Taurus ELECTRO G2 Flight Manual And Maintenance Manual Download Page 68

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TAURUS ELECTRO

www.pipistrel.si

REV. 3

Aircraft and systems on board

ESYS-MAN V2

electric system control & monitoring instrument

In order to simplify aircraft handling, the ESYS-MAN system takes complete control over the propul-

sion unit, including the “throttle” . The system is very light and reliable as all switches and sensors

used to monitor the operations are inductive type and as such not sensitive to vibration, mechanical

damage and/or dirt. ESYS-MAN provides protections to systems and is networked to the power con-

troller, motor arm controller, BMSs and charger via CAN bus.

System enable switch (ON/OFF)

– This is the switch that enables the power to the system. When

set to ON (up), the status of the system will be confirmed with the Status message above the switch.

This is the first switch to be enabled and last to be disabled during the operation of the propulsion

system. Indication via message (ON, OFF).

Position selector (UP/DOWN)

– use this switch to extend or retract the motor. The procedure is

fully automated (see next page!). Indication via message (UP, DN, UP-intermittant, DN-intermittant).

Throttle (RPM selector)

– rotary knob that acts as the throttle command. Rotate right for

incremental RPM increase and left for incremental RPM decrease. The throttle bar (bluish white)

below the RPM and PWR fields on the display corresponds to current throttle level. Rotating the

knob to the right will overrun the current throttle setting and initiate full power immediately

(regardless of engine temperatures and should only be used in emergency).

Extending the propeller arm:

WARNING!

BEFORE EXTENDING THE PROPELLER ARM IN-FLIGHT, SET FLAPS TO T STAGE AND

REDUCE SPEED TO 80 KM/H (45KTS) OR BELOW.

1. Switch the System enable switch ON (pull switch and move up).

This activates the system. Wait for ON indication on left-bottom of ESYS-MAN V2 (typically less

than 5 sec).

2. Switch the Position selector switch to UP (pull switch and move up).

The electric brake will hold the propeller steady when it is moving towards the extended position.

An intermittent UP message is displayed, indication the system in motion. Do not touch the unit

until solid UP is displayed.

Summary of Contents for ELECTRO G2

Page 1: ...aft make sure this document is given to the new owner Copyright Pipistrel d o o Ajdovščina Slovenia EU Revision 3 24th April 2015 This is the original manual of Pipistrel d o o Ajdovščina Should third party translations to other languages contain any discrepancies Pipistrel d o o Ajdovščina denies all responsibility Aircraft Registration Number Aircraft Serial Number ...

Page 2: ...ont ballast Available crew weight 9 kg front ballast Available luggage weight List of equipment included in aircraft empty weight Date and place of issue Ajdovščina To log into the Owner s section receive updates and Service Bulletins go to www pipistrel si and log in the top right corner of the page with Username owner1 Password ab2008 THANK YOU ...

Page 3: ...ginal date of Approval March 2011 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 Pipistrel d o o Ajdovščin...

Page 4: ... 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 27 October 2012 First original release Tomazic 1 Various Updates Revision 1 1 May 2013 Version No 1 All Coates M Revision 2 Reordering of chapters to comply with ASTM F2746 12 Revision 2 31 January 2014 Revision 2 All Coates M Revisi...

Page 5: ...EV 1 General 9 12 REV 1 Limitations 13 20 REV 3 Emergency procedures 21 28 REV 1 Normal procedures 29 42 REV 1 Performance 43 51 REV 1 Weight and balance 53 59 REV 1 Aircraft and systems on board 61 73 REV 1 Handling and maintenance 75 84 REV 1 Appendix 85 93 REV 1 CAUTION This manual is valid only if it contains all of the original and revised pages listed above Each page to be revised must be re...

Page 6: ...6 TAURUS ELECTRO www pipistrel si REV 3 This page is intentionally left blank ...

