PILOT'S OPERATING HANDBOOK - VELIS Electro

List of effective pages 3 3 - 1 2 3 - 2 2 3 - 3 2 3 -4 blank 5 5 - 1 2 5 - 2 2 5 - 3 2 5 - 4 blank NOTE: since the last released revision B01, the content of this POH has undergone some significant changes. With the revision C00 (not released to the public) all the page revisions have been reset to 2. The current revision C01 introduces additional corrections and page revision of affected pages has been set to 3. All the changes and amendments made in revisions C00 and C01, however, have been marked by a vertical bar, so as to highlight the differences between document revisions B01 and C01. 4 4 - 22 2 4 - 23 2 4 - 24 2 4 - 25 2 4 - 26 2 4 - 27 3 4 - 28 2 4 - 29 2 4 - 30 2 4 - 31 2 4 - 32 blank vii VELIS Electro Pilot's Operating Handbook POH-128-00-40-001 PAGE REV. 3 PAGE PAGE NUMBER PAGE REV. PAGE NUMBER PAGE REV. PAGE NUMBER PAGE REV. 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PAGE NUMBER PAGE REV. 3 3 10-3A-34 2 10-3A-35 2 10-3A-36 2 10-3A-37 3 10-3A-38 2 10-3A-39 2 10-3A-40 2 10-3A-41 2 10-3A-42 2 10-3A-43 3 10-3A-44 2 10-3A-45 2 10-3A-46 2 10-3A-47 2 10-3A-48 2 10-3A-49 2 10-3A-50 2 10-3A-51 2 10-3A-52 blank 10-3A-53 2 10-3A-54 2 10-3A-55 2 10-3A-56 2 10-3A-57 2 10-3A-58 2 10-3A-59 2 10-3A-60 2 10-3A-61 2 10-3A-62 2 10-3A-63 2 10-3A-64 2 10-3A-65 2 10-3A-66 2 10-3A-67 2 10-3A-68 2 3 10-3A-69 3 10-3A-70 2 10-3A-71 2 10-3A-72 2 10-3A-73 2 10-3A-74 blank 5 10-5A-1 2 10-5A-2 2 10-5A-3 2 10-5A-4 2 10-5A-5 2 10-5A-6 2 10-5A-7 2 10-5A-8 2 10-5A-9 2 10-5A-10 2 10-5A-11 2 10-5A-12 2 10-5A-13 2 10-5A-14 2 10-5A-15 2 10-5A-15 2 10-5A-17 2 10-5A-18 2 10-5A-19 2 10-5A-20 2 10-5A-21 2 10-5A-22 2 10-5A-23 2 10-5A-24 2 10-5A-25 2 10-5A- 26 2 10-5A-27 3 10-5A-28 3 3 10-3B-1 2 10-3B-2 2 10-3B-3 2 10-3B-4 2 10-3B-5 2 10-3B-6 blank 10-3B-7 2 10-3B-8 2 10-3B-9 2 10-3B-10 2 10-3B-11 2 10-3B-12 2 10-3B-13 2 10-3B-14 3 10-3B-15 2 10-3B-16 2 10-3B-17 2 10-3B-18 2 10-3B-19 2 10-3B-20 2 10-3B-21 2 10-3B-22 2 10-3B-23 2 10-3B-24 2 10-3B-25 2 10-3B- 26 2 10-3B-27 2 10-3B-28 3 10-3B-29 2 10-3B-30 2 10-3B-31 2 10-3B-32 2 10-3B-33 2 10-3B-34 2 10-3B-35 2 3 3 10-3B-36 2 10-3B-37 3 10-3B-38 2 10-3B-39 2 10-3B-40 2 10-3B-41 2 10-3B-42 2 10-3B-43 3 10-3B-44 2 10-3B-45 2 10-3B-46 2 10-3B-47 2 10-3B-48 2 10-3B-49 2 10-3B-50 2 10-3B-51 2 10-3B-52 blank 10-3B-53 2 10-3B-54 2 10-3B-55 2 10-3B-56 2 10-3B-57 2 10-3B-58 2 10-3B-59 2 10-3B-60 2 10-3B-61 2 10-3B-62 2 10-3B-63 2 10-3B-64 2 10-3B-65 2 10-3B-66 2 10-3B-67 2 10-3B-68 2 10-3B-69 3 10-3B-70 2 ix VELIS Electro Pilot's Operating Handbook POH-128-00-40-001 PAGE REV. 3 PAGE PAGE NUMBER PAGE REV. PAGE NUMBER PAGE REV. PAGE NUMBER PAGE REV. PAGE NUMBER PAGE REV. 3 10-3B-71 2 10-3B-72 2 10-3B-73 2 10-3B-74 2 5 10-5B-1 2 10-5B-2 2 10-5B-3 2 10-5B-4 2 10-5B-5 2 10-5B-6 2 10-5B-7 2 10-5B-8 2 10-5B-9 2 10-5B-10 2 10-5B-11 2 10-5A-12 2 10-5B-13 2 10-5B-14 2 10-5B-15 2 10-5A-15 2 10-5B-17 2 10-5B-18 2 10-5B-19 2 10-5B-20 2 10-5B-21 2 10-5B-22 2 10-5B-23 2 10-5B-24 2 10-5B-25 2 10-5B- 26 2 10-5B-27 3 10-5B-28 3 10-5B-29 blank back-cover - This page is intentionally left blank. SECTION 1 1-2PAGE VELIS Electro Pilot's Operating Handbook POH-128-00-40-001 PAGE REV. 2 PART SUBJECT PAGE NUMBER 1.1 INTRODUCTION 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 and TERMINOLOGY 1-7 1.8 CONVERSION TABLE 1-11 1.9 LIST OF APPLICABLE DOCUMENTS 1-12 SECTION 1 – GENERAL TABLE OF CONTENTS 1-3 VELIS Electro Pilot's Operating Handbook PAGE POH-128-00-40-001 PAGE REV. 2 SECTION 1 GENERAL 1.1. INTRODUCTION This section contains information of general interest to pilots and owners. You will find the information useful in acquainting yourself with the airplane, as well as in loading, sheltering, and handling the airplane during ground operations. Additionally, this section contains definitions or explanations of symbols, abbreviations, and terminology used throughout this handbook. 