Sling 4 TSi, Pilot Operating Handbook

Page 1: ... T HANG AR 8 T EDDERF I EL D AI R PARK J HB S OUT H EI KENHOF 1872 S OUT H AF RI CA PO BOX 308 EI KENHOF 1872 S OUT H AF RI CA Phone 27 11 948 9898 I nf or m at i on t echni cal s l i ngai r cr af t com REVI S I ON 3 0 DAT E 14 J UL Y 2021 S E RI AL NO RE GI ST RAT I ON ...

Page 2: ... Pty Ltd Airplane Serial Number Date of Construction Registration Airworthiness Category FAR Part 23 Issue Date of POH 2021 07 14 Please advise Sling Aircraft upon change of ownership of this aircraft This airplane must be operated in compliance with information and limitations contained herein This pilot operating handbook must be available on board of the airplane at all times ...

Page 3: ... manufactured on premises by Sling Aircraft Pty Ltd Aircraft which differ from the production standard in whatever way are not addressed in this manual except to the extent said aircraft corresponds with the production standard NOTICE This manual may contain specific references to South African regulations Therefore the manual can be regarded as a manual accordingly consistent with RSA regulations...

Page 4: ...ntinued airworthiness for the Sling 4 TSi are FAA FAR Part 23 Airworthiness Standards Normal Utility Aerobatic and Commuter Category Quality Assurance records are stored with the manufacturer in South Africa at the address below Sling Aircraft Pty Ltd Hangar 8 Tedderfield Air Park Johannesburg South Eikenhof 1872 South Africa PO Box 308 Eikenhof 1872 South Africa Tel 27 11 948 9898 sales slingairc...

Page 5: ...g 4 TSi shall be responsible for providing the manufacturer with current contact information where the manufacturer may send the owner operator supplemental notification bulletins letters The owner operator of a Sling 4 TSi shall be responsible for notifying the manufacturer of any flight safety issues or significant service difficulty upon discovery The owner operator of a Sling 4 TSi shall be re...

Page 6: ...ble be endorsed by the responsible airworthiness authority Revision numbers and dates appear at the foot of each page Rev No Affected Section Affected Pages Date of Issue Approved by Sign 0 Initial Issue Initial Issue 2018 07 24 Andrew Pitman 1 1 4 2 2 5 1 9 2 3 5 5 5 7 2019 05 20 Andrew Pitman 2 0 All All 2020 01 31 Andrew Pitman 2 1 All All 2020 12 09 Andrew Pitman 2 2 All All 2021 01 26 Andrew ...

Page 7: ...sed 3 0 1 2 Revised 3 0 2 15 Removed 3 0 1 3 Revised 3 0 2 16 Removed 3 0 1 4 Revised 3 0 3 0 Inserted 3 0 1 5 Revised 3 0 3 1 Revised 3 0 1 6 Revised 3 0 3 2 Revised 3 0 1 7 Revised 3 0 3 3 Revised 3 0 1 8 Revised 3 0 3 4 Revised 3 0 1 9 Revised 3 0 3 5 Revised 3 0 1 10 Revised 3 0 3 6 Revised 3 0 1 11 Revised 3 0 3 7 Revised 3 0 1 12 Revised 3 0 3 8 Revised 3 0 1 13 Revised 3 0 3 9 Revised 3 0 1...

Page 8: ... Revised 3 0 6 6 Revised 3 0 4 6 Revised 3 0 6 7 Revised 3 0 4 7 Revised 3 0 6 8 Revised 3 0 4 8 Revised 3 0 6 9 Revised 3 0 4 9 Revised 3 0 6 10 Removed 3 0 4 10 Revised 3 0 6 11 Removed 3 0 4 11 Revised 3 0 6 12 Removed 3 0 4 12 Revised 3 0 6 13 Removed 3 0 4 13 Revised 3 0 7 0 Inserted 3 0 4 14 Revised 3 0 7 1 Revised 3 0 4 15 Revised 3 0 7 2 Revised 3 0 4 16 Revised 3 0 7 3 Revised 3 0 4 17 Re...

Page 9: ...25 Revised 3 0 8 5 Revised 3 0 7 26 Revised 3 0 8 6 Revised 3 0 7 27 Revised 3 0 8 7 Revised 3 0 7 28 Revised 3 0 8 8 Revised 3 0 7 29 Revised 3 0 8 9 Removed 3 0 7 30 Revised 3 0 9 0 Inserted 3 0 7 31 Revised 3 0 9 1 Revised 3 0 7 32 Revised 3 0 9 2 Revised 3 0 7 33 Revised 3 0 9 3 Revised 3 0 7 34 Revised 3 0 9 4 Revised 3 0 7 35 Revised 3 0 9 5 Revised 3 0 7 36 Revised 3 0 9 6 Revised 3 0 7 37 ...

Page 10: ...0 Page ix Revision 3 0 Date 2021 07 14 Table of Contents 1 General Information 1 0 2 Limitations 2 0 3 Emergency Procedures 3 0 4 Normal Procedures 4 0 5 Performance 5 0 6 Weight and Balance 6 0 7 Aircraft and Systems 7 0 8 Ground Handling and Servicing 8 0 9 Supplementary Information 9 0 ...

Page 11: ...F 3 0 Page 1 0 Revision 3 0 Date 2021 07 14 1 General Information 1 1 Introduction to Airplane 1 1 1 2 Warnings Cautions and Notes 1 2 1 3 Aircraft 3 View Drawing 1 3 1 4 Data for Sling 4 TSi Aircraft and Systems 1 5 1 5 Terminology Symbols and Conversion Factors 1 10 1 6 Supporting Documents 1 15 ...

Page 12: ...w wing design The aircraft design is based upon the FAA FAR 23 certification standards and has a maximum all up weight of 950 kg 2 095 lb Notwithstanding that the aircraft design is based upon the FAA FAR 23 certification standards the aircraft has not been proven to comply with all the provisions of the standard The Sling 4 TSi is intended chiefly for recreational and cross country flying It is n...

Page 13: ...otes in the Pilot Operating Handbook Warning Indicates that non observation of the corresponding procedure leads to a serious and immediate degradation of flight safety Caution Indicates that non observation of the corresponding procedure leads to minor and possible long term degradation of flight safety Note Draws special attention to any item that is not related to safety but is still important ...

Page 14: ... POH 001 X F 3 0 Page 1 3 Revision 3 0 Date 2021 07 14 1 3 Aircraft 3 View Drawing DIMENSIONS IN THIS DRAWING ARE IN MILLIMETRES CAUTION Do not use these values for weight and balance as they are overall dimensions for illustration purposes and do not use the prescribed reference plane ...

Page 15: ...Sling 4 TSi Section 1 Pilot Operating Handbook General Information Document Number DC POH 001 X F 3 0 Page 1 4 Revision 3 0 Date 2021 07 14 DIMENSIONS IN THIS DRAWING ARE IN MILLIMETRES ...

Page 16: ...79 Dihedral 4 5 Tip Washout 1 5 1 4 2 Fuselage Parameter Value Fuselage Length 6 220 m 20ft 5in Overall Length 7 175 m 23ft 6in Fuselage Width 1 188 m 3ft 11in Overall Height 2 414 m 7ft 11in 1 4 3 Empennage Parameter Value Horizontal Stabilizer Span 3 020 m 9ft 11in Horizontal Stabilizer Surface Area 1 065 m2 11 5 ft2 Horizontal Stabilizer Angle of Incidence 0 8 Elevator Surface Area 1 164 m2 12 ...

Page 17: ...face Travel Limits Parameter Value Ailerons 24 up down 2 Elevator 32 up 22 down 2 Trim Tab 5 up 25 down 5 Rudder 23 left right 2 Flaps 0o up 34o down 3 1 4 6 Engine Parameter Item Value Manufacturer Bombardier Rotax GmbH Model 915 iS Type 4 cylinder horizontally opposed turbocharged with an overall displacement of 1352cc mixed cooling fuel injection integrated reduction gearbox with torque damper ...

Page 18: ...m Value Fuel Grade Anti Knock Minimum MON 85 RON 95 AKI 91 Fuel Grade MOGAS EN 228 Super EN 228 Super Plus Fuel Grade AVGAS AVGAS 100 LL ASTM D910 Standard Fuel Tanks Fuel Tanks Capacity 88 L 23 2 US GAL Fuel Tanks Useable Capacity 86 L 22 7 US GAL Total Fuel Capacity 176 L 46 5 US GAL Total Useable Fuel Capacity 172 L 45 4 US GAL Long Range Fuel Tanks Fuel Tanks Capacity 99 L 26 2 US GAL Fuel Tan...

Page 19: ...ded Conventional aircraft oils a d ashless dispersant are not suitable Refer to the latest revision of the engine operator s manual for more Oil Viscosity Multi grade oils are recommended Oil Capacity Approx 3 0 litres 3 2 quarts 6 3 pints from dry 1 4 10 Cooling Parameter Item Value Cooling System Mixed Air and closed circuit pressurized liquid Air cooled cylinders and liquid cooled cylinder head...