Page 7: ...ipistrel si REV 3 Table of contents 1 General 2 Limitations 3 Emergency procedures 4 Normal procedures 5 Performance 6 Weight and balance 7 Description of aircraft systems 8 Handling and maintenance 9 Appendix 10 Supplements ...

Page 8: ...8 TAURUS ELECTRO www pipistrel si REV 3 This page is intentionally left blank ...

Page 9: ...9 TAURUS ELECTRO www pipistrel si REV 3 Introduction Notes and remarks Technical data 3 view drawing General General ...

Page 10: ...consent of PIPISTREL d o o Ajdovscina unless they are directly related to the opera tion of our aircraft by an owner or his appointed maintenance authority Notes and remarks Safety definitions used in the manual WARNING DISREGARDING THE FOLLOWING INSTRUCTIONS WILL LEAD TO SEVERE DETERIORATION OF FLIGHT SAFETY AND HAZARDOUS SITUATIONS INCLUDING SUCH RESULTING IN INJURY AND LOSS OF LIFE CAUTION DISR...

Page 11: ...11 TAURUS ELECTRO www pipistrel si REV 3 3 view drawing General Dimensions in millimeters ...

Page 12: ...12 TAURUS ELECTRO www pipistrel si REV 3 This page is intentionally left blank ...

Page 13: ... REV 3 Introduction Operational velocities Motor Weight limits Centre of gravity limits Manoeuvre limits G load factors Cockpit crew Types of operations Minimum equipment list Other restrictions Warning placards Limitations Limitations ...

Page 14: ...ers above this speed Once fully extended VNE is the limit VLO Max ldg down speed 163 88 Do not fly with landing gear extended above this speed Airspeed indicator markings MARKING IAS km h kts Definition white arc 69 130 37 70 Speed range where flaps may be extended Lower end is de fined as 110 of VS stall speed in landing configuration at MTOM upper end of speed range is limited by VFE see above g...

Page 15: ...tude meters 0 500 1000 1500 2000 2500 3000 3500 4000 4500 5000 Altitude flight level 0 FL16 FL33 FL50 FL66 FL82 FL98 FL115 FL131 FL148 FL165 VNE IAS km h 220 215 211 206 202 197 192 188 184 179 175 VNE IAS kts 119 116 114 111 109 106 104 102 99 97 94 ISA 20 35 C at sea level Altitude meters 0 500 1000 1500 2000 2500 3000 3500 4000 4500 5000 Altitude flight level 0 FL16 FL33 FL50 FL66 FL82 FL98 FL1...

Page 16: ... recommended max continuous temperature 45 55 C WARNING DO NOT UNDER ANY CIRCUMSTANCES ATTEMPT TO USE ANY OTHER BATTERIES OTHER THAN PIPISTREL FACTORY ORIGINAL BATTERY SYSTEM WITH THIS MOTOR CONTROLLER Battery system Battery system Standard Maximum voltage 285 V Minimum voltage 204 V Recommended voltage range for storage 240 V 260 V Maximum operating temperature 70 C Minimum operating temperature ...

Page 17: ...ombined cockpit crew weight depends on C G of empty aircraft see p 55 maximum combined cockpit crew weight depends on C G of empty aircraft see p 55 water balance reservoir max weight 9 kg allowable luggage weight 10 kg WARNING SHOULD ONE OF THE ABOVE LISTED VALUES BE EXCEEDED OTHERS MUST BE REDUCED IN ORDER TO KEEP MTOM BELOW 550 KG MAKE SURE MAXIMUM AND MINIMUM COCKPIT CREW WEIGHT AS WELL AS AVA...

Page 18: ...s at VA at VNE max positive wing load 5 3 G 4 0 G max negative wing load 2 65 G 1 5 G Cockpit crew Actual minimum and maximum combined cockpit crew weight heavily depend on the centre of gravity of an empty aircraft Minimum and maximum combined cockpit crew weight is determined after weighing the aircraft each time Procedure for the deter mination of minimum and maximum combined cockpit crew weigh...