1.2. DESCRIPTION The VELIS Electro is a two-seat aircraft of composite construction. The air- craft is arranged as a high wing mono-plane with cantilevered wings and a conventional empennage with a T-tail. It is equipped with a Pipistrel electric 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 to the cockpit is via two large gull-wing doors. There is no baggage compartment on the aircraft. The load-bearing structure of the airplane is made of carbon, glass and ara- mid fiber composite material, the components of which, epoxy resin as well as fiber materials, are in compliance with worldwide accepted aviation spec- ifications. The proven, low-pressure wet lay-up method from the sailplane industry is used to build the airplane structure. The airplane is not approved for intentional spins and glider-towing. 1.3. CERTIFICATION BASIS This aircraft is being certified under EASA CS-LSA Light Sport Aircraft Certi- fication Specifications. Operation is restricted to VFR-day operations and a maximum take off weight of 600 kg. 1-4PAGE VELIS Electro Pilot's Operating Handbook POH-128-00-40-001 PAGE REV. 2 SECTION 1 GENERAL VELIS Electro 3-view drawing 1.4. THREE VIEW DRAWING 1-5 VELIS Electro Pilot's Operating Handbook PAGE POH-128-00-40-001 PAGE REV. 2 SECTION 1 GENERAL 1.5. DIMENSIONS AND WEIGHTS Basic Dimensions Length 6.47 m Span 10.71 m Height 1.90 m * Wing Area 9.51 m² Span 10.71 m Mean aerodynamic chord 0.898 m Horizontal Tail Metric Area 1.39 m² Span 2.18 m Vertical Tail Reference area 1.24 m² Height 1.11 m Weights Maximum take off weight 600 kg Design empty weight 428 kg Design useful load 172 kg Maximum baggage weight No baggage * In-operation measurement, aircraft not leveled as per WBR. 1.6. SYSTEMS 1.6.1. ENGINE The aircraft's Pipistrel E-811-268MVLC engine consists of an electric motor, the Pipistrel 268 MVLC VHML, and a dedicated H300C controller, which pro- vides a maximum rated take off power of 65 kW. The motor is a liquid cooled, axial flux synchronous permanent magnet elec- tric motor. The aircraft's power electronics system is a liquid-cooled, high-voltage pow- er controller, which provides three phase alternating supply (AC) to the mo- tor. Maximum continuous current is 300A. 1-6PAGE VELIS Electro Pilot's Operating Handbook POH-128-00-40-001 PAGE REV. 2 SECTION 1 GENERAL 1.6.2. PROPELLER VELIS Electro is equipped with a 3-blade fixed pitch, Pipistrel-designed P-812-164-F3A propeller. It has a diameter 1640 mm. Its blades are made from carbon fiber composite material and stainless steel. The blade root and propeller hub are machined aluminum parts. 1.6.3. BATTERY SYSTEM The airplane features a high voltage electric power system. The primary energy source are two Pipistrel PB345V124E-L or two PB345V119E-L battery packs, which are located fore 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 standalone operation and has enough power output capability to support aircraft climb and continuation of flight. The batteries are controlled by a BMS, that con- tinuously monitors and manages battery parameters and status to ensure safe operations. 1.6.4. LANDING GEAR The airplane has as a tricycle type fixed landing gear. The nose wheel is steerable via rudder pedals. The main wheels are equipped with hydraulic disc brakes, which are independently operated via toe-pedals. A parking brake lever is also present. Propulsion system terminology 1-7 VELIS Electro Pilot's Operating Handbook PAGE POH-128-00-40-001 PAGE REV. 2 SECTION 1 GENERAL 1.7. SYMBOLS, ABBREVIATIONS AND TERMINOLOGY 1.7.1. GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS Knots Calibrated Airspeed is the indicated airspeed corrected for posi- tion and instrument error expressed in knots. Calibrated airspeed (CAS) is equal to true airspeed in standard atmosphere at sea level. KIAS Knots Indicated Airspeed is the speed shown on the airspeed indicator (IAS) expressed in knots. The IAS values published in this handbook as- sume no