Pipistrel VELIS Electro Pilot Operating Handbook Download

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5-5

VELIS Electro

Pilot's Operating Handbook

POH

128

001

PAGE REV. 0

PAGE

SECTION

PERFORMANCE DATA

APPROVED

5.3

WIND COMPONENT

EXAMPLE:

Runway Heading:

10°

Wind Direction:

60°

Angle between wind and runway: 50°
Wind Velocity:

15 Knots

Component parallel:

~9,6 Knots

Component perpendicular:

~11,5 Knots

Summary of Contents for VELIS Electro

Page 1: ..._________ All rights reserved Reproduction or disclosure to third parties of this document or any part thereof is not permitted except with the prior and express written permission of Pipistrel Group...

Page 2: ...Tel 386 5 36 63 873 Fax 386 5 36 61 263 Email info pipistrel si This handbook includes all of the material required to be provided to the pilot by CS LSA regulations Additional information deemed nece...

Page 3: ...POH 128 00 40 001 PAGE REV 0 PAGE SECTION CONTENTS 0 FOREWORD 1 GENERAL 2 LIMITATIONS 3 EMERGENCY PROCEDURES 4 NORMAL PROCEDURES 5 PERFORMANCE DATA 6 WEIGHT AND BALANCE 7 AIRPLANE DESCRIPTION 8 HANDLI...

Page 4: ...e within the POH As revisions to the POH occur the revision number on the affected pages is updated and the page number in the log is highlighted with bold font type When two pages display the same pa...

Page 5: ...v VELIS Electro Pilot s Operating Handbook POH 128 00 40 001 PAGE REV 0 PAGE Doc Rev Reason for revision Affected pages Authority B00 Initial ALL EASA 10 06 2020 Index of document revisions...

Page 6: ...Cover ii 0 iii 0 iv 0 v 0 vi 0 vii 0 viii 0 3 3 3 35 0 3 36 0 3 37 0 3 38 0 3 39 0 3 40 0 3 41 0 3 42 0 3 43 0 3 44 0 3 45 0 3 46 0 3 47 0 3 48 0 3 49 0 3 50 blank 3 51 0 3 52 0 3 53 0 3 54 0 3 55 0...

Page 7: ...UMBER PAGE REV PAGE NUMBER PAGE REV PAGE NUMBER PAGE REV 5 5 1 0 5 2 0 5 3 0 5 4 0 5 5 0 5 6 0 5 7 0 5 8 0 5 9 0 5 10 0 5 11 0 5 12 0 5 13 0 5 14 0 5 15 0 5 16 0 5 17 0 5 18 0 5 19 0 5 20 0 5 21 0 5 2...

Page 8: ...AGE NUMBER PAGE REV 9 A1 9 A1 1 0 9 A1 2 0 9 A1 3 0 9 A1 4 0 9 A1 5 0 9 A1 6 0 9 A1 7 0 9 A1 8 0 9 A1 9 0 9 A1 10 0 9 A1 11 0 9 A1 12 0 9 A1 13 0 9 A1 14 0 9 A1 15 0 9 A1 16 0 9 A1 17 blank back cover...

Page 9: ...SECTION 1...

Page 10: ...N 1 3 1 2 DESCRIPTION 1 3 1 3 CERTIFICATION BASIS 1 3 1 4 THREE VIEW DRAWINGS 1 4 1 5 DIMENSIONS AND WEIGHTS 1 5 1 6 SYSTEMS 1 5 Engine Propeller Battery System Landing Gear 1 7 SYMBOLS ABBREVIATIONS...

Page 11: ...ectric engine E 811 268MVLC and a fixed pitch propeller Pipistrel P 812 164 F3A The seats are side by side with full dual flight controls and shared levers for power output and flaperon control Access...

Page 12: ...1 4 PAGE VELIS Electro Pilot s Operating Handbook POH 128 00 40 001 PAGE REV 0 SECTION 1 GENERAL VELIS Electro 3 view drawing 1 4 THREE VIEW DRAWING...

Page 13: ...Design empty weight 428 kg Design useful load 172 kg Maximum baggage weight No baggage 1 6 SYSTEMS 1 6 1 ENGINE The aircraft s Pipistrel E 811 268MVLC engine consists of an electric motor the Pipistr...

Page 14: ...ore and aft of the cabin This ensures redundancy of the power source In case of battery failure the faulty battery gets automatically disconnected from the system A single battery is capable of standa...

Page 15: ...which applica tion of full control movement will not overstress the airplane VFE Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position VNO Max...

Page 16: ...n sea level It is the altitude read from the altimeter when the altimeter s barometric adjustment has been set to the altimeter set ting obtained from ground meteorological sources OAT Outside Air Tem...

Page 17: ...TEM In this POH is defined as the system composed by electric mo tor power controller propeller and batteries RFT Remaining Flight Time displayed on EPSI for information only RPM Revolutions Per Minut...

Page 18: ...ge of Mean Aerodynamic Chord is the forward edge of MAC aft of the reference datum Maximum Gross Weight is the maximum permissible weight of the air plane and its contents as listed in the aircraft sp...

Page 19: ...8 CONVERSION TABLE SI US US SI 1 bar 14 5037 psi 1 psi 0 0689 bar 1 mm2 0 0016 in2 1 in2 625 mm2 1 cm2 0 1550 in2 1 in2 6 4510 cm2 1 daN 2 2481 lbf 1 lbf 0 4448 daN 1 g 0 0353 oz 1 oz 28 328 g 1 hPa...

Page 20: ..._Manual_Y1 03 0282J 3 EIM 811 00 60 7202 Engine Operator s Manual 4 PIM 812 61 00 001 Propeller Instruction Manual 5 AMM 128 00 60 001 Aircraft maintenance manual 6 Horis Installation and User Manual...

Page 21: ...SECTION 2...

Page 22: ...OF GRAVITY LIMITS 2 5 2 7 OCCUPANCY 2 5 2 8 COOLANT 2 6 2 9 FLIGHT LOAD FACTOR LIMITS 2 6 2 10 MANEUVER LIMITS 2 6 2 11 ALTITUDE LIMITS 2 7 2 12 TEMPERATURE LIMITS 2 7 2 13 MINIMUM FLIGHT CREW 2 7 2 1...

Page 23: ...emarks VNE 108 Never Exceed Speed is the speed limit that may not be exceeded at any time Maximum speed for all operations VNO 98 Maximum Structural Cruising Speed is the speed that should not be exce...

Page 24: ...el propeller P 812 164 F3A Maximum rpm 2500 RPM Maximum continuous rpm 2300 RPM MARKING VALUE REMARKS White Arc 46 81 Flap Operating Range Lower limit is the most adverse stall speed in the landing co...

