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Flight Manual STEMME S6 

 

 

Doc.-No.:P400-006.000 E 

Page: 1-6 

Revision: 9 

Date of Issue: 07. October 2008 

Date of Rev.: 01.10.2012 

Engine 

Design 

4-Cylinder 4-Stroke Otto-engine in 

opposed-cylinder design, 

Turbocharger with electronic 

Manifold-Air-Pressure (MAP) control, 

integrated reduction gear 

Model 

Rotax 914 F2 

Max. Take-off Power  113.3 HP / 84.5 kW at 5800 RPM 

(Takeoff RPM limited to 5600 RPM) 

Max. Continuous 

Power 

98.4 HP / 73.4 kW at 5500 RPM 

Fuel Consumption at 

Max. Continuous 

Power (100%) 

7.0 US gal/h / 26.6 l/h 

Fuel Consumption at 

75% Power  

5.4 US gal/h / 20.4 l/h 

Fuel Consumption at 

55% Power 

3.4 US gal/h / 13.0 l/h 

Transmission-Ratio 

of Reduction-Gear 

i=2.428 

Propeller 

Design 

Electrically-adjustable  3-Blade 

Constant-Speed Propeller 

Model 

MTV-7-A/170-051 with Constant-

Speed Control-Unit 

Diameter 

5.58 ft / 1.70 m 

Front-Drive 

Design 

Gear in Magnesium-Casing, mounted 

elastically on rubber elements 

Model 

STEMME 050.251 

Transmission-Ratio  i=1.100 

Fuel-Tanks 

Design 

Integral-tanks located in the forward 

section of the inner-wing 

Capacity 

17.2 US gal / 65 l in right-hand inner-

wing (optionally 17.2 US gal / 65 l in 

left-hand inner-wing) 

Non-useable Fuel 

0.55 US gal / 2.1l in right-hand wing-

tank (optionally 0.3 US gal/ 1l in left-

hand wing-tank) 

 
 

Summary of Contents for S6

Page 1: ...0 006000 E Page i Revision 10 Date of Issue 07 October 2008 Date of Rev 06 07 2020 FLIGHT MANUAL TSA M VARIANT S6 DOCUMENT NUMBER P400 006000 E DATE OF ISSUE OCTOBER 07 2008 Model S6 Serial number _ _ _ _ _ _ _ _ Specification EASA A 143 Registration _ _ _ _ _ _ _ _ ...

Page 2: ...ancies in the translation the German version is deemed binding This motorglider may only be operated in correspondence to the instructions and operating limitations specified in this Flight Manual CONTACT STEMME AG Flugplatzstraße F2 Nr 6 7 D 15344 Strausberg Phone 49 3341 3612 0 E mail info stemme com Web www stemme com All rights reserved Reproduction or disclosure of this document or any part t...

Page 3: ...outer side of the page The newest revision number of all revi sions on the page is mentioned in the footnote section of the page along with the date of the newest revision Compliance with the new revisions to the operations manual and the corre sponding aircraft is documented by the signature of the correcting person in the table below Rev No Section No of Pages Date of Revision Pertaining to Note...

Page 4: ...6 7 6 7 20 7 28 7 29 7 33 7 36 8 5 26 09 2011 P061 2011 056 HoA Stemme AG 7 0 6 9 iv v vii viii 6 16 9 3 01 11 2011 P061 2011 072 HoA Stemme AG 8 0 9 iii iv v viii 9 3 16 03 2012 P061 2011 125 HoA Stemme AG 9 0 2 5 7 iv v vii 1 6 2 5 to 2 7 5 11 5 13 5 16 7 20 01 10 2012 P061 2012 094 EASA Approval 10013559 10 0 2 4 7 i x 2 17 4 8 4 23 7 1 7 2 7 36 7 44 06 07 2020 P061 2018 027 The technical conte...

Page 5: ... v 11 12 10 2020 vi 11 12 10 2020 vii 11 12 10 2020 viii 11 12 10 2020 ix x 10 06 07 2020 Chap 1 1 1 1 2 1 28 01 2011 1 3 1 4 1 5 2 20 05 2011 1 6 9 01 10 2012 1 7 1 8 1 9 1 10 1 11 1 12 Chap 2 2 1 2 2 X 2 3 X 2 4 X 2 5 X 9 01 10 2012 Page EASA appro ved Rev No Date of Issue or Revision 2 6 X 9 01 10 2012 2 7 X 9 01 10 2012 2 8 X 2 9 X 2 10 X 2 11 X 2 20 05 2011 2 12 X 2 13 X 2 14 X 2 15 X 2 20 05...

Page 6: ... X 3 39 X 3 40 X Chap 4 4 1 4 2 X 6 26 09 2011 4 3 X Page EASA appro ved Rev No Date of Issue or Revision 4 4 X 1 28 01 2011 4 5 X 1 28 01 2011 4 6 X 4 7 X 4 8 X 10 06 07 2020 4 9 X 4 10 X 6 26 09 2011 4 11 X 4 12 X 4 13 X 1 28 01 2011 4 14 X 6 26 09 2011 4 15 X 6 26 09 2011 4 16 X 1 28 01 2011 4 17 X 1 28 01 2011 4 18 X 1 28 01 2011 4 19 X 1 28 01 2011 4 20 X 1 28 01 2011 4 21 X 1 28 01 2011 4 22...

Page 7: ...2011 6 2 1 28 01 2011 6 3 6 4 6 5 6 6 6 7 6 8 6 9 6 10 6 11 6 12 1 28 01 2011 6 13 3 14 06 2011 6 14 1 28 01 2011 6 15 3 14 06 2011 6 16 7 01 11 2011 Page EASA appro ved Rev No Date of Issue or Revision Chap 7 7 1 10 06 07 2020 7 2 10 06 07 2020 7 3 7 4 7 5 1 28 01 2011 7 6 6 26 09 2011 7 7 7 8 2 20 05 2011 7 9 3 14 06 2011 7 10 1 28 01 2011 7 11 1 28 01 2011 7 12 1 28 01 2011 7 13 1 28 01 2011 7 ...

Page 8: ...te of Issue or Revision 7 35 1 28 01 2011 7 36 10 06 07 2020 7 37 10 06 07 2020 7 38 10 06 07 2020 7 39 10 06 07 2020 7 40 10 06 07 2020 7 41 10 06 07 2020 7 42 10 06 07 2020 7 43 10 06 07 2020 7 44 10 06 07 2020 Chap 8 8 1 8 2 8 3 1 28 01 2011 8 4 8 5 6 26 09 2011 8 6 8 7 8 8 8 9 8 10 8 11 8 12 Chap 9 9 1 1 28 01 2011 9 2 1 28 01 2011 9 3 8 16 03 2012 9 4 ...

Page 9: ...___________________________ Chapter 1 General Chapter 2 Operating Limitations Chapter 3 Emergency Procedures Chapter 4 Normal Operating Procedures Chapter 5 Flight Performance Chapter 6 Mass and Balance Chapter 7 Description of the Motorglider and its Systems and Equipment Chapter 8 Handling Servicing and Maintenance Chapter 9 Supplements ...

Page 10: ...FLIGHT MANUAL TSA M VARIANT S6 Doc No P400 006000 E Page x Revision 10 Date of Issue 07 October 2008 Date of Rev 06 07 2020 INTENIONALLY LEFT BLANK ...

Page 11: ...ication 1 3 1 3 Warnings Cautions and Notes 1 4 1 4 Dimensions and Specifications 1 5 1 5 Three View Drawing 1 7 1 6 Terminology and Abbreviations 1 8 1 6 1 Speeds 1 8 1 6 2 Meteorological Terminology 1 8 1 6 3 Mass and Balance 1 9 1 6 4 Abbreviations for Aircraft and Powerplant 1 9 1 6 5 Miscellaneous 1 10 1 7 Units and Conversion Factors 1 11 1 8 References 1 12 ...

Page 12: ...ll information necessary for safe practical and optimized operations of the motorglider Stemme S6 equipment option S6 T Fix Landing Gear The Flight Manual contains all information for the pilot required by CS 22 Additionally it contains further data and details considered by the manufacturer to be useful to the pilot The operating instructions for the engine model ROTAX 914 F2 and for the propelle...

Page 13: ...n type certified type certificate nr EASA A 143 by EASA on November 22 2008 in Cologne Germany The variant STEMME S6 has been certified in correspondence to the Certification Specifications for Sailplanes and Powered Sailplanes CS 22 of EASA published as EASA Decision ED 2003 13 RM on November 14 2003 Airworthiness has been certified in the utility category The noise certification is based on ICAO...

Page 14: ...have been especially marked by the use of one of the following terms Warning implies that non observation of corresponding procedure leads to immediate or significant degradation of flight safety Caution implies that non observation of the corresponding procedure leads to a minor yet possibly long term degradation of flight safety Note draws attention to any special item not directly related to sa...

Page 15: ...threepart Spar carbon fiber composites Shell carbon fiber composites sandwich structure Span 59 05 ft 18 00 m Wing Area 187 51 ft 17 42 m Aspect Ratio 18 62 Dihedral 2 Wing Airfoil DU changes with wingspan Air brakes Design Schempp Hirth style Air brakes at outer wing Length 4 905 ft 1 495 m Horizontal Stabilizer Design Carbon fiber composite bars and sandwich structure Stabilizer Span 10 73 ft 3 ...

Page 16: ...tion at 75 Power 5 4 US gal h 20 4 l h Fuel Consumption at 55 Power 3 4 US gal h 13 0 l h Transmission Ratio of Reduction Gear i 2 428 Propeller Design Electrically adjustable 3 Blade Constant Speed Propeller Model MTV 7 A 170 051 with Constant Speed Control Unit Diameter 5 58 ft 1 70 m Front Drive Design Gear in Magnesium Casing mounted elastically on rubber elements Model STEMME 050 251 Transmis...

Page 17: ...nual STEMME S6 Doc No P400 006 000 E Page 1 7 Revision Date of Issue 07 October 2008 Date of Rev 1 5 Three View Drawing ______________________________ Illustration 1 1 Threeview Drawing of STEMME S6 Version S6 T ...

Page 18: ...ed only in calm air vFE Maximum Flaps Extended Speed vH Maximum Cruise Speed vNE Never Exceed Speed vRA Maximum Speed in Rough Air vS0 Stalling Speed in landing configuration vS1 Stalling Speed in given configuration vx Speed for best angle of climb vy Speed for best rate of climb 1 6 2 Meteorological Terminology ISA International Standard Atmosphere Temperature at MSL 59 F 15 C Air Pressure at MS...

Page 19: ...maginary point at which gravity acts on the aircraft Lever Horizontal distance between the center of gravity of a body and the reference plane Moment Product of Mass and Lever of a body Non useable Fuel Fuel which remains in the tank and is not available for the flight Useable Fuel Amount of fuel which is available for the flight Payload Difference between empty mass and take off mass NLP Non Lift...

