Sling Aircraft Sling LSA Pilot Operating Handbook Download Page 133

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Sling LSA

Section 7

Pilot Operating Handbook

Ground Handling

Servicing

Document Number: DC-POH-002-X-A-6

Page | 8-4

Revision: 3.0

Date: 2021/04/23

8.2.4

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.

Summary of Contents for Sling LSA

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 23 APRI L 2021 SERI AL NO REGI ST RAT I ON ...

Page 2: ...Airplane Serial Number Date of Construction Registration Airworthiness Category Light Sport Aircraft LSA Issue Date of POH 2021 04 23 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: ... LSA such as a 912 ULS powered Sling LSA are included in a supplement in Section 9 of this handbook 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 although written to accommodate all regions regulations may contain specific references to South African ...

Page 4: ...rformance of a Light Sport Airplane ASTM F2295 Practice for Continued Operational Safety Monitoring of a Light Sport Aircraft ASTM F2972 Specification for Light Sport Aircraft Manufacturer s Quality Assurance System 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 So...

Page 5: ...er operator of an LSA 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 an LSA shall be responsible for notifying the manufacturer of any flight safety issues or significant service difficulty upon discovery The owner operator of an LSA shall be re...

Page 6: ...applicable 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 1 1 All All 2011 04 20 1 2 All All 2012 03 12 1 3 All All 2012 05 10 2 0 All All 2012 06 04 2 1 2 7 2012 09 01 2 2 All All 2012 11 01 2 3 All All 2014 11 10 2 4 2 2 10 2 11 2015 03 30 2 5 1 2 4 6 7 All 201...

Page 7: ... xi Removed 3 0 2 12 Revised 3 0 1 0 Inserted 3 0 2 13 Revised 3 0 1 1 Revised 3 0 2 14 Revised 3 0 1 2 Revised 3 0 2 15 Revised 3 0 1 3 Revised 3 0 2 16 Removed 3 0 1 4 Revised 3 0 2 17 Removed 3 0 1 5 Revised 3 0 3 0 Inserted 3 0 1 6 Revised 3 0 3 1 Revised 3 0 1 7 Revised 3 0 3 2 Revised 3 0 1 8 Revised 3 0 3 3 Revised 3 0 1 9 Revised 3 0 3 4 Revised 3 0 1 10 Revised 3 0 3 5 Revised 3 0 1 11 Re...

Page 8: ...sed 3 0 7 3 Revised 3 0 4 8 Revised 3 0 7 4 Revised 3 0 4 9 Revised 3 0 7 5 Revised 3 0 4 10 Revised 3 0 7 6 Revised 3 0 4 11 Revised 3 0 7 7 Revised 3 0 4 12 Revised 3 0 7 8 Revised 3 0 4 13 Revised 3 0 7 9 Revised 3 0 4 14 Revised 3 0 7 10 Revised 3 0 4 15 Revised 3 0 7 11 Revised 3 0 4 16 Revised 3 0 7 12 Revised 3 0 4 17 Revised 3 0 7 13 Revised 3 0 4 18 Revised 3 0 7 14 Revised 3 0 4 19 Revis...

Page 9: ...moved 3 0 9 16 Revised 3 0 7 32 Removed 3 0 9 17 Revised 3 0 7 33 Removed 3 0 9 18 Revised 3 0 7 34 Removed 3 0 9 19 Revised 3 0 7 35 Removed 3 0 9 20 Revised 3 0 7 36 Removed 3 0 9 21 Revised 3 0 7 37 Removed 3 0 9 22 Revised 3 0 7 38 Removed 3 0 8 0 Inserted 3 0 8 1 Revised 3 0 8 3 Revised 3 0 8 4 Revised 3 0 8 5 Revised 3 0 8 6 Revised 3 0 8 7 Revised 3 0 8 8 Removed 3 0 8 9 Removed 3 0 9 0 Ins...

Page 10: ...Page ix Revision 3 0 Date 2021 04 23 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: ... A 6 Page 1 0 Revision 3 0 Date 2021 04 23 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 LSA Aircraft and Systems 1 5 1 5 Terminology Symbols and Conversion Factors 1 10 1 6 Supporting Documents 1 15 ...

Page 12: ...ll up weight of 600kg 1 320lb The design has been tested against and complies with this standard With only minor modifications to the aircraft and the application of a revised Pilot Operating Handbook the aircraft may be made to comply with the requirements of the EASA European Aviation Safety Agency CS VLA Certification Standard Very Light Aircraft standard having a maximum all up weight of 700 k...

Page 13: ...es 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 or...

Page 14: ... 002 X A 6 Page 1 3 Revision 3 0 Date 2021 04 23 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 821 1495 ...

Page 15: ...Sling LSA Section 1 Pilot Operating Handbook General Information Document Number DC POH 002 X A 6 Page 1 4 Revision 3 0 Date 2021 04 23 DIMENSIONS IN THIS DRAWING ARE IN MILLIMETRES ...