Page 19: ...r functional Compass functional Electric System Manager instrument ESYS MAN Battery Management System BMS functional Parachute rescue system where required legally Other restrictions Due to flight safety reasons it is forbidden to fly in any rainfall fly during thunderstorm activity fly in a blizzard fly according to instrumental flight rules IFR or attempt to fly in zero visibility condi tions IM...

Page 20: ...ecure baggage at all times N 030 060 300 W 330 E 120 150 S 210 240 N 030 060 300 W 330 E 120 150 S 210 240 VSO VS1 VFE VA VNO 34 kts 40 kts 70 kts 82 kts 82 kts VNE 120 kts Respect limits from POH EAW MTOW CREW WT LUGGAGE WT lbs 1212 lbs see POH 22 lbs EAW MTOW CREW WT LUGGAGE WT kg 550 kg see POH 10 kg PULL FOR PARACHUTE DEPLOYEMENT WARNING ROCKET FOR PARACHUTE DEPLOYEMENT INSIDE DANGER E X P L O...

Page 21: ...l si REV 3 Introduction Stall recovery Spin recovery Motor failure Landing out Motor fire Smoke in cockpit ESYS MAN failure Landing gear failure Flutter Exceeding VNE Parachute rescue system Emergencyprocedures Emergency procedures ...

Page 22: ...having spun 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 AIR CRAFT 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 THAN OVERSTRESSING THE AIRCRAFT HOWEVER VNE MUST NOT ...

Page 23: ...eserve if the chosen landing terrain length permits 4 After landing exit the aircraft immediately Propulsion unit extended or refusing to retract 1 Your first priority is to fly the aircraft Attempt to retract the propulsion unit by setting the retraction switch up and back down IF your height is 300 m or higher Otherwise proceed with emergency landing 2 Fasten your seat belts tightly 3 Master swi...

Page 24: ...ch to OFF 2 Open slide windows and set all ventilation devices to ON 3 Perform side slip crab manoeuvre in direction opposite the fire 4 Perform emergency landing procedure and abandon the aircraft immediately Battery system fire Land and abandon the aircraft as soon as possible WARNING USE ONLY WATERLESS FIRE EXTINGUISHING AGENTS TO EXTINGUISH ANY FIRE ON THE AIRCRAFT Smoke in cockpit 1 Leave the...

Page 25: ...n the whole aircraft start to vibrate violently Should flutter occur pull on the stick and reduce power immediately WARNING FLUTTERING OF AILERONS OR TAIL SURFACES MAY CAUSE PERMANENT STRUCTURAL DAMAGE AND OR INABILITY TO CONTROL THE AIRCRAFT AFTER A SAFE LANDING THE AIRCRAFT MUST UNDERGO A SERIES OF CHECK UPS PER FORMED BY AUTHORISED SERVICE PERSONNEL TO VERIFY AIRWORTHINESS Exceeding VNE Should ...

Page 26: ... OR HANGARED TO PREVENT ACCIDENTAL DEPLOYMENT HOWEVER AS SOON AS THE 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 motor failure over hostile terrain pilot incapacitation incl heart attack stroke temp blindness disorientation the parachute SHOULD be deployed Prior to firin...

Page 27: ...ou suspect any possible damage to the sys tem do not hesitate and immediately contact the manufacturer Handling and maintenance of Parachute rescue system Prior to every flight all visible parts of the system must be checked for proper condition Special at tention should be paid to corrosion on the activation handle inside the cockpit Also main fastening straps on the inside of the fuselage must r...

Page 28: ...28 TAURUS ELECTRO www pipistrel si REV 3 Emergency procedures This page is intentionally left blank ...

Page 29: ... TAURUS ELECTRO www pipistrel si REV 3 Introduction Assembling and disassembling the aircraft Daily check up Preflight check up Normal procedures and recommended speeds Normalprocedures Normal procedures ...

Page 30: ...ust make sure the spoiler and flap connectors 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 position holding the wing whereas the other two move over to the...

