Airplane Factory Sling-2 Pilot Operating Handbook Download Page 41

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Airplane Factory SLING 2

Pilot Operating Handbook

Page | 2-13

DC-POH-002-X-B-6

Revision : 2.6

ENGINE OPERATING AND SPEEDS LIMITS (912 ULS)

Engine Model:

ROTAX 912 ULS

Engine Manufacturer:

Bombardier-Rotax GMBH

Power

Maximum take-

off

73.5 kW (98.6 hp) at 5800 rpm, max. 5 min.

Maximum

continuous

69 kW (92.5 hp) at 5500 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

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

Summary of Contents for Sling-2

Page 1: ......

Page 2: ...erial Number Date of Construction Registration Airworthiness Category CS VLA Very Light Aircraft Issue Date of POH 2018 09 21 PLEASE ADVISE THE AIRPLANE FACTORY ON CHANGE OF OWNERSHIP OF THE AIRCRAFT...

Page 3: ...ING 2 AIRCRAFT AS MANUFACTURED ON PREMISES BY THE AIRPLANE FACTORY PTY LTD ARE INCLUDED IN APPLICABLE SUPPLEMENTS IN SECTION 9 OF THIS HANDBOOK AIRCRAFT WHICH DIFFER FROM THE PRODUCTION STANDARD IN WH...

Page 4: ...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 Date of approval Date inserted Sign 1 1...

Page 5: ...2 6 1 17 Not Revised 2 4 vii Revised 2 6 1 18 Not Revised 2 4 viii Revised 2 6 1 19 Revised 2 6 ix Revised 2 6 1 20 Revised 2 6 x Revised 2 6 2 1 2 2 Not Revised 2 4 1 1 1 2 Not Revised 2 4 2 3 Not Re...

Page 6: ...ed 2 4 3 3 Not Revised 2 4 4 4 Not Revised 2 4 3 4 Not Revised 2 4 4 5 Revised 2 6 3 5 Not Revised 2 4 4 6 Revised 2 6 3 6 Not Revised 2 4 4 7 Revised 2 6 3 7 Not Revised 2 4 4 8 Revised 2 6 3 8 Not R...

Page 7: ...ot Revised 2 4 7 13 Revised 2 6 5 6 Not Revised 2 4 7 14 Revised 2 6 5 7 Not Revised 2 4 7 15 Revised 2 6 6 1 6 2 Not Revised 2 4 7 16 Not Revised 2 4 6 3 Revised 2 6 7 17 Not Revised 2 4 6 4 Revised...

Page 8: ...vised 2 4 7 34 Not Revised 2 4 9 12 Revised 2 6 7 35 Revised 2 6 9 13 Revised 2 6 7 36 Not Revised 2 4 9 14 Revised 2 6 8 1 8 2 Not Revised 2 4 9 15 Not Revised 2 4 8 3 Revised 2 6 9 16 Not Revised 2...

Page 9: ...ed 2 4 9 52 Not Revised 2 5 9 31 Not Revised 2 4 9 53 Not Revised 2 5 9 32 Not Revised 2 4 9 54 Not Revised 2 5 9 33 Not Revised 2 4 9 55 Not Revised 2 5 9 34 Not Revised 2 4 9 56 Not Revised 2 5 9 35...

Page 10: ...X B 6 Revision 2 6 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...

Page 11: ...2 X B 6 Revision 2 6 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 2 aircraft and systems 1 7 1 5 Termin...

Page 12: ...y minor modifications to the aircraft and the application of a revised Pilot Operating Handbook the Sling 2 may be made to comply with the requirements of the FAA Light Sport Aircraft LSA category acc...

Page 13: ...lot 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 procedu...

Page 14: ...Airplane Factory SLING 2 Pilot Operating Handbook Page 1 5 DC POH 002 X B 6 Revision 2 6 1 3 Aircraft 3 view drawing DIMENSIONS IN THIS DRAWING ARE IN MILLIMETRES...

Page 15: ...Airplane Factory SLING 2 Pilot Operating Handbook Page 1 6 DC POH 002 X B 6 Revision 2 6 DIMENSIONS IN THIS DRAWING ARE IN MILLIMETRES...

Page 16: ...7 m 19 ft Overall length 6 675 m 21ft 11 inch Overall width 1 18 m 45 inch Overall height 2 45m 98 inch EMPENNAGE Horizontal stabilizer span 2 825 m 9 ft 3 inch Horizontal stabilizer surface area 0 96...