Page 20: ...by COM Communication GFC Glass fiber composites CFC Carbon fiber composites VFR Visual Flight Rules NVFR Night time Visual Flight Rules EASA European Aviation Safety Agency SB Service Bulletin LBA German Aviation Authority Luftfahrt Bundesamt CS Certification Specification Constant Speed Propeller MOGAS Regular higher octane car gasoline Motor Gasoline LDG Landing T O Take off AVGAS Gasoline for A...

Page 21: ...__________ Dimension Conversion Imperial Unit Metric Unit Distance 1 1 1 in ft NM 25 4 0 3048 1 852 mm m km Speed 1 1 1 kts fpm mph 1 852 0 00508 1 609 km h m s km h Mass 1 lbs 0 454 kg Volume 1 1 US gal qts 3 7854 0 9464 l l Temperature 1 F F 32 1 8 C Pressure 1 1 psi inHg 68 95 1000 33 86 bar hPa mbar Revolution Speed 1 RPM 1 RPM Force 1 lbf 4 448 N ...

Page 22: ...om other manufacturers However the information presented in this Flight Crew Operation Manual is obligatory Engine and Engine Instruments Manufacturer BRP Rotax GmbH Co KG Welser Strasse 32 A 4623 Gunskirchen Austria Telefone 43 0 7246 601 0 Fax 43 0 7246 6370 Internet www rotax aircraft engines com Constant Speed Propeller Manufacturer mt Propeller Entwicklung GmbH Aiport Straubing Wallmuehle D 9...

Page 23: ... Markings 2 7 2 6 Markings on other Instruments 2 8 2 7 Masses 2 9 2 8 Center of Gravity CG 2 10 2 9 Permitted Maneuvers 2 11 2 10 Maneuver Load Factors 2 12 2 11 Operating Altitude 2 13 2 12 Flight Crew 2 14 2 13 Permitted Modes of Operation 2 15 2 14 Minimum Equipment 2 16 2 15 Fuel 2 17 2 16 Lubricant and Coolant 2 18 2 16 1 Lubricant 2 18 2 16 2 Coolant 2 19 2 17 Additional Limitations 2 21 2 ...

Page 24: ...e 07 October 2008 Agency approved Date of Rev 2 1 Introduction ____________________________________ This chapter describes the operating limitations instrument markings and placards These need to be followed for a safe operation of the motorglider its engine and its standard equipment ...

Page 25: ...t High Altitude When flying at this speed the flight controls are not allowed to be moved more than 1 3 of their maximum deflection vA vRA Maneuvering Speed and Maximum Speed in Rough Air Strong Turbulence 102 kts 190km h Above this speed the flight controls are not allowed to be moved to their maximum deflection In strong turbulence the pilot may not fly faster than this air speed Strong turbulen...

Page 26: ... flaps set to TO LDG 1 Green Arc 52 to 102 kts 96 to 190 km h Normal operating range The lower limit is 1 1 VS1 at MTOM and most forward CG location with flaps set in the neutral position The upper limit is the maximum air speed in strong turbulence Yellow Arc 102 to 145 kts 190 to 270 km h The airplane may not be flown in this range in strong turbulence Maneuvers may only be flown carefully Red L...

Page 27: ...M Takeoff RPM limited to 5600 RPM by const speed propeller control g Max Continuous Power 98 4 HP 73 4 kW at 5500 RPM h Max Altitude with Constant Power T O Power Continuous Power To max 8000 ft 2450 m MSL To max 16000 ft 4875 m MSL Max Cylinder Head Temperature CHT minimum maximum 122 F 50 C 275 F 135 C i Fuel Pressure minimum normal maximum Air Box Pressure 4 43 inHg 1 5 x 10 1 bar 7 38 inHg 2 5...

Page 28: ...C b Oil Pressure minimum maximum normal 44 3 inHg 1 5 bar 206 7 inHg 7 0 bar only briefly allowed when starting cold engine 44 3 inHg to 147 7 inHg 1 5 to 5 0 bar c Amount of Oil minimum maximum max permitted Oil Consumption 0 5 US gal 2 l 0 8 US gal 3 l 0 02 US gal h 0 06 l h Coolant a Coolant Conventional coolant on the basis of ethylene glycol mixtures mixture of 50 water 50 ethylene glycol For...

Page 29: ... Green Arc Normal Operating Range Yellow Arc Upper Warning Range Red Line Upper Limit Tachometer RPM 1400 5500 5500 5600 5600 Oil Temperature F C 122 50 122 266 50 130 266 130 CHT F C 122 275 50 135 275 135 Oil Pressure inHg bar 44 3 147 7 1 5 5 147 7 206 7 5 7 206 7 7 Manifold Air Pressure inHg bar 36 0 40 5 1 22 1 37 40 5 1 37 A short time overspeed up to max 5800 RPM max allowed engine RPM of e...

Page 30: ...te of Issue 07 October 2008 Agency approved Date of Rev 2 6 Markings on other Instruments ____________________ Indicating Range Instrument Red Line Lower Limit Green Arc Normal Operating Range Yellow Arc Upper Warning Range Red Line Upper Limit Voltmeter V 11 5 Amperemeter A ...

Page 31: ...Masses _________________________________________ Maximum Take Off Mass 1874 lbs 850 kg Maximum Landing Mass 1874 lbs 850 kg Maximum Payload in Rear Baggage Compartment 44 lbs 20 kg Warning Exceeding the mass limits can cause the A C to be overstressed and might cause a significant reduction in flight performance and flight qualities ...

Page 32: ... measured from the reference plane RP This plane is vertical to the wing leading edge near the wing root For orientation of the plane see chapter 6 Location Limits for the Center of Gravity The in flight CG must be kept within the following limits when flying 1 Most forward in flight CG Limit x 8 82 in 224 mm behind RP 2 Most rearward in flight CG Limit x 16 10 in 409 mm behind RP Warning Operatin...

Page 33: ...rmitted Maneuvers _____________________________ The STEMME S6 motorglider is certified according to CS 22 in the Utility category This certification includes the following maneuvers 1 All regular non aerobatic maneuvers 2 Maneuvers with a maximum bank angle of 60 Caution Aerobatics including intentional spins and flights in clouds are NOT permitted ...

Page 34: ...tors __________________________ When flying the permitted maneuvers the following maximum load factors are only allowed at vA at vNE Positive 5 3 4 0 Negative 2 65 1 5 Warning Increasing the maneuver load factors past the allowed limits causes the aircraft structure to be overloaded Caution Maneuvers with an intentional negative load are not permitted ...

Page 35: ... Issue 07 October 2008 Agency approved Date of Rev 2 11 Operating Altitude _______________________________ The maximum demonstrated operating altitude with the engine running is at 16000 ft 4875 m MSL At higher altitudes an unproblematic restart of the engine cannot be guaranteed ...

Page 36: ..._______ Maximum Number of Crew Members 2 Minimum Number of Crew Members 1 Pilot If the A C has all necessary equipment additional air speed indicator and wheel brake on the right hand side it may be flown from the left seat or the right seat Caution Keep the minimum load in mind It may be needed to carry ballast mass in the aircraft to reach the minimum load see also page 2 22 ...

Page 37: ... 20 05 2011 2 13 Permitted Modes of Operation _____________________ Permitted modes of operation are 1 VFR flights in day time only 2 No Aerobatics no maneuvers with negative load factors Caution Flights into known icing conditions or into thunderstorm conditions are not permitted Note Aerotow and winch launching are not permitted ...

Page 38: ... Speed Indicator 0 200kts 0 350 km h Magnetic Compass Electric Trim Indicator Minimum Equipment Engine Instruments Fuel Gauge Oil Temperature Gauge Fuel Pressure Warning Light Oil Pressure Gauge Cylinder Head Temperature CHT Gauge Manifold Air Pressure MAP Gauge Amperemeter Voltmeter Tachometer Generator Caution Light Engine Hours Meter additional operational minimum equipment Safety belts for eac...

Page 39: ...left 0 3 US gal 1 l AVGAS contains lead which deposits at the valve lip and in the combustion chamber According to ROTAX AVGAS may only be used when vapor bubbles form or when other fuel is not available refer to ROTAX SI 914 019 latest Revision Caution Only use fuels which are appropriate for the local climate conditions Note The fuel sensor is calibrated to RON 95 All other fuel types and mixtur...

Page 40: ...VGAS is used do NOT use fully synthetic oil Note Only use oils according to the API specifications Only oils of the type SF or SG with gear additives GL4 or GL5 are permitted Note Because it is stable in high temperatures and causes little residue partially synthetic and fully synthetic oils are preferred These should be for 4 stroke high performance engines Select the viscosity of the lubricating...

Page 41: ...s of a ethylene glycol mixture For recommended coolants refer to latest Revision of Service Instruction Selection of suitable Operating Fluids for ROTAX Engine Type 912 and 914 Series SI 914 019 by ROTAX The coolant should be used with a mixture ratio of 1 1 Waterless coolants are NOT recommended by the manufacturer With the same operating conditions they cause higher engine temperatures Warning H...

Page 42: ... cooling system This might lead to bad cooling performance Caution Because of the possible deposits and the fire danger do NOT use pure anti freeze concentrate Pure anti freeze solidifies at 18 C Coolant Capacity maximum Coolant Capacity 0 66 US gal 2 5 l minimum Coolant Capacity 0 63 US gal 2 4 l max Capacity of Expansion Reservoir 0 05 US gal 0 2 l min Capacity of Expansion Reservoir 0 03 US gal...

Page 43: ...ake offs and landings in conditions with higher crosswind components may cause uncontrollable flight conditions 2 17 2 Electronic Equipment Do NOT use or turn on other electronic equipment except the equipment which is installed in the airplane Other equipment may cause interference with the aircraft s avionics Examples of non allowed equipment are Mobile phones Radio remote controls Devices using...

Page 44: ...9 2011 2 18 Placards for Operating Limitations _________________ The following section describes placards for operating limitations and their position in the cockpit Note Additional placards and their positions are mentioned in the maintenance manual Illustration 2 2 Position of Placards on the Instrument Panel and Canopy Frame 4 3 1 5 ...

Page 45: ...nded pos Flaps TO LDG 1 VFE 190 km h LDG 2 VFE 140 km h Empty Weight kg Max Take Off Weight 850 kg Min Seat Load kg otherwise ballast Max Cockpit Load kg Permitted Flight Figures None Note Check Load before every flight Change in the cockpit load with load in the baggage compartment LMCL New LMCL L x 2 2 LMCL New increased min cockpit load LMCL min cockpit load L baggage weight baggage weight kg I...

