Airplane Factory SLING 4 Pilot Operating Handbook Download Page 109

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Airplane Factory SLING 4

Pilot Operating Handbook

Page | 7-6

DC-POH-001-X-C-3

Revision : 1.3

Propeller

PROPELLER CONTROLLER

MANUAL PROPELLER CONTROL SWITCH

PROPELLER CONTROL
SELECTOR KNOB (BLUE)

AUTOMATIC / MANUAL
SELECTOR SWITCH

FEATHER ENGAGE SWITCH

FEATHER

INDICATOR LIGHT

COARSE

INDICATOR LIGHT

FINE

INDICATOR LIGHT

Summary of Contents for SLING 4

Page 1: ......

Page 2: ...ne Factory Pty Ltd Aircraft Serial Number Date of Construction Registration Issue Date 2014 11 10 PLEASE ADVISE THE AIRPLANE FACTORY ON CHANGE OF OWNERSHIP OF THE AIRCRAFT This aircraft must be operat...

Page 3: ...THE AIRPLANE FACTORY PTY LTD 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 STAN...

Page 4: ...le and where applicable be endorsed by the responsible airworthiness authority Revision numbers appear at the foot of each page Revision No Affected Section Affected Pages Date of Issue Approved by Da...

Page 5: ...1 3 2 1 2 Revised 1 3 vi Revised 1 3 2 3 Revised 1 3 vii Revised 1 3 2 4 Revised 1 3 viii Revised 1 3 2 5 Revised 1 3 ix Revised 1 3 2 6 Revised 1 3 1 1 2 Revised 1 3 2 7 Revised 1 3 1 3 Revised 1 3 2...

Page 6: ...ised 1 3 4 3 Revised 1 3 3 8 Revised 1 3 4 4 Revised 1 3 3 9 Revised 1 3 4 5 Revised 1 3 3 10 Revised 1 3 4 6 Revised 1 3 3 11 Revised 1 3 4 7 Revised 1 3 3 12 Revised 1 3 4 8 Revised 1 3 3 13 Revised...

Page 7: ...3 Revised 1 3 7 5 Revised 1 3 5 4 Revised 1 3 7 6 Revised 1 3 5 5 Revised 1 3 7 7 Revised 1 3 5 6 Revised 1 3 7 8 Revised 1 3 5 7 Revised 1 3 7 9 Revised 1 3 5 8 Revised 1 3 7 10 Revised 1 3 6 1 2 Re...

Page 8: ...Revised 1 3 7 45 Revised 1 3 7 25 Revised 1 3 8 1 2 Revised 1 3 7 26 Revised 1 3 8 3 Revised 1 3 7 27 Revised 1 3 8 4 Revised 1 3 7 28 Revised 1 3 8 5 Revised 1 3 7 29 Revised 1 3 8 6 Revised 1 3 7 30...

Page 9: ...Revision 1 3 TABLE OF CONTENTS 1 GENERAL INFORMATION 1 1 2 LIMITATIONS 2 1 3 EMERGENCY AND ABNORMAL PROCEDURES 3 1 4 NORMAL PROCEDURES 4 1 5 PERFORMANCE 5 1 6 WEIGHT AND BALANCE 6 1 7 SYSTEMS 7 1 8 A...

Page 10: ...X C 3 Revision 1 3 1 GENERAL INFORMATION 1 1 Introduction to aircraft 1 3 1 2 Warnings cautions and notes 1 4 1 3 Aircraft 3 view drawing 1 5 1 4 Data for the Sling 4 aircraft and systems 1 6 1 5 Term...

Page 11: ...ircraft design is based upon the FAA FAR 23 certification standard having a maximum all up weight of 920 kg 2028 25 lb Notwithstanding that the aircraft design is based upon the FAA FAR 23 certificati...

Page 12: ...e Pilot Operating Handbook Means that non compliance to the corresponding procedure leads to immediate or important degradation of flight safety Means that non compliance to the corresponding procedur...

Page 13: ...Airplane Factory SLING 4 Pilot Operating Handbook Page 1 5 DC POH 001 X C 3 Revision 1 3 1 3 Aircraft 3 view drawing Note that dimensions in this drawing are in millimetres...

