Pipistrel Virus SW 121 Pilot Operating Handbook Download

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VIRUS SW 121

Document No.: POH-121-00-40-001_B00

REVISION B00

Date of Issue: December 20

, 2018

PIPISTREL VERTICAL SOLUTIONS d.o.o.

Vipavska cesta 2

SI-5270 Ajdovščina

Slovenia

Tel: + 386 5 36 63 873

Fax: + 386 5 36 61 263

Email: [email protected]

part thereof is not permitted, except with the prior and express written permission of

Pipistrel Group’s R&D division, Pipistrel Vertical Solutions d.o.o., which is authorized to

publish technical documentation for Pipistrel Group’s subsidiaries.

PILOT OPERATING

HANDBOOK

Summary of Contents for Virus SW 121

Page 1: ...386 5 36 61 263 Email info pipistrel si 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...

Page 2: ...__ Authorized signature ____________________________ Authority Verified and approved under the authority of DOA No EASA 21J 524 Date of Approval The airplane must be operated in compliance with inform...

Page 3: ...0 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 HANDLING SERVIC...

Page 4: ...ithin 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 page...

Page 5: ...6 3 28 4 21 4 22 7 50 9 S1 8 EASA A04 4th Update due inconsistency with compliance documen tation 2 15 2 16 EASA 21J 524 A05 5th Towing speed range added Airspeed Indicator Markings amended Check list...

Page 6: ...blank 3 27 0 3 28 0 3 29 0 3 30 0 3 31 0 3 32 0 3 33 0 3 34 0 3 35 0 3 36 0 4 4 1 0 4 2 0 4 3 0 4 4 blank 4 5 0 4 6 0 4 7 0 4 8 0 4 9 0 4 10 0 4 11 0 4 12 0 4 13 0 4 14 0 4 15 0 4 16 0 4 17 0 4 18 0 4...

Page 7: ...16 0 7 17 0 7 18 0 7 19 0 7 20 0 7 21 0 7 22 0 7 23 0 7 24 0 8 8 1 0 8 2 0 8 3 0 8 4 0 8 5 0 8 6 0 8 7 0 8 8 0 8 9 0 8 10 0 8 11 0 8 12 0 8 13 0 8 14 0 9 1 0 9 2 0 List of effective pages continued 4...

Page 8: ...ating Handbook POH 121 00 40 001 PAGE REV 0 List of effective pages continued PAGE NUMBER PAGE REV 9 S4 9 S4 1 0 9 S4 2 0 9 S4 3 0 9 S4 4 blank 9 S4 5 0 9 S4 6 0 9 S4 7 0 9 S4 8 blank 9 S4 9 0 9 S4 10...

Page 9: ...SECTION 1...

Page 10: ...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 Powerplant Propeller Fuel System Landing Gear Ballistic Parachute Rescue S...

Page 11: ...full dual flight controls and joint levers for throttle choke propeller flaps and airbrake control Access to cockpit is via two large gull wing doors Baggage area is behind the seats and accessible vi...

Page 12: ...1 4 PAGE Virus SW 121 Pilot Operating Handbook POH 121 00 40 001 PAGE REV 0 SECTION 1 GENERAL Figure 01 001 Virus SW 121 1 4 THREE VIEW DRAWING...

Page 13: ...weight 25 kg 55 lb Max wing loading 63 07 kg m 12 92 lb ft 1 6 SYSTEMS 1 6 1 POWERPLANT The engine installed is Rotax 912 S3 providing 73 5 kW takeoff power All limits as defined by the engine manufa...

Page 14: ...from the fuel system is present and equipped with a 60 micron filter An auxiliary fuel pump is not present 1 6 4 LANDING GEAR The airplane has as a tricycle type fixed landing gear The nose wheel is s...

Page 15: ...lica 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 Struc...

Page 16: ...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 setting obtained from ground meteorological sources OAT Ou...

Page 17: ...certification testing Service Ceiling is the maximum altitude at which the aircraft at maxi mum weight has the capability of climbing at a 100 ft min Unusable Fuel is the quantity of fuel that cannot...

Page 18: ...iplied 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 passengers fuel and baggage Reference Da...

Page 19: ...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 qua...

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Page 21: ...SECTION 2...

Page 22: ...IMITS 2 6 2 7 OCCUPANCY 2 6 2 8 FUEL 2 6 2 9 OIL COOLANT 2 7 2 10 FLIGHT LOAD FACTOR LIMITS 2 7 2 11 MANEUVER LIMITS 2 7 2 12 ALTITUDE LIMITS 2 8 2 13 TEMPERATURE LIMITS 2 8 2 14 MINIMUM FLIGHT CREW 2...

Page 23: ...and alternate static sources Speed KTAS KIAS Remarks VNE 163 See table below Never Exceed Speed is the speed limit that may not be exceeded at any time DA ft 0 2000 4000 6000 8000 10000 12000 14000 16...

Page 24: ...p 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 81 135 Flap s...

Page 25: ...perature 550 885 C Maximum Exhaust Gas Temperature 900 C 2 5 ENGINE INSTRUMENT MARKINGS INSTRUMENT RANGE RED LINE GREEN ARC YELLOW ARC RED LINE MINIMUM NORMAL CAUTION MAXIMUM Tachometer 0 6000 RPM 175...

Page 26: ...ANCY Max Occupancy Pilot and 1 Passenger Maximum weight per seat 110 kg 242 lbs 200 kg 440 lbs total Minimum weight solo pilot 54 kg 119 lbs Maximum baggage weight 25 kg 55 lbs 2 8 FUEL Approved fuels...

Page 27: ...to design of engine s fuel and oil system Limitations from Rotax Specification apply 2 11 MANEUVER LIMITS This airplane is certified in the CS LSA category and is not designed for aer obatic operatio...