Page 46: ... speed indicator not required if these markings are on the air speed indicator Fuel Diff Pressure 2 5 1 0 4 Mounted on the instrument panel next to the Fuel Pressure Difference Gauge AUX 64 l MAIN 62 9 l 5 Mounted below the fuel gauges left right VNE IAS ft MSL kts 0 145 6500 145 10000 138 13000 132 16500 124 19500 119 26000 105 33000 92 39500 81 VNE IAS m MSL km h 0 270 2000 270 3000 255 4000 245...

Page 47: ...und 3 10 3 8 2 Engine Failure during Take Off 3 11 3 8 3 Engine Failure during Flight 3 12 3 8 4 Drive Section Failure 3 14 3 8 5 Failure of Engine Starter 3 14 3 9 Fire 3 15 3 9 1 Fire in the Engine Compartment 3 15 3 9 2 Electrical Fire 3 16 3 10 Emergency Procedures during Take Off 3 17 3 10 1 Aborted Take Off 3 17 3 11 Emergency Landing Procedures 3 18 3 11 1 Off Field Landing 3 18 3 11 2 Emer...

Page 48: ...occur When all mandatory procedures for pre flight checks and maintenance are observed a malfunction of the engine or important equipment is very unlikely To manage an occurring problem the emergency procedures described here are recommended It is not possible to incorporate all types and combinations of possible emergencies into this Flight Manual therefore a good knowledge of the design and hand...

Page 49: ...res ________ Emergency Airspeed IAS kts km h Engine Failure during take off Flaps set to TO LDG 1 60 kts 110 km h Air speed for the best glide angle Flaps set to NEUTRAL 60 kts 110 km h Approach speed for safety landing Flaps set to TO LDG 1 engine running 60 kts 110 km h Approach speed for emergency landing engine malfunction Flaps set to TO LDG 1 60 kts 110 km h ...

Page 50: ..._______________ Jettison the canopy as follows 1 Red emergency handle PULL strongly center of instrument console 2 The canopy is pushed upwards by a gas spring If necessary push by hand Warning The rear canopy lock must remain engaged when the canopy is jettisoned This causes the canopy to be lifted only at the front end and to be torn away by the air stream ...

Page 51: ... Out ________________________________________ After the canopy is jettisoned 1 Central lock of the safety belts OPEN 2 Bail out over the side Drop below the wing to avoid collision with the tail unit Note The fixed side parts of the cockpit are made of a strong structure without sharp edges Use the side parts to pull out and brace ...

Page 52: ...ight an acoustic signal gives warning of a stall If the angle of attack is increased when the acoustic stall warning is activated or if a turn is then flown a wing drop may occur Depending on the CG position afterwards the A C may spin Stall Recovery in powered configuration 1 Elevator RELEASE back pressure PUSH forward 2 Throttle FULL POWER 3 Air speed WAIT for increase 4 Attitude CORRECT to norm...

Page 53: ...ynamic buffeting warns against the stall If the angle of attack is increased while aerodynamic buffeting occurs or if a turn is then flown a wing drop may occur Depending on the CG position afterwards the A C may spin Stall Recovery in glider configuration 1 Elevator RELEASE back pressure PUSH forward 2 Air speed WAIT for increase 3 Attitude CORRECT to normal flight attitude Warning When recoverin...

Page 54: ...EUTRAL as soon as the spin has stopped 7 A C with elevator PULL OUT of dive with caution Warning Altitude loss from start of the spin recovery to level flight may be 330 ft 100 m Warning Recovery from the spin with flaps in landing configuration can cause structural damage If the A C spins with flaps in landing configuration retract flaps to NEUTRAL and use standard procedure of spin recovery Caut...

Page 55: ...nning A C has the tendency to start a spiral dive after some spinning turns During a spiral dive the air speed and g forces will increase in a short time Spiral dive Recovery 1 Rudder and Aileron STOP ROTATION Deflect in the direction opposite to the turn 2 Elevator PULL OUT of the dive with caution Warning Do not exceed VNE 145 kts 270 km h during the recovery Note If the A C stops the spin by it...

Page 56: ...cy approved Date of Rev 3 8 Engine Failure __________________________________ 3 8 1 Engine Malfunction on Ground 1 Throttle IDLE 2 Brakes as required Warning Do NOT fly the A C if a malfunction is not completely repaired Caution If the oil pressure is in the red range turn OFF the engine immediately ...

Page 57: ...5 Fuel shut off valve CLOSE 6 Ignition OFF Depending on the situation it is possible to increase the glide ratio by setting the propeller to the feathered position 7 left Propeller switch MANU 8 right Propeller switch FEATHER Caution Final position is reached not until 90 sec In either case 9 Master switch OFF Caution If possible turn OFF the master switch just before landing The master switch als...

Page 58: ...ngine master switch at the panel fails In most cases the propeller windmills in the airstream In this case the engine starter does not need to be operated to restart the engine After engine failure in flight the following restart procedure is recommended 1 Air speed 55 kts 75 kts 100 km h 140 km h 2 Fuel shut off valve OPEN 3 Auxiliary fuel pump ON green lamp ON 4 Master Switch battery CHECK if ON...

Page 59: ...start of the engine fails 17 Prepare for an off field landing or a landing on next suitable airfield Caution Within 10 seconds after engine restart the oil pressure must be in the green range If not a major engine problem may exist Note With very low fuel it is possible to use the last remaining fuel by rocking the wings More instructions for engine restart in flight see 4 7 3 5 ...

Page 60: ... is recommended 1 Throttle immediately to IDLE 2 Air speed 60kts 110km h 3 Engine OFF if essential 4 Prepare for an off field landing or a landing on next suitable airfield 3 8 5 Failure of Engine Starter If the engine ignition switch fails the engine starter will not work for an in flight engine restart A failure of the engine ignition switch may be the cause The following procedure is recommende...

Page 61: ...4 Air speed 55 kts 65 kts 100 km h 120 km h 5 left Propeller switch MANU 6 right Propeller switch FEATHER Caution Final position is reached not until 90 sec 7 Engine master switch OFF 8 Cabin ventilation side window and or nozzle OPEN in case of smoke in cockpit 9 Emergency descent INITIATE as soon as possible EXTEND air brakes to perform 10 Off field landing PREPARE for next suitable terrain Warn...

Page 62: ...tor trim and propeller feathering If there is no open fire especially in the engine compartment an emergency landing can be done with engine power The engine ignition and electrical main fuel pump are independent from the master switch Keep in mind that the engine instrumentation except manifold air pressure cylinder head temperature gauge and the propeller feathering will NOT work The propeller w...

Page 63: ...oad on front wheel 4 Wheel brakes ACTIVATE If the take off needs to be aborted just after lift off establish a stable attitude and enough airspeed Then make a normal landing and use the wheel brakes with elevator pulled carefully 1 Throttle IDLE 2 Air speed 60 kts 110 km h 3 Air brakes EXTEND 4 Landing normal FLARE and TOUCH DOWN 5 Elevator on ground PULL carefully to reduce load on front wheel 6 ...

Page 64: ... always check 1 Loose Items STOW and SECURE 2 Seat belts TIGHTEN 3 11 2 Emergency Landing 3 11 2 1 Emergency Landing on Soft Ground When landing on soft ground which does not carry the A C well the following procedure is recommended For landing at the selected area with soft ground change to glider configuration 1 Fuel shut off valve CLOSE 2 Ignition OFF drain float chamber if possible 3 left Prop...

Page 65: ...11 2 2 Landing with Damaged Tire When a tire is actually or possibly damaged after take off the following procedure is recommended Damaged Main wheel 1 Flaps TO LDG 1 2 Land the A C at the runway side of the undamaged wheel Then there is enough space for direction changes 3 Land the A C with the wing low on the side of the undamaged wheel 4 Taxi with aileron fully deflected to the side of the unda...

Page 66: ... glider configuration Before landing close the cabin ventilation and the emergency window Approach and Landing 1 Approach GLIDER CONFIGURATION 2 Cabin ventilation and emergency window CLOSED 3 Touch down with MINIMUM AIR SPEED If the A C is under water after touch down open the cabin ventilation and emergency window to equalize the pressure between the cockpit and the water This is needed to open ...

Page 67: ...essure equalization by opening the cabin ventilation and emergency window 3 11 2 5 Landing with Ground Loop If a collision is not avoidable during the final part of the landing initiate a ground loop with enough distance from the obstacle 1 Wheel brakes Activate FULL At the same time 2 Rudder DEFLECT FULL in one direction 3 Aileron DEFLECT FULL in the same direction Caution The nose wheel is only ...

Page 68: ... is below 1 5 the fuel pressure is below the allowable limit of 150 mbar 2 1 psi There can also be a malfunction of the gauge or sensor system The low fuel pressure can cause an engine malfunction The cause could be no fuel supply to engine engine malfunction fuel system malfunction The following procedure is recommended 1 Fuel shut off valve OPEN 2 Auxiliary fuel pump ON green light is ON 3 Fuel ...

Page 69: ...ure If it is not possible to restore the normal fuel pressure prepare to land on the next suitable airfield A sudden engine failure must be expected at anytime b Fuel pressure above 3 5 If the fuel pressure indicator is above 3 5 the fuel pressure is above the allowable limit There can also be a malfunction of the gauge or sensor system The high fuel pressure can cause an engine failure The reason...

Page 70: ...ion Light is continuously ON If the yellow low fuel caution light is continuously ON there is only 1 3 1 9 US gal 5 7 l of fuel in the main tank feeder compartment This can also be a malfunction of the sensor system A blinking low fuel caution light may be triggered by sloshing fuel Lack of fuel will cause an engine failure The reason for not enough fuel can be a malfunction of the fuel system The...

Page 71: ...uel flowing from the left auxiliary tank to the right main tank where it could not be used the following procedure is recommended 5 Fuel Transfer Pump If a malfunction of the fuel circulation pump is suspected ON until the yellow Low Fuel Caution Light goes OFF Then OFF until the yellow Low Fuel Caution Light comes ON again Repeat until landing If there is NO MALFUNCTION and the yellow Low fuel Ca...

Page 72: ...Hg engine speed 5000 RPM 2 Lower engine power has to be expected the MAP control is not running correctly Caution If the allowed engine limits are exceeded this must be documented by the pilot in the A C logbook with details like nature of incident date duration and the degree of exceeding Red MAP warning light is FLASHING Take off power was used for more than 5 minutes 1 Throttle REDUCE to maximu...

Page 73: ...with THROTTLE red MAP warning light must be OFF Recommended operating limits 75 MCP MAP 31 inHg engine speed 5000 RPM 2 Turn OFF waste gate actuator with TCU isolation switch the red safety switch is UP if manual control is not satisfactory 3 Lower engine power has to be expected when the manifold air pressure control is not operating correctly 4 Run up to maximum RPM Caution If the yellow TCU cau...