Page 16: ...s ft2 Aspect Ratio 7 04 Taper Ratio 1 375 Dihedral 5 1 4 2 Fuselage Parameter Value Fuselage Length 5 77 m 18ft 11in Overall Length 6 675 m 21ft 11in Overall Width 1 15 m 45 3 in Overall Height 2 5 m 98 4 in 1 4 3 Empennage Parameter Value Horizontal Stabilizer Span 2 825 m 9ft 3in Horizontal Stabilizer Surface Area 0 96 m2 10 33 ft2 Horizontal Stabilizer Angle of Incidence 4 Elevator Surface Area...

Page 17: ...Elevator 30 up down 2 Trim Tab 5 up 20 down 5 Rudder 25 left right 2 Flaps 0o up 32o down 3 1 4 6 Engine Parameter Item Value Manufacturer Bombardier Rotax GmbH Model 912 iS Type 4 cylinder horizontally opposed with an overall displacement of 1352cc mixed cooling fuel injection integrated reduction gearbox with torque damper see 7 11 Engine Maximum Power 73 5 kW 100 hp at 5 800 rpm max 5 minutes 6...

Page 18: ... South Africa One tank integrated in the leading edge of the right wing International US Two tanks integrated in the leading edges of both wings Both Tank s equipped with finger strainers in the pick up line and drain fittings Total Fuel Capacity South Africa 75 L 19 8 US Gallons International US 150 L 39 6 US Gallons Total Useable Fuel Capacity South Africa 73 L 19 3 US Gallons International US 1...

Page 19: ...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 5 litres 3 7 Quarts 7 4 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 heads Coolant Ethylene glycol based...

Page 20: ...aximum Landing Weight 600 kg 1 320 lb Maximum Baggage Weight 15 kg 33 lb Front Luggage Compartment Max Weight 15 kg 33 lb Rear Luggage Compartment Max Weight 15 kg 33 lb 1 4 12 Standard Weights Parameter Value Standard Configuration Empty Weight 370 kg 814 lb Maximum Useful Load 230 kg 506 lb 1 4 13 Specific Loadings Parameter Value Wing Loading MAUW 50 65 kg m2 10 0 lb ft2 Power Loading MAUW 6 00...

Page 21: ...FIS Electronic 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 ...

Page 22: ...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 spee...

Page 23: ...e 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 fro...

Page 24: ... is the forward flat propeller mounting flange on the Rotax engine 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 ...

Page 25: ...tors 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: ...2 ULS engine a The latest revision of the Operators Manual for Rotax Engine Type 912 Series ref no OM 912 b Latest Revision of the Rotax service instruction SI 912 016 entitled Selection of Suitable Operating Fluids 3 Garmin G3X a The latest revision Operators Manual for the Garmin G3X 4 COM Radio transponder and any other relevant equipment fitted to the aircraft a The latest revision of the rele...

Page 27: ...ngs 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 Lim...

Page 28: ...ss in smooth air and then only with caution VA Manoeuvring Speed 91 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 118 Never exceed this speed in level flight at MAUW VS Stall Speed 45 The aircraft wi...

Page 29: ...NG KIAS SIGNIFICANCE White Arc 40 85 Flap Operating Range Lower Limit VS0 At MAUW Upper Limit Vfe Max flap operation speed Green Arc 45 105 Normal Operating Range Lower Limit VS At MAUW max forward CG Upper Limit VNO Max Structural Speed Yellow Arc 105 135 Manoeuvres must be conducted with caution and only in smooth air Red Line 135 Maximum speed for all operations ...

Page 30: ... 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 leve...

Page 31: ...ling Item Value Service Ceiling 12 000 ft 3658 m 2 7 Load Factors Item Value Maximum positive limit load factor 4g Maximum negative limit load factor 2g Maximum positive load factor with flap 2g Maximum negative load factor with flap 1g 2 8 Weights Item Value Maximum take off weight MAUW 600kg 1 320 lb Maximum landing weight 600kg 1 320 lb Maximum total baggage weight 15kg 33 lb Front luggage comp...

Page 32: ... Reference Longitudinal Levelling Upper surface of canopy sliders on cockpit side skins with canopy open Reference Transverse Levelling Upper surface of centre spar cap under pilot and passenger seats Forward Limit 1 635 m 5 364 ft 20 MAC aft of datum Aft Rear Limit 1 808 m 5 931 ft 33 MAC aft of datum WARNING It is the pilot s responsibility to ensure that the airplane is properly loaded Refer to...

Page 33: ...not exceeding 60 Lazy Eights Chandelles Stalls not including whip stalls 2 11 Flight Crew Minimum crew for flight is one pilot seated on the left side 2 12 Passengers Only one passenger is allowed on board the aircraft in addition to the pilot WARNING Aerobatics and intentional spins are prohibited WARNING Limit load factor would be exceeded by moving flight controls abruptly to their limits at a ...

Page 34: ... 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 LSA fitted with the following additional equipment may also be operated a...

Page 35: ...y requirements are met along with the installation of the required systems and instrumentation for IFR and IMC flight However in the United States of America all flights VFR and IFR are to be conducted in VMC as per the applicable LSA standards WARNING Notwithstanding that installed equipment may include GPS and other advanced flight and navigational aids such equipment may not be used as the sole...