Page 28: ...night if the aircraft complies with SB 121 00 80 005 Service Bulletin Installation of Night VFR kit NOTE The airplane must be equipped according to the MLE for the planned kind of operation see 2 15...

Page 29: ...ity Indicator 1 1 Oil Temperature Indication 1 1 Parachute Rescue System Autopilot System Autopilot Pitch Servo Autopilot Roll Servo Airplane Flight Manual 1 1 Instrument Lights 1 Navigation Lights 3...

Page 30: ...rument Flight Rules IFR is not permitted In addition the following limitations apply Autopilot operation is prohibited above 135 KIAS The autopilot must not be engaged for takeoff or landing The autop...

Page 31: ...2 LIMITATIONS APPROVED 2 18 PLACARDS 2 18 1 PLACARDS EXTERNAL Next to each wing fuel tank filler neck Next to each wing fuel tank filler neck Next to nose wheel Next to main wheels On each main landin...

Page 32: ...Virus SW 121 Pilot Operating Handbook POH 121 00 40 001 PAGE REV 0 SECTION 2 LIMITATIONS APPROVED Next to door opening latches Next to fuel drain 2 18 2 PLACARDS ENGINE COMPARTMENT On coolant bottle o...

Page 33: ...E SECTION 2 LIMITATIONS APPROVED 2 18 3 PLACARDS INSTRUMENT PANEL 2 18 4 PLACARDS CENTER CONSOLE Next to propeller lever The BATTERY CAUTION placard is found on aircraft VSW121001 VSW1210039 that comp...

Page 34: ...121 00 40 001 PAGE REV 0 SECTION 2 LIMITATIONS APPROVED Next to choke and throttle levers On flap lever 2x Next to cabin air control lever Next to parking brake lever 2 18 5 PLACARDS CABIN Next to fu...

Page 35: ...IMITATIONS APPROVED Next to microphone jacks Next to headphone jacks In front of control sticks rudder pedal adjustment 2x Below each door to depict door handle operation On upper tube in front of pil...

Page 36: ...40 001 PAGE REV 0 SECTION 2 LIMITATIONS APPROVED 2 18 6 PLACARDS BALLISTIC PARACHUTE RESCUE SYSTEM On adjecent to parachute rescue system hatch and over rocket position Next to doors Next to rocket ex...

Page 37: ...SECTION 3...

Page 38: ...Altitude Engine Failure in Flight Engine Start in Flight Engine Partial Loss of Power Low Oil Pressure Propeller Governor Failure 3 53 FIRE IN FLIGHT 3 11 Smoke in the Cockpit Engine Fire in Flight W...

Page 39: ...3 10 GENERATOR FAILURE 3 20 3 11 ENGINE INDICATING SYSTEM FAILURE 3 21 3 12 COMMUNICATION FAILURE 3 21 3 13 PITOT STATIC MALFUNCTION 3 21 Static Source Blocked Pitot Tube Blocked 3 14 ELECTRIC TRIM A...

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Page 41: ...on the ground Pay special attention to any oil fluid leaks or fuel stains that could indicate engine problems Aircraft emergencies are very dynamic events Because of this it is impossi ble to address...

Page 42: ...on the ground 3 2 AIRSPEEDS FOR EMERGENCY OPERATIONS Maneuvering Speed 100 KIAS Best Glide flaps 0 70 KIAS Emergency Landing Engine out Flaps 0 63 KIAS Flaps 1 60 KIAS Flaps 2 58 KIAS 3 3 GROUND EMER...

Page 43: ...ing the airplane 3 4 IN FLIGHT EMERGENCIES 3 4 1 ENGINE FAILURE AT TAKEOFF LOW ALTITUDE If the engine fails immediately after becoming airborne abort with landing on the runway if possible If altitude...

Page 44: ...landing area attempt to identity the cause of the failure and correct it If altitude or terrain does not permit a safe landing BPRS deployment may be required WARNING If engine failure is accompanied...

Page 45: ...nclude fluctuating RPM reduced or fluctuating manifold pressure low oil pressure high oil temperature and a rough running engine Mild engine roughness in flight may be caused by one or more spark plug...

Page 46: ...Cycling the ignition switch momentarily from BOTH to L and then to R may help identify the problem An obvious power loss in single ignition operation indicates ignition system or spark plug trouble R...

Page 47: ...case land as soon as practical and determine cause 1 Throttle Lever MINIMUM REQUIRED 2 Land AS SOON AS POSSIBLE 3 4 5 PROPELLER GOVERNOR FAILURE If the RPM does not respond to propeller lever movemen...

Page 48: ...g is assured 1 Temperature control knob COLD 2 Airflow direction knob FEET POSITION 3 Fan toggle switch ON 4 Cabin Air Selector ON 5 Door windows OPEN If source of smoke and fume is firewall forward 1...

Page 49: ...a fire extinguisher 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 cabin o...

Page 50: ...t the chances of door failure occuring increase as the speed at which the door s opened at increases 3 6 SPINS The airplane is approved for intentional spins according to F2245 12d para graph 4 5 9 wh...

Page 51: ...such as high deployment speed low altitude or rough terrain may result in severe injury or death to the occupants Because of this BPRS should only be activated when any other means of handling the eme...

Page 52: ...VATE 8 Seat Belts and Harnesses TIGHTEN All occupants must have seat belts securely fastened 9 Loose Items SECURE If time permits all loose items should be secured to prevent injury from flying object...

Page 53: ...old the nose wheel off the ground as long as possible If engine power is available before attempting an off airport landing fly over the landing area at a low but safe altitude to inspect the terrain...