Page 74: ...able airfield In the case of a failed alternator the battery will be discharged constantly To save energy switch OFF all electrical equipment that is not needed 3 12 1 7 Yellow Internal Generator Caution Light is ON If the engine is running the yellow internal generator caution light ON shows a malfunction of the internal generator This is not a critical situation The internal generator bus is sup...

Page 75: ...witch OFF not the engine ignition switch 2 All electrical systems OFF Generator Avionics 3 All system circuit breakers CHECK do not push in popped out circuit breakers 4 Master circuit breaker CHECK PULL and then PUSH 5 Master switch ON When the electrical system is available again the voltmeter shows normal voltage try to switch ON individual systems If possible avoid to switch ON systems with ci...

Page 76: ...CK the corresponding circuit breakers 3 WAIT for about 10 seconds TCU self test 4 Turn ON the waste gate actuator with TCU isolation switch in the DEACTIVATED position the switch is DOWN 5 If it is not possible to restore the electric power supply the RPM and manifold air pressure must be controlled by hand Recommended operating limits 75 MCP MAP 31 inHg engine speed 5000 RPM Lower engine power mu...

Page 77: ...tion might be possible if there is no safe landing area MONITOR engine instruments especially oil pressure If the MAP and RPM suddenly drop and the yellow TCU caution light is FLASHING at the same time a malfunction of the turbocharger control is most likely 3 The waste gate possibly will not close Lower engine power must be expected With the waste gate open the engine power is limited to approx 8...

Page 78: ... throttle the throttle cable is most likely broken The power setting rises by spring load to 115 full throttle It is recommended to climb to a safe altitude for changing to the glider configuration and landing on a suitable airfield Then TURN OFF the engine 3 Air speed 62 kts 115 km h 4 At safety altitude fuel shut off valve CLOSE 5 After engine stops Ignition OFF 6 After the engine has cooled dow...

Page 79: ...to re activate waste gate actuator If the system is not operating normally 3 TCU isolation switch to ACTIVATED position the switch is UP to isolate the waste gate actuator permanently 4 Manifold air pressure is not controlled automatically anymore Control MAP red MAP warning light must remain OFF with the throttle Recommended operating limits 75 MCP MAP 31 inHg engine speed 5000 RPM Caution If the...

Page 80: ...ad temperature CHT is exceeded this must be documented by the pilot in the A C logbook with details like nature of incident date duration and the degree of exceeding 3 12 1 14 Exceeding the Maximum Oil Temperature If the maximum allowed oil temperature is exceeded the following procedure is recommended 1 Cowl flaps fully OPEN 2 Throttle REDUCE as necessary for safe flight 3 If the oil temperature ...

Page 81: ...il pressure drops below minimum this must be documented by the pilot in the A C logbook with details like nature of incident date duration and the degree of exceeding 3 12 1 16 Oil Pressure below Minimum on Ground If the oil pressure is below minimum on ground the following procedure is recommended 1 Engine SHUTDOWN immediately 2 Oil quantity CHECK 3 Type of oil in use CHECK 4 Oil system and or en...

Page 82: ...itch high RPM STOP constant pitch constant RPM FEATHER high pitch low RPM Warning With the Constant Speed Control not working the RPM changes with the airspeed Correct the propeller pitch manually when changing the airspeed When changing to higher airspeed there is the danger of exceeding the maximum allowed RPM when not correcting the propeller pitch in the FEATHER direction to the desired RPM 4 ...

Page 83: ...cause propeller and engine are not working under proper conditions 7 Before LANDING CHECK at 115 km h 62 kts airspeed if the Start RPM is reached when executing a carefully THROTTLE UP Avoid exceeding the maximum allowed RPM If the Start RPM is reached the propeller is near the START pitch Landing can be executed normally If the Start RPM is NOT reached the propeller is near the CRUISE pitch the p...

Page 84: ...ally The control light may have failed If the Start RPM is NOT reached the propeller is near the CRUISE pitch the pitch is too high for Take Off and Landing Reduced performance and rate of climb must be expected in the case of a go around The yellow light comes ON for more than 1 second 1 Notify manufacturer After consultation with the manufacturer and some tests of the propeller pitch a ferry fli...

Page 85: ...re for an off field landing or landing on the next suitable airfield 3 12 3 Flights in Icing Conditions Flights into icing conditions are not allowed If icing conditions are met unintentionally ice can build up on Wings Tail surfaces Flight controls Propeller The risk of ice is greater at high altitudes Additionally ice on the cockpit canopy can reduce the visibility It is recommended to initiate ...

Page 86: ...ired 2 CHECK if all flight controls react as intended 3 Afterwards immediately LAND on next suitable airfield Caution After a lightning strike all electrical systems will most likely have malfunctions or be completely inoperational Communication and Transponder will be the first systems to fail after lightning strike Warning An A C made of composite materials is more easily damaged by lightning st...

Page 87: ... Exterior Inspection 4 14 4 6 2 Interior Inspection 4 15 4 7 Normal Operating Procedures and recommended Airspeeds 4 16 4 7 1 Start of Engine Warm Up and Taxiing 4 16 4 7 2 Take Off and Climb 4 18 4 7 3 Cruise Cross Country Flying 4 22 4 7 4 Landing in Powered Configuration 4 27 4 7 5 Landing in Glider Configuration 4 30 4 7 6 After Landing and Parking 4 31 4 7 7 Flights at High Altitude 4 32 4 7 ...

Page 88: ...ative position for fast cruise permitted up to VNE 145 kts 270 km h NEUTRAL neutral position for slow cruise also intended for flights between regions of lift in glider configuration permitted up to VNE 145 kts 270 km h TO LDG 1 positive position for T O approach landing thermalling in glider configuration permitted up to VF 102 kts 190 km h LDG 2 Landing position for final approach and landing pe...

Page 89: ...m h Air speed for initial climb over 50 ft 15 m obstacle Flaps set to TO LDG 1 60 kts 110 km h Air speed for best angle of climb vX at MSL Flaps set to TO LDG 1 46 kts 85 km h Air speed for best rate of climb vY at MSL Flaps set to NEUTRAL 62 kts 115 km h Landing Approach speed for normal landing Flaps set to TO LDG 1 or LDG 2 60 kts 110 km h Minimum air speed for go around Flaps set to TO LDG 1 o...

Page 90: ...ly rotate the propeller in direction of rotation of propeller and engine 4 3 1 Fuselage 1 Position the fuselage and prevent it from rolling away with parking brake and chocks 2 Master switch MUST be OFF ignition key MUST be REMOVED 3 Close the canopy 4 Rotate 3 blade propeller by hand into Y position one blade vertically down 5 Remove side fairings and upper fairing 4 3 2 Wing Inner wing IW 1 Prep...

Page 91: ...ntion to correct audible engagement of the quick disconnect fittings Pull to test for secure fit 8 Connect the plug for the electrical connections and the fuel sensor 9 Install the cover at the cockpit s rear wall 10 Connect the 2 plugs for the pressure tubes at the left side of the center frame with quick disconnect fittings 11 Connect the 3 push rods with red quick disconnect fittings Start from...

Page 92: ...n bolt Use the T handle tool to insert the main bolt fully rotate the bolt for easy movement Unscrew and remove the tool The main bolt is inserted correctly when the outer contour of the axial safety mechanism fits smoothly to the contour of the wing surface 20 Mount the right outer wing in the same manner as described above Winglet 21 Insert the spar of the winglet into the main spar of the outer...

Page 93: ...h with the leading edge of the vertical stabilizer Only then the connection is properly secured 5 Check correct installation of the horizontal tail unit by pushing the leading edge upwards 4 3 4 Fuselage Fairings 1 Install the upper fairing 2 Install side fairings They must overlap the upper fairing at the rear Note Before installing the fairings perform checks according to section 4 5 Daily Inspe...

Page 94: ...ibrated to RON 95 All other fuel types and mixtures of fuel will cause a lower fuel level indication in the tanks than actual The real fuel level has to be determined visually optional by using a dip stick see ch 7 12 4 1 and compared to the indicated fuel level on the display in the cockpit The deviation has to be considered for flight planning Note The filling holes end close to the upper brim o...

Page 95: ...eneral condition Additionally control surfaces must be checked for mobility Additionally to the mentioned checks the motorglider must be inspected for cracks in the finish deformations and roughness of surfaces If there is any doubt about any results or findings consult a specialist During walk around check any drainage holes and ventilation openings and clean them if necessary see maintenance man...

Page 96: ...er until a flushing sounds can be heard at the oil reservoir 8 Oil level CHECK min lower mark max upper mark For flights durations of more than 8 hours the oil level should be at least half way between the min and max marks If necessary REFILL oil 9 Oil reservoir CLOSE the cap 10 Movement of throttle and choke CHECK for mobility 11 Lateral firewall covers REINSTALL 12 Cowl flaps and exhaust flaps ...

Page 97: ...rols CONNECTED and SECURED with cotter pins one connector each for ailerons flaps and air brakes 3 Flight controls CHECK for mobility 4 Fuel lines CONNECTED and NO LEAKAGE 5 Connectors for electric elements in wings CONNECTED 6 Pressure tubes from static port and pitot tube CONNECTED red red blue blue 7 Check for foreign objects PERFORM 8 Upper fairing and side fairings REINSTALL III Propeller and...

Page 98: ...Gear 1 Tire pressure Main wheels 51 1 5 psi 3 5 0 1 bar Nose wheel 51 3 0 psi 3 5 0 2 bar 2 Slip marks and tread pattern CHECK 3 Brakes CHECK effectiveness of brakes by pulling the brake levers pilot side and optionally co pilot side There must be a clear resistance V Empenage 1 Check horizontal tail unit for correct rigging The forward vertical edge of the horizontal tail unit flange must be flus...

Page 99: ...ng 4 IW OW bolts Check for correct mounting of the main bolts The safety pins must smoothly fit to the contour of the wing surface 5 Static pressure port CHECK during pre flight inspection see chapt 4 6 1 6 Stall warning CHECK during pre flight inspection see chapt 4 6 1 VII Cockpit 1 Canopy Sufficient visibility 2 Cockpit Area and seats CHECK for foreign objects 3 Behind seats CHECK for foreign o...

Page 100: ...rect setting 8 Cowlings CHECK for correct mounting 9 Pitot tube and static ports on pressure probe CHECK for correct mounting and for foreign objects or contamination 10 Dynamic pressure and vertical speed indicators variometers CHECK carefully blow against tip of pressure probe 11 Stall warning CHECK function 12 Foreign objects CHECK secure loose objects CHECK flight controls an assisting person ...