instrument error. KTAS Knots True Airspeed is the airspeed expressed in knots relative to undis- turbed air which is KCAS corrected for altitude and temperature. VG Best Glide Speed is the speed at which the greatest flight distance is at- tained per unit of altitude lost with power off. VA Operating Maneuvering Speed is the maximum speed at 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 Maximum Structural Cruising Speed is the speed that should not be ex- ceeded except in smooth air, and then only with caution. VNE Never Exceed Speed is the speed that may not be exceeded at any time. VS0 Stalling Speed is the minimum steady flight speed at which the aircraft is controllable in the landing configuration (100% flaps) at the most unfavor- able weight and balance. VX Best Angle of Climb Speed is the speed at which the airplane will obtain the highest altitude in a given horizontal distance. The best angle-of-climb speed normally increases slightly with altitude. VY Best Rate of Climb Speed is the speed at which the airplane will obtain the maximum increase in altitude per unit of time. The best rate-of-climb speed decreases slightly with altitude. VH Maximum speed in level flight with maximum continuous power. GS Ground Speed is the horizontal speed relative to the ground. 1-8PAGE VELIS Electro Pilot's Operating Handbook POH-128-00-40-001 PAGE REV. 2 SECTION 1 GENERAL 1.7.2. METEOROLOGICAL TERMINOLOGY IMC Instrument Meteorological Conditions are meteorological conditions ex- pressed in terms of visibility, distance from cloud, and ceiling less than the minimal for visual flight defined in FAR 91.155. ISA International Standard Atmosphere (standard day) is an atmosphere where (1) the air is a dry perfect gas, (2) the temperature at sea level is 15 °C, (3) the pressure at sea level is 1013.2 millibars (29.92 inHg), and (4) the temperature gradient from sea level to the altitude at which the temperature is -56.5 °C is -0.00198 °C per foot and zero above that altitude. MSL Mean Sea Level is the average height of the surface of the sea for all stages of tide. In this Handbook, altitude given as MSL is the altitude above the mean 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 Temperature is the free air static temperature obtained from in-flight temperature indications or from ground meteorological sources. It is expressed in either degrees Celsius or degrees Fahrenheit. PA Pressure Altitude (ft) is the altitude read from the altimeter when the al- timeter’s barometric adjustment has been set to 1013 mb (29.92 inHg) corrected for position and instrument error. In this Handbook, altimeter instrument errors are assumed to be zero. DA Density Altitude (ft) is pressure altitude corrected for non-standard tem- perature. As temperature and altitude increase, air density decreases. - Standard Temperature is the temperature that would be found at a given pressure altitude in the standard atmosphere. It is 15 °C at sea level pres- sure altitude and decreases approx. 2 °C for each 1000 feet of altitude increase. AAL Above Aerodrome Level 1-9 VELIS Electro Pilot's Operating Handbook PAGE POH-128-00-40-001 PAGE REV. 2 SECTION 1 GENERAL 1.7.3. PROPULSION SYSTEM TERMINOLOGY BMS Battery Management System ENGINE In this POH is defined as the system composed by electric motor and power controller. HP Horsepower is the power developed by the motor. INTERLOCK A system that detects power cable connection to the battery box. In case of disconnection, also interlock signal is lost and disconnection is detected. kW Kilowatt: it is unit that express the power developed by the motor. MCP Maximum Continuous Power is the maximum power that can be used continuously. MPTOP Minimum Performance Take off Power is the maximum power available for take off with batteries at the end of their service life and low SOC (SOH~0% and SOC=15%). MTOP Maximum Take Off Power is the maximum power available for take