Page 14: ...2 m 141 22 ft Aspect ratio 7 52 Dihedral 5 Tip washout 2 Aileron area 0 62 m 6 7 ft Flap area 1 26 m 13 6 ft HORIZONTAL STABILIZER Span 2 820 mm 9 252 ft Area 1 05 m 11 3 ft Aspect ratio with elevator...

Page 15: ...7 125 mm 23 36 ft LANDING GEAR Wheel track 1 95 m 6 4 ft Wheel base 1 68 m 5 51 ft Brakes Hydraulic Main gear tyres 15x6 00 6 6 ply 2 5 bar 36 26 psi pressure Nose gear tyres 5 00 5 6 ply 1 8 bar 26...

Page 16: ...d turbocharged 1211 2 cc displacement mixed cooling water cooled heads and air cooled cylinders twin carburettors integrated reduction gearbox with torque damper Maximum power 85 76 kW 115 hp at 5 800...

Page 17: ...s 2 Wing tanks one tank integrated within each wing leading edge each tank equipped with finger strainers in pick up line and drain fittings Capacity of each tank 84 litres 22 19 US gallons Total capa...

Page 18: ...latest revision Rotax engine manuals and latest revision of the Rotax service instruction SI 914 019 Capacity 2 5 litres 5 28 pints approximately MAXIMUM WEIGHTS Maximum take off weight 920 kg 2028 2...

Page 19: ...radio EFIS Electronic Flight Information System FAA Federal Aviation Authority FAR Federal Aviation Regulations GLS GPS Landing System GmbH Gesellschaft mit beschr nkter Haftung company with limited l...

Page 20: ...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 21: ...er to indicate local height above airfield Engine terminology CHT Cylinder Head Temperature EGT Exhaust Gas Temperature OHV Overhead Valve RPM rpm Revolutions per minute being the number of revolution...

Page 22: ...f an item CG Centre of Gravity being the point at which the aircraft or equipment would balance if suspended Its distance from the reference datum is found by dividing the total moment by the total we...

Page 23: ...e under nose main wheel during aircraft weighing WR Weight read from scale under right main wheel during aircraft weighing WT Aircraft total weight Useful conversion factors 1 pound 0 4536 kilogram 1...

Page 24: ...stant Speed Propeller Operators Manual 3 Latest revision edition of Rotax service instruction SI 914 019 4 Latest revision of the MGL iEFIS panel operator manual 5 Latest revision of the MGL Avionics...

Page 25: ...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 26: ...ith caution VA Maneuvering speed 105 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 exce...

Page 27: ...s VSO at maximum weight and upper limit is the maximum speed VFE permissible with flaps deployed Green arc 54 105 Normal Operating Range lower limit is VS at maximum weight most forward CG with flaps...

Page 28: ...usted 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 d...

Page 29: ...off and landing 15 kt 2 6 Service ceiling Service ceiling 14 000 ft 2 7 Load factors Maximum positive limit load factor 3 8 g Maximum negative limit load factor 1 9 g Maximum positive load factor with...

Page 30: ...row of rivets down from below the canopy frame edge on the aircraft fuselage side above the wing Reference transverse leveling Upper surface of centre spar cap under pilot and passenger seats Forward...

Page 31: ...ls not including whip stalls 2 11 Flight crew Minimum crew for flight is one pilot seated on the left side 2 12 Passengers Only three passengers are allowed on board the aircraft in addition to the pi...

Page 32: ...ndicator 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 s...

Page 33: ...e marked set to reflect the minimum and maximum values Always refer to the latest edition revision of the engine Operators Manual for the latest information regarding operating limitations ENGINE STAR...

Page 34: ...pm 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...

Page 35: ...7 bar 102 psi permissible for short period on cold engine start Normal 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 b...

Page 36: ...llowed on board of the aircraft VFR flights only are permitted 2 16 Flight in rain When flying in rain no additional actions procedures are required Aircraft qualities and performance are not substant...

Page 37: ...instrument panel In a place visible to pilot and passenger s OPERATE UNDER VMC ONLY MAXIMUM PERMISSIBLE AIRSPEED 135 KIAS MAXIMUM PERMISSIBLE RPM 5 800 RPM FOR 5 MINUTES MAXIMUM CONTINUOUS RPM 5 500...

Page 38: ...er caps On the inboard upper wing flap surface On a fireproof metal plate attached to the aircraft Note represents the information applicable to the specific aircraft AVGAS OR MOGAS 84 LITRES ZU CONST...

