reached Warming up the engine you should 1 Point aircraft s nose against the wind 2 Verify the engine temperature ranges within operational limits CAUTION Avoid engine warm up at idle throttle as this causes sparks...

Страница 35: ...e engine faster Take off and initial climb Before lining up verify the following Spoilers retracted and secured Fuel valves fully open Fuel quantity sufficient Safety harnesses fastened Cabin doors closed securely Trim handle in neutral position or slightly forward Flap handle 2nd position flap handle full up Propeller pitch minimum flat setting propeller pitch knob screwed to the left fully Runwa...

Страница 36: ...flap handle full down Check engine operation and flight parameters regularly WARNING Sinus ultralight motorglider is sensitive to correct flap settings To maintain ex cellent and safe flight performance it is important to set flaps according to airspeed As the pilot you must know that the higher the speed the greater the force on the flapperons To prevent overstressing the flapperons it is of vita...

Страница 37: ...performance Roundout and touchdown flare should be performed at following airspeeds Calm air aircraft at MTOM 75 km h 40 kts IAS Rough air aircraft at MTOM incl strong crosswinds up to 28 km h 15 kts 78 km h 42 kts IAS CAUTION Land the aircraft in such a manner that all three wheels touch the ground at exactly the same time When touching down rudder MUST NOT be deflected in any direction rudder pe...

Страница 38: ...t fully Unlock spoilers handle hanging down freely and insert paracute rescue system handle s safety pin if rescue system installed Open cabin door unfasten safety harnesses and exit the cockpit watch for the wheel fairings Block the wheels and secure the pitot tube by putting on a protection cover CAUTION Should the aircraft be parked on a slope it is recommended to shut one of the fuel valves to...

Страница 39: ...w pipistrel si REV 0 Introduction Airspeed indicator calibration Take off performance Climb performance Cruise Descent Landing performance Vg diagram Speed polar Additional technical data Noise levels Performance Performance ...

Страница 40: ...5 up 69 km h 36 7 kts flaps in neutral position 0 neutral 66 km h 35 6 kts flaps in 1st position 9 down 65 km h 35 0 kts flaps in 2nd position 18 down 63 km h 34 0 kts Take off performance All data published in this section was obtained under following conditions aircraft at MTOM elevation 100 meters 330 feet wind calm runway dry grass runway with low cut grass ICAO standard atmosphere SINUS Model...

Страница 41: ...10 C The graph below indicates how takeoff runway length changes as altitude increases 50 160 150 500 200 650 100 330 250 820 takeoff runway length elevation m Rotax 503 Rotax 582 Rotax 912 elevation ft 650 1300 2000 2600 3200 4000 4600 m ft 0 200 400 600 800 1000 1200 1400 Effect of the wind Wind head cross or downwind also called tailwind affects aircraft s ground speed GS Headwind on takeoff an...

Страница 42: ...oes The table below provides data about the effect of headwind and tailwind on takeoff runway length windspeed m s 3 2 1 0 2 4 6 Takeoff runway length m ft Model 503 193 630 165 540 143 465 123 405 99 325 80 260 69 225 Model 582 172 565 145 475 123 405 100 330 84 275 70 230 59 195 Model 912 146 655 124 405 105 345 93 305 76 245 64 210 54 175 The graph below indicates how takeoff runway length chan...

Страница 43: ...t 140 km h 75 kts 2 8 m s 560 fpm 4 2 m s 840 fpm 6 3 m s 1260 fpm Effect of elevation The table below provides data about the effect of elevation on climb rate at best climb speed Vy SINUS Model 503 Model 582 Model 912 0 m 0 ft 3 2 m s 640 fpm 4 2 m s 840 fpm 6 5 m s 1300 fpm 500 m 1600 ft 2 9 m s 580 fpm 3 9 m s 780 fpm 6 0 m s 1200 fpm 1000 m 3300 ft 2 5 m s 500 fpm 3 5 m s 700 fpm 5 5 m s 1100...