off, albeit for a limited time. This value can be reached when batteries are in good condition (high SOC/SOH). PROPULSION SYSTEM 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 Minute is motor rotational speed. SOC State Of Charge (displayed on EPSI - Flight page) is the amount of energy stored in the battery, expressed as percentage of full capacity. Absolute full capacity is not constant, but can be af- fected by several factors (i.e. SOH, temperature). SOH State Of Health (displayed on EPSI - System page) indicates the "age" of the battery. End of life is SOH=0%. This parameter af- fects the absolute capacity of the battery (energy that can be stored), and the power that the battery can deliver. TC Power module of the charger. 1.7.4. PERFORMANCE TERMINOLOGY g One “g” is a quantity of acceleration equal to that of earth’s gravity. - Demonstrated Crosswind Velocity is the velocity of the crosswind com- ponent for which adequate control of the airplane during taxi, take off, and landing was actually demonstrated during certification testing. - Service Ceiling is the maximum altitude at which the aircraft at maximum weight has the capability of climbing at a 100 ft/min. 1-10PAGE VELIS Electro Pilot's Operating Handbook POH-128-00-40-001 PAGE REV. 2 SECTION 1 GENERAL 1.7.5. WEIGHT AND BALANCE TERMINOLOGY MTOM Maximum Take Off Mass is the maximum overall mass allowed at take off. C.G. or CG Center of Gravity is the point at which an airplane would balance if sus- pended. Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane. All references to C.G. in this manual are references to the in-flight C.G. - Arm is the horizontal distance from the reference datum to the center of an item’s gravity. The airplane’s arm is obtained by adding the airplane’s individual moments and dividing the sum by the total weight. - Basic Empty Weight is the actual weight of the airplane including all op- erating fix installed equipment of the airplane. MAC Mean Aerodynamic Chord is the chord drawn through the centroid of the wing plan area. R or LEMAC Leading Edge 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 specifications. - Moment is the product of the item weight multiplied by its arm. - Useful Load is the basic empty weight subtracted from the maximum weight of the aircraft. It is the maximum allowable combined weight of pilot and passenger. - Reference Datum is an imaginary vertical plane from which all horizontal distances are measured for balance purposes. - Tare is the weight of all items used to hold the airplane on the scales for weighing. Tare includes blocks, shims, and chocks. Tare weight must be subtracted from the associated scale reading. WBR Weight and Balance Report is part of the aircraft documentation and is a record of aircraft empty weight and C.G. location. MLE Minimum List of Equipment is the list of instruments, systems and equip- ment that must be on board and functional for a kind of operation. TOM Take Off Mass is the aircraft mass at take off. On VELIS Electro this value does not change during the entire flight. 1-11 VELIS Electro Pilot's Operating Handbook PAGE POH-128-00-40-001 PAGE REV. 2 SECTION 1 GENERAL 1.7.6. ADDITIONAL ABBREVIATIONS AH Artificial Horizon AHRS Attitude and Heading Reference System AOA Angle Of Attack BATT Battery/Batteries COM Communication - Radio EA Electrical Aircraft ELT Emergency Locator Transmitter HV High Voltage IFR Instrumental Flight Rules NVFR Night-Visual Flight Rules PVS Pipistrel Vertical Solutions VFR Visual Flight Rules 1.8 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 0.0295 inHg 1 inHg 33.898 hPa 1 kg 2.2046 lb 1 lb 0.4536 kg/min 1 kg/min 2.2046 lb/min 1 lb.min 0.4536 kg/min 1 l 0.2641 US gal 1 US gal 3.7864 l/min 1 l 1.057 US quart 1 US quart 0.9461 l 1 l/min 0.2641 US gal/min 1 US gal.min 3.7864 l/min 1 daNm 88.4956 lbf.in 1 lbf.in 0.0113 daNm 1 daNm 7.3801 lbf.ft 1 lbf.ft 0.1355 daNm 1 m 3.2809 