Page 17: ...8 DC POH 002 X B 6 Revision 2 6 Nose gear tyres 5 00 5 6 ply 1 8 bar 26 107 psi pressure CONTROL SURFACE TRAVEL LIMITS Ailerons 24o up and down 2 Elevator 30o up and 20o down 2 Trim tab 8o up and 20o...

Page 18: ...buretors integrated reduction gearbox with torque damper Maximum power 73 5 kW 98 5hp at 5 800 rpm max 5 minutes 69 kW 92 5hp at 5 500 rpm continuous For Sling 2 aircraft fitted with the 912 iS or 914...

Page 19: ...perator maintenance manual and latest revision of service instruction SI 912 016 For aircraft fitted with the 912 iS or 914 UL engine refer to the applicable supplement at the end of this manual Fuel...

Page 20: ...ntenance manual and latest revision of service instruction SI 912 016 For aircraft fitted with the 912 iS or 914 UL engine refer to the applicable supplement at the end of this manual Capacity 3 5 lit...

Page 21: ...ximum landing weight 700 kg 1 543 23 lb Maximum baggage weight 35 kg 77 lb Front luggage compartment maximum 35 kg 77 lb Rear luggage compartment maximum 25 kg 55 lb STANDARD WEIGHTS Standard empty we...

Page 22: ...ASA European Aviation Safety Agency EFIS Electronic Flight Information System FAA Federal Aviation Authority GLS GPS Landing System GmbH Gesellschaft mit beschr nkter Haftung company with limited liab...

Page 23: ...mum 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 spe...

Page 24: ...ocal 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 su...

Page 25: ...ding run The distance measured 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...

Page 26: ...front face of the engine flange of the Rotax engine Empty weight The weight of the airplane with engine fluids and oil at operating levels MAC Mean Aerodynamic Chord MAUW Maximum All Up Weight Maximum...

Page 27: ...1 pound per square inch 6 895 kilopascal 1 inch 25 4 millimetres 1 foot 0 3048 metre 1 statute mile 1 609 kilometres 1 nautical mile 1 852 kilometres 1 millibar 1 hectopascal 1 millibar 0 1 kilopascal...

Page 28: ...For 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 4 For aircraft fitted with an Airmaster constant speed prope...

Page 29: ...g Handbook Page 1 20 DC POH 002 X B 6 Revision 2 6 Reference should be made to these documents for operational guidelines and instructions These should be incorporated into the normal and emergency pr...

Page 30: ...Stall speed adjustment for turning flight and 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 Centre of gravity rang...

Page 31: ...ith 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 excee...

Page 32: ...s VS0 at maximum weight and upper limit is the maximum speed Vfe permissible with flaps deployed Green arc 46 105 Normal Operating Range lower limit is VS at maximum weight most forward CG with flaps...

Page 33: ...sted 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 de...

Page 34: ...ice 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...

Page 35: ...eling Upper surface of canopy sliders on cockpit side skins with canopy open Reference transverse leveling Upper surface of centre spar cap under pilot and passenger seats Forward limit 1 635 m 5 364...

Page 36: ...d 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...

Page 37: ...t Operating Handbook Page 2 9 DC POH 002 X B 6 Revision 2 6 2 11Flight crew Minimum crew for flight is one pilot seated on the left side 2 12Passengers Only one passenger is allowed on board the aircr...

Page 38: ...emperature indicator Outside air temperature indicator Tachometer Chronometer First aid kit compliant with national legislation Fire extinguisher Subject to the legal requirements applicable in the co...

Page 39: ...applicable regulations should be complied with at all times NOTICE Provided that the aircraft is appropriately equipped the aircraft may also be safely flown in IMC and in accordance with IFR The equ...

Page 40: ...ays refer to latest edition revision of the Operators Manual for latest information regarding operating limitations ENGINE START AND OPERATION TEMPERATURE LIMITS 912 ULS Maximum 50 C 122 F ambient tem...

Page 41: ...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 temperatur...

Page 42: ...is allowed on board of the airplane VFR flights only are permitted 2 16Flight in rain When flying in the rain no additional steps are required Airplane qualities and performance are not substantially...

Page 43: ...On the instrument panel In a place visible to pilot and passenger OPERATE UNDER VMC ONLY MAXIMUM PERMISSABLE AIRSPEED 135 KIAS MAXIMUM PERMISSIBLE RPM 5 800 RPM FOR 5 MINUTES MAXIMUM CONTINUOUS RPM 5...

