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Airplane Factory SLING LSA

Pilot Operating Handbook

Page | 7-8

Date of Issue: 07 July 2014

Revision : 1.3

7.8

Pitot and static systems

A pitot tube is located below the left wing. Pressure distribution to the
instruments is through flexible plastic hoses. The tube incorporates a
second inlet for 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 that the pitot tube cover is removed
prior to every flight and that it is replaced after every flight.

Pitot and static system (example)

Please note that this drawing is
representative of a pitot and static
system only and may differ from the
actual installation in the aircraft,
with regard to, for example,
placement of instruments and
actual instruments installed.

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Summary of Contents for ZU-NRC

Page 1: ...ELD AIR PARK JHB SOUTH EIKENHOF 1872 SOUTH AFRICA PO BOX 308 EIKENHOF 1872 SOUTH AFRICA Phone 27 11 948 9898 Information info airplanefactory co za The Airplane Factory Inc 3401 Airport Drive Torrance CA 90505 Phone 424 241 0341 info airplanefactory com Date of Issue 07 July 2014 Revision Number 1 3 ...

Page 2: ...of Construction Registration Airworthiness Category Light Sport Aircraft LSA Issue Date of POH 07 July 2014 PLEASE ADVISE THE AIRPLANE FACTORY ON CHANGE OF OWNERSHIP OF THE 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: ...RENCES APPLICABLE TO THE STANDARD 912 iS POWERED SLING LSA AIRCRAFT AS MANUFACTURED ON PREMISES BY THE AIRPLANE FACTORY PTY LTD 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 CORRESPOND WITH THE PRODUCTION STANDARD NOTICE THIS EDITION OF THIS MANUAL IS ...

Page 4: ...e stored both with the original manufacturer in South Africa and with its US distributor at the addresses below The Airplane Factory Pty Ltd Hangar 8 Tedderfield Air Park Johannesburg South Eikenhof 1872 South Africa PO Box 308 Eikenhof 1872 South Africa Phone 27 11 948 9898 info airplanefactory co za The Airplane Factory USA 3401 Airport Drive Torrance CA 90505 Phone 424 241 0341 info airplanefac...

Page 5: ...Sport Aircraft is also responsible for alerting the manufacturer of any potential safety of flight issues Report a Safety of Flight Issue Please contact our US Distribution Center to report any maintenance service or safety issues Service Maintenance Safety issues safety airplanefactory com or fill out a safety service form on our website www airplanefactory com Sign up to receive safety notices M...

Page 6: ...ponsible for notifying the manufacturer of any safety of flight issue or significant service difficulty upon discovery The owner operator of a LSA shall be responsible for complying with all manufacturer issued notices of corrective action and for complying with all applicable aviation authority regulations in regard to maintaining the airworthiness of the LSA An owner of a LSA shall ensure that a...

Page 7: ...ing Handbook must be recorded in the following table and where 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 Approve d by Date of approval Date inserted Sign 1 1 All All 04 20 2011 1 2 All All 03 12 2012 1 3 All All 07 07 2014 ...

Page 8: ... 1 12 Revised 1 3 iv Revised 1 3 1 13 Revised 1 3 v Revised 1 3 1 14 Revised 1 3 vi Revised 1 3 1 15 Revised 1 3 vii Revised 1 3 1 16 Revised 1 3 viii Revised 1 3 1 17 Revised 1 3 ix Revised 1 3 1 18 Revised 1 3 x Revised 1 3 2 1 2 2 Revised 1 3 xi Revised 1 3 2 3 Revised 1 3 xii Revised 1 3 2 4 Revised 1 3 1 1 1 2 Revised 1 3 2 5 Revised 1 3 1 3 Revised 1 3 2 6 Revised 1 3 1 4 Revised 1 3 2 7 Rev...

Page 9: ...3 16 Revised 1 3 2 16 Revised 1 3 3 17 Revised 1 3 2 17 Revised 1 3 3 18 Revised 1 3 2 18 Revised 1 3 3 19 Revised 1 3 2 19 Revised 1 3 4 1 4 2 Revised 1 3 2 20 Revised 1 3 4 3 Revised 1 3 2 21 Revised 1 3 4 4 Revised 1 3 2 22 Revised 1 3 4 5 Revised 1 3 3 1 3 2 Revised 1 3 4 6 Revised 1 3 3 3 Revised 1 3 4 7 Revised 1 3 3 4 Revised 1 3 4 8 Revised 1 3 3 5 Revised 1 3 4 9 Revised 1 3 3 6 Revised 1...

Page 10: ...Operating Handbook Page x Date of Issue 07 July 2014 Revision 1 3 3 9 Revised 1 3 4 13 Revised 1 3 3 10 Revised 1 3 4 14 Revised 1 3 3 11 Revised 1 3 4 15 Revised 1 3 3 12 Revised 1 3 4 16 Revised 1 3 3 13 Revised 1 3 4 17 Revised 1 3 ...

Page 11: ...5 4 Revised 1 3 7 11 Revised 1 3 5 5 Revised 1 3 7 12 Revised 1 3 5 6 Revised 1 3 7 13 Revised 1 3 5 7 Revised 1 3 7 14 Revised 1 3 6 1 6 2 Revised 1 3 7 15 Revised 1 3 6 3 Revised 1 3 7 16 Revised 1 3 6 4 Revised 1 3 7 17 Revised 1 3 6 5 Revised 1 3 7 18 Revised 1 3 6 6 Revised 1 3 7 19 Revised 1 3 6 7 Revised 1 3 7 20 Revised 1 3 6 8 Revised 1 3 7 21 Revised 1 3 6 9 Revised 1 3 7 22 Revised 1 3 ...

Page 12: ... 30 Revised 1 3 9 10 Revised 1 3 7 31 Revised 1 3 9 11 Revised 1 3 7 32 Revised 1 3 9 12 Revised 1 3 8 1 8 2 Revised 1 3 9 13 Revised 1 3 8 3 Revised 1 3 9 14 Revised 1 3 8 4 Revised 1 3 9 15 Revised 1 3 8 5 Revised 1 3 9 16 Revised 1 3 8 6 Revised 1 3 9 17 Revised 1 3 8 7 Revised 1 3 9 18 Revised 1 3 8 8 Revised 1 3 9 19 Revised 1 3 8 9 Revised 1 3 9 20 Revised 1 3 9 1 9 2 Revised 1 3 9 21 Revise...

Page 13: ...ue 07 July 2014 Revision 1 3 TABLE OF CONTENTS 1 GENERAL INFORMATION 1 1 2 LIMITATIONS 2 1 3 EMERGENCY PROCEDURES 3 1 4 NORMAL PROCEDURES 4 1 5 PERFORMANCE 5 1 6 WEIGHT AND BALANCE 6 1 7 SYSTEMS 7 1 8 AIRPLANE GROUND HANDLING AND SERVICING 8 1 9 SUPPLEMENTARY INFORMATION 9 1 ...

Page 14: ... 07 July 2014 Revision 1 3 1 GENERAL INFORMATION 1 1 Introduction to airplane 1 3 1 2 Warnings cautions and notes 1 4 1 3 Aircraft 3 view drawing 1 5 1 4 Data for Sling LSA aircraft and systems 1 7 1 5 Terminology symbols and conversion factors 1 12 1 6 Supporting documents 1 18 ...

Page 15: ...nly minor modifications to the aircraft and the application of a revised Pilot s Operating Handbook the Sling LSA 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 kg 1543 24 lb The Sling LSA is intended chiefly for recreational and cross country flying It is not i...