Page 25: ...al markings for motor power indication on EPSI570C are a Single battery operation power setting 40 kW b Minimum Performance Take Off Power MPTOP 50 kW low battery SOH 2 6 WEIGHT AND CENTER OF GRAVITY...

Page 26: ...xpansion tanks visible through check windows Cooling system capacity 0 9 L for engine system 5 4 L for battery system 2 9 FLIGHT LOAD FACTOR LIMITS Up to VA 4 0 g 2 0 g Up to VNE 4 0 g 2 0 g 2 10 MANE...

Page 27: ...Minimum battery temperature before engine start is 0 C Protected by automatic self test at start up Maximum battery temperature at take off is 45 C Charging temperature range is 0 C battery temperatu...

Page 28: ...h Trim Actuator 1 Airplane Flight Manual 1 Airspeed Indicator 1 Altimeter 1 Magnetic Compass 1 Pitot System 1 Static System 1 Kanardia Horis Vertical Speed Indicator EPSI570C 1 High Voltage Battery 2...

Page 29: ...risk of thunderstorms should be avoided Smoking is prohibited Do not fly when the temperature of the aircraft s surface is at risk of exceed ing 55 C Aircraft can be operated only when 20 C OAT 35 C...

Page 30: ...S 135 KIAS VNE MAX EXTENSION SPEED VFE VNE 163 KTAS OPERATING SPEEDS 1111824 47 KIAS 53 KIAS 100 KIAS 120 KIAS ALT SL FL60 FL120 FL180 VNE 163 149 136 123 VS0 VS VA VNO 1111500 3 5 l OIL Refer to ROTA...

Page 31: ...H VOLTAGE 1111986 On battery packs BATTERY COOLING INLET KEEP CLEAR 1111590 Next to battery cooling inlet outlet on the fuselage Around the static ports 2x Around the drainage holes in fuselage wings...

Page 32: ...0LL change oil and oil filter every 50 hrs FUEL QTY 50 LITRES 13 2 USgal min 95 RON AKI 91 max 10 ethanol content MOGAS or AVGAS 100LL OPE CLOSED OPEN CLOSE 1111728 This aircraft is approved to fly in...

Page 33: ...T w w w p i p i s t r e l s i 1111700 1111701 1111705 L R HEADSET L R MIC 1111706 T H R O T T FULL ON C H O K E OFF PARKING BRAKE ON OFF 1111717 USgal Liter Liter USgal 5 5 1 1 10 10 3 3 15 15 20 20 4...

Page 34: ...MIT 25 KG 5 DANGER O C K E T E X P L O 1111552 3 8 6 5 p i s t r e l s i is equipped with ally deployed arachute system 1111553 1111559 WARNING When using AVGAS 100LL change oil and oil filter every 5...

Page 35: ...Electro Pilot s Operating Handbook POH 128 00 40 001 PAGE REV 0 PAGE SECTION 2 LIMITATIONS APPROVED 2 16 6 PLACARDS EXTERNAL HIGH VOLTAGE HAZARD On the aircraft belly 3x On battery compartment access...

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Page 37: ...SECTION 3...

Page 38: ...ss Battery Failure at System Start Up Battery Coolant Fan Failure Only One Battery Connected DC DC Converter Failures Propulsion System Component Failures Power Lever Engine Communication Failure 3 5...

Page 39: ...ht Power Lever Communication Failure Battery Current Not Equal 3 6 FIRE IN FLIGHT 3 39 Engine Fire in Flight Battery System Fire Cockpit Fire in Flight 3 7 SPINS 3 41 3 8 EXCEEDING VNE 3 41 LANDING EM...

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Page 41: ...d during the previous flight or while the airplane was on the ground Aircraft emergencies are very dynamic events Because of this it is impossi ble to address every action a pilot might take to handle...

Page 42: ...e nearest suitable landing area 3 2 WARNING CAUTION INDICATION SYSTEM The aircraft is equipped with two main independent failure indication sys tems The first is composed of the EPSI570C display and a...

Page 43: ...display software malfunction the analog system remains operative NOTE Battery overtemperature requires emergency procedures described in section Battery Overtemperature 3 5 7 See section 3 2 1 for th...

Page 44: ...RE This message indicates that the system has automatically disconnected a battery pack due to one of the reasons listed 3 4 9 3 5 5 BATTERY F R DISCONNECTED DUE TO OVERTEMPERATURE This message indica...

Page 45: ...State of charge is less than 30 3 4 9 3 5 12 NO GO AROUND AVAILABLE Appears when SOC 15 Batteries are almost discharged Only few minutes of power left 3 5 13 BATTERY F R STARTUP FAILED This message a...

Page 46: ...ONS Caution Message Description Action SYSTEM ISOLATION FAILURE The system has detected a failure in the electrical insulation between high voltage and low voltage systems lines 3 5 19 DC DC COMMUNICA...

Page 47: ...nd react as follows 1 Come to a complete standstill 2 MASTER switch OFF 3 BATT EN switch OFF 4 PWR EN switch OFF 5 BATT REAR BATT FRONT circuit breakers DISENGAGE 6 PWR CTRL circuit breaker DISENGAGE...

Page 48: ...continually cooling down the batteries and surrounding items with copious amount of water NOTE expect battery overtemperature analog warning lights ON in case of battery fire overtemperature WARNING D...

Page 49: ...malfunction during system test or temperatures below 0 C the following caution messages can appear EPSI570C message Annunciator BATTERY F R SELFTEST PBIT LOW TEMP FAILED amber or BATTERY F R STARTUP F...

Page 50: ...amber 1 Recharging procedure ABORT NOTE Contact CAMO CAO 3 4 7 ONLY ONE BATTERY CONNECTED If a battery is not detected in the CAN bus communication line also conse quent to battery circuit breaker di...

Page 51: ...off Check battery connec tors If the problem is not solved contact CAMO CAO If they appear in flight see Single battery disconnection emergency procedures 3 5 5 3 4 8 DC DC CONVERTER FAILURES When th...

Page 52: ...ble runway permit safe aircraft stoppage 1 Come to a complete standstill PERFORM 2 MASTER switch OFF NOTE If the warning caution message is battery related disengage affect ed battery circuit breaker...

Page 53: ...t for lift off and climb 1 PWR CTRL circuit breaker DISENGAGE 2 Power lever CUT OFF 3 Come to a complete standstill PERFORM 4 Shutdown procedure PERFORM 5 Push the aircraft off the runway PERFORM 6 Pa...

Page 54: ...opriate ESTABLISH 2 BATT FRONT BATT REAR Circuit breakers DISENGAGE 3 PWR CTRL Circuit breaker DISENGAGE 4 Flaps AS REQUIRED 5 Land emergency landing PREPARE TO LAND WARNING Do not change course or ma...