Page 20: ...ht 950 kg 2 095 lb Maximum Landing Weight 950 kg 2 095 lb Maximum Baggage Weight Total 35 kg 77 lb Maximum Baggage Weight Baggage Extension 3 kg 7 lb 1 4 12 Standard Weights Parameter Value Standard Configuration Empty Weight 500 kg 1 102 lb Maximum Useful Load 450 kg 992 lb 1 4 13 Specific Loadings Parameter Value Wing Loading MAUW 82 54 kg m2 16 90 lb ft2 Power Loading MAUW 6 74 kg kW 14 85 lb h...

Page 21: ...ic Flight Information System FAA Federal Aviation Authority FAR Federal Aviation Regulations GLS GPS Landing System GmbH Gesellschaft mit beschränkter Haftung company with limited liability GPS Global Positioning System IFR Instrument Flying Rules IMC Instrument Meteorological Conditions LE Leading Edge LED Light Emitting Diode MOGAS Automobile car Gasoline MON Motor Octane Number NGL Normal Groun...

Page 22: ...d at which the aircraft generally lifts off from the ground during take off VNE Never Exceed Speed the speed that may not be exceeded at any time VNO Maximum Structural Cruising Speed the speed that should not be exceeded except in smooth air and then only with caution VREF Reference Speed the indicated airspeed at 15 m 50 ft above threshold which is not less than 1 3Vso VROT Rotation Speed The sp...

Page 23: ...ure OHV Overhead Valve RPM Revolutions per Minute Coolant Temperature Temperature of the coolant as it leaves the cooling jacket of cylinder head 4 1 5 5 Airplane Performance and Flight Planning Terminology Terminology Description Crosswind Component The velocity of the crosswind component during take off and landing G The acceleration load factor Landing Run The distance measured during landing f...

Page 24: ... Sling 4 TSi datum is 52mm aft of the propeller flange Empty Weight The weight of the airplane with engine fluids at operating levels MAC Mean Aerodynamic Chord The average chord value of the main wing MAUW Maximum All Up Weight or Maximum Takeoff Weight Maximum permissible weight approved for takeoff flight Maximum Landing Weight The maximum weight approved for the landing touch down Moment The p...

Page 25: ...actors Imperial Metric pound 1 0 4536 kilogram pound per square inch 1 6 895 kilopascal inch 1 25 4 millimetres foot 1 0 3048 meters statute mile 1 1 609 kilometres nautical mile 1 1 852 kilometres millibar 1 1 hectopascal 0 1 kilopascal imperial gallon 1 4 546 litres US gallon 1 3 785 litres US quart 1 0 946 litres cubic foot 1 28 317 litres F 1 8 C 32 𝐹𝐹 32 5 9 C ...

Page 26: ...ion of Suitable Operating Fluids 3 The latest revision of the Operators Manual for the Airmaster AP3 and AP4 Series Constant Speed Propellers 4 The latest revision of the Operators Manual for the Garmin G3X Glass Cockpit 5 The latest revision of the Operators Manual for the relevant COM radio transponder and any other relevant equipment fitted 6 The latest revision of the Operators Manual for the ...

Page 27: ...kings 2 2 2 4 Stall Speed Adjustment for Turning Flight 2 3 2 5 Crosswind and Wind Limitation Demonstrated 2 4 2 6 Service Ceiling 2 4 2 7 Load Factors 2 4 2 8 Weights 2 4 2 9 Centre of Gravity Range 2 5 2 10 Prohibited Manoeuvres 2 6 2 11 Flight Crew 2 6 2 12 Passengers 2 6 2 13 Kinds of Operation 2 7 2 14 Engine Limitations 2 9 2 15 Other Limitations 2 11 2 16 Flight in Precipitation 2 11 2 17 L...

Page 28: ...less in smooth air and then only with caution VA Manoeuvring Speed 108 Do not make full or abrupt control movements above this speed as this may cause stress in excess of limit load factor VFE Maximum Flap Extended Speed 85 Never exceed this speed unless the flaps are fully retracted VH Maximum Speed in Level Flight 140 Never exceed this speed in level flight at MAUW VS Stall Speed 55 The aircraft...

Page 29: ...king KIAS Significance White Arc 48 85 Flap Operating Range Lower Limit VS0 At MAUW Upper Limit Vfe Max flap operation speed Green Arc 55 135 Normal Operating Range Lower Limit VS At MAUW max forward CG Upper Limit VNO Max Structural Speed Yellow Arc 135 155 Manoeuvres must be conducted with caution and only in smooth air Red Line 155 Maximum speed for all operations ...

Page 30: ...or turning flight or increased load factor MULTIPLICATION FACTOR 0 2 0 4 0 6 0 8 1 0 1 2 1 4 1 6 1 8 0 10 20 30 40 50 60 70 80 90 BANK ANGLE DEGREES This graph is only valid for level i e non descending turning flight 𝑉𝑉𝑇𝑇 𝑉𝑉 𝑉𝑉 𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀 𝐹𝐹𝐹𝐹𝐹𝐹𝐹𝐹𝐹𝐹𝐹𝐹 V is straight and level stall speed at load factor 1 g VT is stall speed in turn non descending 𝑉𝑉𝑆𝑆𝑆𝑆 𝑉𝑉 𝑁𝑁 V is straight and le...

Page 31: ...ng 15 kts 2 6 Service Ceiling Item Value Service Ceiling 18 000 ft 4 486 m 2 7 Load Factors Item Value Maximum positive limit load factor 3 8g Maximum negative limit load factor 1 9g Maximum positive load factor with flap 2 5g Maximum negative load factor with flap 1g 2 8 Weights Item Value Maximum take off weight MAUW 950kg 2 094 lb Maximum landing weight 950kg 2 094 lb Maximum total baggage weig...

Page 32: ...gitudinal Levelling Second row of rivets below the canopy frame edge on the outside of the fuselage above the wing Reference Transverse Levelling Upper surface of centre spar cap under pilot and passenger seats Forward CG Limit 1 847 mm 6 060 ft 18 MAC aft of datum Rear CG Limit 2 043 mm 6 703 ft 33 MAC aft of datum WARNING It is the pilot s responsibility to ensure that the airplane is properly l...

Page 33: ...ights Chandelles Stalls not including whip stalls 2 11 Flight Crew Minimum crew for flight is one pilot seated on the left or right side 2 12 Passengers Only three passengers are allowed on board the aircraft in addition to the pilot and in accordance with CG limitations WARNING Aerobatics and intentional spins are prohibited WARNING Limit load factor would be exceeded by moving flight controls ab...

Page 34: ...ss Fuel Gauges Oil Pressure Indicator Oil Temperature Indicator Cylinder Head Temperature Indicator Outside Air Temperature Indicator Tachometer Chronometer First Aid Kit Compliant with Local Authority Fire Extinguisher 2 13 2 Night Operation Subject to the legal requirements applicable in the country of registration the Sling 4 TSi fitted with the following additional equipment may also be operat...

Page 35: ...bility of the aircraft operator to ensure that all legal and safety requirements are met along with the installation of the required systems and instrumentation for IFR and IMC flight WARNING Notwithstanding that installed equipment may include GPS and other advanced flight and navigational aids such equipment may not be used as the sole information source for purposes of navigation or flight expe...

Page 36: ...marked set to reflect the minimum and maximum figures Always refer to the latest edition revision of the engine Operators Manual for latest information regarding operating limitations 2 14 1 Engine Start and Operation Temperature Limits Item Value Start Maximum Ambient Temperature 50 C 122 F Start Minimum Oil Temperature 20 C 4 F 2 14 2 Engine Load Factor Limits Acceleration Item Value Maximum 5 s...

Page 37: ...tinuous 5500 rpm Cruise 5000 rpm 5400 rpm Idle 1 400 rpm minimum Oil Temperature Minimum 50 C 122 F Maximum 130 C 266 F Normal 90 to 110 C 194 to 230 F a EGT Maximum 950 C 1742 F Coolant Temperature Minimum 20 C 4 F Maximum 120 C 248 F Oil pressure Minimum 0 8 bar 12 psi below 3500 rpm Maximum 7 bar 102 psi permissible for short period during cold engine start Normal 2 to 5 bar 29 to 73 psi above ...

Page 38: ...FR only flights are permitted unless the operator has equipped the aircraft correctly for IFR flight 2 16 Flight in Precipitation Flying though rain should be avoided but can be achieved with no additional steps Airplane qualities and performance are not substantially changed However VMC should be maintained unless flight is under IFR WARNING Intentional flights under icing conditions are prohibit...

Page 39: ...17 2 Visible to Pilot and Passenger 2 17 3 Exterior of Baggage Door OPERATE UNDER VMC ONLY MAXIMUM PERMISSIBLE AIRSPEED 155 KIAS MAXIMUM PERMISSIBLE RPM 5 800 RPM FOR 5 MINUTES MAXIMUM CONTINUOUS RPM 5 500 MAXIMUM PERMISSIBLE MASS 950 KG 2 094 LB WARNING NON CERTIFIED AIRCRAFT THIS AIRCRAFT IS NOT REQUIRED TO COMPLY WITH ALL THE REGULATIONS FOR TYPE CERTIFIED AIRCRAFT YOU FLY IN THIS AIRCRAFT AT Y...