Page 44: ...g flap surface On a fireproof metal plate attached to the aircraft Note represents the information applicable to the aircraft AVGAS OR MOGAS 75 LITRES ZU CONSTRUCTOR THE AIRPLANE FACTORY MODEL SLING 2...

Page 45: ...ating Handbook Page 2 17 DC POH 002 X B 6 Revision 2 6 The airplane must be placarded to show the identity of All fuses circuit breakers Magneto ignition switches All other switches Choke Starter Trim...

Page 46: ...POH 002 X B 6 Revision 2 6 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 13 3 6...

Page 47: ...pplied as necessary to correct 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 ap...

Page 48: ...rical system switches off 3 3 2 Engine failure immediately after take off 1 Speed trim best glide speed 72 KIAS 2 Find a suitable place on the ground to land safely The landing should be planned strai...

Page 49: ...5 Change fuel selector valve to tank not in use if not empty If engine continues to run irregularly 6 Change to fullest tank 7 Land as soon as possible 3 3 3 2 Low fuel pressure refer to engine limita...

Page 50: ...ns low or temperature remains high or increasing 3 Land as soon as possible and remain vigilant for impending engine failure 3 3 4 In flight engine restart 1 Electric fuel pump on 912 ULS Electric fue...

Page 51: ...tion of the starter switch may be required If the propeller stops rotating increasing airspeed may result in it again starting to do so NOTE It is possible that the propeller may continue to rotate if...

Page 52: ...ff 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...

Page 53: ...ke off run 1 Throttle idle 2 Brakes stop the aircraft 3 Cabin heat close 4 Fuel selector close 5 Electric fuel pump s off 6 Magnetos ignition off 7 Master switch off 8 Retrieve fire extinguisher if po...

Page 54: ...d and engine has shut down 5 Electric fuel pumps both off 914 UL 912 iS 6 Choose landing area choose emergency landing area 7 Emergency landing perform according to 3 5 1 8 Retrieve fire extinguisher...

Page 55: ...urce 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 ma...

Page 56: ...low 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 pa...

Page 57: ...ty harness tighten 5 Engine restart if time permits and if appropriate attempt to identify reason for engine failure and attempt restart 6 Propeller if applicable if windmilling consider feathering to...

Page 58: ...ding where a propeller blade may dig into the landing surface due to an undercarriage failure or the like consideration should be given to leaving the propeller unfeathered NOTE The automatic feather...

Page 59: ...ding 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 circui...

Page 60: ...practical speed with the aircraft slightly banked towards the serviceable tyre wheel Maintain directional control during the landing run and keep the flat tyre damaged wheel off the ground just above...

Page 61: ...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 enter...

Page 62: ...aight 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 appl...

Page 63: ...emperatures 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 cruis...

Page 64: ...ropeller if applicable AUTO CLIMB or as desired 6 When propeller if applicable governs at climb setting MAN 7 Propeller switch if applicable off 8 Set EFIS brightness to minimum 9 Restrict avoid the u...

Page 65: ...manual Refer to paragraph 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 provide...

Page 66: ...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 13 4 7 Normal take off 4 14 4 8 Climb 4 16 4 9 Cruise 4 17 4 10 Descend 4 17 4 11 Approach 4 18...

Page 67: ...tude gain over a given horizontal distance i e largest climb angle VY Best Rate of Climb Speed 74 The speed at MAUW flaps fully retracted which results in the greatest altitude gain over a given time...

Page 68: ...pedestrians 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 Giv...

Page 69: ...t incident maintenance activity assembly of any aircraft component or suchlike Incomplete or careless inspection can result in an accident Carry out the inspection following the instructions in the In...

Page 70: ...y harnesses Verify condition security of attachment and operation of buckles Seats Verify security of attachment and correct operation of adjustment mechanism ensure seat mechanisms lock correctly aft...

Page 71: ...ut 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...

Page 72: ...ks as per Rotax manual complete Other actions according to the engine manual Parachute cover if fitted check sealed and secure Tyre condition inflation wear Wheels security general condition Chocks an...

Page 73: ...d 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 c...

Page 74: ...just and secure 5 Brakes on 4 5 2 Engine start If a Rotax 912 iS or 914 UL engine is installed rather than a Rotax 912 ULS engine please refer to the supplement at the end of this manual 1 Master swit...

Page 75: ...switch on and verify battery charging 15 Avionics master switch on 16 Warm engine 2 000 rpm for 2 minutes then 2 500 rpm until oil temp is 50 C 122 F CAUTION The starter should be activated for a max...