Страница 44: ...e become inoperative in flight as a result of either intended or unintended action and it cannot be restarted react as follows establish rightened flight at the speed providing best lift over drag ratio if you desire to over come greatest distance at reach from initial altitude establish rightened flight at speed providing minimum sink rate if you desire do stay airborne the longest This may come ...

Страница 45: ...Runway proportions must be in excess of 250 x 30 meters 820 x 100 feet with no obstacles in 4 range off runway heading in order ensure safe flying activity Use of shorter strips should be considered a major exception and is allowed to experienced pilots at own risk only Crosswind landing limitations Maximum allowed crosswind speed on takeoff and landing with flaps in 2nd position is 28 km h 15 kts...

Страница 46: ...kts max climb rate at MTOM 3 2 m s 640 fpm 4 4 m s 880 fpm 6 5 m s 1300 fpm climb rate at 140 km h 2 8 m s 560 fpm 4 2 m s 840 fpm 6 3 m s 1260 fpm minimum sink speed 90 km h 48 kts 90 km h 48 kts 90 km h 48 kts minimum sink rate BAM 2 prop 1 24 m s 250 fpm 1 24 m s 250 fpm 1 24 m s 250 fpm minimum sink rate VARIO prop 0 96 m s 185 fpm 1 03 m s 205 fpm 1 03 m s 205 fpm max sink rate with spoilers ...

Страница 47: ...ink rates and fuel consumption increase while climb rates ceiling lift over drag ratio and endurance decrease Some of the these are effected by as much as 30 Noise levels Noise levels are measured from the ground The aircraft at MTOM must fly over the microphone at a height of 150 meters 500 feet exactly at VNE with engine power needed to maintain horizontally rightened flight All versions of Sinu...

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Страница 49: ...49 SINUS motorglider www pipistrel si REV 0 Weight and balance Introduction Weighing procedure Equipment list Determination of CG Sample CG calculation Weightandbalance ...

Страница 50: ...g Retract flaps and spoilers leave control surfaces centred Support fuselage at the rear and level the aircraft inside a closed space To do this use the provided airfoil template at lower side of the wing close to the wing root and make sure its straight edge is level horizontal Once leveled read the scale readings and subtract eventual tare weight Now measure and record all readings and fill out ...

Страница 51: ...ed Furthermore the momentum must be recalculated This is rather unchalanging to do First mul tiply the new part s weight by it s lever arm measured from the reference point wing s trailing edge Then sum up all momentums and divide the sum by the new total weight WARNING Aircraft s safe center of gravity position ranges between 20 and 39 of mean aerodynamic chord and is not affected by cockpit crew...

Страница 52: ... datum wing s leading edge at wing root For Tail wheel edition of Sinus ultralight motorglider use the following formula where G2tail is the scale reading at the tail wheel Gtotal is the sum of G1 and G2tail G1 G2tail a k a aircraft empty weight a is the distance from main wheel axis to wing s leading edge b is the distance between main and tail wheel axis For Nose wheel edition of Sinus ultraligh...

Страница 53: ...ulate the formulas using the weights and c g of your empty aircraft and the planned amount of baggage for your flight CAUTION The baggage weight limitations mentioned on page 15 of this manual represent fool proof limits for safe operation even without special c g calculation However the actual baggage weight limitation is different of each individual aicraft and can be determined using the above ...

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Страница 55: ...nstrument panel Undercarriage Seats and safety harnesses Pitot static lining Air brakes spoilers Power plant and propeller Fuel system Electrical system Engine cooling system Engine lubrication system Wheel brake system Aircraftandsystemsonboard Aircraft and systems on board ...

Страница 56: ...in Fuel hose connectors are self securing this prevents fuel spills when disassembling the aircraft The gascolator is located beneath the lower engine cover Refuelling can be done by pouring fuel through the reservoir openings on top of the wings or by using an electrical fuel pump instead Also featured are low fuel signal lights on the instrument panel All glass surfaces are made of 2 mm anti UV ...