Page 40: ...Surface 2 17 6 Fireproof Metal Plate Attached to Aircraft AVGAS OR MOGAS 98 LITRES NO STEP ZU CONSTRUCTOR SLING AIRCRAFT MODEL SLING 4 TSi AIRCRAFT SERIAL NO ENGINE ROTAX 915 iS 141 HP MANUFACTURED NOTE represents the information applicable to the specific aircraft The registration number on above plate is specific to the country of registration The format shown above is the South African standard...

Page 41: ...n 3 0 Date 2021 07 14 2 17 7 Other Placards The aircraft must be placarded to show the identity of All Fuses Circuit Breakers Ignition switches Starter Trim NOSE UP and NOSE DOWN Flaps UP STAGES 1 2 3 DOWN All Other Switches Canopy handle OPEN and CLOSED position Ballistic parachute deployment handle if equipped ...

Page 42: ... X F 3 0 Page 3 0 Revision 3 0 Date 2021 07 14 3 Emergency Procedures 3 1 Introduction 3 1 3 2 Speeds for Emergency Operations 3 2 3 3 Engine Related Emergencies 3 3 3 4 Emergency Landing Procedures 3 7 3 5 Smoke and Fires 3 10 3 6 Recovery from Unintentional Spin 3 13 3 7 Other Emergencies 3 14 ...

Page 43: ...re followed such as pre flight inspections and general maintenance Should an emergency arise however basic guidelines described in this section should be considered and applied accordingly to mitigate the consequences of the emergency In case of an emergency the pilot should remember the following priorities in order of importance 1 FLY THE AIRCRAFT Keep control and continue flying 2 ANALYSE Analy...

Page 44: ...2021 07 14 3 2 Speeds for Emergency Operations Speed KIAS Remarks VBG Best Glide Speed 72 This speed MAUW flaps up results in the best gliding distance along the ground Horizontal distance travelled in still air is approx 3 660m 12 000ft per 305m 1 000ft decent Glide ratio 12 1 Speed for in flight engine start 75 Recommended speed ...

Page 45: ...ter OFF 5 Fuel Selector OFF 6 Fuel Pumps BOTH OFF MAIN AUX 7 Boost Pump OFF 3 3 2 Engine Failure Immediately After Take Off 1 Airspeed 72 KIAS 2 Landing Area LOCATE CLEAR GROUND 3 Flaps AS NEEDED 4 Fuel Pumps BOTH OFF MAIN AUX 5 Fuel Selector OFF before touch down 6 Ignition Lanes OFF A B 7 Boost Pump OFF 8 Master OFF WARNING Flaps and elevator trim will not operate with the master switch off and ...

Page 46: ...D WITH CAUTION 5 Land AS SOON AS POSSIBLE If engine should fail to restart 6 Land FORCED LANDING 3 3 4 Air Start 1 ECU Backup Switch ON 2 Fuel Pumps BOTH ON MAIN AUX 3 Boost Pump ON 4 Fuel Selector CHANGE UNLESS 2ND TANK DRY 5 Throttle CHECK MOVEMENT 6 Throttle MIDDLE POSITION 7 Master ON 8 Ignition Lanes ON A B 9 Starter ENGAGE NOTE An air start is possible with the propeller windmilling and the ...

Page 47: ... CHANGE UNLESS 2ND TANK DRY 6 Fuel Pumps BOTH ON BOTH 7 Boost Pump ON 8 Oil Pressure CHECK 9 Oil Temperature CHECK 10 Coolant Temperature CHECK 11 EGT Temperature CHECK If engine continues to run rough 12 Land AS SOON AS POSSIBLE 3 3 6 Low Fuel Pressure 1 Fuel Quantity CHECK 2 Fuel Selector CHANGE UNLESS 2ND TANK DRY 3 Fuel Pumps BOTH ON MAIN AUX 4 Boost Pump ON If fuel pressure remains low 5 Thro...

Page 48: ...7 14 3 3 7 Low Oil Pressure 1 Oil Temperature CHECK MAX 120 C If oil temperature is high or increasing 2 Airspeed 72 KIAS a If oil pressure remains low or temperature remains high increasing 3 Land AS SOON AS POSSIBLE b NOTES a 72 KIAS is the speed at which the aircraft is most efficient b Remain vigilant for an impending engine failure ...

Page 49: ... If engine fails to restart 4 Fuel Pumps BOTH OFF MAIN AUX 5 Boost Pump OFF 6 Ignition Lanes OFF A B 7 Fuel Selector OFF 8 Throttle CLOSED 9 Flaps FULL PRIOR TO TOUCHDOWN 10 Communication REPORT IF TIME PERMITS 11 Passenger BRIEF Immediately Before Touchdown 12 Master OFF NOTES a Do not lose perspective of time trying to restart the engine Retry a limited number of times which will depend on the a...

Page 50: ... Pump ON 5 Landing Area INSPECT AS PER PROCEDURE 6 Flaps FULL ON FINAL APPROACH 7 Airspeed 65 KIAS 8 Brakes APPLY when aircraft is under control 9 Ignition Lanes OFF A B 10 Fuel Selector OFF 11 Master Switch OFF 3 4 3 Ditching 1 Airspeed 65 KIAS 2 Flaps FULL 3 Decent ESTABLISH 50 ft min 4 Direction i High Wind INTO WIND ii Light Wind PARALLEL TO SWELLS 5 Crew BRIEF 6 Canopy OPEN 7 Touch down Speed...

Page 51: ... Wheel 1 Approach NORMAL 2 Airspeed 65 KIAS 3 Airspeed at flare SLOWEST PRACTICAL 60 𝐾𝐾𝐾𝐾𝐾𝐾𝐾𝐾 If nosewheel is damaged flat 4 Nosewheel KEEP OFF GROUND FOR AS LONG AS POSSIBLE WITH ELEVATOR NOTE The Sling 4 TSi lands within ground effect since the wings are low to the ground Anticipate an increase in lift just before touch down unless airfoil stalls before entering ground effect ...

Page 52: ...2 Fuel Selector CLOSE 3 Fuel Pumps BOTH OFF MAIN AUX 4 Boost Pump OFF 5 Throttle IDLE 6 Ignition Lanes OFF A B 7 Master OFF 8 Fire Extinguisher RETRIEVE 9 Exit Aircraft 10 Extinguish Fire 3 5 2 Engine Fire on Ground 1 Cabin Heat CLOSE 2 Fuel Selector CLOSE 3 Fuel Pumps BOTH OFF MAIN AUX 4 Boost Pump OFF 5 Throttle IDLE 6 Ignition Lanes OFF A B 7 Master OFF 8 Fire Extinguisher RETRIEVE 9 Exit Aircr...

Page 53: ... Selector CLOSE 5 Fuel Pumps BOTH OFF MAIN AUX 6 Boost Pump OFF 7 Ignition Lanes OFF A B 8 Master OFF 9 Fire Extinguisher RETRIEVE 10 Exit Aircraft 11 Extinguish Fire 3 5 4 Engine Fire in Flight 1 Cabin Heat CLOSE 2 Cabin Air Vent OPEN 3 Throttle IDLE 4 Fuel Pumps BOTH OFF MAIN AUX 5 Boost Pump OFF 6 Ignition Lanes OFF A B 7 Master OFF AFTER FLAP DEPLOYMENT 8 Fuel Selector CLOSE 9 Airspeed INCREAS...

Page 54: ...re is NOT extinguished 7 Forced Landing EXECUTE 3 5 6 Cabin Fire 1 Master OFF 2 Cabin Heat CLOSE 3 Ventilate Cabin OPEN VENTS 4 Extinguisher USE IF POSSIBLE If fire is extinguished 5 Precautionary Landing CONSIDER If fire in NOT extinguished 6 Forced Landing EXECUTE NOTES a If the location source of the fire can be determined electrical power can be removed from that circuit via the isolating swit...

Page 55: ...rol RUDDER NEUTRAL 5 Longitudinal Control RECOVER FROM DIVE a In the unlikely event that the aircraft enters a flat spin and the steps above do not result in recovery of control the following may be implemented 1 Throttle IDLE 2 Lateral Control AILERONS NEUTRAL 3 Longitudinal Control FULL NOSE DOWN 4 Yaw Control RUDDER FULL IN OPPOSITE DIRECTION OF SPIN when rotation stops 5 Yaw Control RUDDER NEU...

Page 56: ...n pitch within flight range 6 Proceed WITH CAUTION treat as if it is fixed propeller If failure results in pitch outside flight range 7 Precautionary Landing EXECUTE CAUTION Selection of too fine a propeller pitch and high throttle settings may result in an engine overspeed Selection of too coarse a propeller pitch may result in the engine being unable to maintain the desired engine speed even at ...

Page 57: ...VIBRATION IS LEAST 7 Precautionary Landing EXECUTE 3 7 3 EFIS System Failure If the EFIS freezes fails or reacts incorrectly in flight 1 Straight and Level Flight MAINTAIN a 2 EFIS Main Switch OFF 3 EFIS Back Up Switch OFF wait for 3 seconds 4 EFIS Main Switch ON 5 EFIS Back Up ON wait for at least 15 seconds for the system to boot 6 EFIS Functionality CONFIRM if EFIS still not functioning correct...