Page 31: ...the person in the cock pit remove the main spar pins one by one smoothly Forcing pins out of their position may result in structural damage therefore the wingtip holders must hold the wing halfs precisely at certain height Using slight circular movement at the wingtip the wing halfs must now be pulled out of the fuselage slowly On pulling each wing half must be held by two one at the wingtip and o...

Page 32: ...MUST be united during 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 Now use the enclosed T key to push the security screw down while spinning it cl...

Page 33: ...uts 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 ONLY No...

Page 34: ...PTER THE DAMAGE MUST BE REPAIRED PRIOR TO MOTOR START UP DISOBEYING THIS INSTRUCTIONS 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 Glass canopy 8 Right wing trailing edge 15 Hor tail surfaces left 2 LH flank 9 Right airbrake 16 Fuselage continued left 3 Nose ti...

Page 35: ...racks no wavy patterns impact spots Fuselage canopy frame joint equal spacing perfect closure Undercarriage wheels Bolts fastened Wheel no mechanical damage e g cracks clean Wheel axis and nut fastened Oil line hydraulic brakes no mechanical damage and or leakage Tyre no cracks adequate pressure Wheel fairing undamaged firmly attached clean e g no mud or grass on the inside Wheel bay doors undamag...

Page 36: ...parations along main chord Surface condition pristine no cracks impact spots or bumps no paint and or edge separations Horizontal tail surfaces Surface condition pristine no cracks impact spots or bumps no paint and or edge separations 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 hor...

Page 37: ... and in position Seat belts undamaged verify unobstructed harness opening fastening points intact Glass canopy perfect closing at all points smooth opening hinges firmly attached glass immacu lately clean with no cracks Flap handle button spring firm locking mechanism working properly smooth movement along full deflections no free play or visible damage Spoilers Airbrakes handle full forward and l...

Page 38: ...ERWISE YOU MAY BUMP INTO THE CANOPY OVERHEAD Motor start up Before motor start up CAUTION TO ENSURE PROPER AND SAFE USE OF AIRCRAFT IT IS ESSENTIAL FOR ONE TO FAMILIARISE WITH MOTOR S LIMITATIONS AND MOTOR MANUFACTURER S SAFETY WARN INGS BEFORE MOTOR START UP MAKE SURE THE AREA AROUND THE PROPELLER IS CLEAR YOU CAN ALSO CHECK THIS IN THE INSTRUMENT PANEL MIRROR IT IS RECOMMENDED TO START UP THE MO...

Page 39: ...COOL DOWN THE MOTOR FASTER Take off and initial climb Before lining up verify the following Spoilers retracted and secured Battery charge status and health sufficient and OK Safety belts fastened Cabin closed securely Trim handle in neutral position or slightly backward Flap handle Tposition Runway clear Now pull the stick to full aft position line up and add full power Verify motor for sufficient...

Page 40: ...speed and continue flying with flaps set to neutral position CAUTION IN ROUGH AIR EXTEND AIRBRAKES UNPOWERED FLIGHT FOR SHORT TIME IF NECESSARY TO KEEP AIRSPEED BELOW VRA Descent and final approach Landing the Taurus Electro with the motor up should be strongly avoided due stress on the propel ler mast It will decrease the life time of critical component as well Therefore it is recommended that yo...

Page 41: ...AIN SHOULD THIS OCCUR HOLD THE ELEVATOR STEADY UNDER NO CIRCUMSTANCES ATTEMPT TO FOL LOW AIRCRAFT S MOVEMENT WITH ELEVATOR DEFLECTIONS SINCE TAURUS ELECTRO TENDS TO ATTENUATE REBOUNDING BY ITSELF HOWEVER IT IS IMPORTANT TO MAINTAIN RUNWAY HEADING USING THE RUDDER AT ALL TIMES TO PREVENT THIS RETRACT SPOILERS ONLY AF TER THE AIRCRAFT HAS COME TO A COMPLETE STANDSTILL WARNING TOUCH AND GOES ARE NOT ...