Страница 57: ...of glass carbon and kevlar fiber manufactured by Interglas GmbH All parts have been tested at safety factor 1 8 meaning stressed to 7 2 G All parts are made in moulds therefore no shape or structural differences can occur All desinging manufacturing and testing complies with following regulations Bauvorschriften für Ultraleichtflugzeuge des Deutschen Aero Club e V Beauftragter des Bundes ministeri...

Страница 58: ...oint control levers throttle lever chock lever flap lever trim lever airbrakes lever fuel valves door levers battery disconnection lever ring and emergency parachute release handle Instrument panel Aircraft and systems on board Note Aircraft delivered prior to year 2004 also feature fuel reserve warning lights on the instrument panel due to a different visual fuel quantity check Exceptions are how...

Страница 59: ... switched ON seperately from the aircraft s master switch Always make sure the instrument is switched OFF when you leave the aircraft not to discharge its internal battery Undercarriage The undercarriage is a taildragger type with two main brake equipped wheels mounted on struts and a free spinning or rudder guided tail wheel distance between main wheels 1 60 m distance between main and tail wheel...

Страница 60: ... ignition cooling water cooling own radiator and water pump lubrication by adding oil into fuel or using an independent oil inject pump reduction gearbox Rotax type B or C reduction ratio 1 2 58 or 1 2 62 1 3 optional el generator output power 170 W at 6000 RPM starter electric engine power 64 HP at 6600 RPM battery 12 V 8 Ah Engine ROTAX 912UL 4 stroke boxer four cylinders 1211 cm3 twin carburate...

Страница 61: ...ch propeller significantly increases aircraft s takeoff cruise and glider performance CAUTION Always fly in such a manner that you are able to reach at least one landing out site every moment of the flight This especially applies to unpowered flight as ignition engine and or propeller malfunction may prevent you from restarting the engine and by that resuming normal flight Use of Vario propeller d...

Страница 62: ...se prop pitch to regain proper engine cruise parameters WARNING Both engine under and overrotation may cause significant damage to the en gine and propeller Propeller feathering WARNING Feather propeller only after the engine has stopped and at minimum pitch To feather the propeller first reduce airspeed to 90 km h 50 kts then pull the propeller pitch knob s metal base backwards fully and then rot...

Страница 63: ...ide relevant information about the actual fuel quantity on board Due to reasons of wing dihedral angle of attack sideslip and reservoir supply point the readout may be incorrect Flying with less than 3 cm 1 Inch of indicated fuel measured from the bottom of the tube upwards in any of the reser voirs is therefore regarded as hazardous any may result in engine fuel starvation and or engine failure C...

Страница 64: ...the battery disconnection the battery discon nection lever and the battery disconnection ring The battery disconnection lever which is a red flag type lever is found on the firewall above the main battery on the left hand side of the cockpit This lever has an attached wire which leads to the battery disconnection ring on the instrument panel s switch column To disconnect the battery from the circu...

Страница 65: ...65 SINUS motorglider www pipistrel si REV 0 Aircraft and systems on board Schematic of electrical system all models ...

Страница 66: ...hrough the hoses via twin cooling circuit For that an integrated pump is used When the engine is still cold cold start the thermostat allows for the fluid to circulate around the cylinders only Later when the engine warms up the thermostat switches cooling mode and the cooling fluid passes through the radiator as well The whole system is pressurised with a pressure valve located on top of the radi...

Страница 67: ... with a pressurised valve placed on one of the hoses The overflow tank fluid level must always be inside the designated limits The engine does not offer cooling water temp monitoring Only CHT is displayed in the cockpit The engine does not feature a cooling fan therefore cooling it is entirely dependant on moving air cur rents and airspeed CAUTION You are strongly discouraged from leaving the engi...

Страница 68: ... passing through a radiator located on the left hand side of the bottom engine cover Oil quantity can be checked visually with a oil level bar Make sure the oil quantity is sufficient limits at all times CAUTION Oil temperature pressure and quality is strictly defined an must not under any cir cumstances vary from its safe values Schematic of engine lubrication system model 912 Wheel brake system ...