Page 58: ...OFF 1 SECOND BACK ON 2 Lane A VERIFY WARNING LIGHT OFF If Lane A warning light is still on assume alternator failure 3 ECU Backup ON 4 EFIS Backup ON 5 Non Essential Equipment ALL OFF a Lights autopilot secondary EFIS etc 6 EFIS Brightness MINIMUM 7 Radio Communication MINIMUM 8 Land AS SOON AS PRACTICABLE NOTES a No battery charging will occur in this scenario and the main battery must be conserv...

Page 59: ...oltage to nominal battery voltage 12 5 V 1 Lane B CYCLE SWITCH OFF 1 SECOND BACK ON 2 Lane B VERIFY WARNING LIGHT OFF If Lane B warning light is still on assume alternator failure 3 ECU Backup ON 4 EFIS Backup ON 5 Non essential Equipment OFF c Lights autopilot secondary EFIS etc 6 Radio Communication MINIMAL 7 Land AS SOON AS PRACTICABLE NOTES c No battery charging will occur in this scenario and...

Page 60: ...FIS Backup ON 3 Main Battery VERIFY VOLTAGE d 4 Non essential Equipment OFF Lights autopilot secondary EFIS etc 5 Radio Communication MINIMAL 6 Precautionary EXECUTE AS SOON AS POSSIBLE NOTES d Expect systems failure when battery voltage drops below 10 Volt This includes the ECU and fuel pumps which will result in engine failure WARNING The engine can run from the main battery for approximately 30...

Page 61: ...f Sensors The engine sensors for redundancy purposes are powered by Lane A B separately This means that if one of the two lanes fail a subset of the engine sensors will also fail Failure of Lane Resultant Sensor Failure A Coolant Temperature Exhaust Gas Temperature Ambient Temperature Ambient Pressure Throttle Level Position B Oil Temperature Oil Pressure ...

Page 62: ...for a list of equipment affected by a loss of power to the main bus 1 ECU Backup ON 2 EFIS Backup ON 3 Land AS SOON AS POSSIBLE CAUTION Power loss to the main bus will not result in the main fuel pump stopping but the starter motor will become unavailable non operational If the engine is allowed to run dry and stop the engine will have to be restarted via airstream driven propeller rotation windmi...

Page 63: ... 001 X F 3 0 Page 4 0 Revision 3 0 Date 2021 07 14 4 Normal Procedures 4 1 Introduction 4 1 4 2 Speeds for Normal Operation 4 1 4 3 Preflight Inspection 4 2 4 4 Engine Start and Taxi 4 8 4 5 Before Takeoff 4 12 4 6 Take off 4 14 4 7 Flight 4 15 4 8 Landing 4 17 4 9 Special Procedures 4 20 ...

Page 64: ...mum weight of 950 kg 2 095lb SPEED KIAS REMARKS Vx Best Angle of Climb Speed 65 The speed flaps fully retracted which results in the greatest altitude gain over a given horizontal distance VY Best Rate of Climb Speed 75 The speed flaps fully retracted which results in the greatest altitude gain over a given time period VROT Rotation Speed 55 The speed at which the aircraft should be rotated about ...

Page 65: ...y It must also be performed after any incident accident maintenance activity etc Incomplete or careless inspections can result in an accident Carry out the inspection following the instructions on the Inspection Checklist NOTE The word condition in the instructions means a visual inspection of surface for damage deformations scratching chafing corrosion or other damages which may lead to flight sa...

Page 66: ...indshield CHECK CONDITION and cleanliness Doors CHECK CONDITION AND SECURITY Cockpit CHECK FOR LOOSE OBJECTS and secure Fire Extinguisher VERIFY PRESENT VALID Documentation VERIFY PRESENT VALID b 4 3 1 2 Fuselage Surface Condition CHECK CONDITION Wing fuselage Fairing CHECK Empennage Fairing CHECK Antenna e CHECK CONDITION SECURITY Luggage Compartment Door CLOSED LOCKED Static Source if applicable...

Page 67: ...ar Wheel Fairing CHECK CONDITION SECURITY Wheel and Brakes CHECK CONDITION a Wheel Struts CHECK CONDITION CRACKS Chocks REMOVE Flap CHECK SECURITY Flap Hinges Control Horn Pushrod CHECK CONDITION SECURITY Wing Trailing Edge CHECK CONDITION Aileron CHECK SECURITY MOVEMENT Aileron Hinges Control Horn Pushrod CHECK CONDITION SECURITY Wingtip CHECK CONDITION Nav Light CHECK CONDITION Taxi Landing Ligh...

Page 68: ...CK COVER SECURITY Nose Wheel CHECK CONDITION Chocks REMOVE WARNING Physically verify the fuel level before each take off Fuel can be visibly seen through the filler cap just covering the total bottom of the fuel tank with 30 litres present NOTES a DO NOT fill the coolant level to the max mark on the overflow bottle mounted to the firewall Its best practice to have the fluid level just above the mi...

Page 69: ...eron Hinges Control Horn Pushrod CHECK CONDITION SECURITY Wing Trailing Edge CHECK CONDITION Flap CHECK SECURITY Flap Hinges Control Horn Pushrod CHECK CONDITION SECURITY Wheel Fairing CHECK CONDITION SECURITY Wheel and Brakes CHECK CONDITION a Wheel Struts CHECK CONDITION CRACKS Chocks REMOVE NOTES a Fluid Leaks brake pad and disc condition tyre condition tyre inflation See 4 3 1 7 Tyre Pressure ...

Page 70: ...essure Visual Inspection The tyres must be visually inspected prior to every flight It is not necessary to check the pressure of the tyre with a gauge it is sufficient to visually inspect the tyre Correct Inflation Underinflation NOTE Pay specific attention to the following in order to decern satisfactory inflation Outmost trendlines Sidewall deflection ...

Page 71: ...C POH 001 X F 3 0 Page 4 8 Revision 3 0 Date 2021 07 14 4 4 Engine Start and Taxi 4 4 1 Before Engine Start 1 Preflight Inspection COMPLETE 2 Emergency Equipment ON BOARD 3 Passenger Briefing COMPLETE 4 Seats CORRECTLY ADJUSTED 5 Harnesses SECURE 6 Park Brake ON 7 Circuit Breakers IN ...

Page 72: ...11 Throttle SET SEE GRAPH BELOW FOR SETTING 12 Propeller AREA CLEAR 13 Starter ENGAGE MAX 10 SECONDS 14 Oil Pressure CHECK CORRECT WITHIN 10 SECONDS 15 Throttle 2500 RPM 16 Lane Lights VERIFY OFF 17 Alternator B CHECK ONLINE a 18 Avionics Switch ON 19 Oil Temperature 2500 RPM until oil temperature is 50 C 122 F b NOTE a Main bus voltage should move up from 12 5V to above 13V when the engine RPM is...

Page 73: ...r can be activated for a maximum of 10 seconds followed by a 2 minute pause to allow the starter to cool Only increase engine speed 10 seconds after start if the oil pressure is steady above 2 bar 29psi NOTE Since the engine tends to vibrate substantially with low throttle settings on start up start the engine with the throttle set as per the graph above to achieve a throttle RPM of approximately ...

Page 74: ...ting Handbook Normal Procedures Document Number DC POH 001 X F 3 0 Page 4 11 Revision 3 0 Date 2021 07 14 4 4 3 Taxi 1 Flaps UP 2 Brakes OFF 3 Control INTO WIND OR NEUTRAL 4 Power AS REQUIRED 5 Brakes VERIFY OPERATION AT START OF TAXI ...

Page 75: ...N ON AUX OFF CHECK FUEL PRESSURE 7 Aux Fuel Pump AUX ON MAIN OFF CHECK FUEL PRESSURE 8 Fuel Pumps BOTH ON MAIN AUX 9 Boost Pump ON 10 Propeller CHECK VP FUNCTIONALITY b 11 Engine RPM 2500 RPM 12 Trim SET NEUTRAL 13 Flaps SET STAGE 1 TAKEOFF 14 Controls FREE FULL CORRECT SENSE 15 Fuel Quantity VERIFY SUFFICIENT FOR PLANNED FLIGHT 16 Circuit Breakers ALL IN 17 Switches CHECK AND SET AS REQUIRED 18 I...

Page 76: ...en switch back on Wait until the lane warning light extinguishes 5 sec before proceeding to the next lane check No more than 250rpm increase decrease during check b Propeller VP Functionality Check 1 Set Propeller Controller to MAN Manual 2 Adjust pitch coarse 500 rpm 3 Adjust pitch fine 500 rpm 4 Adjust pitch coarse 500 rpm 5 Set propeller controller to AUTO 6 Confirm rpm return to 4 000 rpm ...

Page 77: ...Y TO STOP WHEEL SPIN 8 Flaps UP MIN 65 KIAS MIN ALT 300FT 9 Trim AS REQUIRED 10 Power AS REQUIRED 11 Climb COMMENCE WARNING Take off is prohibited if The engine is running rough or intermittently The engine parameters instrument indications are outside operational limits The crosswind component exceeds permitted limits 15 knots CAUTION Ensure that engine oil temperature is above 50 C prior to take...