Page 42: ...knob left and select engine DOWN Reduce speed to 80 km h 43 kts and set flaps to 1st stage Continue decelerating towards 70 km h 40 kts The system will complete the retraction extension by itself Once retracted confirmed by green LED status light select System enable OFF For more details please consult the ESYS MAN section in chapter Aircraft and Systems on board in this manual To restart the moto...

Page 43: ... pipistrel si REV 3 Introduction Airspeed indicator calibration Take off performance Climb performance Cruise Descent Landing performance Maneuver gust envelope Speed polar Additional technical data Performance Performance ...

Page 44: ...km h 40 5 kts flaps in neutral position 0 neutral 71 km h 38 3 kts flaps in 1st position 5 down 68 km h 36 7 kts flaps in T position 9 down 65 km h 35 0 kts flaps in L 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 550 kgs runway elevation 100 meters 330 feet wind calm runway dry grass runway with l...

Page 45: ...tude increases Effect of the wind Wind head cross or downwind also called tailwind affects aircraft s ground speed GS Headwind on takeoff and landing causes the Takeoff and Landing runway length to shorten as the GS is smaller during these two flight stages The opposite stands for tailwind on takeoff and landing as tailwind prolongs Takeoff and Landing runway length significantly The data on the n...

Page 46: ... data about the effect of headwind and tailwind on takeoff runway length windspeed m s 3 2 1 0 2 4 6 windspeed kts 6 4 2 0 4 8 12 Takeoff runway length m ft Electro 297 975 243 800 205 670 160 520 154 505 147 480 122 400 The graph below indicates how takeoff runway length changes when affected by wind Effect of outside temperature The table below provides data about the effect of outside temperatu...

Page 47: ...s data about the effect of elevation on climb rate at best climb speed Vy Taurus Electro 0 m 0 ft 3 1 m s 620 fpm 500 m 1600 ft 2 9 m s 580 fpm 1000 m 3300 ft 2 7 m s 540 fpm 1500 m 5000 ft 2 5 m s 500 fpm The graph below indicates how climb rate changes as altitude increases outside temperature C 5 10 15 20 25 30 35 0 50 160 150 500 200 650 100 330 250 820 m ft takeoff runway length 0 m s fpm 650...

Page 48: ... AND SHOULD ONLY BE ATTEMPTED BY EXPERIENCED PILOTS AND AT OWN RISK Crosswind landing limitations Maximum allowed crosswind speed for landing with flaps in L position as well as take off with flaps in T position is 28 km h 15 kts Performance Gliding performance The glide is defined as unpowered straight and level flight at a speed providing best lift over drag ratio or minimum sink rate Should the...

Page 49: ...30 4 00 1 50 2 65 2 04 4 81 2 81 4 04 4 3 2 1 0 1 2 3 4 5 6 0 20 40 60 80 100 120 140 160 180 200 220 240 260 280 300 EAS km h load factor manouever and gust TAURUS 360kg flap 0 6 96 5 25 1 97 3 48 2 68 5 61 4 68 3 61 4 3 2 1 0 1 2 3 4 5 6 7 0 20 40 60 80 100 120 140 160 180 200 220 240 260 280 300 EAS km h load factor ...

Page 50: ...strel si REV 3 Speed polar 472 kg prop unit landing gear retracted optimal flap settings Performance 0 0 0 5 1 0 1 5 2 0 2 5 3 0 60 80 100 120 140 160 180 200 airspeed km h sink speed m s 0 5 10 15 20 25 30 35 40 45 glide ratio ...

Page 51: ...x sink rate with spoilers extended 5 8 m s 1160 fpm best glide ratio speed 108 km h 58 kts takeoff runway length at MTOM 160 m 525 ft takeoff runway length at MTOM over 15 m obst 245 m 800 ft best glide ratio 1 41 glide ratio at 150 km h 1 32 45 left to 45 right bank to bank time 3 5 s battery capacity standard configuration 4 75 kWh battery capacity optional configuration 7 10 kWh useful battery ...