Страница 69: ...tion periods Repairs and spare part replacements Preventative maintenance Special check ups Draining and refuelling Connecting Auxilary power supplies Tie down Storage Cleaning Keeping your aircraft in perfect shape Handling andmaintenance Handling and maintenance ...

Страница 70: ...icates recommended maintenance periods see Service manual for detailed in formation Table legend C Check up visual only check for free play and whether everything is in position DO IT YOURSELF CL Cleaning DO IT YOURSELF LO Lubricating oiling lutbirace all designated parts and spots using proper lubricant DO IT YOURSELF R Replacement replace designated parts regardless of state and condition You ar...

Страница 71: ... main strut rear fork condition C C SC wheel axis and wheels C brake wires C SC R brake drums C C R wheel bearings C SC R tail wheel main bolt C R wheel fairings C C C tail wheel mounting bolt check and fasten every 50 landings CONTROLS R general free play C C SC control stick C LO SC rudder pedals damage centered paral C C C LO rudder wire rope C SC bolts visible bearings tail fuselage SC LO diff...

Страница 72: ...nts and connectors hoses radiator mount C C SC pre chamber and exhaust silencer C C SC R exhaust pipe springs and fire protect C C R throttle choke propeller wire drive R ENGINE CONTROL O choke and throttle lever wire ropes C C SC R levers C SC PROPELLER AND SPINNER SC O surface condition C fastening bolts C R propeller bushings R propeller pitch C propeller balance C FUEL LINES O general leakage ...

Страница 73: ...C thermal switch pressure ctrl cover C C R PITOT STATIC LINING SC O instrument to pitot tube lining C C instrument setting C C pitot tube condition clean firmly att C C whole pitot static lining C C Spoilers airbrakes drive fine adjustment CAUTION Perform this operation only once after first 50 flight hours Check spoilers thoroughly for unobstructed smooth and even extention every 200 flight hours...

Страница 74: ... in cold temperatures you may encounter click clack like noises above your head The remedy for this unpleasant noises is to add washers tipically of 0 5 mm thickness in between wing and fuselage Washers must be added both at rear and front bushings at one side of the fuselage only WARNING It is mandatory to consult the manufacturer or authorised service personnel before applying washers Venting th...

Страница 75: ...e air bubbles in the hydraulic lining which is causing the problem The main wheel s main axis nut especially after a wheel and or axis replacementnut may be tight ened incorrectly so that the brake shims do not make contact with the brake plate Please consult the manufacturer or authorised service personnel for further information Schematic of wheel and wheel brakes Schematic of hydraulic brakes l...

Страница 76: ...hand side of the fuselage To drain the fuel system open the drain valve on the gascolator Drain no more than a couple of spoonfuls of fuel Try to prevent ground pollution by intercepting the fuel with a canister To close the valve simply turn it in the opposite direction Do not use force or special tools CAUTION Always drain the fuel system before you have moved the aircraft from a standstill to p...

Страница 77: ...ply use battery connector cables with clamps at either ends Connect the negative wire to aircraft s exhaust sticking out below the engine cowlings The positive wire leads inside the cockpit to the relay mounted top right of the aircraft s battery on the firewall This relay has 3 nipples the positive wire must be connected to the upper left nip ple the only one to which 2 cables are connected to Af...

Страница 78: ...ing on the instrument panel s switch column during storage period CAUTION Should the aircraft be stored and or operated in areas with high atmospheric hu midity pay special attention to eventual corrosion of metal parts especially inside the wings Under such circumstances it is necessery to replace the spoilers airbrakes connector rod every 2 years Cleaning Use pure water and a soft piece of cloth...

Страница 79: ... laminate When using the aircraft in difficult atmospheric conditions intense sunshine dusty winds coastline acid rains etc make sure to clean the outer surface even more thoroughly If you notice you cannot remove the bug spots from the leading edges of the aircraft this means the lacquer is not protected any more therefore it is necessary to polish these surfaces CAUTION Do not under any circumst...