Page 101: ... CHECK before engine start 1 Parachutes optional worn correctly 2 Saftey belts worn correctly by all occupants 3 Canopy CLOSED and LATCHED left right and top 4 Rebound strap REMOVED 5 Seat position and rudder pedals CHECK for comfortable position and fixation 6 Control elements and Panel easily reached 7 Flight controls FREE movement ailerons elevator rudder flaps air brakes cowl flaps 8 Master sw...

Page 102: ...e OPEN 2 Cowl flaps OPEN fully In 3 Parking brake SET 4 Electrical master switch Battery ON 5 Engine master switch ON 6 TCU self test CHECK if red MAP warning light and yellow TCU caution light are ON for approx 1 to 2 seconds and then OFF again 7 Propeller switch CHECK function SET left propeller switch to MANU and right propeller switch to FEATHER Also CHECK if green indication light goes OFF Th...

Page 103: ...ox 120 F 50 C 16 Flaps SET to NEUTRAL 17 Propeller Area CHECK CLEAR 18 Ignition switch ACTIVATE START until engine is running RPM in the green range then set to BOTH Note The ignition is activated only approx 2 seconds after operating the ignition switch Do not activate the engine starter for more than 10 seconds then allow a 2 minute break 19 Oil pressure CHECK if in the green range If performing...

Page 104: ...h RUDDER PEDALS 5 Brakes Activate with BRAKE LEVER at the control stick 4 7 2 Take Off and Climb 4 7 2 1 Before Take Off Check at Taxi Hold Position 1 Parking brake ACTIVATE 2 Fuel shut off valve OPEN 3 Cowl flaps fully OPEN 4 Air Brake Lever IN and LOCKED 5 Flaps SET to TO LDG 1 6 Choke fully CLOSED 7 Propeller switch AUTO 8 Propeller RPM SET propeller RPM to 2100 RPM 9 Magneto check R L SET engi...

Page 105: ...ntrol light can go OFF before reaching FULL POWER This is NOT a malfunction The Constant Speed Control has limited the RPM under the given circumstances 11 All Circuit breakers and fuses CHECK 12 Voltmeter CHECK 12V to 14V 13 Ampmeter POSITIVE 14 Oil pressure oil temperature CHT CHECK must be in the green range 15 All caution lights and warning lights OFF only the green indication lights may be ON...

Page 106: ...0 RPM green indication light ON 4 Throttle Increase gradually to FULL POWER Move to forward stop past detent for MCP Warning THROTTLE UP too fast can result in exceeding the engines maximum allowed RPM This can be avoided by using the throttle carefully Note Depending on the air density airfield elevation or temperature the green start control light can go OFF before reaching FULL POWER This is NO...

Page 107: ...eels at approx 43 kts 80 km h if flaps are set to TO LDG 1 4 7 2 3 Climb 1 Climb speed at MTOM best rate of climb vy 62 kts 115 km h flaps set to NEUTRAL best angle of climb vx 46 kts 85 km h flaps set to TO LDG 1 2 after reaching safety altitude Auxiliary fuel pump OFF green control light goes OFF If necessary ADJUST trim 3 Oil temp CHT MONITOR Before exceeding allowable ranges REDUCE throttle 4 ...

Page 108: ...are located in the inner wing section with automatic fuel extraction The only way to control the fuel extraction is by using the fuel shut off valve to interrupt the fuel flow or the auxiliary fuel pump which assists the main fuel pump The correct extraction of fuel can be monitored with the two fuel gauges and one low fuel caution light The fuel tank system consists of one main tank with a feeder...

Page 109: ...into account that only the remaining amount of fuel in the right tank is available Note After a shut down of the engine the low fuel caution light yellow LED can go ON After setting the engine switch to ON it should go OFF after a short time when the circulation pump has refilled the feeder compartment Note The fuel sensor is calibrated to RON 95 All other fuel types and mixtures of fuel will caus...

Page 110: ... 7 3 5 Engine Restart Transition to Powered Configuration Warning When restarting the engine in flight with a windmilling propeller and at high air speed the THROTTLE must be set to IDLE Otherwise the engine can exceed its maximum RPM immediately after restarting Warning If the engine is running windmilling do NOT use the starter The engine could be damaged Caution With low battery voltage near mi...

Page 111: ...re gauge 2 5 1 0 250 100 hPa 3 6 1 5 psi If necessary ACTIVATE auxiliary fuel pump 9 Choke fully OPEN if engine is cold oil temp approx 120 F 50 C fully CLOSED if engine is warm oil temp approx 120 F 50 C 10 Throttle IDLE if engine is cold oil temp approx 120 F 50 C approx 10 THROTTLE if engine is warm oil temp approx 120 F 50 C 11 Indication light of propeller T O position WAIT for green LIGHT is...

Page 112: ...f the airspeed is high enough 13 Oil pressure CHECK if in the green range If performing cold start it is allowed to be in the yellow range at first 14 External alternator CHECK if red external alternator warning light goes OFF 15 Internal generator CHECK if yellow internal generator caution light goes OFF 16 Voltmeter CHECK 17 Ampmeter POSITIVE 18 Choke fully CLOSED If performing cold start set ba...

Page 113: ...ing of flare 2 Trim SET according to approach speed 3 Flaps SET to TO LDG 1 4 Cowl flaps fully OPEN 5 Auxiliary fuel pump ON 6 Propeller switch AUTO 7 Propeller RPM SET propeller RPM to 2100 RPM 8 Throttle IDLE 9 All caution lights and warning lights OFF only green indication lights may be ON 10 Air brakes control glideslope by OPERATING air brakes accordingly during final approach 11 Flare and to...

Page 114: ... extend partially LOCK in partially extended CENTER position intended for low engine power landing 10 Throttle OPERATE as required for glideslope control 11 Flare and touch down Set THROTTLE to IDLE at beginning of flare Flare carefully with the elevator Let the A C touch down on the main gear 12 Wheel brake ACTIVATE as necessary after touch down 4 7 4 3 Go Around with or without Touch Down Accord...

Page 115: ...ps were set to LDG 2 before Warning Setting the flaps from LDG 2 to TO LDG 1 too quickly can cause the A C to plunge down unintentionally 4 Climb according to section 4 7 2 3 After approach with low engine power 1 Throttle FULL POWER Warning THROTTLE UP to fast can result in exceeding the engines maximum allowed RPM This can be avoided by using the throttle carefully Note If the A C has enough spe...

Page 116: ... to Landing in Glider Configuration 1 Approach speed 60 kts 110 km h recommended for MTOM keep constant until beginning of flare 2 Trim SET according to approach speed 3 Propeller Switch left MANU right FEATHER 4 Flaps SET to TO LDG 1 5 Air brakes control glideslope by OPERATING air brakes accordingly during final approach 6 Flare and touch down If enough airspeed is available set the air brakes t...

Page 117: ...TRAL 2 Air brakes RETRACT and LOCK 3 Auxiliary fuel pump OFF 4 XPDR STBY OFF 5 Throttle use setting adequate for taxiing 6 Directional Control OPERATE rudder pedals 7 Braking OPERATE brake lever at control stick 4 7 6 2 Parking 1 Throttle REDUCE to IDLE 2 Parking brake SET 3 Engine cool down WAIT until oil temp and CHT are 212 F 100 C 4 COM NAV XPDR OFF 5 Avionic switch OFF 6 Ignition switch OFF 7...

Page 118: ...s 150 km h Always keep the air speed below the never exceed speeds given above Only then can it be guaranteed that the motorglider will not flutter Due to the extremely low outside air temperatures OAT at high altitude it is possible that the capacity of the battery is reduced significantly This might prevent the engine from being started with the electric starter Starting the engine might only be...

Page 119: ...is should also be done for all other minimum air speeds 2 The climb rate will decrease up to 50 and the cruise speed will decrease up to 30 These reductions have to be taken into account when flight planning Also take into account the decreases in maximum range and endurance 3 For flying in rain no important changes of trim have been observed However changes in the trim speed should be expected 4 ...

Page 120: ...t into a slip by lowering the upwind wing This is the steady heading sideslip procedure recommended for powered A C It has the advantage that the attitude usually does not need to be changed until touch down This procedure has been demonstrated for crosswind components of up to 16 kts 30 km h The wing tip still has enough ground clearance 4 Approach with a crab angle against the wind and keep the ...

Page 121: ...ecommended speeds for take off and landing by at least 6kts 10 km h This should also be done for all other minimum air speeds 4 The climb rate will decrease up to 50 and the cruise speed will decrease up to 30 4 7 12 Flights near Thunderstorms 1 Avoid flights near or into a thunderstorm Strong turbulences ice strong rain or hail can be expected The motorglider also has no adequate lightning protec...

Page 122: ...FLIGHT MANUAL TSA M VARIANT S6 Doc No P400 006 000 E Page 4 36 Revision Date of Issue 07 October 2008 Agency approved Date of Rev 4 7 13 Aerobatics Aerobatics are not allowed ...

Page 123: ...00 006 000 E Page 4 37 Revision 2 Date of Issue 07 October 2008 Agency approved Date of Rev 20 05 2011 4 7 14 Spins Intentional Spins are not allowed If the aircraft spins unintentionally follow the emergency procedures according to chap 3 6 ...

Page 124: ...cation Error 5 4 5 3 2 Pressure Altitude and Density Altitude 5 6 5 3 3 ISA International Standard Atmosphere 5 7 5 3 4 Stall Speed and Minimum Air Speeds 5 7 5 3 5 Wind Components 5 10 5 3 6 T O Ground Roll and T O Distance at MTOM 5 11 5 3 7 Climb Performance 5 13 5 3 8 Power Settings in Cruise Flight 5 13 5 3 9 Climb Gradient during Go Around 5 13 5 3 10 Landing Distance 5 14 5 3 11 Polars for ...

Page 125: ...iven which does not need to be approved This collection of data is good for pre flight planning purposes The performance data given in the tables and diagrams was determined in flight tests with a motorglider and engine in serial configuration It has been corrected to the conditions of the international standard atmosphere ISA 59 F 15 C 29 92 inHg 1013 25 hPa MSL The values were gained with averag...

Page 126: ...s for good flight planning when the pilot knows all outside influences and available information Good flight planning good maintenance of the motorglider and good pilot experience will cause the actual performance values to be near to the values given in this operating manual When planning a flight always estimate the values from the tables and diagrams to the safe side This way unknown influences...

Page 127: ...nce Tables and Diagrams _________________ 5 3 1 Corrections of Air Speed Indicator Indication Error The following air speed indicator correction takes into account the installation error It does NOT take into account the instrument error of the air speed indicator All air speed values in this Flight Manual are indicated air speeds IAS ...

Page 128: ...of Issue 07 October 2008 Agency approved Date of Rev 28 01 2011 Illustration 5 1 Corrections of Air Speed Indicator For information This airspeed calibration is valid for powered as well as unpowered flight and also for all flap settings Reference Line Airspeed Calibration ...