Page 39: ...C 3 Revision 1 3 The aircraft must be placarded to show the identity of All fuses circuit breakers Starter and Ignition Magneto switches All other switches Choke Trim control NOSE UP and DOWN Flap co...

Page 40: ...EMERGENCY AND ABNORMAL PROCEDURES 3 1 Introduction 3 3 3 2 Speeds for emergency operations 3 4 3 3 Engine related emergencies 3 5 3 4 Smoke and fire 3 11 3 5 Emergency landings 3 15 3 6 Recovery from...

Page 41: ...ely rare if proper pre flight inspections and maintenance are practiced However should an emergency arise the basic guidelines described in this section should be considered and applied as necessary t...

Page 42: ...ns SPEED KIAS REMARKS VBG Best Glide Speed 65 The speed at MAUW flaps fully retracted which results in the greatest gliding horizontal distance Horizontal distance travelled in still air is approximat...

Page 43: ...operational guidelines and instructions These should be incorporated into the normal or emergency procedures as applicable 3 3 1 Engine failure during take off run 1 Throttle idle 2 Brakes as required...

Page 44: ...red 6 Magnetos ignition off 7 Master switch off 8 Electric fuel pumps both off 9 Fuel selector valve off 3 3 3 Engine irregularities in flight 3 3 3 1 Irregular engine rpm 1 Verify magneto switches bo...

Page 45: ...low 4 Change fuel selector valve to the fullest tank 5 Decrease throttle setting if viable to do so If fuel pressure remains low 6 Land as soon as possible 3 3 3 3 Low oil pressure 0 8 bar 12 psi or l...

Page 46: ...e gate not closing Fractured turbocharger A loud bang may be heard as a result of and indicating turbocharger fracture Flight with reduced performance may be possible Monitor oil pressure Land as soon...

Page 47: ...ste gate is fully closed The TCU CAUTION light may be flashing indicating equipment failure The BOOST lamp will illuminate continuously when admissible boost pressure is exceeded Immediately reduce en...

Page 48: ...both 6 Starter engage 7 Auxiliary fuel pump off after positive start If engine should fail to restart 8 Apply the forced landing without engine power procedure according to paragraph 3 5 1 NOTE It is...

Page 49: ...f 7 Retrieve fire extinguisher if possible 8 Exit the aircraft 9 Extinguish the fire by fire extinguisher or call for fire services if unable to do so 3 4 2 Engine fire on ground with engine running 1...

Page 50: ...f unable to do so 3 4 4 Engine fire in flight 1 Cabin heat close 2 Electric fuel pumps both off 3 Fuel selector close 4 Throttle full power 5 Magnetos switch off after the fuel in carburettors is cons...

Page 51: ...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 The EFIS and ass...

Page 52: ...he procedure for electrical fires in flight paragraph 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 instrume...

Page 53: ...and preferably into wind 4 Safety harness secure tighten 5 Engine restart if time permits and if appropriate attempt to identify the cause for the engine failure and attempt a restart 6 Propeller if...

Page 54: ...ropeller 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 cycle takes 20...

Page 55: ...he landing location 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 pa...

Page 56: ...st 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 abo...

Page 57: ...r 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 ente...

Page 58: ...refer to paragraph 7 7 1 2 Throttle close 3 Fuel pump s both off 4 Fuel selector lever off 5 Magneto ignition switches off 6 Deploy the parachute by pulling the T shaped activation handle situated in...

Page 59: ...ight 1 Maintain 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...

Page 60: ...engine temperatures The following procedure is recommended for recovering engine power 1 Speed 75 KIAS 2 Throttle 1 3 power 3 If possible leave the icing area 4 After 1 to 2 minutes gradually increase...

Page 61: ...as possible NOTE When landing with adequate battery power remaining to power both the propeller motor and the fuel pump s the propeller can be re energized and selections made as applicable The auxil...

Page 62: ...ided that the EFIS battery back up switch is on if not switch on EFIS battery back up switch and the back up battery contains adequate charge 4 Switch off all main bus connected equipment switches Ref...

Page 63: ...ions should be followed in the event of any propeller control failure 1 If required immediately reduce throttle to avoid exceeding engine speed limitations 2 Select manual mode MAN 3 If manual control...