Page 76: ...maximum difference in rpm drop between magnetos ignition circuits should not exceed 115 rpm 912 ULS 914 UL For verification of ignition circuits on an aircraft fitted with a 912 iS engine refer to the...

Page 77: ...fy that the stop brake valve park brake is off 4 Controls neutral position or as required for wind 5 Power and brakes as required 6 Brakes verify 7 Instruments verify Apply power and brakes as needed...

Page 78: ...9 Instruments verify all 10 Altimeter set QNH QFE 11 Switches verify as required 12 Power and ignition verify magnetos at 4 000rpm max difference 115 rpm max drop 300 rpm 912 ULS 914 UL 13 Propeller c...

Page 79: ...300 ft 8 Electric fuel pump off 912 ULS minimum 300 ft Auxiliary electric fuel pump off 912 iS 914 UL 300 ft minimum 9 Brakes apply briefly brakes to stop wheel rotation 10 Transition to climb CAUTION...

Page 80: ...speed VX 65 KIAS VY 74 KIAS Cruise climb 75 to 90 KIAS 4 Trim as required 5 Instruments verify Oil temperature and pressure Cylinder temperature within limits CAUTION If the cylinder head temperature...

Page 81: ...ine of fuel 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 engi...

Page 82: ...not advisable to reduce the engine throttle control lever to minimum on final approach or when descending from very high altitude In such cases the engine can become over cooled although unlikely and...

Page 83: ...e as required 3 Airspeed 65 KIAS 4 Wing flaps extend as required 5 Trim as required 6 Brakes off carefully check that the brake stop valve is off 4 12 2 Landing 1 Throttle as required 2 Controls flare...

Page 84: ...minimum 300 ft 6 Trim adjust 7 Repeat circuit pattern 4 14Short field take off and landing procedures Not considered necessary Ordinary short field procedures may be used if pilot deems it appropriat...

Page 85: ...l switches 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 ta...

Page 86: ...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...

Page 87: ...5 1 5 2 DC POH 002 X B 6 Revision 2 6 5 PERFORMANCE 5 1 Introduction 5 3 5 2 Take off and landing distance 5 3 5 3 Rate of climb 5 4 5 4 Cruise speeds with fixed pitch propeller 5 5 5 5 Fuel consumpt...

Page 88: ...s valid for maximum take off weight 700 kg 1 540 lbs and under ISA conditions The performance shown in this section is valid for aircraft fitted with a ROTAX 912 ULS 73 5 kW 98 6 hp 5 2 Take off and l...

Page 89: ...Page 5 4 DC POH 002 X B 6 Revision 2 6 5 3 Rate of climb Conditions Max continuous power 5 500 rpm Weight 700 kg 1 540 lb Best rate of climb speed VY Rate of climb KIAS fpm 0 ft ISA 74 700 3 000 ft I...

Page 90: ...opeller Altitude ft ISA Engine speed rpm KIAS KTAS 100 4 500 78 79 4 800 93 94 5 000 98 99 5 300 103 105 5 500 109 111 3 000 4 500 69 73 4 800 84 90 5 000 95 102 5 300 101 107 5 500 105 111 6 000 4 50...

Page 91: ...umption Altitude ft ISA 3 000 Fuel quantity l 150 US gallons 39 63 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 70 4 23 4 76 5 29 5 55 Airspeed KIAS...

Page 92: ...2 X B 6 Revision 2 6 5 6 Airspeed indicator system calibration IAS knots CAS knots average CAS knots this aircraft 25 28 30 33 35 37 40 41 45 45 50 50 55 55 60 60 65 65 70 70 75 75 80 80 85 85 90 90 9...

Page 93: ...ndbook Page 6 1 6 2 DC POH 002 X B 6 Revision 2 6 6 WEIGHT AND BALANCE 6 1 Installed equipment list 6 3 6 2 Center of gravity CG range 6 4 6 3 Determination of aircraft GC 6 6 6 4 Empty CG determinati...

Page 94: ...balance records and the payload range for safe operating of the Sling 2 6 1 Installed equipment list Garmin multifunction glass cockpit instrument G3X GTR 200 COM radio Mode S transponder optional An...

Page 95: ...allowable CG envelope CG range is 1 635 mm 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 MAC is 1 366 mm 4 482 ft aft of the reference datum The MAC...

Page 96: ...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 lim...

Page 97: ...nt 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...

Page 98: ...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 Computed empty CG Empty weight WE kg lb CG mm ft MAC Aircraft...