Страница 80: ...g solutions are necessary and a really clean drying towel always use a separate towel ONLY for the glass surfaces Should the glass surfaces be dusty remove the dust first by puring water not spraying and gliding your hand over the surface Using the drying towel simply glide it over the surface then squeeze it and soak it before touch ing the glass again If there are bugs on the windshield soak the...

Страница 81: ... rescue system use handling and maintenance How fast is too fast Myth I can fully deflect the controls below maneuvering speed Aircraft familiarisation Conversion tables Preflight check up pictures Sinus ultralight motorglider checklist Appendix Appendix ...

Страница 82: ...onds WARNING Activation handle safety pin should be inserted when the aircraft is parked or hangared to prevent accidental deployment However the instant pilot boards the aircraft safety pin MUST be removed Use of parachute rescue system In situations such as structural failure mid air collision loss of control over aircraft engine failure over hostile terrain pilot incapacitation incl heart attac...

Страница 83: ...achute rescue system has been used or if you suspect any possible damage to the sys tem do not hesitate and immediately contact the manufacturer Handling and maintenance Prior to every flight all visible parts of the system must be checked for proper condition Special at tention should be paid to eventual corrosion on the activation handle inside the cockpit Also main fastening straps on the outsi...

Страница 84: ...pperon control tubes went broken The pilot of the second machine then landed safely using elevator and rudder only Fortunately both pi lots survived the accident without being even slightely injured Thanks to the Brauniger ALPHAmfd s integrated Flight Data Recorder we were able to reconstruct the flights and reveal what had really happened What was the reason for the flutter causing both accidents...

Страница 85: ...slick wings are more prone to flutter at high speeds than to structural failure So flutter is the main factor of determining VNE for us and most other carbon reinforced plastic aircraft producers Flutter speed is linked to TAS as it is directly caused by small differences in speed of air circulating the airframe Hence air density is not a factor For all who still doubt this here are two quotes fro...

Страница 86: ...35 178 96 270 145 196 103 8000 m 26300 ft 250 135 169 91 270 145 185 98 The table below indicates how TAS increases with altitude while keeping IAS constant IAS km h kts TAS km h kts IAS km h kts TAS km h kts 1000 m 3300 ft 250 135 266 144 270 145 289 156 2000 m 6500 ft 250 135 279 151 270 145 303 164 3000 m 10000 ft 250 135 290 157 270 145 316 171 4000 m 13000 ft 250 135 303 164 270 145 329 178 5...

Страница 87: ...8 G s it is only certified for a nega tive G load of 1 52 G s In other words you can fail the wing in the negative direction by pushing forward on the stick well below the Va Few pilots know this Also for airliners certification basis require that the rudder can be fully deflected below Maneuvering Speed but only if the plane is not in a sideslip of any kind e g crab method of ap proach Does this ...

Страница 88: ...the stick back completely and slowly add throttle to full power then verify RPM Taxi Taxiing with the Sinus ultralight motorglider is rather simple considering the stearable tail wheel For sharper turns on the ground you can also use wheel brakes to assist yourself I would recommend you taxi slow up to 10 km s 5 kts Sinus ultralight motorglider s long wings cause quite a bit of iner tia if turning...

Страница 89: ...n and initial climb Having lifted off the ground gently push the stick forward just a bit to accelerate At some 75 80 km h 40 43 kts set flaps to 1st stage at 90 km h 50 kts set them to neutral Climb A comfortable setting for climb is flaps in neutral position speed of 115 km h 62 kts at some 5000 RPM 912 version and full power for 2 stroke engines In summer time or when outside tempera ture excee...

Страница 90: ...his way you will always be on the safe side even if your engine fails you will still be able to safely reach the runway Turn to final at 90 km h 50 kts When in runway heading set flaps to 2nd stage Operate the air brakes to obtain the desired descent path How to determine how much airbrakes you need for a certain angle of attack Open them half way and observe the runway If the runway treshold is m...

Страница 91: ... one of the main wheels touches down an instant before the other e g if there is crosswind from your left left wheel should touch down just before the right wheel does This way undercarriage almost cannot be damaged due to side forces on cross touch down Landing in strong turbulence and or gusty winds First of all airspeed must be increased for half of the value of wind gusts e g if the wind is gu...