Page 64: ...flight range continued flight is possible but with caution Use the engine throttle to control engine propeller speed as with a fixed pitch propeller Propeller switch off CAUTION If failure occurred wi...

Page 65: ...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 14 4 7 Normal take off 4 15 4 8 Climb 4 17 4 9 Cruise 4 18 4 10 Descent 4 18 4 11 Approach 4 19...

Page 66: ...izontal distance i e largest climb angle NOTE the resultant climb angle is approximately 3 7 VY Best Rate of Climb Speed 75 The speed at MAUW flaps fully retracted which results in the greatest altitu...

Page 67: ...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 68: ...Check List Inspection Check List 1 Cabin Ignition off Master switch on EFIS switch on Fuel level indicator check fuel quantity both tanks Flaps select full down position EFIS switch off Master switch...

Page 69: ...haust manifold condition check Oil and coolant quantity check Visual inspection of fuel and electrical system check Engine checks as per the Rotax engine manual complete Other actions according to the...

Page 70: ...ge condition check Taxi landing lights and lens check for cracks and condition Wheel and brakes fluid leaks security general condition tyre condition inflation wear Wheel strut condition cracks Fuel v...

Page 71: ...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 conditio...

Page 72: ...ty general condition tyre condition inflation wear Wheel strut condition cracks Fuel vent underside unobstructed Wing trailing edge check condition Aileron freedom of movement attachment surface condi...

Page 73: ...ne 1 Pre flight inspection completed 2 Emergency equipment on board 3 Passenger s briefed 4 Seats seatbelt s and harnesses adjust and secure 5 Brakes on CAUTION In case of long term parking it is reco...

Page 74: ...5 Propeller AUTO 6 Magneto ignition switches on 7 Throttle closed if choke used cracked just open if not 8 Fuel selector emptiest tank if not empty 9 Electric fuel pumps both on 10 Choke cold engine p...

Page 75: ...ify 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 t...

Page 76: ...cuit is switched off should not exceed 300 rpm The maximum engine speed reduction drop difference between magnetos ignition circuits should not exceed 115 rpm Set maximum power for the verification of...

Page 77: ...ke stop valve is off 4 Controls neutral position or as required for wind 5 Power and brakes as required 6 Brakes verify correct operation 7 Instruments check Apply power and brakes as needed Apply bra...

Page 78: ...ll 10 Altimeter set QNH QFE 11 Switches verify as required 12 Power and ignition verify magnetos at 4 000 rpm maximum difference 115 rpm maximum drop 300 rpm 13 Propeller set 4000 engine rpm select MA...

Page 79: ...KIAS is reached at altitude of minimum 300 ft 8 Auxiliary electric fuel pump off at 300 ft minimum 9 Brakes apply briefly to stop wheel rotation 10 Transition to climb WARNING Take off is prohibited...

Page 80: ...0 KIAS 4 Trim trim the aircraft 5 Instruments check oil temperature and pressure cylinder head temperatures within limits CAUTION If the cylinder head temperatures or oil temperature approach their li...

Page 81: ...an 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 ta...

Page 82: ...sed 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...

Page 83: ...d after the nose wheel touch down for controlled slowing down 4 12 3 After landing 1 Engine speed as required for taxi 2 Wing flaps retract CAUTION Rapid engine cooling should be avoided during operat...

Page 84: ...hutdown 1 Engine speed idle 2 Instruments engine parameters within limits 3 Avionics switch off 4 Magnetos ignition off 5 Electric fuel pumps both off 6 Switches off 7 EFIS off battery back up off 8 M...

Page 85: ...necessary 7 Secure the aircraft NOTE Use anchor eyes on the wings and fuselage rear section to secure the aircraft Move the control column forward and secure it together with the rudder pedals if hig...

Page 86: ...Handbook Page 5 1 5 2 DC POH 001 X C 3 Revision 1 3 5 PERFORMANCE 5 1 Introduction 5 3 5 2 Take off and landing distance 5 3 5 3 Rate of climb 5 5 5 4 Cruise speeds 5 6 5 5 Fuel consumption 5 7 5 6 A...

Page 87: ...alid for maximum take off weight 920 kg 2028 25 lb under ISA conditions The performance stated in this section is valid for SLING 4 aircraft fitted with a ROTAX 914 UL 85 76 kW 115 hp engine and an Ai...