ft 1 ft 0.3040 m 1 mm 0.0394 in 1 in 25.4 mm 1 cm3 0.06102 in3 1 in3 16.393 cm3 1 hPa 0.0145 psi 1 psi 68.965 hPa 1-12PAGE VELIS Electro Pilot's Operating Handbook POH-128-00-40-001 PAGE REV. 2 SECTION 1 GENERAL 1.9 LIST OF APPLICABLE DOCUMENTS Reference Document [1] WBR-128-08-10-XXX* Weight and Balance Report [2] ELT_345_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 (by Kanardia d.o.o.) [7] SB-128-00-80-001 Flight_Data_Logging [8] SPOH-128-00-40-001 Leaflet ground risks * Where XXX represents the last three digits of the aircraft's serial number NOTE: Latest revision of listed documents has to be used. SECTION 2 2-2PAGE VELIS Electro Pilot's Operating Handbook POH-128-00-40-001 PAGE REV. 2 PART SUBJECT PAGE NUMBER 2.1 INTRODUCTION 2-3 2.2 AIRSPEED LIMITATION 2-3 2.3 AIRSPEED INDICATOR MARKINGS 2-4 2.4 ENGINE AND PROPELLER LIMITATIONS 2-4 2.5 ENGINE INSTRUMENT MARKINGS 2-5 2.6 WEIGHT AND CENTER 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 2.14 KINDS OF OPERATIONS 2-7 2.15 OPERATIONAL RESTRICTIONS 2-9 2.16 PLACARDS 2-10 Placards (External) Placards (Engine and batt compartments) Placards (Instrument Panel) Placards (Center Console) Placards (Cabin) Placards (External - High Voltage Hazard) TABLE OF CONTENTS APPROVED SECTION 2 – LIMITATIONS 2-3 VELIS Electro Pilot's Operating Handbook PAGE POH-128-00-40-001 PAGE REV. 2 SECTION 2 LIMITATIONS APPROVED 2.1 INTRODUCTION This section provides operating limitations, instrument markings and basic placards necessary for the safe operation of the airplane and its standard systems and equipment. 2.2 AIRSPEED LIMITATIONS All speeds in the table below are KIAS. Speed KIAS Remarks 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 exceeded except in smooth air. VA 100 Operating Maneuvering Speed is the maximum speed at which full control travel may be used. VFE 81 Maximum Flap Extended Speed is the highest speed permissible with wing flaps extended at (+1) stage, 65 KIAS for (+2) stage. VS0 46 Stall speed in landing configuration. Stall speed for flaps (+2) stage. VS 53 Stall speed clean. Stall speed for flaps (0) stage. 2-4PAGE VELIS Electro Pilot's Operating Handbook POH-128-00-40-001 PAGE REV. 2 SECTION 2 LIMITATIONS APPROVED 2.3 AIRSPEED INDICATOR MARKINGS All speeds in the table below are KIAS. 2.4 ENGINE AND PROPELLER LIMITATIONS ENGINE Pipistrel electric engine E-811-268MVLC Maximum rated take off power (MTOP) 57.6 kW (limited to 90 sec) Maximum rated continuous power (MCP) 49.2 kW Maximum take off rpm 2500 RPM (electronically limited) Maximum continuous rpm 2350 RPM Motor temperature min -20 °C, max +110 °C Power controller temperature min -20 °C, max +70 °C PROPELLER Pipistrel 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 configuration. Upper limit is the maximum speed permissible with flaps extended at 1st stage. White triangle 65, 81 Flap speed limitations for (+2) stage, (+1) stage. Green Arc 53 - 98 Normal Operating Range. Lower limit is the max- imum weight stall at most forward C.G. in clean configuration. Upper limit is the maximum struc- tural cruising speed. NOTE: Clean configuration is regarded as Flaps in position (0). Yellow Arc 98 - 108 Caution Range. Operations must be conducted with caution and only in smooth air. Red Line 108 Never exceed speed. Maximum speed for all op- erations. 2-5 VELIS Electro Pilot's Operating Handbook PAGE POH-128-00-40-001 PAGE REV. 3 SECTION 2 LIMITATIONS APPROVED 2.5 ENGINE INSTRUMENT MARKINGS (EPSI570C) EPSI570C RED LINE GREEN ARC YELLOW ARC RED LINE MINIMUM NORMAL CAUTION MAXIMUM Tachometer (RPM) 0 / 2299 2300 / 2499 2500 Motor temp. (°C) (-20) / 99 100 / 109 110 Power controller temp. (°C) (-20) / 64 65 /69 70 Battery sys temp. (°C) 5 11 / 50 6 / 10 51 / 57 58 Motor Power (PWR) (kW)* 0 / 48 49 / 65 66 * NOTE: Additional 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 LIMITS Maximum take off weight 600 kg Minimum useful load 172 kg Maximum useful