Page 55: ...ing area attempt to identify the cause of the failure and correct it 1 Best Glide Speed flaps 0 ESTABLISH 70 KIAS If time permits 2 Motor restart in flight procedure 3 5 3 ATTEMPT If restart is not ef...

Page 56: ...e 9 Emergency landing procedure 3 9 1 PERFORM 3 5 4 PARTIAL POWER LOSS Possible causes for a partial loss of power include power controller system controller or power lever malfunctions fluctuating RP...

Page 57: ...57 KIAS 3 Climb over the obstacles to safe altitude PERFORM 4 Propulsion system parameters CHECK MONITOR 5 Land AS SOON AS PRACTICAL Partial power loss in flight If a partial engine failure permits le...

Page 58: ...tic battery f r disconnected due to overtempera ture see specific Battery overtemperature procedures 3 5 7 EPSI570C message Annunciator BATTERY F R DISCONNECTED DUE TO OVERVOLTAGE UN DERVOLTAGE INTERL...

Page 59: ...battery operative However in exceptional cases i e traffic obstacle avoidance full throttle can be ap plied for a recommended maximum duration of 30 seconds If possible use power settings below 30 kW...

Page 60: ...SI570C message Annunciator BATTERY F R HIGH TEMPERATURE amber or Perform the following 1 Power Lever Reduce 30 kW 2 Battery temperature MONITOR If battery temperature remains in the caution range 3 La...

Page 61: ...DISCONNECTED DUE TO OVERTEMPERATURE red or Also expect the battery overtemperature warning light of the affected bat tery to illuminate independent analog system Perform the following 1 Reduce power...

Page 62: ...ttings or prolonged full power applications may cause overtemperature or disconnection due to undervoltage of the remaining battery WARNING Battery overtemperature may induce battery thermal run away...

Page 63: ...l disconnection is required HV BATT F R circuit breaker disengage ment applying Single battery disconnection procedure 3 5 5 Double battery loss of communication EPSI570C message Annunciator BATTERY F...

Page 64: ...to engine coolant pump malfunction Engine coolant pump malfunction is usually detected and sig naled by a caution message see 3 5 18 If the engine high temperature is caused by coolant pump failure e...

Page 65: ...the temperatures have dropped out of the warning range Expect imminent power cut to zero in case of high power usage If partial power is still available and the engine coolant pump is functional perf...

Page 66: ...uce power AS MUCH AS POSSIBLE 2 Battery status current of both batteries CHECK if both batteries are still connected current of both batteries 0 A 3 Battery temperatures and currents MONITOR 4 Land AS...

Page 67: ...EPARE TO LAND NOTE A normal mission must terminate with SOC 30 at landing 3 5 13 NO GO AROUND AVAILABLE If the flight continues and SOC decreases to 15 the following caution message appears EPSI570C m...

Page 68: ...is is not the case for normal SOC decrease during flight After SOC is recalculated expect the following caution message EPSI570C message Annunciator BATTERY F R SOC ADJUSTED amber or 1 Updated SOC val...

Page 69: ...ttery voltage decreases rapidly especially when high power is applied at low SOC If the battery disconnects 3 Single battery disconnection procedure 3 5 5 PERFORM CAUTION In the case of battery underv...

Page 70: ...acle avoidance 3 5 17 ENGINE COMMUNICATION FAILURE In the case of engine communication failure the power setting can t be ad justed by the pilot and will stay the same as it was before the communica t...

Page 71: ...t valid output Engine temperatures and other parameters will not be available and can t be monitored Be prepared to the possibility of engine temperature rising if communication was lost at high power...

Page 72: ...M INSULATION FAILURE When the system detects an electrical insulation failure between high volt age and low voltage systems wirings expect the following caution message to appear EPSI570C message Annu...

Page 73: ...AS SOON AS PRACTICAL NOTE aux battery guarantees at least 30 minutes of power 3 5 21 POWER LEVER COMMUNICATION FAILURE In the case of power lever communication failure the power setting can t be chan...

Page 74: ...h the motor off 3 PWR CTRL circuit breaker DISENGAGE 4 Emergency Landing 3 9 1 PERFORM 3 5 22 BATTERY CURRENT NOT EQUAL If the system detects disproportionate current drain between the two batter ies...

Page 75: ...ystem fire will trigger warning and cautions similar to those in a battery high temperature emer gencies see section 3 5 6 Expect battery high overtemperature cautions and warnings to appear on the EP...

Page 76: ...ilable or any other means to extinguish flames and land as soon as possible Opening the vents may feed the fire but to avoid incapacitating the crew from smoke inhalation it may be necessary to rid ca...

Page 77: ...elt and a spiral or spin may be entered In some cases it may be difficult to determine if the aircraft has entered a spiral or the beginning of a spin In any case spin recovery technique is classic 1...

Page 78: ...ting an off airport landing fly over the landing area at a low but safe altitude to inspect the terrain for obstructions and surface conditions NOTE Use of full 2 flaps will reduce glide distance Full...

Page 79: ...ELT switch ON 11 Approach High seas high wind into the wind Light wind heavy swells parallel to the swells 12 Doors OPEN 13 AUX BATT circuit breaker DISENGAGE 14 Flaps 2 15 Landing at the lowest possi...

Page 80: ...t be applied strongly if necessary to the point where the wheel locks CAUTION A defective tire is not easy to detect The damage normally occurs during take off or landing and is hardly noticeable duri...

Page 81: ...e EPSI display the Kanardia instrument serves as backup for kW and RPM indication and can be used together with other remaining instruments for the continuation of the flight ASI ALT Compass VSI Horis...

Page 82: ...peed are suspected the information from the GPS system should be used for situational awareness NOTE Referring to the GPS for flying adjust indicated airspeed during climb or approach Use 10 KTS on to...

Page 83: ...GRASP STICK MAINTAIN MANUALLY If problem is not corrected 2 TRIM Circuit Breaker DISENGAGE 3 Power Lever AS REQUIRED 4 Control Stick MANUALLY HOLD PRESSURE 5 Land AS SOON AS PRACTICAL 3 14 AUXILIARY B...

Page 84: ...ilures use the GPS information to reference to approximate ground speed Plan the landing at the nearest airport or a suitable off airport landing site in case of an extremely rapid ice build up Increa...

Page 85: ...EV 0 PAGE SECTION 3 EMERGENCY PROCEDURES 3 49 VELIS Electro Pilot s Operating Handbook PAGE SECTION 3 EMERGENCY PROCEDURES CHECKLISTS CHECKLISTS EMERGENCY PROCEDURES 3 16 NOTE Use of the following che...