Страница 92: ...rcle flying below the ridge s top fly eights instead until you reach a height of 150 meters 500 feet above the ridge top From then on it is safe to fly full circles in a thermal Entering and exiting a turn when flying unpowered requires more rudder input than when flying with the engine running So work with your legs To quickly enter a sharp turn at speeds between 80 90 km h 43 48 kts basically ap...

Страница 93: ...93 SINUS motorglider www pipistrel si REV 0 Appendix This page is intentionally left blank ...

Страница 94: ... 94 14 7 55 87 10 47 25 36 148 25 80 43 16 27 79 15 8 09 88 95 48 25 90 150 10 51 43 70 29 65 16 8 63 90 80 49 26 44 151 96 82 44 24 31 50 17 9 17 92 66 50 26 98 153 81 83 44 78 33 35 18 9 71 94 51 51 27 52 155 66 84 45 32 35 21 19 10 25 96 36 52 28 05 157 52 85 45 86 37 06 20 10 79 98 22 53 28 59 159 37 86 46 40 38 91 21 11 33 100 07 54 29 13 161 22 87 46 94 40 77 22 11 81 101 92 55 29 67 163 08 ...

Страница 95: ...e 100 ft min m sec 100 ft min m sec 100 ft min m sec 100 ft min 0 50 1 1 96 10 66 21 41 33 20 82 41 80 70 1 01 2 3 93 11 17 22 43 30 21 33 42 82 67 1 52 3 5 90 11 68 23 45 27 21 84 43 84 64 2 03 4 7 87 12 19 24 47 24 22 35 44 86 61 2 54 5 9 84 12 75 25 49 21 22 86 45 88 58 3 04 6 11 81 13 20 26 51 18 23 36 46 90 53 3 55 7 13 78 13 71 27 53 15 23 87 47 92 52 4 06 8 15 74 14 22 28 55 11 24 38 48 94 ...

Страница 96: ... 942 1 029 3 000 914 9 056 48 30 0 896 0 915 1 045 4 000 1219 7 075 44 73 0 863 0 888 1 061 5 000 1524 5 094 41 16 0 832 0 861 1 077 6 000 1829 3 113 37 60 0 801 0 835 1 090 1 000 2134 1 132 34 03 0 771 0 810 1 110 8 000 2438 0 850 30 47 0 742 0 785 1 128 9 000 2743 2 831 26 90 0 714 0 761 1 145 10 000 3090 4 812 23 33 0 687 0 738 1 163 11 000 3353 6 793 19 77 0 661 0 715 1 182 12 000 3658 8 774 1...

Страница 97: ...259 18 4 267 14 45 93 14 32 47 154 1 24 38 80 262 46 4 572 15 49 21 14 63 48 157 4 24 68 81 265 74 4 876 16 52 49 14 93 49 160 7 24 99 82 269 02 5 181 17 55 77 15 24 50 164 1 25 29 83 272 31 5 48 18 59 05 15 54 51 167 3 25 60 84 275 59 5 791 19 62 33 15 84 52 170 6 25 90 85 278 87 6 096 20 65 61 16 15 53 173 8 26 21 86 282 15 6 400 21 68 89 16 45 54 177 1 26 51 87 285 43 6 705 22 72 17 16 76 55 18...

Страница 98: ... 23 5 250 1043 7 30 8 2050 790 0 23 3 200 1037 5 30 6 2100 785 1 23 2 150 1031 4 30 5 2150 780 2 23 0 100 1025 3 30 3 2200 775 3 22 9 50 1019 3 30 1 2250 770 5 22 8 0 1013 3 29 9 2300 165 7 22 6 50 1007 3 29 7 2350 760 9 22 5 100 1001 3 29 6 2400 756 2 22 3 150 995 4 29 4 2450 751 4 22 2 200 989 4 29 2 2500 746 7 22 1 250 983 6 29 0 2550 742 1 21 9 300 977 7 28 9 2600 737 4 21 8 350 971 9 28 7 265...