Page 16: ... the Pilot Operating Handbook Means that non observation of the corresponding procedure leads to an immediate or important degradation of flight safety Means that non observation of the corresponding procedure leads to a minor or possible long term degradation of flight safety Draws attention to any special item not directly related to safety but which is important or unusual WARNING CAUTION NOTE ...

Page 17: ...Airplane Factory SLING LSA Pilot Operating Handbook Page 1 5 Date of Issue 07 July 2014 Revision 1 3 1 3 Aircraft 3 view drawing DIMENSIONS IN THIS DRAWING ARE IN FEET ...

Page 18: ...Airplane Factory SLING LSA Pilot Operating Handbook Page 1 6 Date of Issue 07 July 2014 Revision 1 3 DIMENSIONS IN THIS DRAWING ARE IN FEET ...

Page 19: ...5 77 m 19 ft Overall length 6 675 m 21ft 11 inches Overall width 1 15 m 45 inches Overall height 2 5m 98 inches EMPENNAGE Horizontal stabilizer span 2 825 m 9 ft 3 inch Horizontal stabilizer surface area 0 96 m2 10 ft2 Elevator surface area 1 02 m2 11 ft2 Horizontal stabilizer angle of incidence 4o Vertical stabilizer span 1 47 m 16 ft Vertical stabilizer surface area 0 53 m2 6 ft2 Rudder surface ...

Page 20: ...cturer Bombardier Rotax GmbH Model 912 ULS Type 4 Cylinder horizontally opposed with overall displacement 1 352 cc mixed cooling water cooled heads and air cooled cylinders twin carburetors integrated reduction gearbox with torque damper Maximum power 73 5 kW 98 5hp at 5 800 rpm maximum 5 minutes 69 kW 92 5hp at 5 500 rpm continuous For Sling LSA aircraft fitted with the 912 iS engine refer to the...

Page 21: ...perator maintenance manual and latest revision of service instruction SI 912 016 For aircraft fitted with the 912 iS engines refer to the applicable supplement at the end of this manual Fuel tanks Two One fuel tank integrated within each wing leading edge Each tank is equipped with finger strainers in pick up line and drain fittings Capacity of tank 75 liters 19 8 US gallons 73 liters 19 3 US gall...

Page 22: ...ator maintenance manual and latest revision of service instruction SI 912 016 For aircraft fitted with the 912 iS engine refer to the applicable supplement at the end of this manual Capacity 3 5 liters 3 5 quarts approximately COOLING Cooling system Mixed air and liquid pressurized closed circuit system Coolant 1 Water free propylene glycol based coolant concentrate this is not allowed for 912 iS ...

Page 23: ... landing weight 600 kg 1320lb Maximum baggage weight 15 kg 77lbs this is what we say lb Front luggage compartment maximum 15 kg 77lb Rear luggage compartment maximum 15 kg 55 lb STANDARD WEIGHTS Standard empty weight 370 kg 814 lb Maximum useful load 230 kg 506 lb SPECIFIC LOADINGS Wing loading MAUW 50 65 kg m 2 10 0 lb ft 2 Power loading 6 00 kg hp 1 13 2 lb hp 1 ...

Page 24: ...e COM Communication radio EFIS Electronic Flight Information System FAA Federal Aviation Authority GLS GPS Landing System GmbH Gesellschaft mit beschränkter Haftung company with limited liability GPS Global Positioning System IFR Instrument Flying Rules LED Light Emitting Diode MOGAS Automobile car gasoline NGL Normal Ground Line NRV Non Return Valve POH Pilot Operating Handbook PTT Push To Talk b...

Page 25: ...H Maximum Speed in level flight at maximum continuous power VLOF Lift off Speed being the speed at which the aircraft generally lifts off from the ground during take off VNE Never Exceed Speed being the speed that may not be exceeded at any time VNO Maximum Structural Cruising Speed being the speed that should not be exceeded except in smooth air and then only with caution VREF Indicated airspeed ...

Page 26: ...d Atmosphere QNH The local pressure setting that if set on the subscale of an altimeter will cause the altimeter to indicate local altitude above mean sea level QFE The local airfield pressure setting that if set on the subscale of an altimeter will cause the altimeter to indicate local height above airfield Engine terminology CHT Cylinder Head Temperature EGT Exhaust Gas Temperature OHV Overhead ...

Page 27: ...sured during landing from actual touchdown to the end of the landing run Landing distance The distance measured during landing from clearance of a 15 m obstacle in the air to the end of the landing run Take off distance The take off distance measured from the actual start of the take off run to clearance of a 15 m 50 ft obstacle in the air Take off run The take off distance measured from actual st...

Page 28: ...runs through the center point of the flat front face of the engine flange of the Rotax engine Empty weight Is the weight of the airplane with engine fluids and oil at operating levels MAC Mean Aerodynamic Chord MAUW Maximum All Up Weight Maximum Landing Weight Is the maximum weight approved for the landing touch down Maximum Take off Weight Is the maximum weight approved for the start of the take ...

Page 29: ...eful conversion factors 1 pound 0 4536 kilogram 1 pound per square inch 6 895 kilopascal 1 inch 25 4 millimeters 1 foot 0 3048 meter 1 statute mile 1 609 kilometers 1 nautical mile 1 852 kilometers 1 millibar 1 hectopascal 1 millibar 0 1 kilopascal 1 imperial gallon 4 546 liters 1 US gallon 3 785 liters 1 US quart 0 946 liter 1 cubic foot 28 317 liters degrees fahrenheit 1 8 x degrees celsius 32 d...

Page 30: ...or aircraft fitted with 912 iS engines latest revision edition of the Operators Manual For Rotax Engine Type 912 i Series Ref No OM 912 i 3 Latest revision edition of Rotax service instruction SI 912 016 or SI 912i 001 as applicable to type of engine fitted 4 MGL EFIS operator manual 5 Operator manual for COM radio and transponder if fitted equipment fitted to the aircraft Reference should be made...

Page 31: ... for turning flight or load factor 2 5 2 5 Crosswind and wind limitation demonstrated 2 6 2 6 Service ceiling 2 6 2 7 Load factors 2 6 2 8 Weights 2 6 2 9 Center of gravity range 2 7 2 10 Prohibited maneuvers 2 8 2 11 Flight crew 2 9 2 12 Passengers 2 9 2 13 Kinds of operation 2 10 2 14 Engine limitations 2 11 2 15 Other limitations 2 14 2 16 Flight in rain 2 14 2 17 Limitation warning information...

Page 32: ...th air and then only with caution VA Maneuvering 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 The aircraft will not exceed this speed at MAUW in level flight VS Stall speed at MAUW 45 A...

Page 33: ...er limit is VS0 at maximum weight and upper limit is the maximum speed Vfe permissible with flaps deployed Green arc 45 110 Normal Operating Range lower limit is VS at maximum weight and most forward CG with flaps retracted and upper limit is maximum structural speed VNO Yellow arc 110 135 Maneuvers must be conducted with caution and only in smooth air Red line 135 Maximum speed for all operations...

Page 34: ...e adjusted for 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 VT V V x MULTIPLICATION FACTOR V is straight and level stall speed at load factor 1 g VT is stall speed in turn non descending VST V N V is straight and level stall speed...