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Page 87: ...ISENGAGE PWR CTRL circuit breaker DISENGAGE Emergency ground egress procedure PERFORM BATTERY FIRE ON THE GROUND Come to a complete standstill MASTER switch OFF BATT EN switch OFF BATT REAR BATT FRONT...

Page 88: ...yet DO NOT TAKE OFF If the take off run is initiated and conditions speed available runway permit safe aircraft stoppage Come to a complete standstill PERFORM MASTER switch OFF Affected battery circu...

Page 89: ...e PERFORM If take off run is initiated and there is enough runway to stop the aircraft or power speed is not sufficient for lift off and climb PWR CTRL circuit breaker DISENGAGE Power lever CUT OFF Co...

Page 90: ...H 70 60 KIAS BATT REAR BATT FRONT circuit breakers DISENGAGE PWR CTRL Circuit breaker DISENGAGE Flaps AS REQUIRED Land emergency landing PREPARE TO LAND COMPLETE IN FLIGHT POWER LOSS Best Glide speed...

Page 91: ...ower lever CUT OFF PWR EN Switch OFF MASTER Switch OFF PWR CTRL Circuit breaker DISENGAGE After 3 seconds PWR CTRL Circuit breaker ENGAGE MASTER switch ON PWR EN switch ON Power lever Slowly increase...

Page 92: ...eed Vx 57 KIAS Climb over obstacles PERFORM Propulsion system parameters EPSI CHECK MONITOR Land AS SOON AS PRACTICAL PARTIAL POWER LOSS in flight EPSI570C annunciator CHECK for Caution Warning messag...

Page 93: ...UNDERVOLTAGE INTERLOCK ERROR INTERNAL HARDWARE FAILURE red Affected battery circuit breaker DISENGAGE Other EPSI messages sub sequent to disconnection ACKNOWLEDGE SOC RFT battery temperature MONITOR...

Page 94: ...OON AS PRACTICAL BATTERY OVERTEMPERATURE temperature in warning range WARNING BATTERY F R DISCONNECTED DUE TO OVERTEMPERATURE red Reduce power AS MUCH AS POSSIBLE Affected battery circuit breaker DISE...

Page 95: ...isconnection ACKNOWLEDGE SOC RFT battery temperature MONITOR Reduce power AS MUCH AS POSSIBLE Land AS SOON AS PRACTICAL BATTERY NOT PRESENT double batt CAUTION BATTERY F NOT PRESENT amber and BATTERY...

Page 96: ...E OVERTEMPERATURE temperature in warning range continues from Engine High Temperature WARNING ENGINE OVERTEMPERATURE red CAUTION POWER DERATING ACTIVE If partial power is still available and the engin...

Page 97: ...ted current of both batteries 0 A Battery temperatures and currents MONITOR Land AS SOON AS PRACTICAL if one battery is disconnected current 0A and caused overcurrent to the other Circuit breaker of b...

Page 98: ...e to drop and eventual battery disconnection BATTERY SOC ADJUSTED CAUTION BATTERY F R SOC ADJUSTED amber Updated SOC value CHECK SOC and RFT MONITOR BATTERY CELL LOW VOLTAGE CAUTION BATTERY F R LOW CE...

Page 99: ...y If both coolant pumps fail two caution messages Reduce power AS MUCH AS POSSIBLE Battery temperatures MONITOR Land AS SOON AS PRACTICAL ENGINE COMMUNICATION FAILURE CAUTION ENGINE COMMUNICATION FAIL...

Page 100: ...se residual power for obstacle avoidance only ELECTRICAL SYSTEM INSULATION FAILURE CAUTION SYSTEM ISOLATION FAILURE amber Land AS SOON AS PRACTICAL CAUTION Any inspection troubleshooting by the pilot...

Page 101: ...gliding distance from the elected landing site and when ready for a power out approach PWR CTRL circuit breaker motor will quit DISENGAGE Emergency landing procedure PERFORM BATTERY CURRENT NOT EQUAL...

Page 102: ...ows OPEN Side slip direction opposite to the fire IF POSSIBLE Land emergency AS SOON AS POSSIBLE Airplane EVACUATE BATTERY SYSTEM FIRE Affected battery circuit breaker DISENGAGE Land IMMEDIATELY Airpl...

Page 103: ...1 PAGE REV 0 PAGE SPIN Power lever CUT OFF Rudder Full deflection direction opposite to the spin Control stick Push forward As rotation stops Rudder Neutralize Horizontal flight Resume careful not exc...

Page 104: ...lts SECURED Flaps when landing is assured 2 If time permits Radio Transmit 121 5 MHz MAYDAY Transponder SQUAWK 7700 ELT Switch ON if necessary DITCHING Best Glide Speed 70 KIAS flaps 0 Power lever CUT...

Page 105: ...anding at the lowest possible speed PERFORM Seat belts Release immediately Airplane EVACUATE Life vest and raft Inflate when outside the cabin Flotation Devices INFLATE WHEN CLEAR OF AIRPLANE LANDING...

Page 106: ...SOON AS PRACTICAL EPSI570C communication failure Reduce power AS MUCH AS POSSIBLE Annunciator Batt Overtemp warning lights MONITOR Land AS SOON AS PRACTICAL RADIO COMMUNICATION FAILURE Switches Contro...

Page 107: ...00 40 001 PAGE REV 0 PAGE ELECTRIC TRIM FAILURE Airplane Control GRASP STICK MAINTAIN MANUALLY TRIM Circuit Breaker DISENGAGE Power Lever AS REQUIRED Control Stick Manually hold pressure Land AS SOON...

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Page 109: ...SECTION 4...

Page 110: ...8 Before Starting Motor Starting the Motor Before Taxiing Taxiing Before Take off 4 5 TAKE OFF 4 12 Take off Run and Flap settings 4 6 CLIMBING 4 13 4 7 CRUISE 4 13 4 8 DESCENT APPROACH 4 13 4 9 LANDI...

Page 111: ...actual mass However to achieve the performance specified in Section 5 for take off and landing dis tance the speed correction adjusted to the particular mass must be used TAKE OFF ROTATION Normal Fla...

Page 112: ...mportant to remove the upper engine cowling and crew seats for a general inspection at least before the first flight of the day Special attention should be paid to any signs of leakage Coolant level s...

Page 113: ...CHECK no warnings cautions 20 AUX BATT Voltage on EPSI570C CHECK 13V 21 Battery SOC SOH temperature and status ACTIVE system page CHECK 22 Engine power controller and motor temperatures CHECK 23 BAT E...

Page 114: ...nkles 6 Hinges nuts CHECK condition Secured EMPENNAGE 1 Tie down rope Remove 2 Horizontal and vertical stabilizers CHECK condition 3 Elevator and elevator U piece Condition and movement 4 Rudder Condi...