Page 88: ...Landing distances 50 ft ISA MAUW Runway Landing run distance braked Landing distance over 15 m 50 ft obstacle Concrete 150 m 492 ft 350 m 1148 ft 7000 ft Density altitude MAUW Runway Landing run dista...

Page 89: ...Page 5 5 DC POH 001 X C 3 Revision 1 3 5 3 Rate of climb Conditions Max continuous power 5500 rpm Weight 920 kg 2028 25 lb Best rate of climb speed VY Rate of climb KIAS fpm 0 ft ISA 75 435 3 000 ft I...

Page 90: ...se speeds Constant speed propeller with cruise setting Altitude ft ISA Throttle position Engine rpm Cruise Speed KIAS 100 75 5 000 108 85 5 000 109 100 5 000 113 3 000 75 5 000 101 85 5 000 105 100 5...

Page 91: ...constant speed propeller Altitude ft ISA 3 000 Fuel quantity l 168 US gallons 44 38 Engine speed rpm 5750 5450 5000 Propeller setting Take off Climb Cruise Throttle setting 115 100 85 Fuel consumptio...

Page 92: ...1 X C 3 Revision 1 3 5 6 Airspeed indicator system calibration IAS knots CAS knots average CAS knots This aircraft 25 28 30 33 35 38 40 44 45 45 50 50 55 55 60 60 65 65 70 70 75 75 80 80 85 85 90 90 9...

Page 93: ...sion 1 3 6 WEIGHT AND BALANCE 6 1 Introduction 6 3 6 2 Installed equipment standard list 6 3 6 3 Center of gravity CG range 6 4 6 4 Determining aircraft CG 6 6 6 5 Empty CG determination 6 7 6 6 Forwa...

Page 94: ...rument Challenger iEFIS with associated equipment iBox RDAC XF autopilot roll and pitch servos MGL SP6 electronic compass MGL SP7 AHRS GARMIN GTR200 COM radio TRIG Mode S transponder TRIG TC20 control...

Page 95: ...le GC envelope CG range is 1 859 mm 6 099 ft to 2 034 mm 6 673 ft aft of the reference datum 18 to 31 of MAC The leading edge of the MAC is 1 616 mm 5 301 ft aft of the reference datum The MAC is 1 34...

Page 96: ...Envelope FLIGHT ALLOWED IN SHADED AREA ONLY WARNING Aircraft CG and MAUW limitations must be adhered to at all times Aircraft Mass lb Aircraft Mass kg 881 84 1102 1323 1543 1764 1984 920 2028 2205 84...

Page 97: ...ple Blank CG form CG formulae 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 instruction...

Page 98: ...weight x arm kg mm lb ft Aircraft Empty CG Right Main Wheel WR LR 2 236 7 335 Left Main Wheel WL LL 2 236 7 335 Nose Wheel WN LN 548 1 797 Computed empty CG Empty weight WE kg lb CG mm ft MAC Aircraft...

Page 99: ...HT kg lb ARM mm ft MOMENT weight x arm kg mm lb ft CREW FRONT 120 264 554 1 902 6 24 228 240 1650 817 PASSENGERS REAR 2 823 9 262 BAGGAGE 3 288 10 787 FUEL 121 266 759 1 761 5 777 213 081 1541 066 ADD...

Page 100: ...g Handbook Page 6 9 DC POH 001 X C 3 Revision 1 3 400 500 600 700 800 900 1000 16 18 20 22 24 26 28 30 32 CG Percentage of MAC Allowable CG Envelope Aircraft Mass lb Aircraft Mass kg 881 84 1102 1323...

Page 101: ...CREW FRONT 160 352 739 1 902 6 24 304 320 2201 091 PASSENGERS REAR 100 220 462 2 823 9 262 282 300 2041 919 BAGGAGE 10 22 046 3 288 10 787 32 880 237 81 FUEL 10 8 23 809 1 761 5 777 19019 137 544 ADD...

Page 102: ...POH 001 X C 3 Revision 1 3 400 500 600 700 800 900 1000 16 18 20 22 24 26 28 30 32 CG Percentage of MAC Allowable CG Envelope Aircraft Mass lb Aircraft Mass kg 881 84 1102 1323 1543 1764 1984 920 2028...