Page 36: ... 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 120 F Start Minimum Oil Temperature 20 C 13 F In Flight Maximum 60 C 140 F Alternative For Sling LSA fitted with the 912 ULS engine please refer to the applicable supplement at the end of this ...

Page 37: ...35 C 275 F Normal 75 to 110 C 167 to 230 F 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 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 3500 rpm Fuel Pressure Minimum 2 8 bar ...

Page 38: ... 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 prohibited...

Page 39: ...l Standard Sling LSA excl USA 2 17 2 Visible to Pilot and Passenger Standard Sling LSA excl USA OPERATE UNDER VMC ONLY MAXIMUM PERMISSIBLE AIRSPEED 135 KIAS MAXIMUM PERMISSIBLE RPM 5 800 RPM FOR 5 MINUTES MAXIMUM CONTINUOUS RPM 5 500 MAXIMUM PERMISSIBLE MASS 600 KG 1 320 LB WARNING NON CERTIFIED AIRCRAFT THIS AIRCRAFT IS NOT REQUIRED TO COMPLY WITH ALL THE REGULATIONS FOR TYPE CERTIFIED AIRCRAFT Y...

Page 40: ...lot Operating Handbook Limitations Document Number DC POH 002 X A 6 Page 2 13 Revision 3 0 Date 2021 04 23 USA Sling LSA 2 17 3 Adjacent to Fuel Filler Cap Standard Sling LSA excl USA USA Sling LSA s AVGAS OR MOGAS 75 LITRES ...

Page 41: ... Sling LSA excl USA 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 USA Sling LSA NO STEP ZU CONSTRUCTOR SLING AIRCRAFT MODEL SLING LSA SERIAL NO ENGINE ROTAX HP MANUFACTURED AIRCRAFT IDENTIFICATION i e N123SL BUILDER SLING AIRCRAFT PTY LTD MODE...

Page 42: ...04 23 2 17 6 Other Placards The aircraft must be placarded to show the identity of All Fuses Circuit Breakers Magneto Ignition switches Choke 912 ULS only 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 43: ... X A 6 Page 3 0 Revision 3 0 Date 2021 04 23 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 44: ...ld 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 Analyse the situation as a whole keeping an open mind 3 PROCEDURES Apply applicable procedures 4 COMMUNICATE Inform ATC local traffic of the situation if...

Page 45: ...21 04 23 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 050m 10 000ft per 305m 1 000ft decent Glide ratio 10 1 Speed for in flight engine start 72 Recommended speed ...

Page 46: ...Magnetos OFF BOTH 4 Master OFF 5 Fuel Selector OFF 6 Fuel Pump s OFF BOTH 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 Pump s OFF BOTH 5 Fuel Selector OFF before touch down 6 Ignition Lanes Magnetos OFF BOTH 7 Master OFF WARNING Flaps and elevator trim will not operate with the master switch off and they are powered ...

Page 47: ...Land AS SOON AS POSSIBLE If engine should fail to restart 6 Land FORCED LANDING 3 3 4 Air Start Alternative for aircraft equipped with a Rotax 912 ULS 1 ECU Backup Switch ON 2 Fuel Pumps ON BOTH 3 Fuel Selector CHANGE UNLESS 2ND TANK DRY 4 Throttle CHECK MOVEMENT 5 Throttle MIDDLE POSITION 6 Master ON 7 Ignition Lanes ON BOTH 8 Starter ENGAGE NOTE An air start is possible with the propeller windmi...

Page 48: ...p Switch ON 4 Fuel Quantity CHECK 5 Fuel Selector CHANGE UNLESS 2ND TANK DRY 6 Fuel Pumps ON BOTH 7 Oil Pressure CHECK 8 Oil Temperature CHECK 9 Coolant Temperature CHECK 10 EGT Temperature CHECK If engine continues to run rough 11 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 Pump s ON BOTH If fuel pressure remains low 4 T...

Page 49: ...23 3 3 7 Low Oil Pressure 1 Oil Temperature CHECK MAX 130 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 50: ...MPT AS TIME PERMITS a If engine fails to restart 5 Fuel Pump s OFF BOTH 6 Fuel Selector OFF 7 Throttle CLOSED 8 Flaps FULL PRIOR TO TOUCHDOWN 9 Communication REPORT IF TIME PERMITS 10 Passenger BRIEF Immediately Before Touchdown 11 Ignition Lanes OFF BOTH 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 alti...

Page 51: ...ing Area INSPECT AS PER PROCEDURE 5 Flaps FULL ON FINAL APPROACH 6 Airspeed 65 KIAS 7 Brakes APPLY when aircraft is under control 8 Ignition Lanes OFF BOTH 9 Fuel Selector OFF 10 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 SLOWEST PRACTI...

Page 52: ...ed 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 LSA 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 53: ...Start 1 Starter RELEASE 2 Fuel Selector CLOSE 3 Fuel Pumps OFF BOTH 4 Throttle IDLE 5 Ignition Lanes OFF BOTH 6 Master OFF 7 Fire Extinguisher RETRIEVE 8 Exit Aircraft 9 Extinguish Fire 3 5 2 Engine Fire on Ground 1 Cabin Heat CLOSE 2 Fuel Selector CLOSE 3 Fuel Pumps OFF BOTH 4 Throttle IDLE 5 Ignition Lanes OFF BOTH 6 Master OFF 7 Fire Extinguisher RETRIEVE 8 Exit Aircraft 9 Extinguish Fire ...