Page 115: ...on 3 Hub and blades CHECK condition and blade pitch marker paint at blade roots 4 Spinner CHECK condition 5 Propeller spinner bolts and screws CHECK 6 Air inlets outlets Unobstructed 7 Charging port d...

Page 116: ...ficient battery power for the planned duration of flight in any case 50 SOC and landing with 30 residual SOC BEFORE START UP 1 MASTER switch CHECK OFF 2 AVIONICS switch CHECK OFF 3 BATT EN switch CHEC...

Page 117: ...ECK sufficient for flight and 50 CAUTION Do not take off if SOC is 50 Recharge the batteries 5 Batteries SOH on EPSI570C CHECK 0 CAUTION Do not take off if SOH 0 Contact CAMO CAO 6 AUX Batt voltage on...

Page 118: ...During the taxi use minimum power for movement and proper braking pro cedures If this is not observed the brake system may overheat and result in brake damage or brake fire 4 4 4 BEFORE TAKE OFF WARNI...

Page 119: ...or high power settings are applied See also Section 3 Emergency procedures 4 5 TAKE OFF 4 5 1 TAKE OFF RUN AND FLAP SETTINGS For take off over a gravel or grass surface advance power lever slowly This...

Page 120: ...rect for drift TAKE OFF 1 Power lever FULL 2 Power indication CHECK 50 kW 3 EPSI570C annunciator CHECK GREEN NORMAL no warnings or cautions 4 Airspeed CHECK increasing 5 Rotate SET slight positive pit...

Page 121: ...egs with short cruise phases at lower power settings is recommended NOTE VX 57 KIAS flaps 0 VY 75 KIAS flaps 0 1 Climb Power SET 2 Flaps 0 3 EPSI570C Parameters CHECK MONITOR CAUTION Prolonged use of...

Page 122: ...ngs are made with full flaps and with power on or off Surface winds and air turbulence are usually the primary factors in determining the most comfortable approach speeds Actual touchdown should be ma...

Page 123: ...ot capabil ity as well as aircraft limitations Operation in direct crosswinds of 15 kts 7 5 m s has been demonstrated 4 10 BALKED LANDING GO AROUND In a balked landing go around apply full power and c...

Page 124: ...After a hard landing the ELT may activate flashing red light on ELT remote switch To reset it set the remote switch to ON first and then back to ARM OFF position Please check OEM documentation 2 for a...

Page 125: ...t skills with less than 20 of yaw or roll The recovery maneuver generally requires less than 250 ft of altitude drop The aircraft is equipped with a haptic stall warning system in control stick handle...

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Page 127: ...Operating Handbook POH 128 00 40 001 PAGE REV 0 PAGE SECTION 4 NORMAL PROCEDURES CHECKLISTS CHECKLISTS NORMAL PROCEDURES 4 16 NOTE Use of the following checklists is not obligatory and at the discret...

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Page 129: ...present Headphones microphones Connected Required documents ON BOARD ELT switches remote sw and transmitter CHECK both switches in ARM OFF position armed Flight Controls and flap handle CHECK free and...

Page 130: ...enna top Condition and attachment Wing fuselage seal CHECK XPDR antenna underside Condition and attachment Static pressure port CHECK for blockage Battery cooling system inlet and outlet CHECK no obst...

Page 131: ...EMPENNAGE Tie down rope remove Horizontal and vertical stabilizers CHECK condition Elevator and elevator U piece Condition and movement Rudder Condition and movement Attachment bolts hinges nuts CHECK...

Page 132: ...GEAR Landing gear General condition Tire Condition inflation and wear Wheel and brakes Fluid leaks evidence of overheating general condition and wear Chocks and tie down rings ropes Remove PROPELLER A...

Page 133: ...R and NOSE LANDING GEAR AREA Strut CHECK condition Nose landing gear CHECK condition Wheel and tire CHECK condition Shock absorber CHECK TEST Front battery compart ment access panels CHECK closed Batt...

Page 134: ...rudder pedals SET and LOCKED Flight Controls FULL FREE AND CORRECT Seat belts ADJUSTED AND FASTENED Power lever CUT OFF Parking brake ENGAGE Circuit breakers CHECK ALL ENGAGED ELT remote switch CHECK...

Page 135: ...er lever CUT OFF BATT EN switch ON PWR EN switch ON EPSI570C system page CHECK BATTERIES ACTIVE Time NOTED Parking brake DISENGAGE Power lever INCREASE FOR TAXI POWER CHECK Parking brake CHECK ENGAGED...

Page 136: ...cover CHECK removed Flaps 1 Trim SET NEUTRAL Power lever CUT OFF Parking brake DISENGAGE MASTER switch CHECK ON AVIONICS switch CHECK ON BATT EN switch CHECK ON PWR EN switches CHECK ON Transponder SE...

Page 137: ...s Airspeed CHECK increasing Rotate SET slight positive pitch and lift off 50 KIAS Airspeed initial climb 57 60 KIAS At safe altitude 300 ft AAL Flaps 0 Power lever REDUCE TO MCP 48 kW Airspeed INCREAS...

Page 138: ...er lever REDUCE TO CUT OFF Flaps below 81 kts 1 Airspeed MAINTAIN 65 KIAS Final Flaps below 65 kts 2 Airspeed MAINTAIN 60 KIAS BALKED LANDING GO AROUND Power Lever FULL Airspeed 59 KIAS After clear of...

Page 139: ...ver CUT OFF ELT CHECK not transmitting PWR EN switch OFF BATT EN switch OFF PARKING Parking brake ENGAGED if necessary Time Noted Hobbs time EPSI system page Noted AVIONICS switch OFF MASTER switch OF...

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Page 141: ...SECTION 5...

Page 142: ...PEED CALIBRATION 5 6 5 5 STALL SPEED 5 8 5 6 TAKE OFF DISTANCE 5 9 5 7 CLIMB PERFORMANCE 5 11 Rate of Climb Climb Gradient 5 8 CRUISE PERFORMANCE 5 12 5 9 ENDURANCE AND RANGE 5 13 Local Flight A A Fli...

Page 143: ...mb at sea level The performance tables do not take into account the expertise of the pilot or the maintenance condition of the airplane The performance illustrated in the tables can be achieved if the...

Page 144: ...FOR ISA CONDITION Pressure Altitude ft ISA 15 C ISA 5 C ISA ISA 5 C ISA 15 C SL 0 10 15 20 30 1000 2 8 13 18 28 2000 4 6 11 16 26 3000 6 4 9 14 24 4000 8 2 7 12 22 5000 10 0 5 10 20 6000 12 2 3 8 18 7...