Page 35: ...ceiling Service ceiling 12 000 ft 2 7 Load factors Maximum positive limit load factor 4 g Maximum negative limit load factor 2 g Maximum positive load factor with flaps 2 g Maximum negative load factor with flaps 1 g 2 8 Weights Maximum take off weight 600 kg 1320 lb Maximum landing weight 600 kg 1320 lb Maximum total baggage weight 15 kg 77 lb Front luggage compartment maximum 15 kg 77lb Rear lug...

Page 36: ...tudinal leveling Upper surface of canopy sliders on cockpit side skins with canopy open Reference transverse leveling Upper surface of center spar cap under pilot and passenger seats Forward limit 1 635 m 5 364 ft 20 MAC aft of datum Rear limit 1 772 m 5 814 ft 30 3 MAC aft of datum WARNING It is the pilot s responsibility to ensure that the airplane is properly loaded Refer to section 6 for infor...

Page 37: ... approved for normal maneuvers including the following Steep turns not exceeding 60 bank Lazy eights Chandelles Stalls not including whip stalls WARNING Aerobatics and intentional spins are prohibited WARNING Limit load factor would be exceeded by moving flight controls abruptly to their limits at a speed above VA 91 KIAS maneuvering speed ...

Page 38: ...erating Handbook Page 2 9 Date of Issue 07 July 2014 Revision 1 3 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 ...

Page 39: ... temperature indicator Cylinder head temperature indicator Outside air temperature indicator Tachometer Chronometer First aid kit compliant with national legislation Fire extinguisher NOTE Additional equipment may be required to fulfill national or specific requirements and may be fitted WARNING Notwithstanding that installed equipment may include GPS and other advanced flight and navigational aid...

Page 40: ... figures For airplanes with the Rotax 912iS engine installed refer to the supplement at the end of this manual Always refer to latest edition revision of the engine Operators Manual for latest information regarding operating limitations ENGINE START AND OPERATION TEMPERATURE LIMITS 912 ULS Maximum 50 C 122 F ambient temperature Minimum 25 C 13 F oil temperature ENGINE LOAD FACTOR ACCELERATION LIMI...

Page 41: ...rpm RPM Maximum take off 5800 rpm maximum 5 minutes Maximum continuous 5500 rpm Idle 1 600 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 Maxi...

Page 42: ...of Issue 07 July 2014 Revision 1 3 Fuel pressure Minimum 0 15 bar 2 2 psi WARNING Exceeding maximum allowed fuel pressure will override the float valves of the carburetors and lead to engine failure Maximum 0 4 bar 5 8 psi 0 5 bar 7 26 psi fuel pump S N 11 0036 onwards ...

Page 43: ...moking is allowed on board of the airplane VFR flights only are permitted 2 16 Flight in rain When flying in the rain no additional steps are required Airplane qualities and performance are not substantially changed However VMC should be maintained WARNING IFR flights and intentional flights under icing conditions are prohibited ...

Page 44: ...ng limitation warning placards must be placed in or on the aircraft and positioned in plain view of the pilot passenger or third person as the case may be In a place visible to pilot and passenger PASSENGER WARNING THIS AIRCRAFT WAS MANUFACTURED IN ACCORDANCE WITH LIGHT SPORT AIRCRAFT AIRWORTHINESS STANDARDS AND DOES NOT CONFORM TO STANDARD CATEGORY AIRWORTHINESS REQUIREMENTS ...

Page 45: ... 2 16 Date of Issue 07 July 2014 Revision 1 3 If a ballistic rescue parachute is fitted adjacent to the ballistic parachute activation lever FASTEN SEATBELTS NO INTENTIONAL SPINS EMERGENCY BALLISTIC CHUTE REMOVE LOCKING PIN BEFORE FLIGHT PULL HANDLE TO FIRE ...

Page 46: ...age 2 17 Date of Issue 07 July 2014 Revision 1 3 On the baggage space separator channel Adjacent to the fuel filler caps 19 8 U S GALS 91 OCT MOGAS 100LL AVGAS MAX TOTAL BAGGAGE WEIGHT 35 KG 77 LB MAX FRONT SECTION 35 KG 77LB MAX REAR SECTION 25 KG 55 LB ...

Page 47: ...ating Handbook Page 2 18 Date of Issue 07 July 2014 Revision 1 3 Adjacent to the filler hole in the main gear wheel pants on each wheel Adjacent to the filler hole in the nose gear wheel pants TIRE PRESSURE 32 P S I TIRE PRESSURE 26 P S I ...

Page 48: ...Airplane Factory SLING LSA Pilot Operating Handbook Page 2 19 Date of Issue 07 July 2014 Revision 1 3 On the inboard upper wing flap surface NO STEP ...

Page 49: ...7 July 2014 Revision 1 3 On the exterior of the fuselage adjacent to the entrance to the cockpit On both pilot and passenger sides If a ballistic rescue parachute is installed LIGHT SPORT WARNING This aircraft is equipped with a ballistically deployed emergency parachute system ...

Page 50: ...ion 1 3 If a ballistic rescue parachute is installed On the exterior of the fuselage adjacent to the egress point of the rescue parachute system On the parachute rocket body inside the rocket housing DANGER EXPLOSIVE EGRESS Rocket Deployed Parachute Egress Area STAY CLEAR DANGER EXPLOSIVE ROCKET ...

Page 51: ...of the cabin Note represents the information applicable to the specific aircraft The airplane must be placarded to show the identity of All fuses circuit breakers Magneto ignition switches All other switches Choke if fitted Starter Trim Nose up and down Flaps Up and Down AIRCRAFT IDENTIFICATION BUILDER THE AIRPLANE FACTORY Pty Ltd MODEL SLING SERIAL NO MADE IN SOUTH AFRICA ...

Page 52: ...f Issue 07 July 2014 Revision 1 3 3 EMERGENCY PROCEDURES 3 1 Introduction 3 3 3 2 Speeds for emergency operations 3 3 3 3 Engine related emergencies 3 4 3 4 Smoke and fire 3 8 3 5 Emergency landings 3 12 3 6 Recovery from unintentional spin 3 15 3 7 Other emergencies 3 16 ...

Page 53: ...e basic guidelines described in this section should be considered and applied as necessary to manage the problem In case of emergency the pilot should remember the following priorities 1 Keep control of and continue flying the aircraft 2 Analyze the situation 3 Apply applicable procedures 4 Inform air traffic control of the situation if time and conditions permit it 3 2 Speeds for emergency operat...

Page 54: ...Auxiliary electric fuel pump off 912 ULS Electric fuel pumps both off 912 iS 3 3 2 Engine failure immediately after take off 1 Speed check 2 Find a suitable place on the ground to land safely The landing should be planned straight ahead with only small changes in direction not exceeding 45 degrees to either side 3 Flaps as needed plan to land as slowly as possible Before touch down 4 Magnetos igni...

Page 55: ...el pump on 912 ULS Auxiliary electric fuel pump on 912 iS If engine continues to run irregularly 5 Land as soon as possible 3 3 3 2 Low fuel pressure refer to engine limitations Section 2 912 ULS or 912 iS engine supplement at end of manual 1 Check fuel quantity indicator 2 Switch electric fuel pump on 912 ULS Switch auxiliary electric fuel pump on 912 iS If fuel pressure remains low 3 Decrease th...

Page 56: ...ion 2 912 ULS or 912 iS engine supplement at end of manual 1 Check oil temperature If oil temperature is high or increasing 2 Set throttle to a setting which gives an aircraft speed of 72 KIAS most efficient speed If oil pressure remains low or temperature remains high or increasing 3 Land as soon as possible and remain vigilant for impending engine failure ...