load Typically 172 kg, or value detailed in [1] Maximum landing weight 600 kg Most forward CG (with crew) 25.2 % MAC / 269 mm Most rearward CG (with crew) 32.6 % MAC / 336 mm NOTE: The reference datum is wing’s leading edge at root. 2.7 OCCUPANCY Max. Occupancy Pilot and 1 Passenger Minimum weight solo pilot 34 kg Maximum weight per seat 110 kg Maximum pilot and occupant weight see [1] Maximum baggage weight No baggage 2-6PAGE VELIS Electro Pilot's Operating Handbook POH-128-00-40-001 PAGE REV. 2 SECTION 2 LIMITATIONS APPROVED 2.8 COOLANT Motor, power electronics and batteries are liquid cooled (distilled water/glycol). Approved coolant 50% water + 50% glycol automotive grade G12+ Coolant level Both expansion tank windows full of coolant and bubble free 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 MANEUVER LIMITS Aircraft is intended for “non-aerobatic” and for “VFR day” operation only. Non-aerobatic operation includes: a) Any maneuver incidental to normal flying b) Stalls (except whip stalls) c) Eights, chandelles, and steep turns, in which the angle of bank is not more than 60º. All spins are prohibited. 2-7 VELIS Electro Pilot's Operating Handbook PAGE POH-128-00-40-001 PAGE REV. 2 SECTION 2 LIMITATIONS APPROVED 2.11 ALTITUDE LIMITS Maximum operating altitude 12,000 ft MSL 2.12 TEMPERATURE LIMITS Aircraft equipped with battery type PB345V124E-L: can be operated only between -20 °C < OAT < +35 °C Aircraft equipped with battery type PB345V119E-L: can be operated only between 0 °C < OAT < +36 °C Do not fly when the temperature of the aircraft’s surface is at risk of ex- ceeding 55 °C. Batteries should be stored between 0 °C < OAT < +30 °C (recommended %SOC range 30-80 %SOC) 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 temperature < +45 °C *CAUTION: when battery temperatures are above 40 °C, prolonged high-power application (circuit patterns or prolonged climb at MCP) may lead to battery high temperature. 2.13 MINIMUM FLIGHT CREW The minimum flight crew is one pilot. 2.14 KIND OF OPERATIONS The airplane is approved for VFR-Day operations only. NOTE: The airplane must be equipped according to the MLE for the planned kind of operation, see 2.14.1. 2-8PAGE VELIS Electro Pilot's Operating Handbook POH-128-00-40-001 PAGE REV. 2 SECTION 2 LIMITATIONS APPROVED 2.14.1 MINIMUM LIST OF EQUIPMENT SYSTEM, INSTRUMENT, EQUIPMENT MLE - REQUIRED FOR KIND OF OPERATION (item Qty) VFR Day VHF COM / (NAV) — Transponder — Low Voltage Battery (aux battery) 1 Ammeter / Indication 1* Emergency Locator Trans. — Pitch Trim Indicator 1 Pitch 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 Warning Panel/Annunciator 1 Batt Overtemp Warning Lights 2 Motor Power Indicator 1* Battery SOC/SOH indicators 2* RPM Indicator 1* RPM/Power Indicator Backup (Kanardia) — Motor Temperature Indicator 1* Power Controller Temperature Indicator 1* Battery Temperature Indicators 2* Stall Warning System 1 * The indication is integrated into the EPSI570C system/display. 2-9 VELIS Electro Pilot's Operating Handbook PAGE POH-128-00-40-001 PAGE REV. 2 SECTION 2 LIMITATIONS APPROVED 2.15 OPERATIONAL RESTRICTIONS Flight under Instrument Flight Rules (IFR) is not permitted. NVFR Flight is not permitted. Minimum SOC at take off = 50%. Standard mission planning must consider 30% SOC as minimum value at landing. Do not initiate a go-around procedure if SOC < 15%. (Remaining energy will not be sufficient for another safe circuit pattern) MTOP must be limited to 90 seconds. Flight into known icing conditions is prohibited. No flights in heavy rainfall or blizzard conditions. Areas with 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. Depending on battery type installed, the aircraft can be operated only when: -20 °C < OAT < +35 °C PB345V124E-L 0 °C < OAT < +36 °C PB345V119E-L Maximum battery temperature at take off is +45 °C * Avoid applying more than 75% rudder deflection during cruise/climb/approach as this may cause a pitch-down moment. The USB power outlets are not approved to supply power to flight-critical com- munication or navigation devices. No intentional spins. AHRS (Kanardia Horis) and GPS is for information only and should not be used for primary navigation as well as attitude and heading references. *CAUTION: when battery temperatures are above 40 °C, prolonged high-power application (circuit patterns or prolonged climb at MCP) may lead to battery high temperature. 