Page 145: ...128 00 40 001 PAGE REV 0 PAGE SECTION 5 PERFORMANCE DATA APPROVED 5 3 WIND COMPONENT EXAMPLE Runway Heading 10 Wind Direction 60 Angle between wind and runway 50 Wind Velocity 15 Knots Component paral...

Page 146: ...Conditions Power power level for level flight or idle when indicated NOTE Indicated airspeed values assume zero instrument error KIAS KCAS Flaps 0 level flight Flaps 1 level flight Flaps 2 level fligh...

Page 147: ...5 7 VELIS Electro Pilot s Operating Handbook POH 128 00 40 001 PAGE REV 0 PAGE SECTION 5 PERFORMANCE DATA APPROVED KIAS KCAS Diagram...

Page 148: ...50 250 ft Normal recovery with power 100 ft Aggressive recovery less than 100 ft Depending on pilot skill the altitude loss during wing level stall may be 250 feet or more NOTE KIAS values may not be...

Page 149: ...test results These extrapolated values serve as an estimation of actual take off roll and total distance to clear a 50 ft obstacle ground roll plus climb distance to clear obstacle Correction Factors...

Page 150: ...t 276 295 304 313 330 50 ft obst 512 547 564 580 610 Ground roll Grass 312 335 345 355 375 50 ft obst 591 631 650 669 704 PRESSURE Altitude ft DISTANCE m Runway Surface TEMPERATURE ISA 15 C ISA 5 C IS...

Page 151: ...us climbs at MCP set ting when flying at high OAT is advisable Alternating climb legs with short cruise phases at lower power settings is recommended 5 7 1 RATE OF CLIMB VY 75 KIAS MASS AIR SPEED Pres...

Page 152: ...n minimum power for level flight 20 kW and maximum continuous RPM power 36 kW POWER SETTING EPSI RPM KIAS KCAS kW 1 min kts kts 20 1780 71 69 25 1950 79 78 30 2120 87 86 35 2270 92 92 36 2300 93 93 NO...

Page 153: ...eries energy storage capability and therefore also endurance CAUTION Always consider that battery temperature 40 C at take off may affect the duration of flight as the mission must be aborted when the...

Page 154: ...min 39 min 32 min 25 min 18 min 25 42 min 37 min 32 min 26 min 21 min 15 min 30 36 min 32 min 27 min 23 min 18 min 14 min 35 31 min 28 min 24 min 20 min 16 min 13 min 2000 20 52 min 45 min 38 min 31...

Page 155: ...tion A B FLIGHT ENDURANCE in minutes 30 min reserve 20 kW Cruise altitude ft Cruise power kW Battery State of Health SOH 100 80 60 40 20 0 1500 20 32 min 25 min 19 min 12 min 25 27 min 21 min 16 min 1...

Page 156: ...km 49 km 35 km 22 km 30 57 km 45 km 33 km 21 km 35 53 km 42 km 31 km 20 km 4000 20 65 km 50 km 34 km 25 62 km 48 km 34 km 30 59 km 46 km 34 km 35 56 km 45 km 33 km 6000 20 62 km 25 61 km 30 59 km 35...

Page 157: ...clearing 50 ft obstacle ground roll included Correction Factors Headwind Subtract 10 from table distances for each 13 knots of headwind Tailwind Add 10 to table distances for each 2 knots of tailwind...

Page 158: ...4 575 592 610 PRESSURE Altitude ft DISTANCE m Runway Surface TEMPERATURE ISA 15 C ISA 5 C ISA ISA 5 C ISA 15 C 4000 Ground roll Asphalt 182 199 206 213 232 50 ft obst 557 568 580 597 615 Ground roll G...

Page 159: ...ld 50 C Battery tempera ture 40 C at take off may result in high in flight battery temperatures when OAT is high or high power settings are applied NOTE Flight phases are to be executed according to t...

Page 160: ...300 ft AGL SOC 4 4 5 6 7 8 1000 ft climb at VY 48 kW SOC 7 7 8 10 12 14 10 min cruise 20 kW 69 KCAS SOC 15 17 19 22 26 32 10 min cruise 25 kW 78 KCAS SOC 19 22 25 28 34 41 10 min cruise 30 kW 86 KCAS...

Page 161: ...tination knowing that as long as the flight does not proceed beyond the halfway point it should be possible to make it back to home airfield safely If the take off is with 100 SOC landing must be plan...

Page 162: ...reference for PNR calculation depending on cruise power speed and wind PNR SOC is the SOC value at which the return to the initial cruise point is possible with 30 SOC remaining 20 kW Tailwind outboun...

Page 163: ...46 45 44 43 42 42 35 kW Tailwind outbound headwind inbound kts No wind Headwind outbound tailwind inbound kts 92 KCAS 20 15 10 5 0 5 10 15 20 INITIAL SOC 90 67 65 63 62 60 58 57 55 53 80 60 59 58 56 5...

Page 164: ...the SOC consumed in each phase CAUTION Always consider that battery temperature 40 C at take off may affect the duration of flight as the mission must be aborted when the in flight battery temperatur...

Page 165: ...gy SOC used for each phase using previous tables all values are obtained from column SOH 80 A Take off 4 SOC B Climb VY at 48 kW to 2000 ft AGL 2 x 7 SOC 14 SOC C Cruise 1 at 25 kW for 5 min 0 5 x 21...

Page 166: ...ttern 1000 ft 10 H Landing to full stop 0 TOTAL SOC 56 5 Calculation of SOC at landing SOC at landing Initial SOC mission SOC 95 56 39 SOC This value is 30 SOC Initial SOC is sufficient for the missio...

Page 167: ...SECTION 6...

Page 168: ...Pilot s Operating Handbook POH 128 00 40 001 PAGE REV 0 PART SUBJECT PAGE NUMBER 6 1 INTRODUCTION 6 3 6 2 C G CALCULATION SAMPLE 6 4 6 3 WEIGHT AND BALANCE CHART 6 5 TABLE OF CONTENTS APPROVED SECTIO...

Page 169: ...e section 6 3 and thus de termine whether aircraft is within the flight limits see section 2 6 A sample calculation is provided for reference WARNING It is the owner and or operator s responsibility t...

Page 170: ...for each item by multiplying its weight by its arm Add up the moments to get the total moment and then divide by the total weight to get the C G WEIGHT kg ARM mm MOMENT kgmm Aircraft empty weight 1134...

Page 171: ...oint in the chart and determine whether or not the aircraft is within the flight limits Points A and B in the chart are taken from the sample calcu lation in section 6 2 POINT MASS kg CG MAC CG mm 1 6...

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Page 173: ...SECTION 7...

Page 174: ...Control System Rudder Control System Wing Flaps Control System Elevator Trim System 7 4 LANDING GEAR 7 8 Main Gear Nose Gear Brake System 7 5 AIRPLANE CABIN 7 9 Cabin Doors Ventilation Seats Battery...