Page 54: ...d break out the windows and crawl through the opening 3 8 3 LANDING WITHOUT ELEVATOR CONTROL The pitch trim spring cartridge is attached directly to the elevator and pro vides a backup should you lose...

Page 55: ...dly noticeable during fast taxiing It is only during the lower taxiing speeds that a tendency to swerve occurs 3 8 5 LANDING WITH DEFECTIVE BRAKES 1 Safety harness CHECK FASTENED AND TIGHTENED After a...

Page 56: ...ds followed by a ATTEMPTING QUICK RESTART message In the event of a power loss greater than 20 seconds a warm start is unlikely and the power interruption will result in loss of attitude information u...

Page 57: ...flight critical systems 3 11 ENGINE INDICATING SYSTEM FAILURE In the event of a Data Acquisition Unit failure the engine indications displayed on the MFD and PFD will be disabled In the event of Data...

Page 58: ...RE Any failure or malfunction of the electric trim or autopilot can be overridden by use of the control stick If runaway trim and or autopilot servo is the prob lem cut the circuit by pulling the circ...

Page 59: ...aircraft verified for airworthiness by authorized service personnel 3 17 ICE BUILD UP Turn back or change altitude to exit icing conditions Consider lateral or ver tical path reversal to return to la...

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Page 61: ...3 25 Virus SW 121 Pilot Operating Handbook POH 121 00 40 001 PAGE REV 0 PAGE SECTION 3 EMERGENCY PROCEDURES APPROVED 3 18 CHECKLISTS EMERGENCY PROCEDURES...

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Page 63: ...If flames are estinghuished Ignition Switch OFF Master Switch OFF If flames persist perform Emergency engine shutdown on Ground and Emergency egress checklist EMERGENCY ENGINE SHUTDOWN Throttle Lever...

Page 64: ...Switch OFF Flaps as required If time permits Throttle Lever IDLE Master Switch OFF Seat belts ensure secured ENGINE FAILURE IN FLIGHT Best Glide Speed ESTABILISH 70 KIAS Fuel Selector CHECK SWITCH TA...

Page 65: ...ne stops perform engine failure in flight check list LOW OIL PRESSURE Throttle Lever Minimum Required Land AS SOON AS POSSIBLE PROPELLER GOVERNOR FAILURE Propeller RPM will not increase Land AS SOON A...

Page 66: ...Selector ON Door Windows OPEN If source of smoke is firewall forward Cabin Air Selector OFF Fan Toggle Switch OFF Door Windows As required Land AS SOON AS POSSIBLE If airflow is not sufficient to clea...

Page 67: ...AS SOON AS POSSIBLE COCKPIT FIRE IN FLIGHT Cabin Air Selector OFF Cabin Heating OFF Battery disconnect switch PULL Master Switch OFF Fire Extinguisher if available ACTIVATE If airflow is not sufficie...

Page 68: ...blish horizontal flight without exceeding g load or airspeed limitations BPRS DEPLOYMENT Airspeed MINIMUM POSSIBLE Ignition switch if time altitude permits OFF Activation Handle PULL After Deployment...

Page 69: ...tions Transponder SQUAWK 7700 ELT ACTIVATE Throttle Lever IDLE Fuel Selector OFF Ignition Switch OFF Flaps When landing is assured 2 Master Switch OFF Seat Belts SECURED DITCHING Radio Transmit 121 5...

Page 70: ...ide angle LANDING WITH DEFECTIVE BRAKES Safety Harnesses SECURED After safe touch down Ignition OFF Fuel Selector OFF Master Switch OFF GENERATOR FAILURE Unnecessary equipment Switch OFF to redurce lo...

Page 71: ...ONDER SQUAWK 7600 PITOT STATIC MALFUNCTION Refer to GPS for flying Ground speed indicator 10 KTS for procedures observe winds TRIM AUTOPILOT FAILURE Airplane Control Graps stick maintain manually Auto...

Page 72: ...3 36 PAGE POH 121 00 40 001 PAGE REV 0 BATT OVERVOLTAGE MALFUNCTION Battery Disconnect Switch PULL...

Page 73: ...SECTION 4...

Page 74: ...E 4 10 Before Starting the Engine Starting the Engine Before Taxiing Taxiing Before Takeoff 4 5 TAKEOFF 4 15 Power Check Flap Setting Normal Takeoff Short Field Takeoff 4 6 CLIMBING 4 16 4 7 CRUISE 4...

Page 75: ...3 Virus SW 121 Pilot Operating Handbook POH 121 00 40 001 PAGE REV 0 PAGE SECTION 4 NORMAL PROCEDURES PART SUBJECT PAGE NUMBER 4 16 SPINNING INTENTIONAL SPINS 4 21 4 17 CHECKLIST NORMAL PROCEDURES 4 2...

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Page 77: ...rmance specified in Section 5 for takeoff and landing dis tance the speed correction appropriate to the particular mass must be used TAKEOFF ROTATION Normal Flaps 1 45 KIAS Obstacle clearance Flaps 0...

Page 78: ...uid reservoirs and lines for evidence of leaking In cold weather remove all frost ice or snow from fuselage wing stabilizers and control surfaces Ensure that control surfaces are free of ice or debris...

Page 79: ...ntenna if available Condition and attachment 5 Baggage compartment Baggage is secure 6 Baggage door Closed and secure locked 7 Static pressure port CHECK for blockage 8 Fuel system water drain Perform...

Page 80: ...ndition and security 6 Leading edge CHECK condition 7 Fuel cap CHECK quantity and secure 8 Water drain holes Clean 9 Pitot tube Cover removed tube clear RIGHT MAIN LANDING GEAR 1 Landing gear General...

Page 81: ...4 Landing light Attachment security lens 5 Strut CHECK condition 6 Nose landing gear General condition 7 Wheel and tire Condition inflation and wear 8 Wheel Fairing CHECK attachment 9 Shock absorber C...