Page 54: ... APPLY UNTIL STOP 4 Fuel Selector CLOSE 5 Fuel Pumps OFF BOTH 6 Ignition Lanes OFF BOTH 7 Master OFF 8 Fire Extinguisher RETRIEVE 9 Exit Aircraft 10 Extinguish Fire 3 5 4 Engine Fire in Flight 1 Cabin Heat CLOSE 2 Cabin Air Vent OPEN 3 Throttle IDLE 4 Fuel Pumps OFF BOTH 5 Ignition Lanes OFF BOTH 6 Master OFF AFTER FLAP DEPLOYMENT 7 Fuel Selector CLOSE 8 Airspeed INCREASE TO VNE 135kt IAS 9 Forced...

Page 55: ... 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 switch...

Page 56: ...l 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 NEUTR...

Page 57: ...EAST 6 Precautionary Landing EXECUTE 3 7 2 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 correctly 7 Land AS S...

Page 58: ... V 1 Lane A CYCLE SWITCH 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 mai...

Page 59: ...tage 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 t...

Page 60: ...S 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 m...

Page 61: ...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: ...r 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 windmill...

Page 63: ... 002 X A 6 Page 4 0 Revision 3 0 Date 2021 04 23 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 11 4 6 Take off 4 12 4 7 Flight 4 13 4 8 Landing 4 15 4 9 Special Procedures 4 18 ...

Page 64: ...of 600kg 1 320lb 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 72 The speed flaps fully retracted which results in the greatest altitude gain over a given time period Normal Climb Out 75 VROT Rotation Speed 45 The speed at which the aircraft should be rotate...

Page 65: ...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 safe...

Page 66: ...ON a Canopy and Windshield CHECK CONDITION and cleanliness 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 CHECK CONDITION N...

Page 67: ... 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 Light ...

Page 68: ... 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 min ...

Page 69: ...on 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 Vi...

Page 70: ...sure 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 002 X A 6 Page 4 8 Revision 3 0 Date 2021 04 23 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: ...D 9 ECU Backup Switch OFF 10 Throttle SET 50 11 Propeller AREA CLEAR 12 Starter ENGAGE MAX 10 SECONDS 13 Oil Pressure CHECK CORRECT WITHIN 10 SECONDS 14 Throttle 2500 RPM 15 Ignition Lane Lights VERIFY OFF 16 Alternator B CHECK ONLINE a 17 Avionics Switch ON 18 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 eng...

Page 73: ...RED 5 Brakes VERIFY OPERATION AT START OF TAXI CAUTION The starter 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 To avoid shock loading start the engine with the throttle to approximately 10 Wait 3 seconds after start for the engine rpm to stabi...

Page 74: ...HT OFF 6 Lane B OFF 2 SEC NO MORE THAN 180 RPM DROP ON WAIT FOR LANE B LIGHT OFF 7 Fuel Pumps AUX OFF MAIN ON 8 Fuel Pressure CHECK CORRECT AND STABLE 9 Fuel Pumps AUX ON MAIN OFF 10 Fuel Pressure CHECK CORRECT AND STABLE 11 Fuel Pumps BOTH ON 12 Engine 2500 RPM 13 Fuel Quantity VERIFY SUFFICIENT FOR PLANNED FLIGHT 14 Circuit Breakers ALL IN 15 Switches CHECK AND SET AS REQUIRED 16 Instruments CHE...

Page 75: ...es APPLY 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 ...

Page 76: ...ngine Parameters VERIFY PRESSURES TEMPERATURES 4 7 2 Cruise 1 Airspeed 105 118 KIAS 2 AUX Fuel Pump OFF 3 Throttle AS REQUIRED 4 Trim AS REQUIRED 5 Fuel SWITCH EVERY HOUR AUX 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 using the full 5...

Page 77: ...mber DC POH 002 X A 6 Page 4 14 Revision 3 0 Date 2021 04 23 4 7 3 Decent 1 ATIS Weather CHECKED 2 Altimeter SET 3 Fuel Selector FULLEST TANK AUX PUMP ON DURING SWITCH 4 Lights AS REQUIRED 5 Seatbelts CHECKED 6 Approach Brief COMPLETE 7 Throttle AS REQUIRED 8 Trim AS REQUIRED ...

Page 78: ...irspeed 70 75 KIAS 2 Flaps FULL ON FINAL 3 Trim AS REQUIRED 4 Throttle AS REQUIRED a NOT BELOW 3000 RPM 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 from This ...

Page 79: ...sion 3 0 Date 2021 04 23 4 8 3 Normal Landing 1 Airspeed 50 ft 65 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 80: ...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 ta...

Page 81: ...SSARY 5 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 Engine Parameters VERIFY PRESSURES TEMPERATURES 9 Throttle FULL OPEN 10 Park Brake RELEASE 11 Rotate 45 KIAS 12 Ab...