Page 129: ...gram can be used This may be needed to determine the engine power If the QNH is known this can be read from the altimeter the density altitude can be calculated with the temperature Diagram for converting pressure altitude and density altitude Illustration 5 2 Conversion of Pressure Altitude and Density Altitude Note The current pressure altitude is shown on the altimeter if it is set to 29 92 in ...

Page 130: ...e configuration of the aircraft and the mode of operation The stall speed is the speed at which a stalled flight state is reached The minimum air speed is lowest stationary speed that is controllable reaching of the control stops Warning When recovering from a stall in horizontal flight an altitude loss of 100 ft 30 m is possible In turning flight an altitude loss of 130 ft 40 m is possible If the...

Page 131: ...ation Flaps NEUTRAL Flaps set to NEUTRAL Engine 100 power Air brakes LOCKED VS1 43 kts 80 km h IAS Landing configuration Flaps LDG 2 Flaps set to LDG 2 Engine IDLE Air brakes LOCKED VS0 42 kts 78 km h IAS Landing configuration Flaps TO LDG 1 Flaps set to TO LDG 1 Engine IDLE Air brakes FULLY EXTENDED VS1 45 kts 83 km h IAS Landing configuration Flaps NEUTRAL Flaps set to NEUTRAL Engine IDLE Air br...

Page 132: ...opeller left MANU right FEATHER Configuration Speed Landing Configuration Flaps LDG 2 Flaps set to LDG 2 Air brakes LOCKED VS0 42 kts 78 km h IAS Landing Configuration Flaps TO LDG 1 Flaps set to TO LDG 1 Air brakes FULLY EXTENDED VS1 45 kts 83 km h IAS Landing Configuration Flaps NEUTRAL Flaps set to NEUTRAL Air brakes FULLY EXTENDED VS1 47 kts 88 km h IAS Thermalling Configuration Flaps TO LDG 1...

Page 133: ...ough aerodynamic buffeting The onset of buffeting begins about 3 to 4 kts 5 to 8 km h above the stall Note If the CG location is far aft then slightly lower stall speeds might be reached The aircraft might drop a wing downwards even if the flight controls are not against the aft stop 5 3 5 Wind Components The maximum demonstrated crosswind component for taxi take off and landing is 16 kts 30 km h ...

Page 134: ...dard atmosphere T O ground roll 770 ft 235 m T O distance 1120 ft 340 m over 50ft 15m obstacle Caution The T O ground roll can increase significantly when flying from grass runways Expect at least a 25 increase in the T O ground roll on grass runways Bad maintenance not following the given procedures bad meteorological conditions moisture snow and similar and bad local conditions rough surfaces an...

Page 135: ...06 490 3280 1000 8 15 795 242 1149 350 32 0 924 282 1335 407 59 15 1066 325 1542 470 86 30 1219 372 1762 537 100 38 1305 398 1889 576 4920 1500 5 15 937 286 1355 413 32 0 1087 331 1573 479 59 15 1253 382 1813 553 86 30 1434 437 2072 632 100 38 1535 468 2222 677 6560 2000 5 15 1106 337 1598 487 32 0 1284 391 1855 566 59 15 1477 450 2137 652 86 30 1689 515 2442 745 100 38 1809 551 2614 797 8200 2500...

Page 136: ... kts 115 km h at 1874 lbs 850 kg Altitude 0 16400 ft 0 5000 m pressure altitude Maximum rate of climb vV 790 ft min 4 m s 5 3 8 Power Settings in Cruise Flight Conditions Throttle As given in Graph Table Flaps CRUISE A C mass 1874 lbs 850 kg Maximum cruise speed vH 116kts 215km h 5 3 9 Climb Gradient during Go Around Conditions Throttle FULL POWER MTOP 115 Flaps TO LDG 1 Air speed IAS v 49 kts 90 ...

Page 137: ...ssible Landing ground roll 640 ft 195 m Landing distance over 50 ft 15 m obstacle 1329 ft 405 m Caution The landing distance can increase significantly when flying from grass runways Bad maintenance not following the given procedures bad meteorological conditions rain high temperatures unfavorable wind and similar and bad local conditions can increase the landing distance significantly Caution A R...

Page 138: ...Flight Manual STEMME S6 Doc No P400 006 000 E Page 5 15 Revision Date of Issue 07 October 2008 Date of Rev 5 3 11 Polars for Soaring Flight Not yet available ...

Page 139: ... right wing tank standard is 0 55 US gal 2 1 l In the left wing tank optional it is 0 3 US gal 1 l To determine the approximate endurance with tanks completely filled without reserve follow this method Standard 16 6 gal 63 l 5 4 gal h 20 4 l h 3 08 h With optional tank 33 5 gal 127 l 5 4 gal h 20 4 l h 6 22 h Available flight time max flight time from table or graph multiplied with amount of useab...

Page 140: ...uction 6 2 6 2 Aircraft Weights 6 3 6 2 1 State during Weighing 6 3 6 3 Empty Mass and CG Location 6 5 6 3 1 Logsheet for Report of Empty Mass and CG Location 6 5 6 4 Operating Mass and Operating CG 6 7 6 4 1 Mass Moments and Payload 6 9 6 4 2 Calculation of Proper Loading for Flight 6 10 6 5 Equipment List and Installed Equipment List 6 12 6 5 1 Equipment List 6 13 ...

Page 141: ...lled in the motorglider during weighing installed equipment list as well as a list of all approved equipment for this motorglider equipment list is given in chapter 6 5 The weight empty CG location and empty mass moment for the aircraft are determined during the pre delivery inspection This data is then noted in the logsheet for report of the empty mass and the CG location section 6 3 1 Repeat the...

Page 142: ...E Doc No P500 006 000 6 2 1 State during Weighing Installed equipment according to the current equipment list No loose ballast Aircraft dry including operating fluids Brake fluid Amount of engine oil 0 5 0 8 US gal 2 3 liters Coolant 0 63 0 66 US gal 2 4 2 5 liters Non useable fuel 0 55 US gal 2 1 liters 0 3 US gal 1 liter optional The aircraft s empty mass and empty CG location are determined usi...

Page 143: ...raft is aligned properly reference points are projected vertically down onto the ground from the root leading edge of the left and right wings This generates a vertical plane The connecting line between the two reference points is the reference line From this reference line the distance to the front landing gear distance b and main landing gear distance a is measured See Illustration 6 1 Aircraft ...

Page 144: ...n for example when changes in equipment are made then new empty mass and empty CG location can be determined through calculations If the cause of the changes is NOT precisely known For example when making repairs the aircraft must be weighted again 6 3 1 Logsheet for Report of Empty Mass and CG Location The following logsheet describes the chronological changes in the aircraft s empty mass and CG ...

Page 145: ...Rev Report of Empty Mass and CG Location continuous report of changes to the aircraft structure and or equipment Registration No Serial No Sheet No STEMME S6 Current Empty Mass Cleared by Authorized Personnel Con No Date Description of Action taken Mass kg Lever to RP m Moment kgm 1 Weighing at delivery ...

Page 146: ...ram or calculate the mass moments more precisely mass x corresponding lever Keep the negative value of the lever in mind if a location is infront of the RP Use seperate columns in row 2 for the left and right seat in table 6 4 2 Calculation of the proper loading for flight 3 Determine the payload carried in the rear baggage compartment by using the same methods as in point 2 Place these values in ...

Page 147: ... of the CG in the T O configuration These values must be within the allowed limits If this is not the case payload and fuel must be adjusted All mentioned and used levers give the distance from the corresponding CG to the reference plane RP Warning The CG must always stay within the allowed limits If this is not the case unstable aircraft behavior might result ...

Page 148: ...Flight Manual STEMME S6 Doc No P400 006 000 E Page 6 9 Revision Date of Issue 07 October 2008 Date of Rev 6 4 1 Mass Moments and Payload e g Step 2 e g Step 6 e g Step 3 ...

Page 149: ... 80 kg Example 36 kgm mean value negative right Example lbs Example ft lb 3 Rear Baggage Compartment Lever 1 699 m Example 18 kg Example 31 kgm 4 Operating Mass and Total Mass Moment without Fuel Sum 1 through 3 Example 773 kg Example 301 kgm 5 CG Location mm RP 1000 kg Mass m mm kgm Moment Example 389 mm mm behind RP Allowed 224 mm to 409 mm 6 Fuel Payload Useable Fuel 0 744kg l Lever 0 111 m see...

Page 150: ...11 Revision Date of Issue 07 October 2008 Date of Rev Note When calculating the CG position without including the change of fuel weight during flight the CG must be within the following limits 8 82 1 26 in to 16 10 1 30 in behind RP 224 32 mm to 409 33 mm ...

Page 151: ...are marked with X in the column Inst Installed Note The installation of additional equipment must be performed in correspondence with the Maintenance Manual The given equipment list contains the following information for a better overview The column Con No includes a continuing number and a character for specification with the meaning I Instruments A Avionics M Miscellaneous Equipment Items The co...

Page 152: ...5934 Ser I 3 Air Speed Indicator Winter 7FMS443 I 4 Compass Airpath C2400 I 5 Variometer Winter 5STVM5 2 I 6 Soaring Computer incl Electr Variometer LX Navigation LX 166 I 7 CDI Garmin Gl 106A I 8 MAP Gauge UMA Instr I 9 Oil Pressure Gauge UMA Instr I 10 Oil Temp Gauge UMA Instr I 11 CHT Gauge left right UMA Instr I 12 Ampmeter UMA Instr I 13 Voltmeter UMA Instr I 14 Fuel Gauge right left UMA Inst...

Page 153: ...Date of Issue 07 October 2008 Date of Rev 28 01 2011 STEMME S6 Serial No Reg No Date Con No Description Manu facturer Type Spec No Inst Mass kg Lever m or I 24 I 25 I 26 I 27 I 28 I 29 I 30 I 31 I 32 I 33 I 34 I 35 I 36 I 37 I 38 I 39 I 40 I 41 I 42 I 43 I 44 I 45 I 46 ...

Page 154: ...ype Spec No Inst Mass kg Lever m or A 1 COM NAV GPS Garmin GNS 430W A 2 Electronic Flight Information Sys Dynon EFIS D 10A A 3 Transponder Garmin GTX 330 A 4 Audio Panel Garmin GMA 340 A 5 Radio Becker AR 4201 VHF A 6 Transponder Becker BXP 6401 2 Mode S A 7 GPS Garmin GPSMAP 695 A 8 Intercom PS Eng PM 1000 A 9 A 10 A 11 A 12 A 13 A 14 A 15 A 16 A 17 A 18 A 19 A 20 A 21 A 22 A 23 A 24 ...