Page 57: ...h on 6 Starter engage 7 Electric fuel pump off 912 ULS after positive start Auxiliary fuel pump off 912 iS after positive start If engine should fail to restart 8 Apply forced landing without engine power procedure according to 3 5 1 NOTE It is possible that the propeller may continue to rotate if the airspeed remains above approximately 72 KIAS In such circumstances no application of the starter ...

Page 58: ...r switch off 7 Retrieve fire extinguisher if possible 8 Exit the airplane 9 Extinguish fire by fire extinguisher or call for a fire brigade if you cannot do it 3 4 2 Engine fire on ground with engine running 1 Cabin heat close 2 Fuel selector close 3 Electric fuel pumps both off 912 iS 4 Throttle idle 5 Magnetos ignition off 6 Master switch off 7 Retrieve fire extinguisher if possible 8 Leave the ...

Page 59: ...es if unable to do so 3 4 4 Engine fire in flight 1 Heating close 2 Fuel selector close 3 Throttle full power 4 Magnetos ignition switch off after the fuel in carburetors is consumed and engine has shut down 5 Electric fuel pumps both off 912 iS 6 Choose landing area choose emergency landing area 7 Emergency landing perform according to 3 5 1 8 Retrieve fire extinguisher if possible 9 Exit the air...

Page 60: ...tical 6 If fire does not extinguish land immediately NOTE If the location source of the electrical fire can be determined and electrical power can be removed from that system location by isolating switching the system off do so This may alleviate the need to switch off the master switch For aircraft equipped with a 912 iS engine refer to the applicable supplement at the end of this manual with reg...

Page 61: ...ure follow the procedure for electrical fires in flight 3 4 5 Alternatively 1 Cabin heat close 2 Use the fire extinguisher if possible 3 Ventilate cabin if required applicable open air vents on instrument panel 4 If fire is extinguished consider executing a precautionary landing land as soon as practical 5 If fire does not extinguish land immediately ...

Page 62: ... most suitable landing location free of obstacles and preferably into wind 4 Safety harness tighten 5 Engine restart if time permits and if appropriate attempt to identify reason for engine failure and attempt restart 6 Flaps extend as needed 7 Communications report your location to third parties if possible 8 Passenger brief Immediately before touchdown 9 Fuel selector shut off 10 Electric fuel p...

Page 63: ...the landing location via radio 3 Perform a low altitude pass into wind over the right hand side of the selected area with flaps extended as required and thoroughly inspect the landing area 4 Perform a circuit pattern 5 Perform approach at increased idle with flaps fully extended 6 Reduce power to idle when flying over the runway threshold and touch down at the very beginning of the selected area 7...

Page 64: ... lowest practical speed with the aircraft slightly banked towards the serviceable tire wheel Maintain directional control during the landing run and keep the flat tire damaged wheel off the ground just above or very lightly on the ground until the lowest speed possible 2 If the nose wheel is damaged flat perform touch down at the lowest practical speed and hold the nose wheel off the ground as lon...

Page 65: ...lumn or push forward if necessary to lower nose then recover from dive ensuring VNE and load factor limitations are not exceeded In the unlikely event that applied control inputs result in the aircraft entering a flat spin and the steps listed above do not result in recovery following their application for a sustained period the following technique may be implemented 1 Throttle set to full power 2...

Page 66: ...ain straight and level flight utilizing other instruments and ground references 2 Switch the EFIS back up battery and the EFIS main switch off i e remove power from the EFIS 3 Following a 3 second delay apply power to the EFIS maintaining straight and level flight at all times 4 Maintain straight and level for at least another 15 seconds while the system boots up when the system reboots the naviga...

Page 67: ... of engine temperatures To recover the engine power the following procedure is recommended 1 Speed 75 KIAS 2 Throttle 1 3 power 3 If possible leave the icing area 4 Increase the engine power gradually up to cruise conditions after 1 to 2 minutes If you fail to recover engine power land on the nearest airfield if possible or depending on the circumstances perform a precautionary landing according t...

Page 68: ...ch off 2 All non critical electrical equipment off navigation strobe taxi landing lights etc 3 Auxiliary fuel pump off 4 Autopilot off 5 Set EFIS brightness to minimum 6 Restrict avoid the use of the elevator trim control Restrict radio transmission to minimum only that which is absolutely necessary 7 Land as soon as possible NOTE The 912 ULS engine operation is independent from the aircraft main ...

Page 69: ...aph 7 17 under Main bus for a list of equipment affected by a loss of power to the main bus 1 The EFIS should automatically switch over to the EFIS back up battery supply provided that the EFIS battery back up switch is on if not switch on the EFIS battery back up switch and the back up battery contains adequate charge 2 Land as soon as possible ...

Page 70: ...Use of taxi landing strobe and navigation lights 4 4 4 4 Pre flight check 4 5 4 5 Engine start 4 10 4 6 Taxi 4 11 4 7 Normal take off 4 12 4 8 Climb 4 14 4 9 Cruise 4 15 4 10 Descend 4 15 4 11 Approach 4 16 4 12 Normal landing 4 17 4 13 Baulked landing procedures 4 18 4 14 Short field take off and landing procedures 4 18 4 15 Engine shutdown 4 19 4 16 Aircraft parking and tie down 4 20 ...

Page 71: ... altitude gain over a given horizontal distance i e largest climb angle VY Best Rate of Climb Speed 72 The speed at MAUW flaps fully retracted which results in the greatest altitude gain over a given time period VROT Rotation Speed 40 The speed at which the aircraft should be rotated about the pitch axis during take off i e the speed at which the nose wheel is lifted off the ground VLOF Lift off S...

Page 72: ...strians wildlife Landing lights should be used as appropriate and their use should be incorporated in the applicable before take off take off climb approach and landing procedures as required Give consideration to landing lights as an aid to enhancing the aircraft s visibility to other traffic pedestrians wildlife Strobe and navigation lights should be used as appropriate and their use should be i...

Page 73: ...ctions in the Inspection Check List Inspection check List 1 Cabin Magnetos ignition off Master switch on Fuel level indicator verify fuel quantity Flaps move to full down position Master switch off Avionics verify condition Control System visual inspection free movement up to stops verify function Canopy attachment condition clean Cockpit check for loose objects Fire extinguisher verify present an...

Page 74: ...k Engine checks as per Rotax manual complete Other actions according to the engine manual Parachute cover if fitted check sealed and secure Tire condition inflation wear Wheels security general condition Chocks and tie down ropes remove Suspension and undercarriage check and test CAUTION In case of long term parking it is recommended to turn the engine over several times Ignition OFF by turning th...

Page 75: ...inflation and wear Wheel strut condition cracks Leading edge condition check Taxi landing lights and lens check for cracks and condition Fuel vent underside of wing unobstructed Wing trailing edge check condition Aileron freedom of movement attachment surface condition Aileron hinges control horn bolts pushrod secure condition Flap hinges control horn bolts pushrod secure condition Wing tip check ...

Page 76: ... Horizontal and vertical stabilizers check condition Elevator and tab condition and movement Rudder condition and movement Hinges control horns bolts pushrod condition and secure 6 Left Fuselage Surface condition check Cowling attachment check Wing fuselage fairings check Empennage fairings check Antenna e check condition and security ...