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Page 53: ...www pipistrel si REV 3 Weight and balance Weightandbalance Introduction Weighing and centre of gravity calculation for empty mass Weight and Balance report including Useful load distribution Definitions and explanations ...

Page 54: ...d scale readings subtract eventual tare weight in order to get net weight NOTE IF ACCURATE HIGH RANGE SCALES FOR MAIN WHEELS ARE NOT AVAILABLE AIR CRAFT EMPTY MASS MAY BE DETERMINED BY ADDING UP MASSES OF ALL COMPONENTS LEFT HAND WING RIGHT HAND WING FUSELAGE HORIZONTAL TAIL 6 Measure distances a and b between verticals through axis of main wheels tail wheel and datum Use plumb line to mark vertic...

Page 55: ...tion Fill in Weight and Balance report on the next page Empty mass c g limits diagram is used to find out maximum and minimum cockpit load with respect to mass and centre of gravity of empty aircraft Each weighing and centre of gravity calculation has to be entered in the Weight and Balance If minimum and maximum cockpit load change with respect to last weighing cockpit placard must be changed or ...

Page 56: ...list and without occupants fuel baggage and water ballast XCG empty G2 b Gempty a Useful load distribution 13 550 550 550 550 550 550 550 g k s s a m x a m 14 max useful load 13 10 kg 252 252 256 15 max cockpit load without w ballast declared see Notes kg 16 min cockpit load without w ballast from Empty mass c g limits diagram kg 86 0 82 0 78 0 17 Inspector signature stamp Notes Declared max cockp...

Page 57: ...G0 kg at the bottom horizontal axis and draw a vertical line through it 3 The intersection of two lines drawn determines minimum cockpit load Interpolate between lines of constant minimum cockpit load RED 65 70 75 kg if necessary NOTE MIN COCKPIT LOAD MAY BE REDUCED FOR 2 3 KG PER EACH LITRE OF W BALLAST Empty mass c g limits Cockpit load in kg with respect to mass and c g of empty aircraft 90 65 ...

Page 58: ...ty and distribution of useful load items are explained below However the influence of useful load items is briefly expressed in the condition that if for a given empty mass and c g the max useful max and min cockpit load from Weight and Balance or cockpit placard are respected aircraft max mass and in flight c g will also be kept within limits Refer to Weight and Balance or cockpit placard for act...

Page 59: ...oments of all items add up masses of all items divide the sum of moments kg mm by the sum of masses kg to obtain flight mass c g mm Reference masses and c g s of different items masses and c g s of different items mass distance from datum positive aft kg mm pilot only 550 pilot passenger 541 water ballast max 9 1800 baggage max 10 150 instruments 1140 parachute rescue system 550 tail wheel 4380 em...

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Page 61: ...vers Instrument panel Undercarriage Seats and safety belts Pitot static lining Air brakes spoilers Flap settings Power plant propeller Energy storage charging Electrical system Cooling system Wheel brake system Aircraftandonboardsystems Aircraft and systems on board ...

Page 62: ...s can be adjusted to suit your size and needs The batteries are in the fuselage placed in four metal boxes with dedicated connectors Charging must be carried out only with origi nal Pipistrel dedicated chargers The motor controller system Electro 40 30 is standard and the aircraft features the Master On board Computer MOC that provides throttle by wire capability The canopy is either transparent o...

Page 63: ...e parts are made of glass carbon and kevlar fiber manufactured by Interglas GmbH All composite parts have been tested at a safety factor of 1 875 All parts are made in molds therefore no shape or structural differences can occur All design manufacturing and testing complies with following regulations Lufttüchtigkeitsforderungen für aerodynamisch gesteuerte Ultraleichtflugzeuge LTF UL vom 30 Januar...

Page 64: ...e handle Instrument panel side window ventilation side window ventilation cabin lock lever cabin lock lever rudder pedals right rudder pedals left canopy lift pad canopy lift pad trim knob airbrakes wheelbrakes landing gear lever flap lever control stick right control stick left fuses pedal adjustment knob 12V socket master switch ESYS MAN throttle ventilation nozzle ventilation nozzle ventilation...