Page 175: ...Distribution Switches Miscellaneous Components 7 8 LIGHTING 7 27 Exterior Lighting 7 9 ENVIRONMENTAL SYSTEM 7 27 7 10 PITOT SYSTEM AND STALL WARNING 7 28 7 11 FLIGHT DECK ARRANGEMENT 7 28 7 12 FLIGHT...

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Page 177: ...ccessible via two access doors on each side of the fuselage The cabin backrest is made of CFRP The cabin floor along with the lower seat structure are made of mostly of CFRP and aramid because of it s...

Page 178: ...nted on stainless steel brackets at the stabilizer rear spar and bottom shell Counterbalance weights are integrated into the elevator tips The vertical fin is designed to be one part with the tail fus...

Page 179: ...cks are mounted on a common lateral rod which actuates the elevator longitudinal pushrod There is a bell crank located on the bottom of the fuselage behind the seats which provides differential mo tio...

Page 180: ...the trim switch 7 4 LANDING GEAR 7 4 1 MAIN GEAR The landing gear is a conventional fixed tricycle type The main landing gear consists of a single composite landing gear strut made of GFRP The strut i...

Page 181: ...ly the brakes with heavy pressure If the brakes are spongy or pedal travel increases pumping the pedals may build braking pressure CAUTION Do not pull the PARK BRAKE lever in flight If a landing is ma...

Page 182: ...anel can be removed reclined to access the rear battery compartment The back panel features a manual pneumatic pump to adjust the size of the lum bar bladder and thus lumbar support 7 5 4 HV BATTERY C...

Page 183: ...7 11 VELIS Electro Pilot s Operating Handbook POH 128 00 40 001 PAGE REV 0 PAGE SECTION 7 AIRPLANE DESCRIPTION 7 6 PROPULSION SYSTEM Propulsion system diagram...

Page 184: ...H300C power electronics It is fitted with a tem perature sensor and is liquid cooled Pipistrel electric motor 268 MV LC VHML characteristics Maximal shaft speed 2500 RPM electronically limited Peak to...

Page 185: ...7 13 VELIS Electro Pilot s Operating Handbook POH 128 00 40 001 PAGE REV 0 PAGE SECTION 7 AIRPLANE DESCRIPTION Engine system installation...

Page 186: ...C DC converter The high voltage power is distributed between the systems through a junction box The main computer system controller controls and oversees operation of high and low voltage power system...

Page 187: ...It is accessi ble via the rear battery inspection panel bolted on the left side of the fuse lage The fore battery pack compartment is positioned in front of the cabin It is accessible via the front in...

Page 188: ...the battery State Of Charge SOC and the State Of Health SOH The SOH calculation takes into account the decrease of bat tery capacity and increase of internal resistance as a consequence of bat tery a...

Page 189: ...ve grade G12 The liquid cooling system consists of a radiator and two electri cally driven pumps located behind the aft battery pack compartment The air inlet for the radiator is located on the left s...

Page 190: ...ve bat tery system cooling during the recharge The fans are controlled and mon itored by the BMS master When the battery temperature rises above the 35 C the fans start spinning and at 40 C they reach...

Page 191: ...or is proportion al to the lever position However during emergency operation see also Engine overtemperature 3 5 10 when engine temperature enters warning range power controller temperature 70 C or mo...

Page 192: ...trol and monitoring Power lever interface Switch panel interface Annunciator Warning panel driver EPSI 570C Interface Charging port interface Garmin Aera 660 Interface Datalogger interface The system...

Page 193: ...raft s instrument panel The data logger records data from propulsion system navigation system and other instru ments Data is always recorded to an internal micro SD card The data log ger also has a US...

Page 194: ...aults issues and provides redundancy if the EPSI570C fails The panel is managed by the BMS software and repli cates warning cautions that are displayed on EPSI570C See Appendix 9 A1 EPSI570C SYSTEM DE...

Page 195: ...endently from the BMS software In case of battery overtem perature 58 C the LED light of the affected battery turns ON see Section 3 Emergency procedures for details NOTE Battery overtemperature analo...

Page 196: ...hen go off ANNUNCIATOR panel MASTER CAUTION and MASTER WARNING buttons are illuminated for few seconds then go off ANNUNCIATOR panel system icon lights 4x are illuminated for few sec onds then go off...

Page 197: ...ry system is used to power avionics and system controllers on the air craft Low voltage power is generated from high voltage batteries by a DC DC converter An auxiliary 12V battery is also present ins...

Page 198: ...is lost the auxiliary battery keeps the avionics system working The 14 V DC bus is split into different buses each with a separate master switch or breaker with each element then subsequently equippe...

Page 199: ...d the AVIONICS power switch must also be turned on AVIONICS Switch A toggle switch labeled AVIONICS controls electrical power from the main bus to the Avionics Bus Typically the switch is used to ener...

Page 200: ...es accept standard USB plugs The outlet may be used to pow er portable equipment non essential to flight Amperage draw through the outlet must not exceed 2 A Power to the convenience outlet is activat...

Page 201: ...r and the altitude airspeed indicators The pitot tube also has a AOA sensing port The aircraft is equipped with a stall warning system that activates a con trol stick vibration and aural warning when...

Page 202: ...ircuit breaker TRIM Trim actuator circuit breaker EPSI EPSI570C display circuit breaker COM Radio COM circuit breaker XPDR Transponder circuit breaker INSTR Other instruments circuit breaker GPS Navig...

Page 203: ...REV 0 PAGE SECTION 7 AIRPLANE DESCRIPTION Switch panel Center Console The center console contains front to back the parking brake lever pow er lever elevator trim switch indicator and the flap lever O...

Page 204: ...IMARY FLIGHT INSTRUMENT 8 Airspeed Indicator Mikrotechna LUN1116 Mechanical ASI PRIMARY FLIGHT INSTRUMENT 9 Radio COM Funke ATR833 10 Transponder Funke TRT800H 11 ELT Artex ELT 345 remote panel 12 Mec...

Page 205: ...l power to function Barometric windows on the instrument s face allow barometric calibrations in either inches of mercury inHg or milli bars mb The barometric altimeter settings are input through the...

Page 206: ...of the in tegrated receiver transmitter control unit an antenna and an integrated alti tude encoder The transponder and integrated controls are mounted on the instrument panel 12 VDC for transponder...

Page 207: ...r until manual deactivation The main transmitter and the remote switches have three positions labeled ON ARM OFF TEST A red LED light on the transmitter and on the remote switch panel flashes when the...