2-10PAGE VELIS Electro Pilot's Operating Handbook POH-128-00-40-001 PAGE REV. 2 SECTION 2 LIMITATIONS APPROVED 2.16 PLACARDS 2.16.1 PLACARDS (EXTERNAL) ROCKET GAS EXHAUST 1111528 1 1 1 1 5 2 8 Rocket Deployed Parachute Egress Area STAY CLEAREmergency information at: www.galaxysky.cz DANGER EGRESS EXPLOSIVE 1111534 CRAFT FLIGHT MANUAL FOR GAGE LIMITATIONS AND AND BALANCE INFORMATION TED FLOOR LIMIT 25 KG / 55 LBS 1111539 1111705 1111706 T H R O TT LE FULL IDLE ON C H O K E OFF RKING BRAKE ON 1111717 USgal Liter Liter USgal 5 5 1 1 10 10 3 3 15 15 20 20 4 4 5 5 1111719 1111719 +2 +1 0 +2 +1 0 FLAPS FLAPS 1111723 1111723 EAW MTOW CREW WT LUGGAGE WT kg 600 kg min. 55 kg 25 kg 1111730 1111564 2.8 bar INFLATE TO 1111562 1.8 bar INFLATE TO ROCKET GAS EXHAUST 1111528 t Deployed Parachute Egress Area TAY CLEARergency information at: www.galaxysky.cz DANGER EGRESS EXPLOSIVE 1111534 IGHT MANUAL FOR ITATIONS AND ANCE INFORMATION R LIMIT 25 KG / 55 LBS 1111539 T H R O TT LE FULL IDLE ON C H O K E OFF 1111711 ON USgal Liter Liter USgal 5 5 1 1 10 10 3 3 15 15 20 20 4 4 5 5 1111719 1111719 +2 +1 0 +2 +1 0 FLAPS FLAPS 1111723 1111723 EAW MTOW CREW WT LUGGAGE WT kg 600 kg min. 55 kg 25 kg 1111730 1111564 2.8 bar INFLATE TO 1111562 1.8 bar INFLATE TO FLAPS +2 +1 0 - 1111824 VFE +2 VFE +1 VFE 0 65 KIAS 81 KIAS 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 V S0 V S V A V NO 1111500 3.5 l OIL Refer to ROTAX manual OPEN CLOSED 1111503 1111 5 1 0 M I N M O G A S R O N 9 5 o r A V G AS100LL M I NM O G A S R O N 9 5 o r A V G A S 1 0 0 L L 1 1 1 1 5 1 1 F U E L / W A T E R D R A I N O P E N 1111514 LATCH BEFORE TAKE-OFF NO STEP1111522 50 % ANTIFREEZE + 50 % WATER1111524 PULL FOR PARACHUTE DEPLOYMENT 1111529 OPEN CLOSED 1111551 DAN EXPLOSIVE 1111 +386 5 3658 160 This aircraft is equipped with a ballistically-deployed emergency parachute system 1111553 1111559 WARNING! When using AVGAS 100LL, 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 OPEN CLOSED OPEN CLOSED L E F T RI G H T O F F 1 1 1 1 7 7 0 LIFT KNOB WEAK LINK MAX 300 kg 1111821 TOW HOOK1111821 1111728 This aircraft is approved to fly in visual meteorological conditions (VMC) only and flights in intrumental meteorological conditions (IMC) are prohibited! INTENTIONAL SPINNING A REFER TO POH Next to nose wheel Next to main wheels (2x) Next to door handles C H A R G I N GP O R T U S E D E D I C A T E D C H A R G E R O N L Y ! w w w . p i p i s t r e l - a i r c r a f t . c o m 1 1 1 3 0 0 6 On charging port door on the upper engine cowling 1111589 BATTERY EXHAUST Covering the battery exhaust outlets (2x) 1111982 Before disconnecting charger CHECK EPSI and annunciator for CAUTIONS and WARNINGS On the inner side of charging port door 2-11 VELIS Electro Pilot's Operating Handbook PAGE POH-128-00-40-001 PAGE REV. 2 SECTION 2 LIMITATIONS APPROVED 2.16.2 PLACARDS (ENGINE AND BATT COMPARTMENTS) BATTERY COOLING OUTLET KEEP CLEAR! 