Page 65: ...ubber cushioned tail wheel Main gear is retracted lowered by operating a lever located between both seats accessible to both crew Once the main landing gear is lowered it is locked into position automatically Wheel brakes are both engaged simultaneously when the airbrakes are fully extended and the pilot continues to pull on the airbrake lever distance between main wheels 0 68 m distance between m...

Page 66: ...ension of 9 and 18 flaps there are recommendations for the use of flaps with different speed ranges and types of flight operation Recommended speed ranges for certain flap settings in when gliding flaps in negative position 5 up faster than 150 km h km h 80 kts flaps in neutral position 0 neutral 120 150 km h 65 80 kts flaps in 1st position 5 down 90 120 km h 50 65 kts flaps in T position 9 down 8...

Page 67: ... e extended or retracted This process is fully automated the propeller is positioned and held in place while the motor extends or retracts The pilot only selects the desired mode with the toggle switch The rotary encoder acts as the throttle selector The ESYS MAN also communicates with the Battery Management System and delivers information about the state of charge battery health information and m...

Page 68: ...tract the motor The procedure is fully automated see next page Indication via message UP DN UP intermittant DN intermittant Throttle RPM selector rotary knob that acts as the throttle command Rotate right for incremental RPM increase and left for incremental RPM decrease The throttle bar bluish white below the RPM and PWR fields on the display corresponds to current throttle level Rotating the kno...

Page 69: ...or IN FLIGHT WARNING WHEN IN FLIGHT SHUTTING DOWN THE SYSTEM IS ONLY PERMITTED WHEN THE PROPELLER IS IN THE RETRACTED POSITION ON GROUND THIS PRECAUTION IS NOT VALID 1 Retract the propeller arm 2 Switch the system enable switch to OFF down WARNING ALWAYS WAIT BEFORE THE SYSTEM IS CONFIRMED IN FULL EXTENDED OR FULL RETRACTED POSITION BEFORE OPERATING THE MASTER SWITCH OR THE SYSTEM ENABLE SWITCH TH...

Page 70: ... is recommended to disconnect the RED power connector on the box behind the cockpit section This will physically disconnect the high voltage part of the propulsion system Make sure you reconnect the battery before next flight Battery management system Each of the battery boxes have an independent BMS monitoring and balancing system voltage All units communicate to the ESYS MAN and log data from ea...

Page 71: ...e aircraft Confirm your selection with the OK button The charger will engage the charging relay and initiate charging During the charge the charger communicates with the BMS and balances the voltage of battery cells When charging and balancing is completed this is indicated by the display It is then safe to disconnect the charger To do so switch the rocker switch on the side of the charger to OFF ...

Page 72: ...fluid used for hydraulic type brakes is DOT 4 If the braking action on your aircraft is poor even while the full backward pressure is applied on the airbrake handle please see chapter on Handling and Maintenance of this manual to learn how to rectify this problem Electrical system Cockpit electrical system power supply lithium polymer pack charged by main charger 13 2 V nominal 10 Ah master switch...

Page 73: ...73 TAURUS ELECTRO www pipistrel si REV 3 Schematic of complete electrical system Aircraft and systems on board ...

Page 74: ...74 TAURUS ELECTRO www pipistrel si REV 3 Aircraft and systems on board This page is intentionally left blank ...

Page 75: ...si REV 3 Introduction Inspection periods Repairs and spare part replacements Preventative maintenance Special check ups Tie down Storage Cleaning Keeping your aircraft in perfect shape Handling andmaintenance Handling and maintenance ...

Page 76: ...nded 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 lubricate all designated parts and spots using proper lubricant DO IT YOURSELF R Replacement replace designated parts regardless of state and condition You are encouraged t...

Page 77: ...ors SC UNDERCARRIAGE O tires C C R wheel axis and wheels C wheel bearings C SC 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 difficult to reach bearings wings under cabin floor LO aileron elevato...