Страница 99: ...37 8 15 3 800 2625 9 8 282 8 0 981 690 6 9389 0 908 0 115 1 134 0 925 1 039 337 4 15 4 900 2953 9 1 282 1 0 979 682 3 9276 0 897 0 114 1 123 0 916 1 044 337 15 5 1000 3281 8 5 281 5 0 977 674 1 9165 0 887 0 113 1 112 0 907 1 049 336 6 15 7 1100 3609 7 8 280 8 0 975 665 9 9053 0 876 0 112 1 101 0 898 1 055 336 2 15 8 1200 3937 7 2 280 2 0 972 657 9 8944 0 865 0 111 1 090 0 889 1 060 335 8 15 9 1300...

Страница 100: ...er www pipistrel si REV 0 Engine cover 1 2 Gascolator Right wingtip lights 7 8 Right wing trailing edge Undercarriage RH wheel 5 6 Right wing leading edge Propeller Spinner 3 5 Undercarriage 4 Preflight check up pictures ...

Страница 101: ...w pipistrel si REV 0 Right spoiler 9 10 Fuselage RH side Incorrect door not secured X OK Correct door secured Horizontal tail surfaces 12 13 Vertical tail surfaces Fuselage 10 11 Fuselage continued Preflight check up pictures ...

Страница 102: ...102 SINUS motorglider www pipistrel si REV 0 This page is intentionally left blank ...

Страница 103: ...t is handed over to the new owner This is the original document issued by Pipistrel d o o Ajdovscina Should third party translations to other languages contain any inconsistencies Pipistrel d o o Ajdovscina denies all responsibility This supplemental sheet provides changes and additions to Sinus ultralight motorglider Flight Manual and Maintenance Manual This supplemental sheet containes four 4 va...

Страница 104: ...ay not be copied or distributed in any manner electronic web or printed without the prior consent of PIPISTREL d o o Notes and remarks Safety definitions used in the manual WARNING Disregarding the following instructions leads to severe deterioration of flight safety and hazardous situations including such resulting in injury and loss of life CAUTION Disregarding the following instructions leads t...

Страница 105: ...a manner that the two main wheels touch the ground first allow the nose wheel touchdown only after speed has been reduced below 30 km h 18 kts When touching down rudder MUST NOT be deflected in any direction rudder pedals centred When on ground start braking action holding the control stick in full back position Stear the aircraft using brakes and rudder only Provided the runway length is sufficie...

Страница 106: ...he ground you can also use wheel brakes to assist your self I would recommend you taxi slow up to 10 km s 5 kts while holding the stick back fully to ease the pressure of the nose wheel Take off and initial climb As you start to move pull the stick 1 3 of elevator s deflection backwards to ease the pressure on the nose wheel and lift it off the runway slightly Do not use full back deflection as th...

Страница 107: ...ttle IDLE Choke AS NEEDED Master switch ON Magnetos ON AC lights ON After start up Warm up at 2500 3500 RPM Magneto RPM drop VERIFIED Engine Propeller check RPM within limits Before takeoff Fuel valves BOTH OPEN Spoilers RETRACTED Doors CLOSED Flight controls CHECKED Flaps 2 nd POSITION Elevator trim SET Propeller pitch SET After takeoff Elevator trim SET Flaps UP Descent Approach Throttle IDLE Fl...

Страница 108: ...108 SINUS motorglider www pipistrel si REV 0 This page is intentionally left blank ...

Страница 109: ... parts in case additional equipment is built in without Pipistrel d o o s prior knowledge in case the purchased goods were changed or modified in any way in case when the defect is caused by user s deficient maintenance inappropriate care and or cleaning user s negligent handling user s inexperience due to use of product and or its individual parts or components in inadequate conditions due to pro...

Страница 110: ...Pipistrel d o o Ajdovščina podjetje za alternativno letalstvo Goriška cesta 50a 5270 Ajdovščina Slovenija tel 386 0 5 3663 873 fax 386 0 5 3661 263 e mail pipistrel siol net www pipistrel si ...

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