Page 155: ...facturer Type Spec No Inst Mass kg Lever m or M 1 Safety Belts Gadringer M 2 Stall Warning STEMME M 3 Cabin Heating STEMME M 4 Aerotow Tail Clutch Tost E22 M 5 Tow Bar STEMME M 6 Release Mechanics STEMME M 7 Rear view Mirror left STEMME M 8 Rear view System Camera Display STEMME M 9 Solar Panel STEMME M 10 M 11 M 12 M 13 M 14 M 15 M 16 M 17 M 18 M 19 M 20 M 21 M 22 M 23 M 24 ...

Page 156: ...Adjustable Rudder Pedals 7 7 7 4 Air Brakes 7 8 7 5 Operating Elements 7 9 7 6 Instrument Panel 7 12 7 6 1 Layout of the Instrument Panel 7 12 7 6 2 Control Elements of the Instrument Panel 7 14 7 7 Landing Gear 7 15 7 7 1 Nose Gear and Steering 7 15 7 7 2 Main Gear and Brakes 7 15 7 8 Seats and Safety Belts 7 16 7 9 Baggage Compartment 7 17 7 10 Canopy and Cockpit 7 18 7 10 1 Canopy 7 18 7 10 2 E...

Page 157: ...el System 7 33 7 12 2 Control Elements and Gauges in the Cockpit 7 34 7 12 3 Circuit Logic and Operation of the Fuel Pumps 7 34 7 12 4 Measurement of the Amount of Fuel 7 36 7 13 Electrical System 7 38 7 13 1 Power Supply and Battery System 7 38 7 13 2 Ignition System 7 38 7 13 3 Electrical Circuits 7 38 7 13 4 Electrical Consumers and Circuit Breaker System 7 39 7 13 5 Control Elements 7 40 7 13 ...

Page 158: ...__ This chapter of the Flight Manual contains a technical description of the motorglider and its systems and components There are also user notes for each system The description of installed non standard systems is given in chapter 9 Additional explanations of the components and systems of the Stemme S6 are given in the maintenance manual Stemme Doc No P500 006 000 ...

Page 159: ...r wing left and right outer wings and two winglets An integral tank for fuel is located in the forward area of the right inner wing an optional second tank can be installed in the left inner wing The air brakes are located in the inner section of the outer wing The wing spars of all wing sections are made completely of carbon fiber composites The wing shells are made of CFC Sandwich elements The c...

Page 160: ...cured quick connectors non automatic 7 3 1 Ailerons Design CFC Sandwich 2 part Aileron across the span of the outer wing Mounting Inner aileron 9 joints and 1 control connector each Outer aileron 7 joints and 1 control connector each Axial fixations near the control connectors Operation Operated with control rods Aileron differential realized by parted ailerons Outer ailerons deflect more than inn...

Page 161: ... wheel steering is also connected to the rudder pedals The steerable nosewheel is operated by control cables 7 3 4 Flaps Design CFC Sandwich Mounting 6 joints and 1 control connector each Operation Operated with push rods flap deflection is effective across whole wing span inner wing and outer wing The flaps are set by using the flap lever with detents Setting indicator is located near the flap le...

Page 162: ...The rudder pedals must be locked properly after they have been adjusted The rudder pedals are unlocked by pulling the black handle forward of the control stick Moving the pedals forward To move the pedals forward pull the handle and push onto the pedals with your feet Keep the handle pulled until the pedals have reached the position you want Afterwards release the handle and lock the pedals Moving...

Page 163: ...The Schempp Hirth style air brakes are located at the inner section of the outer wing Design Air brake designed as aluminum section sealing plates made of CFC placed at top ends of air brakes Mounting 2 rotational shafts in each air brake box Operation Operated with control rods the air brakes lock at the wing joint The air brakes are operated by moving the blue air brake lever ...

Page 164: ...w of all control elements in the cockpit More detailed descriptions of each element are given in each relevant section of this Flight Crew Operation Manual as well as in the maintenance manual For operation instructions of the installed equipment refer to the maintenance manual of the STEMME S6 STEMME Doc No P500 006 000 and to the operation manuals of the manufacturer provided for the installed e...

Page 165: ...L TSA M VARIANT S6 Doc No P400 006 000 E Page 7 10 Revision 1 Date of Issue 07 October 2008 Date of Rev 28 01 2011 Illustration 7 1 Overview of the Control Elements in the Cockpit 3 2 1 4 5 2 6 7 8 9 10 11 12 13 1 ...

Page 166: ...oke Lever is realised by pre defined clamping 7 Canopy Jettison Red handle on top of the forward center console below the instrument panel 8 Cowl Flaps Lever Black handle on top of the forward center console below Canopy Jettison handle to operate the inlets and outlets of the engine cowling The lever is unlocked by pushing a push button and locked again by releasing the button 9 Rudder Pedals One...

Page 167: ...______________ 7 6 1 Layout of the Instrument Panel The illustration shows the layout and position of the most important control elements and instruments on the instrument panel in the standard configuration Illustration 7 2 Standard Layout of the Instrument Panel 2 1 3 4 5 6 7 12 13 14 15 16 18 19 10 20 21 22 23 24 25 26 27 11 8 9 L1 L2 L3 L4 L5 L6 17 A 1 7 A 8 14 ...

Page 168: ...ntilation 22 Oil Pressure Gauge 9 Trim Indicator 23 Cylinder Head Temperature right 10 Compass Airpath C2400 24 Fuel Gauge right Tank 11 Audio Panel Garmin GMA 340 25 Ampèremeter 12 COM NAV GPS Garmin GNS 430W 26 Engine Hours Meter 13 Transponder Garmin GTX 330 27 Spare 14 Tachometer of Engine Announciator panel on the instrument panel L1 Low Fuel Caution Light yellow L4 MAP Warning Light red L2 I...

Page 169: ... the instrument panel 1 Master Switch Batt and Switch for Engine Bus 5 TCU Isolation Switch red safety switch 2 Control Unit for Propeller Pitch 6 Main Circuit Breaker 50A 3 Ignition Switch 7 Circuit Breaker for External Alternator 50A see also 7 13 4 Electrical Consumers and Circuit Breaker System 4 Fuel Pressure Difference Gauge Circuit breakers switches of the instrument panel S1 Auxiliary Fuel...

Page 170: ...tion it is automatically disconnected from the rudder controls and locks in the direction of the longitudinal axis 7 7 2 Main Gear and Brakes The struts of the main landing gear are welded tubes which are stiff to torque They are connected to the central steel tube framework of the mid section of the fuselage The elastically mounted main wheels are located at the end of rockers which in turn are s...

Page 171: ...side at the same time the backrest is unlocked and can be moved to the desired position Pay attention to even move of left and right rail to avoid wedge of adjustment After adjustment lock the rails in the nearest position Also the slope of the backrest can be adjusted This allows the backrest to be positioned by placing a small lever in one of several detents near the mounting of the seat belts E...

Page 172: ...e tail boom just behind the connector frame between the mid section and rear section of the fuselage A maximum payload of 44 lbs 20 kg may be loaded into the compartment It can be loaded through a forward opening door at the top of the fuselage The locks are engaged with quick closing push buttons at the rear of the door Caution Do NOT place rigid or sharp objects in the baggage compartment withou...

Page 173: ...nomically located white levers at the left and right side of the cockpit frame At the rear it is also locked by a rear canopy hook This so called Roeger hook hook is designed to hold the rear of the canopy down at the beginning of the canopy jettison procedure and causes it to rotate upwards and be torn away Warning For canopy jettison ONLY pull the canopy jettison handle The rear canopy hook Roeg...

Page 174: ...ccurs individually for each seat and the canopy The air for the cabin ventilation flows from the free airflow beneath propeller spinner into two air inlets From there it is lead into a centralized air distribution system where the airflow splits to the separate vents The canopy vents are located near the canopy hinge They are operated with a Bowden cable installed at the center top of the instrume...

Page 175: ...d overload clutch The engine is mounted in the mid section of the fuselage with the engine suspension connecting it to the steel tube framework There the engine causes low noise emissions for the cabin and the aircraft s surroundings Specifications of the ROTAX 914 F2 Max T O power MTOP 113 HP 84 5 kW at 5800 RPM Takeoff RPM limited to 5600 RPM by const speed propeller control Max continuous power...

Page 176: ...remaining surfaces Spinner with baseplate and commutator ring or with commutator ring and starter disk The propeller pitch is continuously adjustable from the T O setting to the cruise setting or glider setting depending on the mode of operation A direct current motor is controlled by the automatic propeller control unit which selects the corresponding propeller pitch according to the power settin...

Page 177: ...itch to MANU and the right flip switch to FEATHER To leave the glide position set the left flip switch to MANU and then set the right flip switch to HIGH RPM T O setting The propeller reaches the final pitch after 90 s After the propeller has moved out of the glide setting a green indication light will go ON and the propeller starts to windmill and after re start of the engine set the left flip sw...

Page 178: ...could lead to stone chippings on the propeller blades Due to this perform engine runs only on appropriate surfaces Also always follow the procedures described in chapters 3 and 4 7 11 3 Operation of the Engine 7 11 3 1 Throttle The throttle is located on the center console between the seats It is equipped with a forward detent for 100 power maximum continuous power MCP and a forward stop for 115 p...

Page 179: ...g the choke the combustion mixture is enriched in the starter carburator with additional fuel This is needed for a cold start of the engine The starter carburator is only operational if the throttle is set to IDLE Caution Only use the choke briefly when performing a cold start Before T O it must be set to the CLOSED position again Note During the daily check check to see if the starter carburator ...

Page 180: ...stead periodic oscillations of the control unit and the engine RPM might occur Avoid the range between 100 115 engine power and move through it quickly when the throttle is set To avoid damage to the engine the MAP is reduced when the engine RPM is too high or when the inducted air is too warm To monitor the turbo control unit use the red MAP warning light and the yellow TCU caution light When tur...

Page 181: ...ystem which in case of an engine fire gives a clear warning signal by a red warning light in combination with an acoustic alarm signal For fire detection 2 thermal sensors are mounted on the outside of the engine fire wall above the carburators and another 2 sensors are mounted on the left and right containment of the fire wall outlet and exhaust shaft The system is designed fail safe that means a...

Page 182: ...f the exhaust gas system on top of the fuselage between the wings Depending on the value of the operating temperature of the engine the position of the gill outlet and of the cowl flaps can be adjusted with a bowden cable Operation of the cowl flaps The cowl flaps of the inlets and outlets are manually operated with a self locking black T handle at the center console below the instrument panel If ...

Page 183: ...x amount up to top of tank if necessary 2 Radiator the radiator 2 is located at the bottom of the central steel tube framework It is supplied with ram air through the lower center NACA cooling inlet 3 Filling Hole The filling hole 3 for the expansion tank 1 is located on top of the expansion tank 1 It is covered with a lid which closes the hole in a pressure resistant manner This is where the cool...