Page 78: ... ENERGY STORAGE SYSTEM Perform the keep alive refreshment charge once every 30 days as per page 71 Perform fill up charge 24 hours before flying ELECTRICAL WIRING SC R instr panel wires and connectors C C fuses instrument panel automatic C C C C C C C fuses motor electrical panel C C R Current maintenance schedule for the power train is preliminary and determined according to Pipistrel s best know...

Page 79: ...V 3 Spoilers airbrakes drive fine adjustment CAUTION PERFORM THIS OPERATION ONLY ONCE AFTER FIRST 50 FLIGHT HOURS CHECK SPOILERS THOROUGHLY FOR UNOBSTRUCTED SMOOTH AND EVEN EXTENSION BEFORE EVERY FLIGHT Handling and maintenance 1 2 3 4 5 4 ...

Page 80: ...sed to low temperatures materials shrink Therefore flying in the winter or in cold temperatures you may encounter click clack like noises from behind you The remedy for this unwanted noise is to add washers typically of 0 5 mm thickness in between wing and fuselage Washers must be added both at rear and front bushings on one side of the fuselage only WARNING IT IS MANDATORY TO CONSULT THE MANUFACT...

Page 81: ... back it is not necessary the 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 replacement nut 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 Sc...

Page 82: ...ake handle unlocked in order to reduce pressure on plate springs in order to maintain their original stiffness As for the parachute rescue system make sure the activation handle safety pin is inserted every time you leave the aircraft CAUTION SHOULD THE AIRCRAFT BE STORED AND OR OPERATED IN AREAS WITH HIGH AT MOSPHERIC HUMIDITY PAY SPECIAL ATTENTION TO EVENTUAL CORROSION OF METAL PARTS ESPECIALLY ...

Page 83: ...ished with flight activity for the day clean the leading edges of the airframe as soon as possible with a lot of water and a drying towel chamois artificial leather skin This will be very easy to do if you applied a coat of Pronto before flight Detailed handling Airframe cleaning instructions Every day care after flight Bugs which represent the most of the dirt to be found on the airframe are to b...

Page 84: ...along the whole span of the gasket Ultimately you may wish to apply Teflon grease in spray over the area where the gaskets touch the control surfaces Polishing by hand Use only the highest quality polishing pastes WITHOUT abrasive grain such as Sonax Extreme no 1 or similar Start polishing on a clean dry and cool surface never in the sunshine Machine polishing requires more skills and has its own ...

Page 85: ...85 TAURUS ELECTRO www pipistrel si REV 3 Conversion tables Preflight check up pictures Appendix Appendix ...

Page 86: ...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 8...

Page 87: ... 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 4...

Page 88: ... 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...

Page 89: ...9 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 55 180 ...

Page 90: ...3 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 2650 ...

Page 91: ... 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 4...

Page 92: ...US ELECTRO www pipistrel si REV 3 Cockpit 1 2 Cockpit aft Undercarriage RH wheel 5 6 Starboard wing leading edge Nose Pitot tube Ventilation 3 5 Wing root Preflight check up pictures 2 Canopy Balance weight 4 ...

Page 93: ...pipistrel si REV 3 Starboard wingtip 7 8 Starboard wing trailing edge Starboard airbrake 9 10 Wing root Horizontal tail surfaces 12 13 Vertical tail surfaces Propulsion system 10 11 Motor bay door Preflight check up pictures ...

Page 94: ...94 TAURUS ELECTRO www pipistrel si REV 3 This page is intentionally left blank ...

Page 95: ...nal equipment is installed 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 prolonged use of the pro...

Page 96: ... Ajdovščina podjetje za alternativno letalstvo Goriška cesta 50a SI 5270 Ajdovščina Slovenija tel 386 0 5 3663 873 fax 386 0 5 3661 263 e mail info pipistrel si www pipistrel si www pipistrel eu www pipistrel usa com ...

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