Page 77: ...Leading edge condition check Taxi landing lights and lens check for cracks and condition Fuel vent underside of wing unobstructed Wing trailing edge check condition Aileron freedom of movement attachment surface condition Aileron hinges control horn bolts pushrod secure condition Flap hinges control horn bolts pushrod secure condition Wing tip check condition Strobe Nav light and lens check for cr...

Page 78: ...1 Before starting engine 1 Pre flight inspection completed 2 Emergency equipment on board 3 Passenger briefed 4 Seats seatbelt and harnesses adjust and secure 5 Brakes on CAUTION In case of long term parking it is recommended to turn the engine over several times Ignition magnetos OFF by turning the propeller in order to prime the lubrication system Always handle the propeller blade area with the ...

Page 79: ...ck up battery voltage 3 Magneto ignition switches on 4 Fuel selector open RIGHT 5 Electric fuel pumps both on 912 iS 6 Choke cold engine pull to open and gradually release after engine start 912 ULS 7 Throttle closed if choke used cracked just open if not 8 Propeller area clear of people and obstructions 9 Starter engage maximum 10 seconds Immediately after start up 10 Throttle adjust for smooth r...

Page 80: ...rify the oil pressure which should increase within 10 seconds Increase the engine speed only if oil pressure is steady above 2 bar 29 psi At an engine start with low oil temperature continue to watch the oil pressure as it could drop again due to the increased resistance in the suction line Increase engine rpm only as required to keep oil pressure steady To avoid shock loading start the engine wit...

Page 81: ...he maximum difference in rpm drop between magnetos ignition circuits should not exceed 115 rpm 912 ULS For verification of ignition circuits on an aircraft fitted with a 912 iS engine refer to the applicable supplement at the end of this manual Set maximum power for verification of maximum engine speed rpm with given propeller and engine parameters temperatures and pressures Check acceleration fro...

Page 82: ...p brake valve park brake is off 3 Controls neutral position or as required for wind 4 Power and brakes as required 5 Brakes verify 6 Instruments verify Apply power and brakes as needed Apply brakes to control movement on ground Taxi carefully when wind velocity exceeds 15 knots Hold the control stick in neutral position or as required using conventional techniques ...

Page 83: ...onfirm 6 Fuel selector open RIGHT 7 Electric fuel pump on 912 ULS Auxiliary electric fuel pump on 912 iS 8 Circuit breakers all in 9 Instruments verify all 10 Altimeter set QNH QFE 11 Switches verify as required 12 Power and ignition verify magnetos at 4 000rpm max diff 115 rpm max drop 300 rpm 912 ULS 13 Engine parameters verify temperatures pressures current voltage 14 Canopy closed and latched ...

Page 84: ... ft 7 Electric fuel pump off 912 ULS minimum 300 ft Auxiliary electric fuel pump off 912 iS 300 ft minimum 8 Brakes apply briefly to stop wheel rotation 9 Transition to climb CAUTION Ensure that engine oil temperature is above 50 C prior to take off Climbing with engine at 5 800 rpm is permissible for 5 minutes Thereafter a maximum continuous engine rpm of 5 500 applies WARNING Take off is prohibi...

Page 85: ...KIAS VY 72 KIAS cruise climb 75 to 90 KIAS 3 Trim as required 4 Instruments verify oil temperature and pressure cylinder temperature within limits CAUTION If the cylinder head temperature or oil temperature approach their limits reduce the climb angle to increase airspeed and thus fulfill the limits CAUTION Climbing with engine at 5 800 rpm is permissible for 5 minutes Thereafter a maximum continu...

Page 86: ... leading to engine stoppage This poses a particular threat when at low altitude typically prior to landing WARNING If a fuel lift pipe is exposed to air the pump will suck air into the engine from the empty tank and engine failure will result When one tank is empty or close to empty the fuel selector valve should be switched to the fullest tank Avoid operation below the normal operational oil temp...

Page 87: ...Wing flaps extend as required 6 Trim as needed 7 Brakes off carefully check that the brake stop valve is off CAUTION It is not advisable to reduce the engine throttle control lever to minimum on final approach and when descending from very high altitude In such cases the engine can become over cooled although unlikely and a loss of power may occur Descent at increased idle approximately 3000 rpm s...

Page 88: ...fter landing 1 Engine speed set as required for taxi 2 Wing flaps retract CAUTION Rapid engine cooling should be avoided during operation This especially happens during aircraft descent taxi low engine rpm or at engine shutdown immediately after landing Under normal conditions the engine temperatures stabilize during descent and taxi at values suitable to stop the engine by switching the ignition ...

Page 89: ...red 3 Wing flaps retract to 50 as soon as possible and retract fully when reaching 65 KIAS at 300 ft minimum height 4 Electric fuel pump off 912 ULS 300 ft minimum Auxiliary electric fuel pump off 912 iS 300 ft minimum 5 Trim adjust 6 Repeat circuit pattern 4 14 Short field take off and landing procedures Not considered necessary Ordinary short field procedures may be used if pilot deems it approp...

Page 90: ...itches off 7 EFIS off battery back up off 8 Master switch off 9 Fuel selector off CAUTION Rapid engine cooling should be avoided during operation This especially happens during aircraft descent taxi low engine rpm or at engine shutdown immediately after landing Under normal conditions the engine temperatures stabilize during descent and taxi at values suitable to stop the engine by switching the i...

Page 91: ...k as necessary 7 Secure the airplane NOTE Use the anchor eyes on the wings and fuselage rear section to secure the airplane Move control stick forward and secure it together with the rudder pedals if high winds are expected Make sure that the cockpit canopy is properly closed and locked NOTE It is recommended that the parking brake shutoff valve be utilised for short period parking only If the air...

Page 92: ...ook Page 5 1 5 2 Date of Issue 07 July 2014 Revision 1 3 5 PERFORMANCE 5 1 Take off and landing distance 5 3 5 2 Rate of climb 5 4 5 3 Cruise speeds with fixed pitch propeller 5 5 5 4 Fuel consumption 5 6 5 5 Airspeed indicator system calibration 5 7 ...

Page 93: ... ISA conditions The performance shown in this section is valid for aircraft fitted with a ROTAX 912 ULS 73 5kW 98 6 hp engine or a ROTAX 912 iS 73 5kW 98 6 hp engine with a 72 inch 3 blade fixed pitch Warp drive composite propeller 5 1 Take off and landing distance Take off distances Surface Take off run Take off distance over 15m 50 ft obstacle Concrete 120 m 395ft 230 m 755 ft Grass 140 m 460 ft...

Page 94: ...ge 5 4 Date of Issue 07 July 2014 Revision 1 3 5 2 Rate of climb Conditions Max continuous power 5 500 rpm Weight 600 kg 1320 lb Best rate of climb speed VY Rate of climb KIAS fpm 0 ft ISA 72 800 3 000 ft ISA 72 600 6 000 ft ISA 72 500 9 000 ft ISA 72 400 ...

Page 95: ...ch propeller Altitude ft ISA Engine speed rpm KIAS KTAS 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 96: ... Fuel consumption Altitude ft ISA 3 000 Fuel quantity l 150 US gallons 39 6 Engine speed rpm 4 500 4 800 5 000 5 300 5 500 Fuel consumption l h 14 16 18 20 21 US gallons 3 7 4 2 4 8 5 3 5 5 Airspeed KIAS 73 91 104 109 114 Endurance hh mm 10 40 9 20 08 20 07 30 07 10 Range no reserve nm 781 853 866 817 815 ...