1111502 DANGER HIGH 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, control surfaces (16x) (6x each battery pack) (6x each battery pack) (1x each battery pack) Next to engine and battery cooling system coolant overflow hoses ENG. COOLANT OVERFLOW1113004 BATT. COOLANT OVERFLOW1113005 2-12PAGE VELIS Electro Pilot's Operating Handbook POH-128-00-40-001 PAGE REV. 2 SECTION 2 LIMITATIONS APPROVED 2.16.3 PLACARDS (INSTRUMENT PANEL) 1111503 1 1 1 1 5 1 0 M I N M O G A S R O N 9 5 orAV G A S 1 0 0 L L M I N M O G A S R O N 9 5 o r A V G A S 1 0 0 L L 1 1 1 1 5 1 1 F U E L / W A T E R D R A I O P E N 1111514 LATCH BEFORE TAKE-OFF NO STEP1111522 50 % ANTIFREEZE + 50 % WATER1111524 PULL FOR PARACHUTE DEPLOYMENT 1111529 OPEN CLOSED 1111551 This aircraft is equipped with a ballistically-deployed emergency parachute system 1111553 1111559 WARNING! When using AVGAS 100LL, 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 visual meteorological conditions (VMC) only and flights in intrumental meteorological conditions (IMC) are prohibited! INTENTIONAL SPINNING REFER TO POH 1111926 FLAPS +2 +1 VFE +2 VFE +1 65 KIAS 81 KIAS MAX EXTENSION SPEED 1111877 OPERATING SPEEDS VNE 108 KIAS 46 KIAS 53 KIAS 100 KIAS 98 KIAS VS0 VS VA VNO On coolant expansion tanks (2x) EAW MTOW CREW WT 1111928 kg 600 kg min. 34 kg 1111929 MAX 40 kW WITH ONE BATTERY INOPERATIVE 1111927 BATT OVERTEMP WARNING F R HPH MIC R HPH MIC L 1111830 1111830 Next to microphone/ headphone jacks 1111983 MIN 50% SOC AT TAKE-OFF 2-13 VELIS Electro Pilot's Operating Handbook PAGE POH-128-00-40-001 PAGE REV. 2 SECTION 2 LIMITATIONS APPROVED 2.16.4 PLACARDS (CENTER CONSOLE) 1111512 LVE CLOS ROCKET GAS EXHAUST 1111528 1 1 1 1 5 2 8 DANGER EGRESS EXPLOSIVE 1111534 SEE AIRCRAFT FLIGHT MANUAL FOR BAGGAGE LIMITATIONS AND WEIGHT AND BALANCE INFORMATION DISTRIBUTED FLOOR LIMIT 25 KG / 55 LBS 1111539 R ROCKET www.pipistrel.si 1111700 1111701 1111705 L R HEADSET L R MIC 1111706 T H R O TT L 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 4 5 5 1111719 1111719 +2 +1 +2 +1 FLAPS FLAPS 1111723 1111723 EAW MTOW CREW WT LUGGAGE WT kg 600 kg min. 55 kg 25 kg 1111730 1111564 2.8 bar INFLATE TO 1111562 1.8 bar INFLATE TO ON CAB I N OFF A I R 1111827 Next to flap lever Next to parking brake lever Next to power lever SOFTWARE UPGRADE PORT 1111988 On the left and right side of the instrument panel DATA LOGGER PORT 1111985 USB PORT 1111984 2-14PAGE VELIS Electro Pilot's Operating Handbook POH-128-00-40-001 PAGE REV. 2 SECTION 2 LIMITATIONS APPROVED 2.16.5 PLACARDS (CABIN) 1 1 1 1 5 1 2 D R A I N V A L V E C L O S E Rocket Deployed Parachute Egress Area STAY CLEAREmergency information at: www.galaxysky.cz DANGER EGRESS EXPLOSIVE 1111534 OPEN 1111 L R MIC 11117 1111707 T H R O TT LE FULL IDLE ON 1111711 +1 0 FLAPS 1111723 NING APPROVED O POH 1111826 FL180 123 M I N M O G A S R O N 9 5 o r A V G 1 1 1 1 5 1 2 F U E L / W A T E R D R AIN V A L V E O P E N C L O S E EXHAUS 1 1 1 1 5 2 8 Rocket Deployed Parachute STAY CLEEmergency information at: www.g DANGER EGR EXPLOSIVE SEE AIRCRAFT FLIGHT MANUAL BAGGAGE LIMITATIONS AN WEIGHT AND BALANCE INFORM DISTRIBUTED FLOOR LIMIT 25 KG / 5 DANGER CKET EXPLOS 1111552 +386 5 istrel.si s equipped with lly-deployed rachute system 1111553 1111559 WARNING! When using AVGAS 100LL, 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 OPEN CLOSED 1111700 OPEN CLOSED 1111701 1111705 L R HEADSET L R MIC 1111706 1111707 PARKING BRAKE ON OFF 1111717 EAW MTOW CREW WT LUGGAGE O 1 1 1 1 7 7 0 LIFT KNOB WEAK LINK MAX 300 kg 1111821 TOW HOOK1111821 1111564 2.8 bar INFLATE TO 1.8 b INFLAT 1111728 (VMC) only rohibited! ON CAB I N OFF A I R 1111827 INTENTIONAL SPINNING APPROVED REFER TO POH 1111826 In front of control sticks rudder pedal adjustment (2x) Below each door to depict door handle operation On the cabin support strut in front of the pilot 1111714 NO INTENTIONAL SPINS DATE: For Steer For N 30 60 E 120 150 S 210 240 W 300 330 Steer Calibrated with radio ON OFF Next to the compass 2-15 VELIS Electro Pilot's Operating Handbook PAGE POH-128-00-40-001 PAGE REV. 2 SECTION 2 LIMITATIONS APPROVED 2.16.6 PLACARDS (EXTERNAL - HIGH VOLTAGE HAZARD) On the aircraft belly (3x) On battery compartment access panels (3x) This page is intentionally left blank. SECTION 3 3-2PAGE VELIS Electro Pilot's Operating Handbook POH-128-00-40-001 PAGE REV. 2 PART SUBJECT PAGE NUMBER 3.1 INTRODUCTION 3-3 SECTION 3 – EMERGENCY PROCEDURES TABLE OF CONTENTS APPROVED