Page 82: ...4 STARTING ENGINE 4 4 1 BEFORE STARTING ENGINE 1 Preflight Inspection Completed 2 Fuel quantity Sufficient 3 Emergency Equipment On board 4 Passenger Briefed 5 BPRS Safety Pin Removed 6 Seats Pedals S...

Page 83: ...Pressure Indication Available 8 Ignition Switch Start Release after engine starts CAUTION Limit cranking to intervals of 20 seconds with a 20 second cool ing period between cranks This will improve ba...

Page 84: ...ut without a reduction in power will result in increased brake temperature and may in extreme cases cause fire Taxi over loose gravel at low engine speed to avoid damage to the propeller tips WARNING...

Page 85: ...Choke Verify closed 4 Throttle Lever 4000 RPM 5 Alternator Check value and warning light 6 Voltage Check value 7 Ignition Switch RIGHT note RPM then BOTH 8 Ignition Switch LEFT note RPM then BOTH WAR...

Page 86: ...rify Pin Removed 3 Airbrakes Closed and locked 4 Flaps Set 1 5 Trim Set neutral 6 Fuel tank selector Select fullest tank 7 Fuel Quantity CHECK 8 NAV Strobe Lights As required 9 Landing Light As requir...

Page 87: ...he flaps up configuration Takeoffs with negative flaps is not approved Soft or rough field takeoffs are performed with 1 flaps by lifting the airplane off the ground as soon as practical in a tail low...

Page 88: ...hly at 45 KIAS 10 Airspeed at Obstacle 60 KIAS 11 At 70 KIAS Flaps Retract to 0 4 6 CLIMBING Normal climbs are performed flaps UP 0 and full power at speeds 5 to 10 knots higher than best rate of clim...

Page 89: ...ing fuel consumption for various altitudes and temperatures can be determined by using the cruise data in Section 5 1 Flaps 2 Cruise Power SET 3 Engine Parameters Check 4 Switch to other Wing Fuel Tan...

Page 90: ...As required 4 Airbrakes on final As required 5 Trim As required 4 10 LANDING CAUTION Landings should be made with full flaps and airbrakes fixed in extended position Glideslope should be controlled wi...

Page 91: ...le and on the main wheels first Immediately after touch down lower the nose wheel and apply braking as required For maximum brake effectiveness retract the flaps hold the control stick full back and a...

Page 92: ...uired 5 Airbrakes Close at taxi speed 4 13 SHUT DOWN 1 Green electrical switches All OFF 2 Throttle lever IDLE 3 Ignition Switch OFF 4 BPRS safety pin Insert 5 AVIONICS OFF 6 MASTER OFF 7 ELT Transmit...

Page 93: ...E NO CAUTION Spin testing was performed according to F2245 12d para graph 4 5 9 which includes investigation of behavior of developed 2 turns and 3 turns spins and subsequent recovery within a maximum...

Page 94: ...an intentional 3 turns spin is 5500 ft AGL SPIN ENTRY PROCEDURE 1 Flaps 0 trim for 67 KIAS fix power setting 2 Pull the control stick back until stall occurs 3 Hold the stick in full aft position sto...

Page 95: ...4 23 Virus SW 121 Pilot Operating Handbook POH 121 00 40 001 PAGE REV 0 PAGE SECTION 4 NORMAL PROCEDURES CHECKLISTS NORMAL PROCEDURES 4 17...

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Page 97: ...es All OFF Required Documents On Board Battery Disconnect Switch CONNECT Flight Controls Flaps and Airbrakes Free and Correct Master Switch ON Avionics Switch ON Circuit Breakers IN PFD MFD Verify ON...

Page 98: ...e Door Closed and secured locked Static Pressure Port CHECK for blockage Fuel System water drain Perform EMPENNAGE Tiedown Rope Remove Horizontal and Vertical Stabilizers CHECK condition Elevator and...

Page 99: ...CHECK condition and secured Tip CHECK attachment Strobe NAV lights CHECK condition and attachment Leading Edge CHECK condition Fuel Cap CHECK quantity and secure Water Drain Holes Clean Pitot Tube Cov...

Page 100: ...st Pipe CHECK security and condition Gascolator Drain 1 cup sample Landing Light Attachment and condition Nose Landing Gear and Strut CHECK condition Wheel and Tire Condition inflation and wear Wheel...

Page 101: ...ment Flaperon Gap Seal CHECK condition attachment and no wrinkles Hinges Bolts Safety Nuts CHECK condition and secured Tip CHECK attachment Strobe NAV lights CHECK condition and attachment Leading Edg...

Page 102: ...ent On board Passenger Briefed BPRS Safety Pin Removed Seats Pedals Seat belts and Baggage Adjust and Secure Parking Brake Disengage Brakes Hold Master Switch ON Avionics Switch ON NAV Strobe Lights O...

Page 103: ...ne starts Throttle Lever Maintain 2500 RPM or below Oil Pressure CHECK Choke Slowly close Engine Parameters Monitor Ammeter Indication CHECK BEFORE TAXIING Flaps 0 or COM Avionics As required Cabin He...

Page 104: ...ECK Value Ignition Switch RIGHT note RPM then BOTH Ignition Switch LEFT note RPM then BOTH Propeller Lever Cycle 3 times observe RPM drop Propeller Lever Full Forward Throttle Lever SET to just above...

Page 105: ...pilot Check disconnect Annunciator PFD CHECK Altimeter SET Engine Parameters CHECK Flight Controls Free and Correct TAKEOFF NORMAL TAKEOFF Brakes Release steer with rudder only Propeller Lever Full Fo...