Page 208: ...inadvertently activated in its distress mode the opera tor should deactivate it AND contact the nearest COSPAS SARSAT Mission Control Centre or local RCC as soon as possible to request cancellation of...

Page 209: ...SECTION 8...

Page 210: ...AND REPAIRS 8 3 8 5 RECHARGING 8 4 Approved Chargers Charger Functions Full Charge Procedure Rest Charge Procedure 8 6 SERVICING 8 10 Tire Servicing Brake Servicing Propeller Servicing 8 7 GROUND HAN...

Page 211: ...The owner is responsible for compliance with all applicable airworthiness directives and periodical inspections 8 3 PILOT CONDUCTED MAINTENANCE Pilots operating the airplane should refer to the regula...

Page 212: ...C or 45 C See also chapter 2 Limitations WARNING Do not start recharging a battery in undervoltage condition e g battery disconnected due to undervoltage during the previous flight or if batteries su...

Page 213: ...CEDURE Full charge is the standard charging procedure performed before the flight 1 Park the aircraft and engage parking brake 2 Connect charger to the grid 3 Power up the charger switching the charge...

Page 214: ...e cooling fans are acti vated Charging options full charge or rest charge will disappear from the charger display once the process has started and CHARGE page will ap pear on EPSI570C display NOTE cha...

Page 215: ...visible on charger display and 100 progress bar on EPSI570C end charging process by pressing CONFIRM on charger display 10 CHECK EPSI570C display for presence of caution warning messages 11 Disconnect...

Page 216: ...n warning messages presented on EPSI570C before acknowledging them and before unplugging the charger from the aircraft charging port WARNING Do not take off if any caution warning messages appear duri...

Page 217: ...2 Vacate the area around the aircraft 3 Douse the fire with as much water as possible in order to delay fire propagation Emergencies SMOKE WARNING Stay away from the aircraft because the batteries ma...

Page 218: ...inspections replenishing the system when necessary To replenish brake fluid 1 Chock tires and release parking brake 2 Clean area on rudder pedals around cap before opening reservoir cap itself 3 Remo...

Page 219: ...mud or snow Observe 1 Be especially cognizant of hangar door clearances 2 Release parking brake and remove chocks 3 Move airplane to desired location by grabbing on the tail cone 4 When moving backwar...

Page 220: ...tarting Motor procedure 3 Release parking brake 4 Advance power lever to initiate taxi Immediately after initiating taxi apply the brakes to determine their effectiveness 5 Taxi airplane to desired lo...

Page 221: ...CAUTION Before lifting hoisting the airframe always clear the immediate area of people and equipment To lift the aircraft 1 Position the hoisting lifting system over the aircraft 2 Remove the wing fus...

Page 222: ...ase use a cloth dampened with degreaser or naphtha 5 Rinse all surfaces thoroughly Any good silicone free automotive wax may be used to preserve paint ed surfaces Soft cleaning cloths or a chamois sho...

Page 223: ...tone or glass window cleaning sprays Use only a non abrasive cotton cloth or genuine chamois to clean acrylic windows Paper towel or newspaper are highly abrasive and will cause hairline scratches NOT...

Page 224: ...ecessary 2 Soiled upholstery may be cleaned with a good upholstery cleaner suitable for the material Carefully follow the manufacturer s instruc tions Avoid soaking or harsh rubbing CAUTION Solvent cl...

Page 225: ...SECTION 9...

Page 226: ...9 A0 2 PAGE VELIS Electro Pilot s Operating Handbook POH 128 00 40 001 PAGE REV 0 APPENDIX NO APPENDIX 9 A1 EPSI570C SYSTEM DESCRIPTION SECTION 9 APPENDIX LIST OF APPENDICES...

Page 227: ...APPENDIX 9 A1...

Page 228: ...The device is composed of a main display a selection knob and a USB port for software updates The device is opera tive when the AVIONICS switch is engaged Rotation of the selection knob allows the use...

Page 229: ...The main task of EPSI is to provide essential information of the electric pro pulsion system to the pilot which includes Motor operating status RPM power and temperature Power controller operating st...

Page 230: ...s done by the selection knob rotation NOTE Values shown in the following pictures are for demonstrative pur poses only and do not apply to any specific real operational situation FLIGHT page FLIGHT pa...

Page 231: ...us Power MCP 4 Minimum Performance Take Off Power MPTOP 5 Maximum Take off Power MTOP NOTE MCP MPTOP and MTOP are defined in section 1 7 3 1 RPM indication 6 Warning and Caution sections when messages...

Page 232: ...A1 6 SECTION 9 APPENDIX Examples of parameters in caution or warning range FLIGHT page Example 1 Temperature in caution or warning range battery temperature Example 2 RPM and Power indication in cauti...

Page 233: ...ground when in caution or warning range Battery SOH Temp Min volt Current Engine temp m Temp I Refer to the following table for a short description of the parameters BATTERY section One column for eac...

Page 234: ...wer controller Temp m Motor temperature Temp I Power controller temperature Coolant IN Engine coolant temperature Sensor coolant cold in engine cooling system diagram Section 7 6 3 Coolant OUT Engine...

Page 235: ...en moved to cut off position DC DC section DC DC converter Parameter Description Status Status of the component Out volt Out curr Voltage and current output of the converter In volt In curr Voltage an...

Page 236: ...0 is charge completed temperature of the charger and of the batteries and charger input output voltage and current values 1 Charging phase progress bar 2 Charger input parameters AC current mains volt...

Page 237: ...s also heard in the headsets Two areas of the EPSI570C display are used to show the messages Central display area The central display area is used to show the first un acknowledged warning or caution...

Page 238: ...LIGHT page an continue the message associated procedure The pilot has to perform the corrective action required by the caution or warning After this action the pilot can push the button on the annunci...

Page 239: ...or warnings which are listed on the EPSI display and give the pilot an overview of systems that are affected by unresolved issues When the cause which triggered the caution or the warning disappears...

Page 240: ...LE BATTERY NOT PRESENT battery loss of communication Some emergency procedures may require front F or rear R high voltage battery manual disconnection This is accomplished by disengaging its circuit b...

Page 241: ...parameters In addition the loss of communication EPSI system controller implies that the EPSI does not display any caution or warning message with the caution and warning list replaced by a red cross...

Page 242: ...00 40 001 PAGE REV 0 9 A1 16 SECTION 9 APPENDIX Flight page Battery parameters not available caution warning messages not available other parameters frozen to the last recorded value System page Batt...

Page 243: ...This page is intentionally left blank...

Page 244: ...pistrel aircraft com Pipistrel Italia Via Fratelli Rusjan 26 34070 Savogna d Isonzo GO Italia EU t 39 3703207623 pipistrel legalmail it www pipistrel aircraft com Pipistrel Vertical Solutions d o o Vi...

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