Page 82: ...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 NORMAL 70 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 NOT...

Page 83: ... Revision 3 0 Date 2021 04 23 4 9 5 Soft Field Takeoff 1 Aircraft Weight MINIMISE 2 Elevator Trim NEUTRAL 3 Flaps STAGE 2 4 Parking Brake SET FULL 5 Engine Parameters VERIFY PRESSURES TEMPERATURES 6 Throttle FULL OPEN 7 Parking Brake RELEASE 8 Elevator FULL BACK UNTIL NOSE WHEEL JUST LIFTS 9 Rotate 45 KIAS ...

Page 84: ...Landing 1 Approach Procedure NORMAL 2 Approach UNDER POWER 3 Final Approach LONG 4 Rudder INTO CROSSWIND 5 Flare OVER THRESHOLD 6 Wing Roll 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 ground...

Page 85: ... Document Number DC POH 002 X A 6 Page 5 0 Revision 3 0 Date 2021 04 23 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 86: ...nce in this section is valid for Maximum takeoff weight of 600 kg 1 320lb ISA conditions Rotax 912 iS 73 5kW 100 hp Warp Drive Composite Propeller o Three Blade Fixed Pitch 72 Diameter 5 2 Takeoff and Landing Distance 5 2 1 Takeoff Distances Surface Type Run Distance Distance over 15m 15ft Obstacle Concrete Tar 120 m 395 ft 230 m 755 ft Grass 140 m 460 ft 250 m 820 ft 5 2 2 Landing Distance Surfac...

Page 87: ...ce Document Number DC POH 002 X A 6 Page 5 2 Revision 3 0 Date 2021 04 23 5 3 Rate of Climb Values relevant for maximum continuous power of 5500 RPM Altitude Best Rate of Climb Speed VIE Rate of Climb ft ISA KIAS fpm 0 72 800 3 000 600 6 000 500 9 000 400 ...

Page 88: ... used for the values below is fixed pitch Altitude Engine Speed KIAS KTAS ft ISA rpm kt kt 100 4 500 81 82 4 800 95 96 5 000 101 102 5 300 106 108 5 500 112 114 3 000 4 500 72 76 4 800 87 91 5 000 98 104 5 300 104 109 5 500 108 114 6 000 4 500 65 73 4 800 80 89 5 000 90 100 5 300 98 108 5 500 101 115 9 000 4 500 63 73 4 800 74 88 5 000 87 99 5 300 91 105 5 500 94 108 ...

Page 89: ...ate 2021 04 23 5 5 Fuel Consumption Altitude ft ISA 3 000 Fuel Quantity Litres 150 US Gallons 39 6 Engine Speed rpm 4 500 4 800 5 000 5 300 5 500 Fuel Consumption L hr 14 16 18 20 21 US gal hr 3 7 4 2 4 8 5 3 5 6 Airspeed KIAS 73 91 104 109 114 Endurance hh mm 10 40 9 20 8 20 7 30 7 10 Range nm 781 853 866 817 815 ...

Page 90: ... 6 Page 5 5 Revision 3 0 Date 2021 04 23 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 91: ...DC POH 002 X A 6 Page 6 0 Revision 3 0 Date 2021 04 23 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 Blank CG Form and Graph for Use 6 7 ...

Page 92: ...ith payload ranges for safe operation of the aircraft 6 2 Installed Equipment List Type Equipment Item Standard Garmin G3X GDU460 Glass Cockpit Garmin GTX35 Transponder Garmin GTR200 Radio 3Ah IBBS Backup Battery Electric Flap Controller Electric Elevator Trim System Magnetic Compass Optional Garmin G5 Certified Electronic Flight Instrument Garmin GMA245R Audio System Garmin GMC507 Auto Pilot Heat...

Page 93: ...G and MAUW limitations must be adhered to at all times NOTE GC range is 1 635mm 5 364 ft to 1 808 mm 5 931 ft aft of the reference datum 20 to 33 of MAC The leading edge of the wing at MAC is 1 366 mm 4 482 ft aft of the reference datum The MAC is 1 339 mm 4 393 ft 464 N W 1511 Fuel 1808 Most Aft 1635 Most Forward 1959 Main Landing Gear Seats 2508 Luggage Front 2896 Luggage Rear ...

Page 94: ...ng LSA Section 6 Pilot Operating Handbook Weight and Balance Document Number DC POH 002 X A 6 Page 6 3 Revision 3 0 Date 2021 04 23 6 4 CG Envelope FLIGHT ALLOWED IN SHADED AREA ONLY Allowable CG Envelope ...

Page 95: ...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 1366𝑚𝑚 100 1339𝑚𝑚𝑚𝑚 𝑜𝑜𝑜𝑜 𝑀𝑀𝑀𝑀𝑀𝑀 𝐶𝐶𝐶𝐶 4 482𝑓𝑓𝑓𝑓 100 4 393𝑓𝑓𝑓𝑓 WARNING For each flight the most forward CG full take off fuel and the most rearward CG landing f...