Page 106: ...ward Engine Parameters CHECK Brakes Release steer with rudder only Airspeed Indication CHECK Elevator Control Rotate smoothly at 45 KIAS Airspeed at Obstacle 60 KIAS at 70 KIAS FLAPS 0 CLIMB Climb Pow...

Page 107: ...ds DESCENT APPROACH Altimeter SET Autopilot Disengage Cabin heat Defrost As requireds Landing Light ON Fuel Selector Fullest Tank Parking Brake Disengaged Brake Pressure CHECK pump pedals Seat Belts S...

Page 108: ...s 1 Airspeed 57 60 KIAS After Clear of Obstacles Flaps 0 Airspeed Vy 78 KIAS AFTER LANDING Throttle Lever IDLE Flaps or 0 Transponder STBY Lights As required Airbrakes Close at taxi speed SHUT DOWN Gr...

Page 109: ...SHUT DOWN continue Avionics Switch OFF Master Switch OFF ELT Transmit Light OUT PARKING BPRS Safety Pin CHECK Inserted Secured Parking Brake ENGAGED Only if necessary Fuel Selector OFF Pitot Covers I...

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Page 111: ...SECTION 5...

Page 112: ...DUCTION 5 3 5 2 OUTSIDE AIR TEMPERATURE FOR ISA CONDITION 5 4 5 3 WIND COMPONENT 5 5 5 4 AIRSPEED CALIBRATION 5 6 5 5 STALL SPEED 5 8 5 6 TAKEOFF 5 9 5 7 RATE OF CLIMB VY 5 10 5 8 CLIMB GRADIENT VX 5...

Page 113: ...the expertise of the pilot or the maintenance condition of the airplane The performance illustrated in the tables can be achieved if the indicated procedures are followed and the airplane is in good m...

Page 114: ...A ISA 10 C ISA 20 C SL 25 5 15 25 35 1000 27 7 13 23 33 2000 29 9 11 21 31 3000 31 11 9 19 29 4000 33 13 7 17 27 5000 35 15 5 15 25 6000 37 17 3 13 23 7000 39 19 1 11 21 8000 41 21 1 10 20 9000 43 23...

Page 115: ...21 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 parall...

Page 116: ...ht or max continuous power whichever is less NOTE Indicated airspeed values assume zero instrument error KIAS KCAS Flaps Flaps 0 Flaps 1 Flaps 2 40 37 37 50 49 46 47 48 60 59 57 59 59 70 69 68 69 80 7...

Page 117: ...5 7 Virus SW 121 Pilot Operating Handbook POH 121 00 40 001 PAGE REV 0 PAGE SECTION 5 PERFORMANCE DATA APPROVED KIAS KCAS Diagram...

Page 118: ...250 ft Normal recovery with power 100 ft Aggressive recovery less than 100 ft Normal recovery with extended airbrakes 150 ft Depending on pilot skill the altitude loss during wings level stall may be...

Page 119: ...Runway Slope Increase table distances by 22 of the ground roll distance at Sea Level for each 1 of upslope Decrease table distances by 7 of the ground roll distance at Sea Level for each 1 of slope We...

Page 120: ...ff 47 KIAS Speed over 50 ft 60 KIAS VX 5 7 RATE OF CLIMB VY Conditions Power throttle full open Propeller full forward fine pitch Flaps 0 Airpseed best rate of climb 78 KIAS VY WEIGHT Pressure Altitud...

Page 121: ...ct the climb performance to degrade with increased outside air temperature 5 9 CRUISING POWER SETTING FUEL CONSUMPTION Conditions Weight 600 kg Temperature ISA Wind zero Total Fuel 99 Liter usable NOT...

Page 122: ...0 25 7 75 119 18 4 4900 24 7 65 105 16 0 4600 24 0 55 102 14 4 PRESSURE Altitude Parameters ISA RPM MAP PWR MCP KTAS FF liter h 4000 ft Not achievable MCP Not achievable 5500 25 3 85 130 25 2 5500 24...

Page 123: ...ievable MCP Not achievable 85 5500 22 0 75 132 23 6 5300 21 7 65 125 21 2 5100 21 0 55 118 18 0 PRESSURE Altitude Parameters ISA RPM MAP PWR MCP KTAS FF liter h 10 000 ft Not achievable MCP Not achiev...

Page 124: ...ground roll distance Wet grass runway Add 60 to ground roll distance Sloped Runway Increase table distances by 27 of the ground roll distance for each 1 of slope Decrease table distances by 9 of the...

Page 125: ...C 30 C 40 C 11 C 2000 Ground roll 267 276 286 296 306 279 Total over 50 ft 452 461 471 481 491 463 PRESSURE Altitude ft DISTANCE m TEMPERATURE 0 C 10 C 20 C 30 C 40 C 7 C 4000 Ground roll 287 298 309...

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Page 127: ...SECTION 6...

Page 128: ...ng Handbook POH 121 00 40 001 PAGE REV 0 SECTION 6 WEIGHT AND BALANCE APPROVED PART SUBJECT PAGE NUMBER 6 1 INTRODUCTION 6 3 6 2 C G SAMPLE CALCULATION 6 4 6 3 WEIGHT AND BALANCE CHART 6 5 SECTION 6 W...

Page 129: ...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 to ensure the aircraft s takeoff we...

Page 130: ...entered into the weight and balance chart in section 6 4 to determine whether the aircraft is within the flight limits prescribed in section 2 6 NOTE Calculate the moment for each item by multiplying...

Page 131: ...HT AND BALANCE APPROVED 6 3 WEIGHT AND BALANCE CHART The chart below shows the Virus SW 121 s mass CG envelope Once the aircraft s takeoff weight and C G have been calculated they can be used to find...

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Page 133: ...SECTION 7...