Page 78: ...ine Parameters VERIFY PRESSURES TEMPERATURES 4 7 2 Cruise 1 Airspeed 108 145 KIAS 2 AUX Fuel Pump OFF 3 Boost Pump OFF 4 Throttle AS REQUIRED 5 Trim AS REQUIRED 6 Fuel SWITCH EVERY HOUR BOOST PUMP ON DURING SWITCH CAUTION If the cylinder head temperature or oil temperature approach their limits reduce the climb angle to increase airspeed and thus fulfil the limits NOTE It is best practice to limit...

Page 79: ...ber DC POH 001 X F 3 0 Page 4 16 Revision 3 0 Date 2021 07 14 4 7 3 Decent 1 ATIS Weather CHECKED 2 Altimeter SET 3 Fuel Selector FULLEST TANK BOOST PUMP ON DURING SWITCH 4 Lights AS REQUIRED 5 Seatbelts CHECKED 6 Approach Brief COMPLETE 7 Throttle AS REQUIRED 8 Trim AS REQUIRED ...

Page 80: ...1 Airspeed 70 75 KIAS 2 Propeller T O 5 800 RPM 3 Flaps FULL ON FINAL 4 Trim AS REQUIRED 5 Throttle AS REQUIRED a WARNING The fuel tank pickup point is situated at the bottom of the inboard wall In normal operation the dihedral of the wing ensures fuel is always present at the pickup The aircraft should never be subjected to a sustained side slip towards a near empty fuel tank that is being drawn ...

Page 81: ...vision 3 0 Date 2021 07 14 4 8 3 Normal Landing 1 Airspeed 50 ft 70 KIAS 2 Power IDLE IN GROUND EFFECT 3 Flare TO MINIMUM FLIGHT SPEED 4 Touchdown MAINS FIRST HOLD NOSE WHEEL OFF 5 Brakes APPLY AS NEEDED 4 8 4 After Landing Clear of Runway 1 Flaps UP 2 Auxiliary Fuel Pump OFF 3 Landing Light OFF 4 Transponder SET ...

Page 82: ...n landing and shutting off the engine If the ambient temperature is excessively warm and causes the coolant temperature to rise then engine may be shut down prior to the 5 minute mark CAUTION Rapid engine cooling should be avoided during operation This happens especially during decent and taxi i e Low engine RPM scenarios Under normal conditions the engine temperatures stabilize during decent and ...

Page 83: ...m AS NECESSARY 7 Complete circuit for new approach 4 9 2 Short Field Takeoff 1 Runway Length MEASURED a WITHIN AIRCRAFT CAPABILITY 2 Abort Point MARKED 3 Aircraft Weight MINIMISE 4 Runway Position MAXIMUM POSSIBLE LENGTH AHEAD 5 Elevator and Trim NEUTRAL 6 Flaps STAGE 2 7 Park Brake SET FULL 8 Throttle FULL OPEN 9 Engine Parameters VERIFY PRESSURES TEMPERATURES 10 Park Brake RELEASE 11 Rotate 50 K...

Page 84: ...MAINS FIRST 7 Braking HEAVY If runway overrun is possible 8 Ignition Lanes OFF MINIMISE PROPELLER GEARBOX DAMAGE 4 9 4 Soft Field Landing 1 Crew SECURE 2 Flaps FULL 3 Approach FLAT UNDER POWER 4 Approach Speed 70 75 KIAS 5 Flare ABOVE THRESHOLD 6 Power IDLE 7 Hold Off IN GROUND EFFECT 0 5M 2FT ABOVE RUNWAY 8 Speed 55 KIAS 9 Main Wheels TOUCH BEFORE STALL 10 Nose Wheel HOLD OFF WITH FULL ELEVATOR N...

Page 85: ...0 Date 2021 07 14 4 9 5 Soft Field Takeoff 1 Aircraft Weight MINIMISE 2 Elevator Trim NEUTRAL 3 Flaps STAGE 2 4 Propeller T O 5 800RPM 5 Parking Brake SET FULL 6 Throttle FULL OPEN 7 Engine Parameters VERIFY PRESSURES TEMPERATURES 8 Parking Brake RELEASE 9 Elevator FULL BACK UNTIL NOSE WHEEL JUST LIFTS 10 Unstuck 61 KIAS ...

Page 86: ... Landing 1 Approach Procedure NORMAL 2 Approach UNDER POWER 3 Final Approach LONG 4 Rudder INTO CROSSWIND 5 Flare OVER THRESHOLD 6 Roll Angle LEVEL 7 Rudder APPLY OPPOSITE 8 Direction ALIGN WITH RUNWAY 9 Main Gear TOUCH DOWN 10 Nose Wheel HOLD OFF 11 Brakes APPLY ONCE NOSE WHEEL ON THE GROUND NOTES a As the aircraft accelerates the pilot must reduce aileron input to avoid the wing hitting the grou...

Page 87: ... Document Number DC POH 001 X F 3 0 Page 5 0 Revision 3 0 Date 2021 07 14 5 Performance 5 1 Introduction 5 1 5 2 Takeoff and Landing Distance 5 1 5 3 Rate of Climb 5 2 5 4 Cruise Speeds 5 3 5 5 Fuel Consumption 5 4 5 6 Airspeed Indicator System Calibration 5 5 ...

Page 88: ...erformance in this section is valid for Maximum takeoff weight of 950 kg 2095 lb 5 2 Takeoff and Landing Distance 5 2 1 Takeoff Distances Surface Type Density Altitude Run Distance Distance over 15m 15ft Obstacle Concrete Tar MSL 220 m 720 ft 350 m 1 150 ft Concrete Tar 7 000 300 m 985 ft 480 m 1 575 ft 5 2 2 Landing Distance Surface Type Density Altitude Landing Distance with braking Distance ove...

Page 89: ... 5 2 Revision 3 0 Date 2021 07 14 5 3 Rate of Climb Values relevant for maximum continuous power at 5 500 RPM Altitude Rate of Climb Best Rate of Climb Speed VY ft ISA fpm KIAS 0 800 75 1 000 795 2 000 785 3 000 780 4 000 770 6 000 755 8 000 740 10 000 730 12 000 715 14 000 700 16 000 685 18 000 670 ...

Page 90: ...134 159 128 150 123 145 12000 133 160 128 152 122 147 13000 132 162 127 153 121 148 14000 131 163 126 154 121 149 15000 130 164 126 156 120 151 16000 129 165 125 157 119 152 17000 128 167 125 159 119 154 18000 127 168 124 160 118 155 NOTES a Maximum continuous power b The Rotax 915 iS uses an automatic switching ECO mode which has a significant effect on fuel consumption At lower altitudes ECO mod...

Page 91: ...es 45 4 US gallons Endurance hrs 3 3 3 7 3 9 5 4 5 6 Range c 1 000 ft nm 535 560 730 740 Range 5 000 ft nm 555 580 765 770 Range 10 000 ft nm 580 610 805 810 Long Range Tanks 194 litres 51 2 US gallons Endurance hrs 3 8 4 2 4 5 6 2 6 4 Range c 1 000 ft nm 620 650 840 845 Range 5 000 ft nm 640 670 875 880 Range 10 000 ft nm 670 700 920 930 NOTES Please see previous page for information regarding no...

Page 92: ... 3 0 Page 5 5 Revision 3 0 Date 2021 07 14 5 6 Airspeed Indicator System Calibration IAS knots CAS knots average CAS knots this aircraft 25 28 30 33 35 38 40 44 45 45 50 50 55 55 60 60 65 65 70 70 75 75 80 80 85 85 90 90 95 95 100 100 105 105 110 110 115 115 120 120 125 125 130 130 135 135 ...

Page 93: ...0 Page 6 0 Revision 3 0 Date 2021 07 14 6 Weight and Balance 6 1 Introduction 6 1 6 2 Installed Equipment List 6 1 6 3 Centre of Gravity Arms 6 2 6 4 CG Envelope 6 3 6 5 Determination of CG 6 4 6 6 Determination of Empty CG 6 6 6 7 CG Determination Example 6 7 6 8 Blank CG Form and Graph for Use 6 8 ...

Page 94: ...ation of the aircraft 6 2 Installed Equipment List Type Equipment Item Standard Garmin G3X GDU460 Glass Cockpit Garmin GTX35 Transponder Garmin GTR200 Radio Garmin GFC500 Autopilot 3Ah IBBS Backup Battery Electric Flap Controller Electric Elevator Trim System Magnetic Compass Airmaster AP430CTF WWR72B Propeller 5V USB Charge Port 12V Power Port Optional Garmin G5 Certified Electronic Flight Instru...

Page 95: ...d to at all times NOTE GC range is 1847mm 6 060 ft to 2043 mm 6 703 ft aft of the reference datum 18 to 33 of MAC The leading edge of the wing at MAC is 1613 mm 5 292 ft aft of the reference datum The MAC is 1302 mm 4 272 ft 2043 Max AFT CG 1847 Max FWD CG 464 NW 1800 Fuel 1902 Front Seats 2236 Main Undercarriage 2948 Rear Seats 3288 Luggage 3288 Luggage Extension Datum 52mm AFT OF FRONT FACE OF E...