Page 96: ...e 2021 04 23 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 600kg 1 320lb Maximum useful load example 𝑊𝑊𝑚𝑚𝑚𝑚𝑚𝑚 𝑢𝑢𝑢𝑢𝑢𝑢𝑓𝑓𝑓𝑓𝑓𝑓 𝑊𝑊𝑀𝑀𝑀𝑀𝑀𝑀𝑀𝑀 𝑊𝑊𝐸𝐸 600𝑘𝑘𝑘𝑘 1 320𝑙𝑙𝑙𝑙 370𝑘𝑘𝑘𝑘 816𝑙𝑙𝑙𝑙 230𝑘𝑘𝑘𝑘 507lb ...

Page 97: ...age 6 6 Revision 3 0 Date 2021 04 23 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 1 959 6 427 Left Main Wheel WL LL 1 959 6 427 Nose Wheel WN LN 464 1 522 Totals Empty weight WE Aircraft moment M0 Final CG CG mm ft ...

Page 98: ...DC POH 002 X A 6 Page 6 7 Revision 3 0 Date 2021 04 23 6 7 Blank CG Form and Graph for Use WEIGHT kg lb ARM mm ft MOMENT weight x arm kg mm lb ft Pilot Passenger 1 959 6 427 Baggage Front 2 508 8 228 Baggage Rear 2 896 9 501 Fuel 1 511 4 957 Cg Empty Value TOTALS WT MT CG mm CG MAC ...

Page 99: ...Sling LSA Section 6 Pilot Operating Handbook Weight and Balance Document Number DC POH 002 X A 6 Page 6 8 Revision 3 0 Date 2021 04 23 Allowable CG Envelope ...

Page 100: ...y Harness and Seats 7 8 7 5 Baggage Compartment 7 9 7 6 Canopy 7 9 7 7 Pitot and Static Systems 7 10 7 8 Cockpit Layout 7 11 7 9 Instruments and Avionics 7 13 7 10 Minimum Instruments and Equipment Required for Flight 7 16 7 11 Engine 7 17 7 12 Cooling System 7 18 7 13 Electric System 7 19 7 14 Propeller 7 22 7 15 Fuel System 7 23 7 16 Lubrication System 7 26 7 17 Autopilot System 7 27 7 18 Positi...

Page 101: ...d 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 4415 and is equipped with semi s...

Page 102: ...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 directional control while on the ground Button Function 1 Trim down 2 Autopilot control 3 Trim up 4 Not allocated...

Page 103: ... 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 inte...

Page 104: ...ber DC POH 002 X A 6 Page 7 4 Revision 3 0 Date 2021 04 23 7 2 3 4 Brake System Diagram 7 2 4 Throttle Lever The aircraft makes use of a single lever power system as the propeller is normally only ground adjustable and mixture is controlled by the ECU Refer to 7 8 Cockpit Layout ...

Page 105: ...tre console Refer to in 7 8 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 operation of the lever is pre...

Page 106: ...from main bus OFF Main bus 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 collisio...

Page 107: ...m 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 failure ...

Page 108: ... wheel regardless of braking architecture The main landing gear uses a single continuous composite spring section 7 4 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 p...

Page 109: ...larger back section Subject to the weight limitation luggage may be loaded into the front or back section 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 6 Canopy The aircraft is equipped with a sliding canopy mechanism External access to the cabin is form either side Latching mechanisms are provided insid...

Page 110: ...econd 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 stat...

Page 111: ... 8 Cockpit Layout The basic cockpit layout is the same for all Sling LSA 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 112: ... valve 10 Rudder pedals with brakes if footbrakes are fitted 11 Ballistic parachute operating lever 12 Fire extinguisher 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 fire exting...

Page 113: ...ntaining 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 its ...

Page 114: ...ude 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 Syste...

Page 115: ... 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 Us...

Page 116: ...or 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 navigat...

Page 117: ...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 43 and features an integrated shock absorber The eng...

Page 118: ...nk 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 o...

Page 119: ...Sling LSA Section 7 Pilot Operating Handbook Aircraft and Systems Document Number DC POH 002 X A 6 Page 7 19 Revision 3 0 Date 2021 04 23 7 13 Electric System 7 13 1 Broad Overview Diagram ...

Page 120: ...ternal alternator is installed the output is used to charge the battery through a breaker switch 7 13 3 Main Battery The 12V 17 Ah main battery is mounted on the engine side of the firewall 7 13 4 Main Bus When power to the main bus is unavailable fails the following equipment will become non operational Item 1 Autopilot specifically the servos 2 Flaps 3 Radio 4 Transponder 5 Cabin Lights 6 Strobe...

Page 121: ... are two separate ignition circuits 7 13 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 13 9 Circuit Breakers Circuit breakers are push to reset i e push in for restoring supplying electrical power to their corresponding...

Page 122: ... options for the propeller with the default being the first 1 Warp Drive 72 inch solid composite ground adjustable 3 blade composite propeller 2 Whirlwind 70 inch hollow composite ground adjustable 3 blade propeller 3 Sensenich 65 inch hollow composite ground adjustable 3 blade propeller NOTE For technical data refer to documentation supplied by the propeller manufacturer ...