Page 99: ...6 8 DC POH 002 X B 6 Revision 2 6 6 5 Blank for 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...

Page 100: ...Airplane Factory SLING 2 Pilot Operating Handbook Page 6 9 DC POH 002 X B 6 Revision 2 6 771 62 881 85 992 08 1102 31 1212 54 1322 77 1433 1763 7 Aircraft Mass lb 1543 23 1653 47...

Page 101: ...ems 7 10 7 9 Cockpit layout 7 11 7 10 Instruments and Avionics 7 13 7 11 Flap and elevator trim systems 7 18 7 12 Minimum instruments and equipment required for flight 7 19 7 13 Engine 7 20 7 14 Cooli...

Page 102: ...nstruction provides long life and low maintenance costs thanks to its durability and corrosion resistant characteristics The wing has a high lift airfoil NACA 4415 and is equipped with semi slotted Fo...

Page 103: ...GHT LEFT OFF rotary fuel selector valve located at the bottom centre of the instrument panel front of centre console Refer to the instrument panel layout in paragraph 7 10 An additional knob must be a...

Page 104: ...off UP ON DOWN OFF EFIS BKUP Connects EFIS system to EFIS back up battery supply FUEL PUMP Switch auxiliary electric fuel pump on off LAND Switch landing lights on off TAXI Switch taxi lights on off N...

Page 105: ...utton allocation Flap control Wing flaps are electrically controlled and selected position by a four position rotary knob or a four pushbutton selector located on the instrument panel refer to paragra...

Page 106: ...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 activated The arrangement is apparent in...

Page 107: ...t comprises two sections positioned behind the seats and is designed to carry up to 35 kg 77 lb in total The baggage compartment comprises a narrow slightly lowered front section and a higher larger b...

Page 108: ...d 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 centre and outside on the ce...

Page 109: ...f 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 a...

Page 110: ...ckpit layout is the same for all Sling 2 aircraft notwithstanding that instrumentation may differ substantially All airplanes contain the minimum instrumentation but particular airplanes may contain s...

Page 111: ...re 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...

Page 112: ...typical back up and additional instrumentation supplied with the aircraft The instrument panel in any particular aircraft may differ from that illustrated in the diagram It is the responsibility of t...

Page 113: ...bin heat activator 2 Ignition Magneto switches 14 Cubby hole 3 Charge warning light 914 UL 912 ULS 15 12 V Power port socket 4 Garmin G3X 16 Air vent 5 EFIS accessory warning light 17 Circuit breakers...

Page 114: ...ided 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 Clo...

Page 115: ...tion supplied with the unit and will not be dealt with in this handbook Refer to the supplied EFIS documentation The EFIS is operated during flight with the EFIS back up battery selection switch label...

Page 116: ...e 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 change...

Page 117: ...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...

Page 118: ...perature indicator Tachometer Chronometer First aid kit compliant with national legislation Fire extinguisher WARNING Notwithstanding that installed equipment may include GPS and other advanced flight...

Page 119: ...ufacturer documentation and applicable supplements to this Pilot operating Handbook for applicable information should the airplane be fitted with a Rotax 914 UL or a Rotax 912 iS engine 7 14Cooling sy...

Page 120: ...SI 912 016 Coolant liquid volume Coolant volume is approximately 2 5 litres 0 66 US gallons 7 15Throttle and Choke Refer to the applicable supplement at the end of this manual for additional informat...

Page 121: ...aircraft only is positioned in the left centre of the instrument panel Refer to paragraph 7 10 Pulling out the choke knob activates the choke mechanism Both controls throttle and choke are mechanical...

Page 122: ...aft s electrical system which are relevant can aid the pilot s understanding of the aircraft s systems and their use with respect to the operational procedures described in this manual Refer to paragr...

Page 123: ...to the aircraft systems e g to charge 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 Refer to...

Page 124: ...autopilot servos 4 Propeller if applicable 5 Radio 6 Transponder if fitted 7 Cabin light s 8 Strobe navigation and taxi lights 9 EFIS unless powered by the EFIS battery back up circuit With regard to...

Page 125: ...starter switches Ignition magneto switches and starter switch are incorporated into a key switch mounted on the instrument panel Refer to paragraphs Error Reference source not found Error Reference s...

Page 126: ...i e ON Optional equipment switches and or fuses are subject to change or installed as requested Refer to the Aircraft Equipment List Circuit breakers Circuit breakers are push to reset i e push in for...