Page 96: ...age 6 3 Revision 3 0 Date 2021 07 14 6 4 CG Envelope 400 500 600 700 800 900 1000 16 18 20 22 24 26 28 30 32 34 Aircraft Mass kg Percentage of MAC Allowable CG Envelope 490 840 950 Allowable CG Envelope FLIGHT ALLOWED IN SHADED AREA ONLY 1323 1764 2095 1852 1543 1080 Aircraft Mass lb 1984 2205 882 1102 ...

Page 97: ...g will be required to complete a CG check Item 1 Empty CG Value 2 Blank CG Form 3 Forward CG Check 4 Rear CG Check The principal formula for CG calculation is 𝐶𝐶𝐶𝐶 𝑇𝑇𝑇𝑇𝑇𝑇𝑇𝑇𝑇𝑇 𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀 𝑇𝑇𝑇𝑇𝑇𝑇𝑇𝑇𝑇𝑇 𝑊𝑊𝑊𝑊𝑊𝑊𝑊𝑊ℎ𝑡𝑡 The MAC formulas are 𝑀𝑀𝑀𝑀𝑀𝑀 𝐶𝐶𝐶𝐶 1613𝑚𝑚 100 1302𝑚𝑚𝑚𝑚 𝑜𝑜𝑜𝑜 𝑀𝑀𝑀𝑀𝑀𝑀 𝐶𝐶𝐶𝐶 5 292𝑓𝑓𝑓𝑓 100 4 272𝑓𝑓𝑓𝑓 WARNING For each flight the most forward CG full take off fuel and the most rearward CG landing...

Page 98: ...te 2021 07 14 The aircrafts empty CG is determined in a conventional manner by weighing the aircraft whilst it is standing level Refer to the Maintenance Manual for more Maximum all up weight MAUW 950kg 2 095lb Maximum useful load example 𝑊𝑊𝑚𝑚𝑚𝑚𝑚𝑚 𝑢𝑢𝑢𝑢𝑢𝑢𝑢𝑢𝑢𝑢𝑢𝑢 𝑊𝑊𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀 𝑊𝑊𝐸𝐸 950𝑘𝑘𝑘𝑘 2 095𝑙𝑙𝑙𝑙 500𝑘𝑘𝑘𝑘 1 102𝑙𝑙𝑙𝑙 450𝑘𝑘𝑘𝑘 992lb ...

Page 99: ... Page 6 6 Revision 3 0 Date 2021 07 14 6 6 Determination of Empty CG ITEM WEIGHT kg lb ARM mm ft MOMENT weight x arm kg mm lb ft Aircraft Empty CG Right Main Wheel WR LR 2 236 7 336 Left Main Wheel WL LL 2 236 7 336 Nose Wheel WN LN 464 1 522 Totals Empty weight WE Aircraft moment M0 Empty CG CG mm ft ...

Page 100: ...CG Determination Example Weight kg lb Arm mm ft Moment weight x arm kg mm lb ft Crew Front 2x 85kg 170kg 1 902 6 240 323340 Passengers Rear 0kg 2 948 9 672 0 Baggage 35kg 3 288 10 787 115080 Baggage Ext 0kg 3 762 12 342 180000 Fuel 100kg 1 800 5 906 936500 AC Empty 500kg 1 873 6 145 323340 Totals WT 805kg MT 1554920 CG 1931 6 mm CG 24 5 MAC X ...

Page 101: ...01 X F 3 0 Page 6 8 Revision 3 0 Date 2021 07 14 6 8 Blank CG Form and Graph for Use Weight kg lb Arm mm ft Moment weight x arm kg mm lb ft Crew Front 1 902 6 240 Passengers Rear 2 948 9 672 Baggage 3 288 10 787 Baggage Ext 3 762 12 342 Fuel 1 800 5 906 AC Empty CG Totals WT MT CG mm CG MAC ...

Page 102: ...umber DC POH 001 X F 3 0 Page 6 9 Revision 3 0 Date 2021 07 14 400 500 600 700 800 900 1000 16 18 20 22 24 26 28 30 32 34 Aircraft Mass kg Percentage of MAC Allowable CG Envelope 490 840 950 Allowable CG Envelope 1323 1764 2095 1852 1543 1080 Aircraft Mass lb 1984 2205 882 1102 ...

Page 103: ...r 7 9 7 4 Landing Gear 7 13 7 5 Safety Harness and Seats 7 13 7 6 Baggage Compartment 7 14 7 7 Canopy 7 14 7 8 Pitot and Static Systems 7 15 7 9 Cockpit Layout 7 16 7 10 Instruments and Avionics 7 18 7 11 Minimum Instruments and Equipment Required for Flight 7 22 7 12 Engine 7 23 7 13 Cooling System 7 24 7 14 Electric System 7 25 7 15 Fuel System 7 28 7 16 Lubrication System 7 33 7 17 Autopilot Sy...

Page 104: ...ssed aluminium alloy skins riveted to stiffeners Construction is of 6061 T6 aluminium alloy sheet metal riveted to angles of the same material with high quality blind rivets This high strength aluminium alloy construction provided long life and low maintenance costs thanks to its durability and corrosion resistance characteristics The wing has a high lift airfoil NACA 2414 and is equipped with sem...

Page 105: ...ith dual control sticks which manipulate two of the three control axes pitch elevator and roll aileron The stick has the following button allocations 7 2 2 Rudder Pedals The aircraft is fitted with dual rudder pedals which control the rudder and the nose wheel for yaw control in flight and directional control while on the ground Button Function 1 Trim down 2 Autopilot control 3 Trim up 4 Not alloc...

Page 106: ...is via the lever located on the cabins centre console 7 2 3 2 Toe Brakes A differential foot controller braking system may also be fitted as an option In such case each brake calliper is separately actuated by way of two master brake cylinders fitted to each pedal with the right pedal actuating the right calliper and left pedal the left calliper 7 2 3 3 Park Brake The park brake is typically an in...

Page 107: ...stems Document Number DC POH 001 X F 3 0 Page 7 4 Revision 3 0 Date 2021 07 14 7 2 3 4 Brake System Diagram 7 2 4 Throttle Lever The aircraft makes use of a single lever FADEC Full Authority Digital Engine Control power delivery system Refer to 7 9 Cockpit Layout ...

Page 108: ...ment panel front of centre console Refer to in 7 9 Cockpit Layout for the location of the selector An additional knob must be activated to move the selector through a detent to the OFF position This prevents accidental closure of the valve OFF position 7 2 6 Ballistic parachute if fitted The red coloured activation lever is located at the bottom centre of the instrument panel The accidental operat...

Page 109: ... connected to power ON Engage starter motor START EFIS Switch power main bus to EFIS system on off UP ON DOWN OFF EFIS BKUP Connects EFIS to EFIS back up battery MAIN PUMP Switch main fuel pump on off AUX PUMP Switch auxiliary fuel pump on off LAND Switch landing lights on off TAXI Switch taxi lights on off NAV Select position navigation lights STROBE Select anti collision strobe lights AVIONICS S...

Page 110: ...rim servo is powered by the main bus though a circuit breaker 7 2 10 Flap Control Wing flaps are electrically controlled by a four position rotary knob or a four pushbutton sector located on the instrument panel Each selector position corresponds to the following flap deflection The flap system makes use of an interconnected torque tube with a servo in the cabin centre console Bar a linkage failur...

Page 111: ...ument Number DC POH 001 X F 3 0 Page 7 8 Revision 3 0 Date 2021 07 14 7 2 11 Cabin Heat Heated air warmed by the heat exchanger with the engine exhaust can be selected via a selection knob located on the instrument panel The system can be activated by pulling out the knob ...

Page 112: ... WWR72B propeller which has variable pitch and constant speed capabilities Power to the propeller propeller controller is provided via the main bust and activated by a switch labelled PROP located on the instrument panel 7 3 2 Pilot Controls Propeller PROPELLER CONTROL SELECTOR KNOB AUTOMATIC MANUAL SELECTOR SWITCH FEATHER ENGAGE SWITCH FEATHER INDICATOR LIGHT COARSE INDICATOR LIGHT FINE INDICATOR...

Page 113: ...control over the propeller pitch allowing the propeller to become a more traditional in flight variable pitch propeller Propeller control selector the blue rotary knob allows the pilot to change between pre set propeller settings This knob has no effect when manual MAN is selected on the automatic manual selector switch These pre set setpoints are o T O Use for take off and landing o CLIMB Use for...

Page 114: ...itch down moves the propeller in the coarse direction The coarse indicator light should be illuminated orange in this operation o With the automatic manual switch set to AUTO and the propeller control selector knob selected to HOLD the switch manual propeller control is used to set a pilot selected propeller governing speed Actuate the switch to change the propeller pitch in the direction desired ...