Page 134: ...TROL SYSTEM 7 5 Elevator Control System Aileron Control System Rudder Control System Wing Flaps Control System Airbrakes Control System Elevator Trim System 7 4 LANDING GEAR 7 7 Main Gear Nose Gear Br...

Page 135: ...rning Lights Circuit Breakers and Fuses Miscellaneous Components 7 9 LIGHTNING 7 19 Exterior Lightning Interior Lightning 7 10 ENVIRONMENTAL SYSTEM 7 20 7 11 PITOT SYSTEM 7 22 7 12 STALL WARNING SYSTE...

Page 136: ...ECT PAGE NUMBER Communication COM Transceivers Navigation NAV Transceivers Optional Transponder Audio System Hour Meter 7 16 AUTOPILOT 7 30 7 17 EMERGENCY LOCATOR TRANSMITTER ELT 7 31 7 18 BALLISTIC P...

Page 137: ...age compart ment there is a CFRP container for the ballistic rescue system Primary and secondary control rods are covered by CFRP fairings to protect them from luggage The baggage compartment floor is...

Page 138: ...luminum bracket that is pivoted to the vertical stabilizer and can be removed The shell of the horizontal tail is designed as CFRP sandwich The horizontal tail is attached to an alumi num bracket at t...

Page 139: ...In case the horizontal tail plane is removed the U member remains attached to the fuselage whereas the elevator remains attached to the horizontal stabilizer There are no cables in the pitch control s...

Page 140: ...he thumb lock button prevents inadverted handle movement The backside of the flap handle connects to the main flaperon bell crank 7 3 6 AIRBRAKES CONTROL SYSTEM Schempp Hirth Style airbrakes are activ...

Page 141: ...f aluminum The inner tube is made out of crome plated steel Inflate to maximum 2 5 bar 7 4 3 BRAKE SYSTEM The main wheels are equipped with hydraulic disc brakes Right and left brake are independent a...

Page 142: ...g normal brake operation When the handle is pulled back the parking brake valve holds applied brake pressure locking the brakes To apply the parking brake set the brakes with the rudder pedal toe brak...

Page 143: ...tched on the rear edge The door is locked from the outside with a key lock The baggage compartment key will also open and close the cabin doors The baggage compartment extends from behind the seats to...

Page 144: ...t Once the oil temperature reaches 80o C the thermostat opens allowing the oil to flow through the cool ers A dipstick is present on the oil tank to check oil quantity CAUTION The engine should not be...

Page 145: ...sible to both pilots on the center console They consist of a single lever throttle control a propeller control lever and the choke lever Throttle Lever A throttle control lever is located in the centr...

Page 146: ...el converts analog signals from the COOLANT EGT MAP oil pressure oil temperature fuel pressure fuel flow voltage amperage and tachometer sensors to digital format which are then transmitted to the MFD...

Page 147: ...from the pilot position and connected to the highest and lowest points of each respective tank serve as a visual indicator of the fuel quantity available Each tank has a strainer at the fuel outlet t...

Page 148: ...he fuel tanks should be filled after each flight to prevent condensation Fuel Selector Valve A fuel selector valve located in the middle of the centerconsole provides the following functions LEFT Allo...

Page 149: ...for actual fuel quantity on board and tracking of fuel situation 7 8 ELECTRICAL SYSTEM 7 8 1 ELECTRICAL SYSTEM The airplane is equipped with a single alternator single battery 14 volt di rect current...

Page 150: ...for the regulator rectifier in the event of momentary interruption of battery voltage This is necessary as generator output voltage is variable with RPM and may increase to as much as 240V AC The avi...

Page 151: ...to the switch panel and circuit breakers To check or use avionics equipment or radios while on the ground the AVIONICS power switch must also be turned on Both 12V sockets are connected via switch fus...

Page 152: ...he flag type lever on the firewall Deflect the lever so that its flag end points towards the firewall Hav ing done this correctly you will feel the flag lever jam into position 7 8 5 WARNING LIGHTS Ge...

Page 153: ...ough the 2 amp 12VDC OUTLET circuit breaker on the Battery Bus 7 9 LIGHTNING 7 9 1 EXTERIOR LIGHTNING Navigation Lights The airplane is equipped with LED standard wing tip navigation lights The lights...

Page 154: ...r either reacting to ambient light conditions automatical ly or as manually set by the pilot Rotating the knob to the right will result in brigher illumination rotating the knob to the left will resul...

Page 155: ...he fresh hot air ratio passing through the cabin air selector which is fastened to the aircraft s firewall The system is controlled from the cabin by a cabin heat panel The cabin heat panel is positio...

Page 156: ...ed indi cator and altimeter 7 12 STALL WARNING SYSTEM The stall warning system is integrated with the PFD by using real AOA sens ing via the AOA measuring pitot tube and the associated AOA display on...

Page 157: ...ight from the dual ADAHRS units the PFD s function does not influence the functionality of the autopilot The autopilot panel indicates modes that are active or armed Below the autopilot panel are the...

Page 158: ...ional gyro HSI horizontal situation indicator wind data FMS and avionics related annunciator In addi tion the PFD communicates with GPS1 GPS2 NAV optional the Multifunc tion Display MFD and Autopilot...

Page 159: ...ircraft reference symbol against a background of labeled pitch ladders and an arced scale along the top of the ADI to indicate bank angle A skid slip indicator is attached to the bottom edge of the ba...

Page 160: ...zon bar which divides the mask into two sections indicates pitch and roll attitudes The upper blue sky section and the lower earth sections have pitch reference lines useful for pitch attitude control...

Page 161: ...Turn Coordinator function and roll data display is integrated into the PFD 7 14 7 COURSE DEVIATION INDICATOR The Course Deviation Indicator is integrated into the PFD 7 14 8 MAGNETIC COMPASS A conven...