Page 97: ...e 07 July 2014 Revision 1 3 5 5 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 98: ...andbook Page 6 1 6 2 Date of Issue 07 July 2014 Revision 1 3 6 WEIGHT AND BALANCE 6 1 Installed equipment list 6 3 6 2 Center of gravity CG range 6 4 6 3 Determination of CG 6 6 6 4 Empty CG determination 6 7 6 5 Blank form and graph for use 6 8 ...

Page 99: ...d balance records and the payload range for safe operating of the Sling LSA 6 1 Installed equipment list MGL multifunction glass cockpit instrument Challenger iEFIS MGL V6 COM radio Mode S transponder optional Analogue altimeter airspeed indicator ball type slip indicator Magnetic compass Electric trim system Electric flap actuator ...

Page 100: ... range and allowable GC envelope GC range is 1 635 mm 5 364 ft to 1 772 mm 5 814 ft aft of the reference datum 20 to 30 3 of MAC The leading edge of the MAC is 1 366 mm 4 482 ft aft of the reference datum The MAC is 1 339 mm 4 393 ft WARNING Aircraft CG and MAUW limitations must be adhered to at all times DIMENSIONS IN THIS DRAWING ARE IN FEET ...

Page 101: ...Limits MAC Allowable CG Envelope WARNING Aircraft CG and MAUW limitations must be adhered to at all times WARNING For each flight the most forward CG i e with take off fuel and the most rearward CG i e with landing fuel must be calculated to be within aircraft CG range limits FLIGHT ALLOWED IN SHADED AREA ONLY 771 62 881 85 992 08 1102 31 1212 54 1332 77 1433 Aircraft Mass lb ...

Page 102: ...ent arm Total Weight MAC CG 1366 mm x 100 1 339 mm MAC CG 4 482 ft x 100 4 393 ft The aircraft empty CG is determined in a conventional manner by weighing the aircraft whilst it is standing level Refer to the aircraft maintenance manual for instructions on aircraft leveling and weighing WARNING For each flight the most forward CG i e with take off fuel and the most rearward CG i e with landing fue...

Page 103: ...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 548 1 797 Computed empty CG Empty weight WE kg lb CG mm ft MAC Aircraft moment Maximum all up take off weight 600 kg 1320 lb Maximum useful load example Wmax useful WMAUW WE 600 kg 1320 lb 370 kg 815 lb 230 kg 507 lb ...

Page 104: ...8 Date of Issue 07 July 2014 Revision 1 3 6 5 Blank 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 ADD EMPTY VALUES TOTAL WT MT CG MAC ...

Page 105: ...ating Handbook Page 6 9 Date of Issue 07 July 2014 Revision 1 3 350 400 450 500 550 600 650 16 18 20 22 24 26 28 30 32 Aircraft Mass kg CG Limits MAC Allowable CG Envelope 771 62 881 85 992 08 1102 31 1212 54 1332 77 1433 Aircraft Mass lb ...

Page 106: ...static systems 7 8 7 9 Cockpit layout 7 9 7 10 Instruments and Avionics 7 11 7 11 Flap and elevator trim systems 7 16 7 12 Minimum instruments and equipment required for flight 7 17 7 13 Engine 7 18 7 14 Cooling system 912 ULS 912 iS 7 19 7 15 Throttle and choke 7 20 7 16 Carburetor pre heating anti ice 7 20 7 17 Electrical System 7 20 7 18 Propeller 7 28 7 19 Fuel system 7 28 7 20 Lubrication sys...

Page 107: ...ks to its durability and corrosion resistant characteristics The wing has a high lift airfoil NACA 4415 and is equipped with semi slotted Fowler type flaps 7 2 Control system pilot controls Control stick s The aircraft is equipped with dual control sticks The control sticks operate in the standard pitch and roll elevator and aileron configuration See the picture below for control stick button allo...

Page 108: ...tom center of the instrument panel front of center console Refer to the instrument panel layout in paragraph 7 10 An additional knob must be activated to move the selection lever through a detent to the OFF position preventing inadvertent closure OFF selection of the valve Ballistic parachute activation lever if fitted The red colored activation lever is located at the bottom center of the instrum...

Page 109: ... Switch power from main bus to EFIS system on off UP ON DOWN OFF EFIS BKUP Connects EFIS system to EFIS back up battery supply FUEL 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 Switch power to radio and transponder if fitted on off AUTOPILOT Switch po...

Page 110: ... buttons on the control column Refer to Control stick s for button allocation Refer to paragraph 7 11 Flap control Wing flaps are electrically controlled and selected for position by a four position rotary knob or a four pushbutton selector located on the instrument panel refer to paragraph 7 10 Refer to paragraph 7 11 Cabin heat Heated air warmed by heat exchange with engine exhaust can be select...

Page 111: ... 4 Brake system The aircraft braking system is typically a single hydraulic system acting on both wheels of the main landing gear through disk brakes Activation is via a lever located on the cabin center console Refer to paragraph 7 9 An intercept valve acts as a parking brake by stopping pressure relief For braking to be operational the brake intercept valve must be off and the brake lever activa...

Page 112: ... forward movement slightly raising the seat height IMPORTANT Ensure that the seat s is are securely locked into position after adjustment 7 6 Baggage compartment The baggage compartment comprises two sections positioned behind the seats and is designed to carry up to 15 kg 77 lb in total The baggage compartment comprises a narrow slightly lowered front section and a higher larger back section Subj...

Page 113: ...equipped with a sliding canopy mechanism External access to the cabin is from either side Latching mechanisms are provided inside the cabin at the top of the roll over bar in the center and outside on the center of the canopy WARNING Ensure that the canopy mechanism is securely latched into position before operating the aircraft ...

Page 114: ...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 that the pitot tube cover is removed prior to every flight and that it is replaced after every flight Pitot and static system example Please note that this drawing is representative of a pitot and static system only and may differ from the actual instal...

Page 115: ...ic 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 below Cockpit layout 11 12 ...

Page 116: ...r vents are located on the lower right and left sides of the instrument panel Baggage space is immediately behind the seats A fire extinguisher is held in place against the front retaining wall of the baggage space An adjustable red interior cockpit light is positioned behind and between the pilot and passenger s heads on rear fuselage front former structure 1 Instrument panel 7 Throttle 2 Air ven...

Page 117: ...h the aircraft The instrument panel in any particular aircraft may differ from that illustrated in the diagram It is the responsibility of the pilot to ensure that s he is familiar with the instrumentation in the aircraft its layout and its operation Standard instrument panel 912 ULS refer to key on next page NOTE Rotax 912 iS equipped aircraft will have in addition to the above two switches for t...

Page 118: ...Master switch and starter 13 Cabin heat activator 2 Ignition Magneto switches 14 Cubby hole 3 Charge warning light 912 ULS 15 12 V Power port socket 4 MGL EFIS 16 Air vent 5 EFIS accessory warning light 17 Circuit breakers 6 Analogue airspeed indicator 18 Blank off Ballistic recovery parachute activator handle if fitted 7 Analogue magnetic compass 19 Fuel selector valve 8 Analogue altimeter 20 Fla...

Page 119: ...entation provided by the EFIS will typically include ASI IAS as well as TAS and ground speed ALT and typically also height above ground VSI Compass Attitude indicator Turn coordinator G meter load factor meter Clock stopwatch and flight time record Comprehensive mapping and navigation software and data including GLS GPS Landing System capability GPS Autopilot if servos are fitted Full engine monit...