Page 123: ...rough two electric fuel pumps and past a fuel pressor sensor which is displayed on the EFIS The fuel return then is routed back to the respective tank which returns excess fuel supplied by the pumps and not used by the engine Total volume of the wing tank s are RSA o 75 litres 73 litres useable o 19 8 gal 19 3 US gal useable International including United States o 150 litres 146 litres useable o 3...

Page 124: ...Sling LSA Section 7 Pilot Operating Handbook Aircraft and Systems Document Number DC POH 002 X A 6 Page 7 24 Revision 3 0 Date 2021 04 23 A diagram of the fuel system is as follows with a key ...

Page 125: ...respective of the master switch status Fuel System Diagram Key 912 iS A Port left fuel tank International version only G 8mm T piece B Starboard right fuel tank H 8mm T piece with jet C Fuel selector OFF ON OFF I Fuel pressure sensor D Fuel filter 90 bend J Fuel filter E Gascolator K Bypass pressure valve F Rotax fuel pump L 912 iS Engine WARNING At least one fuel pump must be operational at all t...

Page 126: ...haft driven pump with an integrated pressure regulator The pump delivers 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 lubric...

Page 127: ...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 clut...

Page 128: ...ing 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 position ligh...

Page 129: ...ating Handbook Ground Handling Servicing Document Number DC POH 002 X A 6 Page 8 0 Revision 3 0 Date 2021 04 23 8 Ground Handling and Servicing 8 1 Introduction 8 1 8 2 Ground Handling 8 1 8 3 Servicing 8 5 8 4 Cleaning and Care 8 7 ...

Page 130: ...es 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 Dir...

Page 131: ...by putting pressure on the wing horizontal stabilizer leading edge directly over a rib 8 2 3 Parking It is advisable to park the aircraft inside a hangar or alternatively 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 tarpaul...

Page 132: ...s 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 th...

Page 133: ... Revision 3 0 Date 2021 04 23 8 2 4 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 134: ...d 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 no...

Page 135: ...the latest revision of the applicable a engine propeller manufacturer documentation More detail is supplied in the Sling LSA 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 part...

Page 136: ...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 polisher...

Page 137: ...0 Revision 3 0 Date 2021 04 23 9 Supplementary Information 9 1 Introduction 9 1 9 2 Supplement 02 2010 Airplanes fitted with a Magnum 601 Ballistic Parachute 9 2 9 3 Supplement 04 2012 Airplanes Fitted with a Rotax 912 ULS Engine 9 4 9 4 Supplement 03 2010 Airplanes Fitted with and Airmaster AP332 Propeller 9 16 ...

Page 138: ... 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 04 06 12 02 2010 Airplanes fitted with a Magnum 601 Ballistic Parachute recovery system 19 10 12 04 2012 Airplanes fitted with a Rotax 912 ULS engine 09 05 19 03 2010 Airplanes fitted ...

Page 139: ...ally 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 601 ballistic parachute The Sling LSA is specifically designed for convenient fitment of the Magnum 601 ballistic parachute recovery system manufactured by Stratos 07 The system is designed to enable the pilot or pa...

Page 140: ...it Speed 3 s Maximum Supported Mass 759 kg or 1674 lb Decent Rate at Maximum Mass 7 m s 9 2 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 the g...

Page 141: ...ok This supplement provides information relating to the operation of an aircraft fitted with a Rotax 912 ULS engine The Rotax 912 ULS makes use of dual carburettors and is not electronically controlled like the iS version The ULS has the same power rating as the iS and airplane performance with the two engines materially similar Better fuel economy especially in cruise may be observed with the iS ...

Page 142: ...e 9 5 Revision 3 0 Date 2021 04 23 9 3 2 Rotax 912 ULS Engine Operating and Speed Limits Engine Start and Operation Temperature Limits Maximum Ambient Temperature 50 C 122 F Minimum Oil Temperature 25 C 13 F Engine Load Factor Limits Acceleration Maximum 5 seconds at 0 5g Engine Bank Angle Limits Maximum 40 ...

Page 143: ...5800 rpm max 5 minutes Maximum continuous 5500 rpm Idle 1 400 rpm minimum Cylinder head temperature Minimum N A Maximum 135 C 275 F Normal 75 to 110 C 167 to 230 F Oil temperature Minimum 50 C 122 F Maximum 130 C 266 F Normal 90 to 110 C 194 to 230 F EGT Maximum 880 C 1616 F Coolant temperature Maximum 120 C 248 F Oil pressure Minimum 0 8 bar 12 psi below 3500 rpm Maximum 7 bar 102 psi permissible...

Page 144: ...t revision of the Rotax ULS Operator Maintenance Manual and to the latest revisions of the Rotax service instruction with regards to the selection of operating fluids Coolant Item Value Cooling System Mixed Air and close circuit pressurized liquid Air cooled cylinders and liquid cooled cylinder heads Coolant Ethylene glycol based coolant mixed 1 1 with distilled water Applicable for engine S N wit...