Page 115: ...ge Pitch decreasing Orange Flashing No speed signal Green Fine pitch limit Green Flashing Pitch motor engaged at fine pitch limit Red Over current while pitch decreasing COARSE Orange Pitch increasing Green Coarse pitch limit Green Flashing Pitch motor engaged at coarse pitch limit Red Over current while pitch increasing FEATHER Orange Pitch Increasing in Feather Green Feather pitch limit Green Fl...

Page 116: ...spring section 7 5 Safety Harness and Seats The aircraft features side by side seating Four point safety belts are provided for each seat Seats can be adjusted forwards and backwards with forward movement also leading to the seat being elevated CAUTION Ensure that the seat s is securely locked into position after adjustment NOTE Prior to each flight ensure that the seat belts are firmly secured to...

Page 117: ...e baggage extension is designed to carry up to 3kg 6 6 lb It is the pilot s obligation to ensure that the aircraft CG is within the permissible limits and that all baggage must be properly secured 7 7 Canopy The aircraft is equipped with two gullwing doors External access to the cabin is form either side Operating levers for the door latching mechanisms are provided on the inside and outside of th...

Page 118: ... second hole for the measurement of angle of attack The static port is located behind the instrument panel Keep the pitot head clean to ensure proper functioning of the system Ensure thar the pitot tube cover is removed prior to every flight and that it is replaced after every flight An example of a pitot static system is below NOTE Please note that this drawing is representative of a pitot and st...

Page 119: ...7 9 Cockpit Layout The basic cockpit layout is the same for all Sling 4 TSi aircraft notwithstanding that instrumentation may differ substantially All airplanes contain the minimum instrumentation but particular airplanes may contain substantial additional instrumentation The basic cockpit layout is configured as in the diagram with key below ...

Page 120: ...anel 6 Rear seat s 14 Rudder pedals 7 Rear headphone connection sockets 15 Fire extinguisher 8 Luggage compartment 16 Rear air vents NOTE If differential footbrakes are fitted the hand operated actuator on the centre console will be absent Seats and pedals are adjustable There is a unlocking leaver that allows the movement of the seat and a locking setting bolt that allows movement of the pedals A...

Page 121: ...containing the required minimum instrumentation together with typical back up and additional instrumentation supplied with the aircraft The instrument panel in any particular aircraft may differ from that illustrated below as choice of instruments and layout is decided by the customer It is the responsibility of the pilot to ensure that they are familiar with the instrumentation in the aircraft it...

Page 122: ...ane B switches 18 GMC 307 Control unit 6 12 V Power port socket 19 Cabin heat fan speed knob 7 Garmin GDU 460 EFIS 20 21 22 Ballistic rescue parachute activation handle Cabin heat temperature control knob Flap position control knob rotary 8 EFIS warning light 9 Propeller controller 10 Garmin G5 23 Propeller control switch 11 Radio GTR 200 24 Switches EFIS EFIS back up battery propeller avionics ta...

Page 123: ...clude but not limited to Feature Comment Speeds ASI IAS and TAS Ground Speed Altitude ALT Height Above Ground Dependent on loaded maps VSI Vertical Speed Indicator Compass Attitude Indicator Turn Coordinator G Meter Time Clock and Stopwatch Flight Time Recorder Autopilot If servos are fitted GPS Navigation Comprehensive mapping and navigation software and data including GPS and GLS GPS Landing Sys...

Page 124: ...ck up switches are kept on during operation of the aircraft This will ensure that if there is a power failure on the main bus the EFIS will automatically change over to the battery NOTE Use and set up of the EFIS and its features extensively described in documentation supplied with the unit and will not be dealt with in this handbook The autopilot functionality is incorporated in the EFIS WARNING ...

Page 125: ...ator 6 Oil Temperature Indicator 7 Cylinder Head Temperature Indicator 8 Outside Air Temperature Indicator 9 Tachometer 10 Chronometer 11 First Aid Kit Compliant with Local Regulations not required in US 12 Fire Extinguisher WARNING Installed equipment may include GPS and other advanced flight and navigational aids Such equipment may not be used as the sole information source for purposes of navig...

Page 126: ...ylinders The lubrication system can be described as sump forced lubrication and the ignition makes use of dual contactless capacitor discharge magneto type ignition system that is ECU controlled The engine is fitted with an electric starter motor two AC alternators and two electric fuel pumps The propeller is driven through a reduction gearbox of ratio 2 52 and features an integrated shock absorbe...

Page 127: ...tank is closed by a pressure cap When the coolant temperature rises there is a pressure increase and coolant is forced into the overflow bottle mounted on the firewall When the coolant cools down the coolant in the overflow bottle is drawn back into the expansion tank Conventional ethylene glycol coolant and distilled water mixture 1 1 Please refer to the latest edition of the engine manufacturers...

Page 128: ...Sling 4 TSi Section 7 Pilot Operating Handbook Aircraft and Systems Document Number DC POH 001 X F 3 0 Page 7 25 Revision 3 0 Date 2021 07 14 7 14 Electric System 7 14 1 Broad Overview Diagram ...

Page 129: ...ternator is installed the output is used to charge the battery through a breaker switch 7 14 3 Main Battery The 12V 17 Ah main battery is mounted on the engine side of the firewall 7 14 4 Main Bus When power to the main bus is unavailable fails the following equipment will become non operational Item 1 Autopilot including servos 2 Flaps 3 Radio 4 Transponder 5 Cabin Lights 6 Strobe navigation land...

Page 130: ...nd are two separate ignition circuits 7 14 8 Electrical Equipment Switches Lever type switches are used and are ON in the UP position and OFF in the DOWN position There are exceptions to this for instance the taxi light switch is a three way switch i e ON WIG WAG OFF 7 14 9 Circuit Breakers Circuit breakers are push to reset i e push in for restoring supplying electrical power to their correspondi...

Page 131: ...er screen is fitted to each fuel pick up The fuel selector valve is mounted on the lower centre instrument panel refer to cockpit layout paragraph 7 9 Fuel feed is through the facet posi flow electrical boost pump and Rotax fuel pump The facet posi flow has a parallel in line check valve and is activated with one signal switch mounted on the instrument panel The Rotax fuel pump has a parallel inst...

Page 132: ...Sling 4 TSi Section 7 Pilot Operating Handbook Aircraft and Systems Document Number DC POH 001 X F 3 0 Page 7 29 Revision 3 0 Date 2021 07 14 A diagram of the fuel system is as follows with a key ...

Page 133: ...uel pressure sensor S M12x1 5 AN6 male G Bypass pressure valve T 90o male 3 8 barb hose H Rotax fuel filter U 90o hose end swivel push on AN6 5 BARB 8mm I Jet T piece V Facet posi flow electrical fuel pump J Rotax 915 iS W Check valve in line barbed 8mm K AN6 90o bulkhead 3 8 fuel hose SAE J30R7 L AN6 straight female barb 3 8 fuel hose SAE J30R9 M Male to female AN6 90o 5 16 fuel hose SAE J30R9 WA...

Page 134: ...eme conditions there may be a decrease in fuel pressure to below the minimum permissible pressure In such circumstances BOTH fuel pumps should be selected In the highly unlikely event that a low fuel pressure warning persists with the use of both fuel pumps the throttle setting or propeller speed should be reduced to a level which results in the fuel pressure returning to within range Should the a...

Page 135: ...ps The main and auxiliary fuel pumps are powered via the EMS ECU As long as power is available to the EMS ECU both fuel pumps can be selected operated irrespective of the master switch status WARNING At least one fuel pump must be operational at all times during flight for the engine to be operational with no pump operational engine stoppage will occur due to fuel starvation ...

Page 136: ...elivers oil from the oil reservoir through an oil cooler and oil filter to points of lubrication Surplus oil emerging from the points of lubrication gather at the bottom of the crankcase from where it is forced back to the oil reservoir by piston blow by gasses Oil temperature is sensed by a sensor located on the crankcase The lubrication circuit is vented at the oil reservoir The oil reservoir is...

Page 137: ...a switch labelled AUTOPILOT located at the instrument panel This switch must be on for the autopilot to have any effect The autopilot can be engaged by The autopilot engage disengage button on the control sticks s Via the EFIS screen interface The autopilot can be disengaged by The autopilot engage disengage button on the control sticks s Via the EFIS screen interface A servo reports a slipping cl...

Page 138: ...itch controlling ON WIG WAG OFF Combination navigation position lights red green and white and anti collision lights white are fitted to the wingtips in the standard configuration red left green right A combination position anti collision light white is fitted underneath the vertical stabilizer The white lights on the wingtips and rudder are dual function lights that can either be on continuously ...

Page 139: ...he pilot and front seat passenger These are each operated with an ON OFF switches and are dimmable through the rotary switch knob located aft of the pilot s light Two white touch lights are fitted for the rear cabin These are dimmable through the rotary switch knob located between the two lights Cabin lights are powered from the main bus via a circuit breaker labelled cabin light located on the in...

Page 140: ...ating Handbook Ground Handling Servicing Document Number DC POH 001 X F 3 0 Page 8 0 Revision 3 0 Date 2021 07 14 8 Ground Handling and Servicing 8 1 Introduction 8 1 8 2 Ground Handling 8 1 8 3 Servicing 8 6 8 4 Cleaning and Care 8 8 ...