Page 120: ...it and will not be dealt with in this handbook Refer to the supplied EFIS documentation Autopilot functionality is incorporated in the EFIS Refer to paragraph 7 21 for additional information The EFIS is operated during flight with the EFIS back up battery selection switch on at all times This will ensure automatic switch over of the EFIS to the EFIS back up battery in the event that power is lost ...

Page 121: ... Set the EFIS screen brightness to the minimum acceptable for readability to reduce current drain on the back up battery WARNING Users should desist from entering the EFIS setup pages during flight as changes to the setup may result in incorrect readings and or warnings resulting in safety degradation ...

Page 122: ... located on the instrument panel refer to paragraph 7 17 2 The trim motor is located in the port elevator and drives a trim tab via a pushrod system located on the elevator trailing edge Pilot control is via buttons located on the control stick s Refer to paragraph 7 2 for button allocation In 912 ULS equipped aircraft the trim system is powered via a circuit breaker located on the instrument pane...

Page 123: ...ndicator Cylinder head temperature indicator Outside air temperature indicator Tachometer Chronometer First aid kit compliant with national legislation Fire extinguisher 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 except where speci...

Page 124: ...d lubrication and has a dual contactless capacitor discharge magneto type ignition system The engine is fitted with an electric starter AC generator alternator and mechanical fuel pump A back up electrical fuel pump is fitted Propeller drive is via reduction gear with integrated shock absorber The engine will continue to run after an alternator and or battery failure See the manufacturer documenta...

Page 125: ...the firewall When cooling down the coolant in the overflow bottle is sucked back into the cooling circuit Refer to the latest revision edition of the applicable Rotax engine operator and maintenance manuals Coolant type 912 ULS For aircraft fitted with the 912 iS engine refer to the supplement at the end of this manual Either water free propylene glycol based coolant concentrate or conventional et...

Page 126: ... positioned in the left center of the instrument panel Refer to paragraph 7 10 Pulling out the choke knob activates the choke mechanism Both controls throttle and choke are mechanically connected via cables to activators levers on the carburetors 7 16 Carburetor pre heating anti ice N A 7 17 Electrical System Refer to the applicable supplement at the end of this manual for aircraft equipped with a...

Page 127: ...e the main battery Charge system output is approximately 13 5 to 14 V DC from 1000 250 rpm and higher The charge system output is connected to the battery main bus via a charge relay Refer to paragraph 7 17 1 The charge relay coil is powered from the main bus i e needs power from the main bus to remain energized closed Loss of power to the main bus will result in the charge relay de energizing and...

Page 128: ... show a reduced reading Main battery The 12 V main battery is mounted on the engine side of the firewall Main bus Refer to the applicable supplement at the end of this manual for aircraft fitted with a 912 iS engine When power to the main bus is unavailable fails the following equipment becomes non operational 1 Auxiliary electric fuel pump 912 ULS 2 Flaps 3 Autopilot i e the autopilot servos 4 Ra...

Page 129: ...firewall under the instrument panel The EFIS back up circuit can be operated independently from the main bus i e with power to the main bus unavailable Master and starter switch es See the applicable supplement at the end of this manual with regard to the Master starter switch es on 912 iS equipped aircraft The master switch and starter switch es are incorporated into a key switch mounted on the i...

Page 130: ... change or installed as requested Refer to the Aircraft Equipment List Circuit breakers Circuit breakers are push to reset i e push in for restoring supplying electrical power to their corresponding electrical circuits Refer to paragraphs 7 17 1 and 7 17 2 Circuit breakers are located on the instrument panel Refer to paragraph 7 10 NOTE The engine 912 ULS 912 iS ignition system is independent of t...

Page 131: ...Airplane Factory SLING LSA Pilot Operating Handbook Page 7 25 Date of Issue 07 July 2014 Revision 1 3 7 17 1 Charge system start system electric fuel pump wiring diagram 912 ULS ...

Page 132: ...Airplane Factory SLING LSA Pilot Operating Handbook Page 7 26 Date of Issue 07 July 2014 Revision 1 3 7 17 2 Switches and circuit breakers wiring diagram 912 ULS ...

Page 133: ...Airplane Factory SLING LSA Pilot Operating Handbook Page 7 27 Date of Issue 07 July 2014 Revision 1 3 7 17 3 EFIS back up circuit battery back up wiring diagram ...

Page 134: ...turn lines return excess fuel supplied by the fuel pump to the fuel tank The system is configured as in the diagram below Volume of each wing tank is 75 liters 19 8 US gal 73 liters 19 28 US gal useable NOTE For technical data refer to documentation supplied by the propeller manufacturer WARNING The fuel lift pipe in each fuel tank is situated adjacent to the lower inside wall of the tank The airc...

Page 135: ...4 Revision 1 3 Fuel system 912 ULS A Port left fuel tank G Barbed T piece B Starboard right fuel tank H Fuel flow sensor C Fuel selector I Port left carburettor D Fuel filter 90 bend J Fuel pressure sensor E Electric auxiliary fuel pump K Starboard right carburettor F Mechanical fuel pump ...

Page 136: ...g from the points of lubrication gathers 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 oil pump housing The lubrication circuit is vented at the oil reservoir The oil reservoir is mounted on the firewall Refer to the latest revision edition of the Rotax 912 ULS engine operator and maint...

Page 137: ...ILOT located on the instrument panel refer to paragraph 7 17 2 This switch must be on for the autopilot EFIS outputs to have any effect on aircraft attitude The autopilot can be engaged in several ways The autopilot engage disengage button on the control stick s refer to paragraph 7 2 Via the EFIS keypad The autopilot can be disengaged in several ways The autopilot engage disengage button on the c...

Page 138: ...ollision light white is fitted on top of the rudder The white lights on the wingtips and rudder are dual function lights that can either be on continuously position light flash anti collision strobe light or flash at a higher brightness level superimposed on continuous operation i e combination position and anti collision strobe light Position and anti collision light functioning is dependent upon...

Page 139: ...NDLING AND SERVICING 8 1 Introduction 8 3 8 2 Servicing fuel oil and coolant 8 3 8 3 Towing and tie down mooring instructions 8 4 8 4 Parking 8 6 8 5 Jacking 8 6 8 6 Road transport 8 7 8 7 Cleaning and care 8 7 8 8 Assembly and Disassembly 8 8 8 9 Aircraft inspection periods 8 8 8 10 Aircraft modifications and repairs 8 9 ...

Page 140: ...inspection and maintenance requirements which should be followed at all times Full details for servicing and maintenance appear in the aircraft maintenance manual This document does not replace the maintenance manual Reference should always be made to the maintenance manual 8 2 Servicing fuel oil and coolant Refer to the appropriate chapters in the applicable Rotax engine maintenance and operator ...

Page 141: ...ose to the root directly over the front spar at the point where it attaches to a rib in order to lift the nose of the aircraft for maneuvering purposes It is best to press down on both points at once to spread the load It is also acceptable to push the aircraft carefully backwards by putting pressure on the wing leading edges close to the root directly on a nose rib or on the horizontal stabilizer...

Page 142: ...oring procedure 1 Verify Fuel selector shut off circuit breakers and Master switch switched off 2 Verify Magnetos switched off 3 Secure the control column s using for example a safety harness 4 Close air vent 5 Close and lock canopy 6 Moor the aircraft to the ground by means of a mooring rope passed through the mooring eyes located on the lower surfaces of the wings and below the rear fuselage NOT...