Page 127: ...Airplane Factory SLING 2 Pilot Operating Handbook Page 7 28 DC POH 002 X B 6 Revision 2 6 7 17 1 Charge system start system electric fuel pump wiring diagram 912 ULS...

Page 128: ...Airplane Factory SLING 2 Pilot Operating Handbook Page 7 29 DC POH 002 X B 6 Revision 2 6 7 17 2 Switches and circuit breakers diagram 912 ULS...

Page 129: ...Airplane Factory SLING 2 Pilot Operating Handbook Page 7 30 DC POH 002 X B 6 Revision 2 6 7 17 3 EFIS back up circuit battery back up wiring diagram...

Page 130: ...ite propeller a Whirlwind 70 inch composite ground adjustable 3 blade propeller or an Airmaster AP332 72 inch composite electric constant speed 3 blade propeller If the aircraft is fitted with the Air...

Page 131: ...nk in use The system is configured as in the diagram below Volume of wing tanks 2 x 75 litres 2 x 19 8 US gal 73 litres 19 2 US gal useable per tank WARNING The fuel lift pipe in each fuel tank is sit...

Page 132: ...el system 912 ULS A Port left fuel tank G 8mm Barbed T piece B Starboard right fuel tank H 8mm T Piece with Jet C Fuel selector LEFT RIGHT OFF I Fuel flow sensor D Fuel filter 90 bend J Left carburett...

Page 133: ...ng 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...

Page 134: ...rument 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 d...

Page 135: ...t 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...

Page 136: ...SERVICING 8 1 Introduction 8 2 8 2 Servicing fuel oil and coolant 8 2 8 3 Towing and tie down mooring instructions 8 3 8 4 Parking 8 5 8 5 Jacking 8 5 8 6 Road transport 8 6 8 7 Cleaning and care 8 6...

Page 137: ...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 m...

Page 138: ...carefully backwards by putting pressure on the wing leading edges close to the root directly on a nose rib or on the horizontal stabilizer leading edge next to the root over a rib Tow Bar The aircraft...

Page 139: ...rocedure 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 ven...

Page 140: ...r 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 hori...

Page 141: ...anopy 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...

Page 142: ...l condition of the aircraft Inspections and servicing should be carried out according to at least the following periods After the first 25 flight hours thereafter after every 100 flight hours or annua...

Page 143: ...cations 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...

Page 144: ...and equipment not provided with the standard airplane List of inserted supplements Date Suppl No Title of inserted supplement 04 06 12 01 2010 Airplanes fitted with a Rotax 914 UL engine 04 06 12 02 2...

Page 145: ...bject to latest information documentation as provided by the engine manufacturer The Rotax 914 UL engine is a 4 stroke 4 cylinder horizontally opposed turbocharged spark ignition engine with one centr...

Page 146: ...MITS Always refer to latest edition revision of the engine Operators Manual for latest information regarding operating limitations ENGINE START AND OPERATION TEMPERATURE LIMITS 914 UL Maximum 50 C 122...

Page 147: ...m maximum 5 minutes Maximum continuous 74 6 kW 100 hp at 5500 rpm Engine RPM Maximum take off 5800 rpm maximum 5 minutes Maximum continuous 5500 rpm Idle 1 500 rpm Temperature EGT Maximum 950 C 1742 F...

Page 148: ...al 2 to 5 bar 29 to 73 psi above 3500 rpm Fuel Minimum 1 15 bar 16 7 psi Maximum 1 85 bar 26 8 psi Manifold Maximum take off 1 35 bar 19 58 psi NOTE Overshoot of manifold pressure is allowed but has t...

Page 149: ...ot Operating Handbook Page 9 7 DC POH 002 X B 6 Revision 2 6 Refer to latest revision of Rotax operator maintenance manuals and latest revision of Rotax service instruction SI 914 019 with regard to s...

Page 150: ...OTAX 914 UL FUEL SYSTEM A Left fuel tank F TAF fuel pump system B Right fuel tank G Garmin fuel pressure sensor C Fuel selector LEFT RIGHT OFF H Fuel flow sensor D 90 Fuel filter I 914 UL Engine E Gas...

Page 151: ...el tank in use Main fuel pump The main fuel pump is connected to the main bus The pump cannot be operated when power to the main bus is unavailable Auxiliary fuel pump The auxiliary fuel pump is conne...

Page 152: ...s the lever at the 100 throttle selection position Moving the throttle lever past the 100 throttle selection requires the manipulation of a detent control enabling knob located on the throttle lever O...