Page 141: ... does not replace the maintenance manual 8 2 Ground Handling 8 2 1 Taxiing When taxiing it is important to use all controls at their minimum to achieve what is required such as the throttle and brakes Speed must be kept to a minimum during all ground operations Caution must be taken in windy conditions and the following control inputs must be made depending on wind direction originating from Wind ...

Page 142: ...putting pressure on the wing horizontal stabilizer leading edge directly over a rib 8 2 3 Tow Bar The aircraft can be towed by making use of a tow bar that is hooked to the nose wheel of the aircraft The aircraft can be steered by rotating the nose wheel through the tow bar The nose wheel is fully rotated once the pedal control stops have been engaged For installation of the tow bar refer to the S...

Page 143: ...ly inside other suitable spaces with good temperature good ventilation low humidity and dust free When parking for extended for extended periods cover the cockpit canopy and possibly the whole aircraft by means of a suitable tarpaulin When parking the aircraft outside avoid parking for extended periods of time Cover the panel interior with a suitable cover or canopy cover to avoid degradation of t...

Page 144: ...ngs and one under the tail The mooring procedure is as follows 1 Fuel Selector OFF 2 Switches ALL OFF 3 Master OFF 4 Ignition Lanes OFF 5 Control Column SECURE a 6 Air Vents CLOSE 7 Canopy CLOSE AND LOCK 8 Moor THOUGH MOORING EYES b 9 Chocks INSTALL NOTES a Through use of a for example safety harness b Typically rope will be used to connect the aircrafts mooring eye with a mooring eye fastened in ...

Page 145: ... 5 Revision 3 0 Date 2021 07 14 8 2 6 Road Transporting The aircraft may be transported after loading on a suitable aircraft specific trailer or a flatbed with suitable rigging It is necessary to remove the wings before road transport It is suggested that the wings should be securely stored in a cradle of some kind ...

Page 146: ...ved by pushing down on the horizontal stabilizer as described under 8 2 2 Towing By lifting the rear fuselage under a bulkhead the rear fuselage may be raised and then supported under that bulkhead The support should comprise of a large flat surface to avoid damage to the under fuselage skin The winds should also be gently supported to prevent the aircraft from rolling as its weight shifts to the ...

Page 147: ... the latest revision of the applicable a engine propeller manufacturer documentation More detail is supplied in the Sling 4 TSi Maintenance Manual 8 3 3 Aircraft Modifications and Repairs It is recommended that you contact the aircraft manufacturer prior to making any modifications to the aircraft to ensure that the airworthiness of the aircraft is not affected Always use only the original spare p...

Page 148: ...or degreaser Detergents with a wax coating will better preserve the paintwork of the aircraft Oil spots on the aircraft surface except for the canopy may be cleaned with petrol gasoline The canopy may only be cleaned by washing it with a sufficient quantity of lukewarm water and an adequate amount of compatible detergent Use either a soft clean cloth sponger or deerskin Then use suitable dry polis...

Page 149: ... 07 14 9 Supplementary Information 9 1 Introduction 9 1 9 2 Supplement 01 2020 Airplanes Fitted with Long Range Fuel Tanks 9 2 9 3 Supplement 02 2020 Airplanes Fitted with an External Alternator 9 8 9 4 Supplement 01 2021 Airplanes fitted with a Magnum 601 Ballistic Parachute 9 10 9 5 Supplement 02 2021 Aircraft Fitted with a Tow Hook 9 12 ...

Page 150: ...plements necessary to safely and efficiently operate the aircraft when equipped with various common optional extras not supplied with the standard aircraft The supplements included in this manual are Date Supplement No Title of inserted supplement 24 03 2020 01 2020 Long Range Fuel Tanks 11 05 2020 02 2020 External Alternators 07 07 2021 01 2021 Stratos 07 Ballistic Parachute 07 07 2021 02 2021 To...

Page 151: ...es and information not addressed in this supplement remain as set out in Sling 4 TSi Pilot Operating Handbook 9 2 1 Introduction The two long range fuel tanks are located inside the leading edge of each outboard wing section Volume of long range tanks 2 x 40 10 57 US gallons litres 80 litres 21 13 US gallons total As in the main tanks each tank is equipped with a vent outlet A drain valve is locat...

Page 152: ...off valves are on the top of the centre console Both arrangements with shut off valves in the closed position are showing in pictures below 9 2 3 Fuel System Valve Setup Location of shut off valves Standard Brakes Toe Brakes The Facet electric pump is activated by the transfer pump switch on the instrument panel Either long range B tank left or right can supply to the main A tank in use Fuel tank ...

Page 153: ...Information Document Number DC POH 001 X F 3 0 Page 9 4 Revision 3 0 Date 2021 07 14 9 2 4 Example of Shut Off Valve States Different Transfer Options Left B Tank to Right A Tank Right B Tank to Right A Tank Left B Tank to Left A Tank Right B Tank to Left A Tank ...

Page 154: ... moment arm for long range tanks 1 822 mm is added as shown in the table below Weight kg lb Arm mm ft Moment weight x arm kg mm lb ft Crew Front 1 902 6 240 Passengers Rear 2 948 9 672 Baggage 3 288 10 787 Baggage Ext 3 762 12 342 Fuel A Tanks 1 800 5 906 Fuel B Tanks 1 822 5 911 AC Empty CG Totals WT MT CG mm CG MAC NOTE The blank form and graph in paragraph 6 5 are still applicable and should be...

Page 155: ... 6 Long Range Fuel System Diagram Key Long Range Fuel System Key A Left fuel tank H Left L R fuel tank B Right fuel tank I Right L R fuel tank C Fuel selector J 90o male to female brass D 90o fuel filter K Straight male 8 mm E 8 mm T Piece L 90o female barb 8 mm F Valve 8 mm fuel hose SAE J30R7 G Electrical fuel pump 8 mm fuel hose SAE J30R7 Return ...

Page 156: ...Sling 4 TSi Section 7 Pilot Operating Handbook Supplementary Information Document Number DC POH 001 X F 3 0 Page 9 7 Revision 3 0 Date 2021 07 14 9 2 7 Long Range Fuel System Diagram ...

Page 157: ...ion SI PAC 001 for Rotax 915 i Series 9 3 1 Operational Parameters The alternating current AC output of the external alternator is routed to its integrated rectifier regulator where it is converted rectified and regulated to provide direct current DC output available to the main battery The external alternators charge output is 14 2 to 14 8 V DC 9 3 2 Operational Instructions The external alternat...

Page 158: ...1 07 14 9 3 3 External Alternator Wiring 9 3 4 Effect on Mass and Balance The CG range mentioned in Section 6 of this document continues to apply and following fitment of the external alternator the empty CG of the aircraft should be measured and appropriately recorded Refer to paragraph 6 5 The external alternator mass is 3 0 kg 6 6 lbs ...

Page 159: ...cally addressed in this supplement remain as set out in the Pilot Operating Handbook This supplement provides information necessary for the operation of an aircraft fitted with a Magnum 901 ballistic parachute The Sling 4 TSi is specifically designed for convenient fitment of the Magnum 901 ballistic parachute recovery system manufactured by Stratos 07 The system is designed to enable the pilot or...

Page 160: ...Limit Speed 3 s Maximum Supported Mass 950 kg or 2095 lb Decent Rate at Maximum Mass 7 m s 9 4 3 Ballistic Parachute Deployment Procedure 1 Speed BELOW 173 kt DEPLOY AS SLOW AS PRACTICABLE 2 Throttle CLOSE 3 Ignition Lanes Magnetos OFF 4 Fuel Pump s OFF BOTH 5 Fuel Selector OFF 6 Harnesses SECURE TIGHT 7 Security ALL LOSE OBJECTS SECURE 8 Parachute DEPLOY PULL ACTIVATION HANDLE before impacting th...

Page 161: ... expected to comply with all safety operating and emergency procedures which would ordinarily be applicable in such circumstances This supplement is intended only to provide abbreviated material to the pilot who is familiar with tugging and towing operations as well as the Sling 4 TSi aircraft type who wishes to understand in what manner the operation of the Sling 4 TSi for tugging and towing oper...

Page 162: ... safely flown by a pilot without a tow rating or experience provided that it is not used for any tug or towing activities 9 5 1 4 Installation of Hook and Release Mechanism The glider tow hook is fitted to an aluminium structure attached to the lower rear fuselage Since the rearward extent of the hook attachment mechanism is forward of the rearmost extent of the rudder there is no change in overal...

Page 163: ...ctivities They should be performed only by experienced persons operating in accordance with clear guidelines and in accordance with good aviation practices Engine and airframe monitoring is especially critical during glider tug and banner tow operations as additional stress is placed upon the aircraft Operate always within the limits applicable to the engine airframe and propeller If this is not p...

Page 164: ...lthough the aerodynamic responses of the aircraft are likely to be similar where other hook engine and propeller combinations are used each pilot flying such a combination is responsible for ensuring that the aircraft performance is sufficient for the operational requirements and that applicable limitations are met at all times It is assumed that at all times pilots and support crew will comply wi...