Page 162: ...ot panel Garmin GMC 305 12 Pipistrel SmartDim controller 13 ELT Kannad 406 AF compact remote panel Kannad RC200 14 Mechanical Compass 15 Slipball Winter 16 Cabin heat control panel 17 Switches and bre...

Page 163: ...ver transmitter receives interrogations from a ground based secondary radar transmitter and then transmits to the interrogating Air Traffic Control Center Digitized altitude information pro vided by t...

Page 164: ...rument panel for easier mode selection recognition activation arming When in an active autopilot mode full guidance is provided including smooth transitions to altitude and head ing captures If not in...

Page 165: ...eading Hold Mode 2 ALT Altitude Capture Hold Mode 3 VS Vertical Speed Hold Mode 4 GPS Track Direct To Mode 5 NAV Capture NAV track or radial Mode 6 VNV Vertical Navigation from GPS source Mode 7 APR s...

Page 166: ...nce Manual The ELT remote switch and indicator panel installed on top right side of the instrument panel provides test and monitoring functions for the ELT The panel contains a button labeled ON a but...

Page 167: ...parachute a solid propellant rocket to deploy the parachute a rocket activation handle a composite container and a harness connecting the canopy to the wingbox structire A composite box containing the...

Page 168: ...teady and continuous force until the rocket activates A chin up type pull works best Up to 200 N force or greater may be required to activate the rocket The greater force required occurs as the cable...

Page 169: ...y be experienced particularly at high speed Following any nose up pitching the nose will gradually drop until the aircraft is hanging nose low beneath the canopy Descent rate is expected to be less th...

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Page 171: ...SECTION 8...

Page 172: ...NANCE 8 3 8 4 CHANGES AND REPAIRS 8 4 8 5 SERVICING 8 4 Tire Servicing Brake Servicing Propeller Servicing Oil Servicing Fuel System Servicing 8 6 GROUND HANDLING 8 8 Application of External Power Tow...

Page 173: ...pections by the issuance of airworthiness directives applicable to the aircraft engine propeller and components The owner is responsible for compliance with all applicable airworthiness directives and...

Page 174: ...lter elements 8 Replace the battery and check fluid level and specific gravity 8 4 CHANGES AND REPAIRS Only licensed personnel is permitted to perform changes or repairs Changes to the aircraft must b...

Page 175: ...l as corrosion on visible metal parts If found they should be repaired as soon as possible by a rated mechanic since a nick or scratch causes an area of increased stress which can lead to serious crac...

Page 176: ...a fire extinguisher available Do not fill tank within 30 m of any electrical equipment capable of pro ducing a spark Permit no smoking or open flame within 30 m of airplane or refuel vehi cle Do not...

Page 177: ...ign material such as water dirt rust and fungal or bacterial growth Additionally chemicals and additives that are incompatible with fuel or fuel system components are also a source of fuel contaminati...

Page 178: ...ery must be removed from the airplane and battery maintenance performed with appro priate procedures To apply external power to the airplane 1 Ensure that external power source is regulated to 14 VDC...

Page 179: ...ded for forward movement Excessive braking may result in overheated or damaged brakes and or fire Observe wing clearance when taxiing near buildings or other stationary objects If possible station an...

Page 180: ...tract and lock airbrakes 3 Chock the wheels 4 Attach tie down rings 5 Secure tie down ropes to the wing tie down rings and to the tail ring at approximately 45 angles to the ground CAUTION Anchor poin...

Page 181: ...ces rinse away all dirt particles before applying cloth or chamois Never rub dry lexan Do not attempt to polish lexan CAUTION Clean windshield and windows only with a solvent free none abrasive antist...

Page 182: ...acrylic cleaner Do not use gasoline alcohol benzene carbon tetra chloride thinner acetone or glass window cleaning sprays Use only a non abrasive cotton cloth or genuine chamois to clean acrylic wind...

Page 183: ...ergents should be avoided Solvents and alcohols may damage or discolor vinyl or urethane parts Cover areas where cleaning solution could cause damage Use the following procedure CAUTION Solvent cleane...

Page 184: ...VICING 3 Soiled upholstery may be cleaned with approved products Avoid soaking or harsh rubbing Carpets To clean carpets first remove loose dirt with a whiskbroom or vacuum For soiled spots and stubbo...

Page 185: ...SECTION 9...

Page 186: ...PACT B00 9 S2 VOR EQUIPMENT B00 9 S3 NIGHT VFR OPERATIONS B00 9 S4 AEROTOWING OPERATIONS B00 Any revision or addition of effective supplements must be recorded in the table A black vertical line in th...

Page 187: ...SUPPLEMENT 9 S1...

Page 188: ...ents Section of the POH This document must be carried in the air plane at all times Information in this supplement adds or replaces informa tion in the basic POH TABLE OF CONTENTS POH SECTIONS STATUS...

Page 189: ...PAGE REV 0 PAGE SECTION 9 SUPPLEMENTS SECTION 9 SUPPLEMENT 9 S1 KANNAD AF406 COMPACT 406 MHz ELT System Signature ____________________________ Authority ____________________________ Stamp ____________...

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Page 191: ...he ELT Remote Switch ON even if the red LED annunciator is flashing If airplane radio operable and can be safely used no threat of fire or explosion turn radio ON and select 121 5 MHz If the ELT can b...

Page 192: ...u tomatically activated upon sensing a change of velocity along its longitudinal axis exceeding 4 to 5 ft sec2 Once activated the transmitter transmits VHF band audio sweeps at 121 5 Mhz until battery...

Page 193: ...be replaced upon reaching the date stamped on the batteries after an inadvertent activation of unknown duration or whenever the batteries have been in use for one cumulative hour Inspection Test After...