Page 153: ...P ON DOWN OFF EFIS BKUP Connects EFIS system to EFIS back up battery supply MAIN PUMP Switch main fuel pump in off AUX PUMP Switch auxiliary fuel pump on off LAND Switch landing lights on off TAXI Swi...

Page 154: ...d applicable in paragraph 7 17 under Main bus becomes non operational 1 Main fuel pump 2 TCU Turbocharger Control Unit waste gate servo With regard to the above 1 The auxiliary fuel pump can be operat...

Page 155: ...Airplane Factory SLING 2 Pilot Operating Handbook Page 9 13 DC POH 002 X B 6 Revision 2 6 CHARGE AND START SYSTEM WIRING DIAGRAM 914 UL...

Page 156: ...Airplane Factory SLING 2 Pilot Operating Handbook Page 9 14 DC POH 002 X B 6 Revision 2 6 SWITCHES AND CIRCUIT BREAKERS WIRING DIAGRAM 914 UL...

Page 157: ...crankcase from where it is forced back to the oil reservoir by a piston blow by gas Oil temperature is sensed by a sensor located on the oil pump housing The lubrication circuit is vented at the oil...

Page 158: ...box The TCU starts adding full boost from the 108 throttle position onward The throttle lever in cabin is equipped with a detent at the 100 throttle lever position A lever on the throttle lever is act...

Page 159: ...LIGHT INDICATION Illuminates steadily Blinks CAUTION LIGHT INDICATION Blinks NOTE Boost pressure will not be reduced automatically Limited operation as boost control may be unavailable or insufficient...

Page 160: ...ng light Procedure as in paragraph 3 7 4 WARNING The engine will continue to run after an alternator charge system failure until the battery voltage is low approximately 30 minutes if all ancillary eq...

Page 161: ...CHARGER CONTROL UNIT TCU Sudden drop in boost pressure Possible causes may be the turbocharger fracturing or the waste gate not closing Fractured turbocharger A loud bang may be heard as a result of a...

Page 162: ...loss of power to the main bus 1 Auxiliary fuel pump on 2 Use the throttle lever to set control engine speed and boost pressure to within operating limits at least maximum continuous values 3 Rest of p...

Page 163: ...ft and 160 m 524 9 respectively 1 5 Rate of climb at 0 3 000 6 000 and 9 000 ft ISA will increase to 1 000 900 800 and 720 fpm respectively 1 6 Cruise speeds will not be altered substantially unless...

Page 164: ...voltage is applied Master switch is switched on both TCU lights should illuminate for approximately 1 to 2 seconds TCU self test and then extinguish If not it indicates a deficiency refer to Rotax 914...

Page 165: ...operation of an aircraft fitted with a Magnum 601 ballistic parachute 1 The Sling 2 is designed specifically for convenient fitment of a Magnum 601 ballistic parachute recovery system The system is d...

Page 166: ...arameters 2 Throttle idle 3 Magneto ignition switches off 4 Electric fuel pump s off 5 Fuel selector lever off 6 Deploy the parachute by pulling the T shaped activation handle situated in the centre f...

Page 167: ...master AP 332 variable pitch constant speed propeller Propeller control is via an electronic control unit mounted on the instrument panel Power to the propeller propeller controller is provided via th...

Page 168: ...for the Airmaster AP332 Propeller operational guidelines and instructions These should be incorporated into the normal and emergency procedures for the aircraft as applicable SUPPLEMENTARY INFORMATIO...

Page 169: ...xed pitch propeller Propeller switch off CAUTION Selection of too fine a propeller pitch for the engine throttle setting will result in an over speed situation Selection of too coarse a propeller pitc...

Page 170: ...Revision 2 6 SUPPLEMENTARY INFORMATION PILOT CONTROLS PROPELLER PROPELLER CONTROLLER MANUAL PROPELLER CONTROL SWITCH PROPELLER CONTROL SELECTOR KNOB BLUE AUTOMATIC MANUAL SELECTOR SWITCH FEATHER ENGAG...

Page 171: ...ntroller unit and to the propeller motor Automatic Manual Selector switch located on the propeller controller This switch selects between propeller automatic AUTO and manual MAN control modes Automati...

Page 172: ...mal cruise operation HOLD Provides constant speed propeller governing at a pilot selected speed Feather Engage switch With automatic AUTO mode selected on the Automatic Manual Selector switch and the...