Page 143: ...g manner By pushing the fuselage rear section down above a bulkhead the fuselage front section may be raised and then supported under the firewall The same effect can be achieved by pressing down on the horizontal stabilizer as described under 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 a la...

Page 144: ...r 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 quantity of detergents Use either a soft clean cloth sponge or deerskin Then use suitable polishers to clean the canopy Upholstery and covers may be removed from the cockpit brushed and washed in lukewarm water with an adequate quantity of deter...

Page 145: ...nce depend upon operating conditions and overall condition of the aircraft Inspections and revisions should be carried out according to at least the following periods After the first 25 flight hours thereafter at 50 flight hours thereafter after every 100 flight hours or annually whichever is soonest Refer to the engine operator s manual for engine maintenance Maintain the propeller according to t...

Page 146: ...y modifications to the aircraft to ensure that the airworthiness of the aircraft is not affected Always use only original spare parts produced by the aircraft or engine propeller manufacturer as the case may be If the aircraft weight is affected by a modification a new mass and balance calculation is necessary This should be completed comprehensively and new data figures should be recorded in all ...

Page 147: ...ents necessary to safely and efficiently operate the aircraft when equipped with various optional systems and equipment not provided with the standard airplane List of inserted supplements Date Suppl 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 iS engine ...

Page 148: ...the operation of an aircraft fitted with a Magnum 601 ballistic parachute 1 The Sling LSA is designed specifically for convenient fitment of a Magnum 601 ballistic parachute recovery system The system is designed to enable the pilot or passenger to deploy the parachute in case of emergency in such a manner that the aircraft structure is carried under the parachute to the ground on the basis that t...

Page 149: ...chute operational parameters Throttle close Magneto ignition switches off Fuel pump s off Fuel selector off Deploy the parachute by pulling the T shaped activation handle situated in the center front positively Master and avionics switch as dictated by radio communication requirements off before impact with ground Other electrical equipment switches off ...

Page 150: ...x 912 iS engine The Rotax 912iS comprises a fuel injected and electronically controlled variant of the Rotax 912 ULS engine It has the same power rating as the Rotax 912 ULS engine and airplane performance with the two engines is accordingly materially similar save for fuel economy which particularly in the cruise may be materially better in the case of the 912 iS engine Notwithstanding this howev...

Page 151: ...st edition revision of the Rotax 912 iS operators manual for latest information regarding operating limitations ENGINE START AND OPERATION TEMPERATURE LIMITS Maxim in flight 60 C 140 F manifold temperature Maximum at start 50 C 122 F ambient temperature Minimum at start 20 C 4 F oil temperature ENGINE LOAD FACTOR ACCELERATION LIMITS Maximum 5 seconds at maximum 0 5 g ...

Page 152: ...minutes Max continuous 5500 rpm Cruise 4 600 rpm to 5 400 rpm Idle 1 400 minimum EGT Maximum 950 C Cylinder head temperature Minimum N A Maximum 150 C 302 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 Oil pressure Minimum 0 8 bar 12 psi below 3500 rpm Maximum 7 bar 102 psi permissible for a short period on cold engine start...

Page 153: ... Ethylene glycol based coolant and distilled water mixture WATER FREE COOLANT NOT PERMITTED FOR USE WITH 912 iS Refer to the latest revision of the Rotax 912 iS operator maintenance manuals and to the latest revision of Rotax service instruction SI 912i 001 with regard to selection of operating fluids FUEL 912 iS Minimum RON 95 Minimum AKI 91 Grade MOGAS DIN EN 228 Super DIN EN 228 Super Plus 91 U...

Page 154: ...ndbook Page 9 9 Date of Issue 07 July 2014 Revision 1 3 ROTAX 912 iS FUEL SYSTEM A Port left fuel tank F Fuel filter B Starboard right fuel tank G 912 iS engine C Fuel selector H Fuel pressure transducer D Fuel filter 90 bend E Fuel pump assembly ...

Page 155: ...Main FUEL PUMP 2 Auxiliary Main and auxiliary fuel pumps The main and auxiliary fuel pumps are powered via the EMS ECU As long as power is available to the EMS ECU via Alternator A Alternator B in event of Alternator A failure or via the main battery the EMS battery back up switch is on any one or both of the fuel pumps can be selected operational irrespective of the master switch status SUPPLEMEN...

Page 156: ... the EMS ECU is automatically switched over to Alternator B Note that in this event Alternator B output is not or only partially available to the aircraft systems and that no or reduced main battery charging can occur Subsequent failure of Alternator B will result in engine stoppage In that event power EMS ECU back up voltage can be supplied to the EMS ECU system via the aircraft system main batte...

Page 157: ...UP Connects EFIS system to EFIS back up battery supply FUEL PUMP 1 Switch main fuel pump in off FUEL PUMP 2 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 Switch power to radio and transponder if fitted on off ECU BKUP Connects the EMS ECU to the main batter...

Page 158: ...rectly connected to the main bus via a circuit breaker and not via the master switch as in 912 ULS engined aircraft This implies that with the Master switch turned off The main bus remains powered provided that the charge system output is operational In the case where Alternator B is used to power the EMS ECU i e Alternator A failed power may not be available the main bus or reduced power may be a...

Page 159: ...Airplane Factory SLING LSA Pilot Operating Handbook Page 9 14 Date of Issue 07 July 2014 Revision 1 3 START SYSTEM ELECTRIC FUEL PUMPS WIRING DIAGRAM 912 iS ...

Page 160: ...Airplane Factory SLING LSA Pilot Operating Handbook Page 9 15 Date of Issue 07 July 2014 Revision 1 3 SWITCHES AND CIRCUIT BREAKERS WIRING DIAGRAM 912 iS ...

Page 161: ...ator and oil filter to points of lubrication Surplus oil emerging from the points of lubrication gathers 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 mounted on the firewall Refer to the latest revisi...

Page 162: ...y switched over to Alternator B Note that in this event Alternator B output is not or only partially available to the aircraft systems to charge the main battery Procedure as in paragraph 3 7 4 Alternator A failure is evidenced by the steady illumination of the Lane A red warning light The main bus system voltage indication on EFIS could show a reduced reading and a battery discharge current may b...

Page 163: ... up switch Procedure as in paragraph 3 7 4 WARNING The engine will continue to run after an Alternator B failure with Alternator A still operative as the EMS ECU is still powered by Alternator A However since no charging of the battery occurs in this circumstance all non critical electrical equipment should be switched off to conserve battery charge as the battery would be needed to supply power t...

Page 164: ... EFIS on and back up battery voltage 3 Magneto ignition switches Lane A and B on both 4 EMS battery back up switch on Once power EMS battery back up is switched on is supplied the Lane A and Lane B warning lights should illuminate for approximately 5 seconds and then extinguish If either or both lights flash or fails to illuminate it is indicative of a deficiency 5 Fuel selector select emptiest ta...

Page 165: ...22 F 15 EMS battery back up switch off At an engine start with low oil temperature continue to watch the oil pressure as it could drop again due to the increased resistance in the suction line Verify all engine instrument readings CAUTION The starter should be activated for a maximum of 10 seconds followed by a at least 2 minute pause to allow the starter to cool Verify the oil pressure which shou...

Page 166: ...RMATION BEFORE TAKE OFF Check the Lane A and Lane B ignition circuits at 4 000 rpm No rpm drop should occur when Lane B is switched off An rpm drop of less than 180 rpm is permissible when Lane A is switched off Please read the applicable Rotax Operators Manual for further information in relation to the use of the engine ...

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