Page 194: ...anel switch ON for about 1 second then back to the ARM position The receiver should transmit 3 audio sweeps 3 At turn off back to ARM state the panel LED and buzzer should present 1 pulse If more are...

Page 195: ...SUPPLEMENT 9 S2...

Page 196: ...erted in the Supplements Section of the POH This document must be carried in the airplane at all times Information in this supplement adds to or replaces information in the basic POH POH SECTIONS STAT...

Page 197: ...0 40 001 PAGE REV 0 PAGE SECTION 9 SUPPLEMENTS SECTION 9 SUPPLEMENT 9 S2 Garmin GNC 255 NAV COM Signature ____________________________ Authority ____________________________ Stamp ____________________...

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Page 199: ...ntegrated into the Garmin GNC 255 The unit has VHF Om nirange Localizer VOR LOC capability The VOR LOC receiver receives VOR LOC on a frequency range from 108 000 MHz to 117 950 MHz with 50 kHz spacin...

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Page 201: ...SUPPLEMENT 9 S3...

Page 202: ...ction of the Pilot Operating Handbook This document must be carried in the airplane at all times Information in this supplement adds to or replaces information in the basic POH TABLE OF CONTENTS POH S...

Page 203: ...00 40 001 PAGE REV 0 PAGE SECTION 9 SUPPLEMENTS SECTION 9 SUPPLEMENT 9 S3 Night VFR operations Signature ____________________________ Authority ____________________________ Stamp _____________________...

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Page 205: ...210001 to VSW1210037 that are equipped for Night VFR and are not compliant with SB 00 80 010 will find the following placard differences on their aircraft The fuel selector valve placard installed in...

Page 206: ...f the emergency parachute is recommended Switch off the engine slow down the airplane and activate the ballistic rescue system Note The aircraft is equipped with a ballistic rescue system Consider usi...

Page 207: ...nds switch off the engine slow down the airplane and activate the ballistic rescue system SECTION 4 NORMAL PROCEDURES 4 18 NIGHT VFR OPERATIONS Virus SW 121 is not an IFR approved type When flying Nig...

Page 208: ...ent and avionic lights set the dimmer to AUTO for automatic bright ness control Use the MANUAL mode to set the desired brightness manually CAUTION Do not dim the lights up too quickly in a very dark e...

Page 209: ...cated in the central column Switch for the fuel tank level lights located on the instrument panel Dimmer display and knob located on the top left side of the instrument panel The cabin light switch ha...

Page 210: ...1 Pilot Operating Handbook POH 121 00 40 001 PAGE REV 0 SECTION 9 SUPPLEMENTS Figure 3 Glare shield and breakers UV LED lights Figure 4 Cabin lights Figure 5 Fuel tank level LED lights Figure 6 Circui...

Page 211: ...SUPPLEMENT 9 S4...

Page 212: ...ANCE ADDED SECTION 6 WEIGHT AND BALANCE NO CHANGE SECTION 7 SYSTEM DESCRIPTION ADDED SECTION 8 HANDLING SERVICING AND MAINTENANCE ADDED SECTION 9 SUPPLEMENT 9 S4 Aerotowing operations When a tow hook...

Page 213: ...Handbook POH 121 00 40 001 PAGE REV 0 PAGE APPROVED SECTION 9 SUPPLEMENT 9 S4 Aerotowing operations Signature ____________________________ Authority ____________________________ Stamp ________________...

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Page 215: ...imum weak link rating 300 kg Aerotowing is only permitted within the speed range of 60 80 KIAS VS at 500 kg is 48 KIAS 1 3 VS is 63 KIAS 2 18 1 PLACARDS EXTERNAL 2 18 3 PLACARDS INSTRUMENT PANEL SECTI...

Page 216: ...ging rope to become tangled into obstacles before the runway After touchdown brake gently Respect all normal operating speeds and procedures Glider cannot disconnect Continue flight to be over a landa...

Page 217: ...e glider TAKEOFF Flaps 1 Trim 1 2 Nose Up Lift Off Speed 55 KIAS Initial climb speed 60 KIAS depends on glider type REACHING SAFE ALTITUDE MIN 300 FT Engine power 5500 RPM WOT Turn crosswind Maximum b...

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Page 219: ...cap which covers the tie down point insert the mirror mounting and screw it in until it is properly fixed Clamp the mirror to the mounting Adjust the mirror posi tion in order to have a clear and unob...

Page 220: ...Idle 13 Flaps 14 Airbrakes As desired 15 Rope Drop before landing CAUTION Should the rope not be dropped before landing use caution to maneuver aircraft so that the rope does not catch obstacles on ap...

Page 221: ...d surface runway TOWED GLIDER MASS GROUND ROLL ISA Sea level TAKE OFF distance 15m obstacle ISA Sea level kg m m 300 180 350 400 200 370 500 250 410 600 280 500 5 12 2 CLIMB TOWED GLIDER MASS Climb ra...

Page 222: ...uipment is limited to use with a weak link max rating 300 kg and for towing of gliders with a take off weight of less than 600 kg SECTION 8 HANDLING SERVICING AND MAINTENANCE 8 6 GROUND HANDLING 8 6 5...

Page 223: ...Move airplane to desired location by grabbing on the tail cone 4 When moving backward lower the tail to keep nose wheel off the ground 5 Install chocks when repositioning complete To obtain a minimum...

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Page 226: ...info pipistrel si www pipistrel si Pipistrel Italia Via Fratelli Rusjan 26 34070 Savogna d Isonzo GO Italia EU t 39 0481 522000 f 39 0481 522110 pipistrel legalmail it www pipistrel eu Pipistrel Verti...

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