Page 145: ...Sling LSA Section 7 Pilot Operating Handbook Supplementary Information Document Number DC POH 002 X A 6 Page 9 8 Revision 3 0 Date 2021 04 23 9 3 4 Rotax 912 ULS Fuel System ...

Page 146: ... pump L Starboard right carburettor SWITCH LABEL FUNCTION POSITION MASTER STARTER KEY SWITCH Power disconnected from main bus OFF Main bus 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 FUEL PUMP Switch main fuel pump on off LAND Switch landing lights on off TAXI Switch taxi lights on ...

Page 147: ...Sling LSA Section 7 Pilot Operating Handbook Supplementary Information Document Number DC POH 002 X A 6 Page 9 10 Revision 3 0 Date 2021 04 23 9 3 6 Electrical System Overview 912 ULS ...

Page 148: ...l Power Generation and Failure Unlike the 912 iS the 912 ULS only has one internal alternator which is rectified and regulated to charge the main battery If this alternator fails the engine will continue to run The ULS does not make use of an ECU but uses magnetos and carburettors instead which is why it can run after an alternator failure All non essential equipment must be turned off to ensure t...

Page 149: ...S 2ND TANK DRY 3 Throttle CHECK MOVEMENT 4 Throttle MIDDLE POSITION 5 Master ON 6 Magnetos BOTH ON 7 Starter ENGAGE 9 3 9 2 Irregular Engine RPM 1 Magnetos BOTH ON 2 Throttle VERIFY POSITION 3 Fuel Quantity CHECK 4 Fuel Selector CHANGE UNLESS 2ND TANK DRY 5 Fuel Pump ON 6 Oil Pressure CHECK 7 Oil Temperature CHECK 8 Coolant Temperature CHECK 9 EGT Temperature CHECK If engine continues to run rough...

Page 150: ...cterized by the charge warning light being illuminated on the instrument panel 1 Battery Charge Voltage VERIFY FAILURE a 2 Non Essential Equipment OFF 3 EFIS Back up ON 4 EFIS Screen Brightness MINIMUM 5 Radio Communications MINIMUM 6 Land AS SOON AS PRACTICABLE NOTES a If alternator is operating correctly the voltage will be above 13V If the charge circuit has failed this voltage will be below 13...

Page 151: ... Pump OFF 9 Choke ON IF REQUIRED 10 Throttle SET 50 11 Propeller AREA CLEAR 12 Starter ENGAGE MAX 10 SECONDS 13 Choke OFF WHEN ENGINE RPM STABLE 14 Oil Pressure CHECK CORRECT WITHIN 10 SECONDS 15 Throttle 2500 RPM 16 Battery Voltage VERIFY CHARGE a 17 Avionics Switch ON 18 Oil Temperature 2500 RPM until oil temperature is 50 C 122 F b CAUTION a Main bus voltage should move up from 12 5V to above 1...

Page 152: ...FF 2 SEC NO MORE THAN 180 RPM DROP ON 7 Fuel Pressure CHECK CORRECT AND STABLE 8 Engine 2500 RPM 9 Fuel Quantity VERIFY SUFFICIENT FOR PLANNED FLIGHT 10 Fuel Selector FULLEST TANK 11 Circuit Breakers ALL IN 12 Switches CHECK AND SET AS REQUIRED 13 Instruments CHECK AND SET ALL 14 Controls FREE FULL CORRECT SENSE 15 Trim SET NEUTRAL 16 Flaps SET STAGE 1 TAKEOFF 17 Engine Parameters VERIFY TEMPERATU...

Page 153: ...m the standard Pilot Operating Handbook with regards only to the specific sections addressed herein Limitations procedures and information not specifically 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 an Airmaster AP332 variable pitch constant speed propeller Propeller cont...

Page 154: ...into the normal and emergency procedure for the aircraft as applicable Improvements 1 Vh will be increased from 116 KIAS to 120 KIAS 2 The aircraft service ceiling will increase to 14 000 ft 3 Take off distance on concrete and grass will improve from 120m 395ft and 140m 460ft to 100m 328ft and 120m 394ft respectively with the AP332 propeller 4 Take off distance Over 15m 50ft on concrete and grass ...

Page 155: ...ropeller control failure 1 Engine Speed PREVENT OVERSPEED 2 Propeller Mode SELECT MANUAL MAN 3 Propeller Pitch VERIFY OPERATION If propeller pitch control is still available 4 Propeller Pitch SET TO REQUIRED If propeller pitch control is unavailable 5 Propeller switch OFF If failure results in pitch within flight range 6 Proceed WITH CAUTION treat as if it is fixed propeller If failure results in ...

Page 156: ...d with propeller pitch set at any other pitch than the fine pitch limit full power from the engine propeller combination may not be available at low speeds Consideration should be given to this during approach and landing PROPELLER CONTROL SELECTOR KNOB BLUE AUTOMATIC MANUAL SELECTOR SWITCH FEATHER ENGAGE SWITCH FEATHER INDICATOR LIGHT COARSE INDICATOR LIGHT FINE INDICATOR LIGHT PITCH ADJUST SWITC...

Page 157: ... 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 fo...

Page 158: ...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 159: ...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...

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