Page 173: ...the Manual Propeller Control switch is used to set a pilot selected propeller governing speed Actuate the switch to change propeller pitch in the direction desired When the desired speed rpm is reache...

Page 174: ...ROPELLER STATUS INDICATOR LIGHT FINE COARSE FEATHER Pitch decreasing Orange Pitch increasing Orange Pitch increasing in feather Orange No speed signal Orange flashing Fine pitch limit Green Coarse pit...

Page 175: ...or information purposes and is subject to latest information documentation as provided by the engine manufacturer The Rotax 912iS is a fuel injected and electronically controlled variant of the Rotax...

Page 176: ...on revision of the engine Operators Manual for latest information regarding operating limitations ENGINE START AND OPERATION TEMPERATURE LIMITS 912 iS Maximum in flight 60 C 140 F manifold temperature...

Page 177: ...maximum 5 minutes Max continuous 5500 rpm Idle 1 400 minimum EGT Maximum 950 C 1742 F Cylinder head temperature Minimum N A Maximum 150 C 302 F Normal 75 to 110 C 167 to 230 F Oil temperature Minimum...

Page 178: ...type 1 1 Ethylene glycol based coolant and distilled water mixture WATER FREE COOLANT NOT PERMITTED FOR USE WITH 912 iS Refer to latest revision of Rotax operator maintenance manuals and latest revisi...

Page 179: ...left fuel tank G 8mm T piece B Starboard right fuel tank H 8mm T piece with Jet C Fuel selector LEFT RIGHT OFF I Fuel pressure sensor D Fuel filter 90 bend J Fuel filter E Gascolator K Bypass pressur...

Page 180: ...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...

Page 181: ...e 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 char...

Page 182: ...onnects EFIS system to EFIS back up battery supply 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 NA...

Page 183: ...SLING 2 Pilot Operating Handbook Page 9 41 DC POH 002 X B 6 Revision 2 6 SUPPLEMENTARY INFORMATION ELECTRICAL SYSTEM OVERVIEW The drawing below provides an overview of the electrical system 912 iS eq...

Page 184: ...powered aircraft the charge system output is directly connected to the main battery which connects to the main bus via a master switch This implies that with the Ignition switch turned off The main b...

Page 185: ...Airplane Factory SLING 2 Pilot Operating Handbook Page 9 43 DC POH 002 X B 6 Revision 2 6 ROTAX 912 iS WIRING DIAGRAM...

Page 186: ...Airplane Factory SLING 2 Pilot Operating Handbook Page 9 44 DC POH 002 X B 6 Revision 2 6 ROTAX 912 iS SWITCHES AND CIRCUIT BREAKERS WIRING DIAGRAM...

Page 187: ...d 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 gas...

Page 188: ...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 to charge the main battery Procedure as in paragr...

Page 189: ...7 4 Alternator B failure could be indicated by a drop in the main bus voltage displayed on EFIS WARNING The engine will continue to run after an Alternator B failure with Alternator A still operative...

Page 190: ...MENTARY INFORMATION MAIN BUS When power to the main bus is unavailable fails the following equipment in addition to those listed and applicable in paragraph 7 17 under Main bus becomes non operational...

Page 191: ...back up switch on Once power EMS battery back up 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 f...

Page 192: ...7 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 en...

Page 193: ...EMENTARY INFORMATION PRIOR TO TAKE OFF Only one ignition circuit lane may be switched on and off at a time Verify the Lane A and Lane B ignition circuits at 4 000 rpm No rpm drop should occur when Lan...

Page 194: ...st be contained in the Pilot Operating Handbook during operation of the aircraft with such mechanism fitted Information contained in this supplement adds to or replaces information from the standard S...

Page 195: ...abbreviated material to the pilot who is familiar with tugging and towing operations as well as the Sling 2 aircraft type who wishes to understand in what manner the operation of the Sling 2 for tuggi...

Page 196: ...empty CG of the aircraft should be measured and appropriately recorded Flight performance There is no noticeable change in flight performance between an aircraft fitted with the tow hook mechanism an...

Page 197: ...y significance The tow hook installation design provides for the fitment of a red release handle immediately beneath the lower edge of the instrument panel and between the pilot s knees The release ha...

Page 198: ...discontinue operations immediately Pilots should at all times operate in accordance with the provisions of the Tost E22 series Operating Manual and good aviation practice The lighter the aircraft dur...

Page 199: ...imitations are met at all times It is assumed that at all times pilots and support crew will comply with good aviation practices applicable to the kinds of operations engaged in Provided that these gu...

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