Page 103: ...CREW FRONT 1 959 6 427 PASSENGERS REAR 2 719 8 92 BAGGAGE 3 296 10 813 FUEL 1 761 5 777 ADD EMPTY VALUES TOTAL WT MT CG MAC WARNING Aircraft CG and MAUW limitations must be adhered to at all times WA...

Page 104: ...f MAC Allowable CG Envelope Aircraft Mass lb Aircraft Mass kg 881 84 1102 1323 1543 1764 1984 920 2028 2205 WARNING Aircraft CG and MAUW limitations must be adhered to at all times 840 1852 WARNING Fo...

Page 105: ...Pitot and static system 7 16 7 11 Cockpit layout 7 17 7 12 Instruments and avionics 7 19 7 13 Flap and elevator trim systems 7 23 7 14 Minimum instruments and equipment required for flight 7 24 7 15...

Page 106: ...d rivets This high strength aluminum alloy construction provides long life and low maintenance costs due to its durability and corrosion resistant characteristics The wing has a high lift airfoil NACA...

Page 107: ...T LEFT RIGHT 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 12 An additional knob must...

Page 108: ...witch power from main bus to EFIS system on off UP ON DOWN OFF EFIS BKUP Connects EFIS system to EFIS back up battery supply MAIN PUMP Switch main fuel pump on off AUX PUMP Switch auxiliary fuel pump...

Page 109: ...6 DC POH 001 X C 3 Revision 1 3 Propeller PROPELLER CONTROLLER MANUAL PROPELLER CONTROL SWITCH PROPELLER CONTROL SELECTOR KNOB BLUE AUTOMATIC MANUAL SELECTOR SWITCH FEATHER ENGAGE SWITCH FEATHER INDI...

Page 110: ...utomatic AUTO and manual MAN control modes Automatic mode AUTO operation includes constant speed governing in pre set take off climb cruise and hold modes and feathering In manual mode MAN the Manual...

Page 111: ...from the propeller controller unit on the instrument panel The Manual Propeller Control switch provides for Direct control of the propeller pitch when manual mode MAN is selected with the Automatic M...

Page 112: ...sts the various propeller status indications provided by said lights in automatic AUTO mode and where applicable manual MAN mode PROPELLER STATUS INDICATOR LIGHT FINE COARSE FEATHER Pitch decreasing O...

Page 113: ...t feather pitch limit Green flashing Over current while pitch decreasing Red Over current while pitch increasing Red Over current while pitch increasing in feather Red Open circuit failure Red flashin...

Page 114: ...is electrically controlled by buttons on the control column Refer to Control stick s for button allocation Flap selection knob Wing flaps are electrically controlled and selected for position by a fou...

Page 115: ...rake system The aircraft braking system is typically a single hydraulic system acting on both wheels of the main landing gear via disk brakes Activation is via a lever located on the cabin centre cons...

Page 116: ...usted backwards and forwards for comfort with forward movement slightly raising the seat height IMPORTANT Ensure that the seat s is are securely locked into position after adjustment 7 7 Ballistic res...

Page 117: ...le safety pin prevents accidental activation of the ballistic rescue parachute activation handle when not in flight This pin must be removed before take off 7 7 1 Ballistic rescue parachute operationa...

Page 118: ...gage must be properly secured The baggage compartment can be accessed via a door in the port left side if the rear fuselage 7 9 Canopy The aircraft is equipped with a two part panel hinged upward open...

Page 119: ...gle 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 fli...

Page 120: ...but particular aircraft may contain substantial additional instrumentation The basic cockpit layout is configured as in the diagram below Cockpit layout 1 Air vent 8 Luggage compartment 2 Ballistic pa...

Page 121: ...t and to ensure that the rudder pedals can be reached easily by all pilots The rudder pedals may be adjusted via removal of the locking bolt s Air vents are located on the lower right and left sides o...

Page 122: ...h 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...

Page 123: ...witches 20 Ballistic rescue parachute activation handle 4 Charge warning light 21 Fuel selector valve handle 5 TCU boost warning light 22 Switches EFIS EFIS back up battery propeller avionics taxi lig...

Page 124: ...ypically 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 dat...

Page 125: ...n 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 to the main bus In the event of a charge system failure Switch the EFIS ma...

Page 126: ...aph 7 12 The flap controller is powered from the main bus The flap controller in turn powers the flap motor via a circuit breaker located on the instrument panel refer to paragraph 7 19 2 The trim mot...

Page 127: ...mperature indicator Tachometer Chronometer First aid kit compliant with national legislation Fire extinguisher WARNING Notwithstanding that installed equipment may include GPS and other advanced fligh...

Page 128: ...ve is via reduction gear with integrated shock absorber 7 16 Cooling system Cylinders are air cooled Cylinder heads are liquid cooled via a closed circuit system with an expansion tank A camshaft driv...

Page 129: ...an be used refer to the latest edition revision of the ROTAX 914 UL engine Operator Manual Refer to the latest revision of the Rotax service instruction SI 914 019 Coolant system volume Coolant system...

Page 130: ...hanism which stops 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...

Page 131: ...lectrical system which are relevant can aid the pilot operator s understanding of the aircraft s systems and their use with respect to the operational procedures described in this manual Refer to para...

Page 132: ...h 7 19 1 The charge relay coil is powered from the main bus i e needs power from the main bus to remain energized closed Loss or removal switching the Master switch off of power to the main bus will r...

Page 133: ...p circuit 9 The charge system relay is de energized and disconnects the charge system from the battery and main bus 10 TCU Turbocharger Control Unit waste gate servo With regard to the above 1 The aux...

Page 134: ...ter switch connects the electrical system main bus to the 12 V main battery and charge regulator rectifier output system via the charge system relay Refer to paragraph 7 19 1 Ignition magneto and star...

Page 135: ...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 136: ...Airplane Factory SLING 4 Pilot Operating Handbook Page 7 33 DC POH 001 X C 3 Revision 1 3 7 19 1 Charge system start system fuel pump wiring diagram...

Page 137: ...Airplane Factory SLING 4 Pilot Operating Handbook Page 7 34 DC POH 001 X C 3 Revision 1 3 7 19 2 Switches and circuit breakers wiring diagram...

Page 138: ...Airplane Factory SLING 4 Pilot Operating Handbook Page 7 35 DC POH 001 X C 3 Revision 1 3 7 19 3 EFIS back up circuit back up battery wiring diagram...

Page 139: ...eller controller is provided via the main bus through a circuit breaker and is activated by a switch labeled PROP located on the instrument panel Refer to paragraph 7 19 2 Reference should be made to...

Page 140: ...POH 001 X C 3 Revision 1 3 7 21 Fuel system A Left fuel tank F Rotax 914 UL engine B Right fuel tank G Fuel flow sensor C Fuel filter s H Fuel pressure sensor D Fuel selector LEFT RIGHT OFF Fuel line...

Page 141: ...fuel pick up An inline mesh fuel filter is fitted in the fuel line from each tank to the fuel tank selector valve which is mounted on the lower centre instrument panel in the cockpit refer to paragra...

Page 142: ...nd main bus as long as the main bus is powered i e the master switch is on and the charge system relay is energized not failed The pump is protected by a circuit breaker located on the instrument pane...

Page 143: ...of the tank The aircraft should at no time be subjected to a sustained side slip towards a near empty fuel tank i e wing with near empty tank down as despite the baffling this may lead to fuel running...

Page 144: ...mperature is sensed by a sensor located on the oil pump housing The lubrication circuit is vented at the oil reservoir The turbocharger is supplied with oil via a separate oil line from the main pump...

Page 145: ...U 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 activated to...

Page 146: ...ure possible airbox leak BOOST LIGHT INDICATION Illuminates steadily Blinks CAUTION LIGHT INDICATION Blinks NOTE Boost pressure will not be reduced automatically Limited operation as boost control may...

Page 147: ...AUTOPILOT located on the instrument panel refer to paragraph 7 19 2 This switch must be on for the autopilot EFIS outputs to have any effect on aircraft attitude The autopilot can be engaged in sever...

Page 148: ...sion 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...

Page 149: ...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...

Page 150: ...spection 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 main...

Page 151: ...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 spre...

Page 152: ...procedure 1 Check Fuel selector shut off circuit breakers and Master switch switched off 2 Check Magnetos switched off 3 Secure the control column s using for example a safety harness 4 Close air vent...

Page 153: ...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 154: ...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 155: ...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 156: ...ications 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 157: ...LEMENTARY INFORMATION This section contains the appropriate supplements necessary to safely and efficiently operate the aircraft when equipped with various optional systems and equipment not provided...

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