Page 184: ... during the cool down phase coolant is sucked into the circuit again Air is automatically bled from the circuit Caution Do NOT open the lid of the expansion tank if the engine is warm The engine cooling system is pressurized There is a severe risk of being burnt by boiling splash water Caution When refilling coolant in the overflow reservoir and tightening the cap afterwards make sure that the plu...

Page 185: ... with filler neck and integrated dip stick 2 Oil cooler located below the radiator 3 Oil pipe for the turbo charger 4 Return pipe for the turbo charger 5 Breather pipe The main oil pump transports the oil from the oil tank through separate oil cooler and oil filter to the lubricating points Escaping oil is returned through the crank case The turbo charger is supplied through a separate oil pipe by...

Page 186: ...the long shaft is reduced to the propeller RPM with the front drive which is located in the nose of the A C The drive shaft of the front drive is screwed to the propeller hub The drive is a belt drive model STEMME 050 251 which is encased in cast magnesium The gear belt discs are made of aluminum and have a transmission ratio of i 1 100 The drive suspension is screwed onto the load transmission fr...

Page 187: ... the long shaft with a spline shaft connector which allows for axial motion of the long shaft A flexible disk on each side of the long shaft compensates angle errors and angular motion In case of a failure of the long shaft it is contained in a protective tunnel made of aramid fiber composites This contains the shaft and sharp fragments in case of shaft rupture The following illustration shows the...

Page 188: ...cted with the fuel system which is installed in the fuselage through quick connectors The fuel flows from the quick connectors to the fuel pumps main fuel pump and auxiliary fuel pump From there it continues to the fuel shut off valve in the cockpit and then to the pressure regulator in front of the carburators A return pipe leads from the pressure regulator through a quick connector back to the f...

Page 189: ... panel settings ON and OFF Low Fuel Caution Light yellow Indication light for remaining fuel less than 1 3 1 9 US gal 5 7 l in feeder compartment Indication Light of Auxiliary Fuel Pump green Status indicator is goes ON if the auxiliary fuel pump s are running Fuel Gauge right and left optional On the instrument panel shows the amount of fuel in the left and right integral tanks Fuel Flow Gauge op...

Page 190: ...FLIGHT MANUAL TSA M VARIANT S6 Doc No P400 006 000 E Page 7 35 Revision 1 Date of Issue 07 October 2008 Date of Rev 28 01 2011 Illustration 7 8 Layout of Fuel System ...

Page 191: ... Measurement of the Amount of Fuel The amount of fuel in each tank is measured with capacitive sensors This data is then displayed on one fuel gauge for each installed tank mounted on the instrument panel An additional optical sensor is mounted in the feeder compartment It signals that less than approx 1 3 1 9 US gal 5 7 l of fuel remain in the feeder compartment Note The fuel sensor is calibrated...

Page 192: ... E Page 7 37 Revision 10 Date of Issue 07 October 2008 Date of Rev 06 07 2020 Wet length of the dip stick Fuel level in the tank 100 110 mm 100 60 70 mm 75 30 40 mm 50 2 5 mm 25 A fuel amount of less than 25 cannot be determined by using the dip stick ...

Page 193: ...intenance free and requires no external power supply Two independent charging coils are mounted on the crankshaft case Each coil supplies one of the two independent ignition circuits The electrical energy is stored in the capacitors of the electronics modules At the ignition point 2 of the 4 external probes discharge the capacitors through the primary coils of the dual ignition transformers The or...

Page 194: ...a distribution box with fuses and is located on the control board in the engine compartment at the rear of the fire wall 7 13 4 Electrical Consumers and Circuit Breaker System Circuit Circuit Breaker A Fuse A Isolation Switch A Main Bus Engine Bus 10 Master Circuit Breaker 50 Circuit Breaker for the Alternator 50 Stall Warning 2 Electrical Trim 5 Propeller Pitch Control 5 Voltmeter 2 External Alte...

Page 195: ...ump 5 Auxiliary Fuel Pump 5 Avionics Bus The ratings of the circuit breakers used depend on the information given by the manufacturers of the installed equipment Internal Generator Bus Main Fuel Pump 5 Fuel Circulation Pump 3 Feed In 15 Internal Generator Caution Light 1 TCU 3 7 13 5 Control Elements In the following section the different settings of important control elements of the electrical sy...

Page 196: ...or from the turbo control unit when necessary The switch is protected against accidental activation because it only needs to be operated in the event of a TCU malfunction The normal operating position is the DOWN protected setting To disconnect the actuator set the switch to the UP position Avionics Master Switch activates the avionics bus It is designed as a 20A circuit breaker Auxiliary Fuel Pum...

Page 197: ...urrent drawn from the battery discharge or flowing into the battery charge Internal Generator Caution Light yellow The yellow light goes ON if the output voltage of the generator controller is below the battery voltage failure of the controller or the generator External Alternator Warning Light red The red light goes ON if the output voltage of the belt driven external alternator falls below the b...

Page 198: ...een the inner wing and outer wing The pressure sensing lines lead to the center of the wing There they need to be connected to the adapters of the mid section of the fuselage From there the lines are lead to the rear side of the instrument panel All tubes of the pressure system in the forward area of the cockpit are equipped with filters against moisture and dust The assignment of the pressure por...

Page 199: ...ing ___________________________________ If the air speed drops to less than 1 1 times the stall speed at any flap setting then stall horn will sound The horn is installed in the instrument panel The stall warning system is designed as a small wind vane with a trigger switch It is mounted at the leading edge of the left wing near the wing joint ...

Page 200: ...s of the Motorglider 8 3 8 3 Changes or Repairs 8 4 8 4 Ground Handling and Road Transport 8 5 8 4 1 Taxiing and Towing on the Ground 8 5 8 4 2 Parking 8 5 8 4 3 Storage Hangaring 8 6 8 4 4 Road Transport 8 6 8 5 Cleaning and Care 8 8 8 5 1 Finished Surfaces 8 8 8 5 2 Canopy 8 9 8 5 3 Propeller 8 10 8 5 4 Engine 8 10 8 5 5 Interior Seats and Fairings 8 10 8 6 Trouble Shooting of the Engine 8 11 ...

Page 201: ...otorglider Certain check regulations and maintenance regulations are mentioned They need to be observed if the motorglider is to retain the performance and reliability of a new aircraft Additional information is given in the maintenance manual Caution Keep to the lubrication chart in the maintenance manual Depending on the climatic conditions and operating conditions preventive maintenance needs t...

Page 202: ...ctured engine Afterwards observe the following maintenance intervals Structure see maintenance manual STEMME S6 lowest interval 100 h Engine see maintenance manual STEMME S6 lowest interval 50 h To retain the airworthiness of the A C an ANNUAL check see maintenance manual S6 must be performed at least once per year This is independent of the operating hours of the A C Caution Unscheduled maintenan...

Page 203: ... approved by the appropriate aviation authorities Repairs Repairs of the aircraft must only be conducted with generally accepted maintenance procedures or specially developed maintenance procedures by authorized personnel If the Daily Check reveals minor damage which do not affect the airworthiness of the aircraft they may be repaired directly If the importance of detected damage is not directly o...

Page 204: ...pot press the rear fuselage section downwards to lift up the nose gear Moving rearwards Steer the airplane at the vertical stabilizer and only push at the inner wing Caution Do NOT lift or push on the control surfaces or flaps 8 4 2 Parking For parking lock the hand brake lever with the locking pin or place chocks at the wheels Align against the wind set flaps to NEUTRAL When parking the motorglid...

Page 205: ...glider Place carpet felt or foamed rubber on all areas of contact Preparations for road transport Fuselage Park the fuselage safely on the main gears and nose gear Secure the fuselage against shifting or rolling by strapping it down with belts Cushion the areas of contact between A C and belts well Keep space clear for the propeller Do not transport loose items head sets parachutes or similar in t...

Page 206: ... parts must be secured against shifting and rotation Caution Do NOT strap the aircraft components down with belts over control surfaces flaps or brackets Horizontal Stabilizer It is recommended to store the horizontal stabilizer in a molding standing on its leading edge or laying down flat All molding should be cushioned use carpet felt or similar This protects the surface and distributes the load...

Page 207: ... Very dark colors can cause the surface to warm up to critical temperatures An unnoticed loss of structural integrity might result Caution Strong contamination of the surfaces will reduce flight performance and will cause light surfaces to heat up when exposed to sunlight 8 5 1 Finished Surfaces The entire surface of the motorglider is finished with a weather resistant white two component finish H...

Page 208: ...M14 at approx 1500 RPM After removing the scatches caused by the sandpaper and the grind applicator clean the surface with fresh water The continue the process with polish of the type Regular Grade G3 To reach the highest quality finish optional clean the surface and grind applicator again with fresh water The continue the process with polish of the type Extra Fine Grade G10 Clean the surface with...

Page 209: ... information see operating instructions and installation instructions ATA 61 01 18 E 118 by mt Propeller the manufacturer 8 5 4 Engine The cleaning of the engine is performed during regular maintenance according to the directions of the manufacturer s ROTAX maintenance manual Maintenance Manual Line Maintenance for ROTAX engine model 914 Series 8 5 5 Interior Seats and Fairings Dirt in the interio...

Page 210: ...Troubleshooting fuel shut off valve closed OPEN fuel shut off valve no fuel REFUEL A C starter RPM too low CHECK battery starter RPM too low problems when performing cold start USE fuel efficient engine oil of high quality hot E starter will lose power quickly let it COOL DOWN for a sufficient period Pre heat the engine Engine runs rough after having warmed up exhaust gas is sooty choke open CLOSE...

Page 211: ...PRE HEAT engine battery power too low INSTALL fully charged battery PERFORM jump start high oil pressure When performing a cold start oil pressure up to 102 psi 7 bar is not an indication of engine problems If necessary perform oil change oil pressure too low after cold start Viscosity of oil too high at oil suction pipe TURN OFF engine and PRE HEAT oil ...

Page 212: ...Manual STEMME S6 Doc No P400 006 000 E Page 9 1 Revision 1 Date of Issue 07 October 2008 Date of Rev 28 01 2011 Chapter 9 Supplements 9 1 Introduction 9 2 9 2 List of Supplemental and Alternative Equipment 9 3 ...

Page 213: ...nts added in this section refer to the installed components It must only be included the supplements according to the aircraft configuration The installation of supplemental or alternative equipment or accessories is based on a service bulletin SB if equipment is not already installed at delivery The necessary supplemental information is provided in the form of Flight Manual Supplements These inse...

Page 214: ...em if necessary The currently installed supplemental or alternative equipment of the motorglider has to be marked in the table below with date and check note This applies to alternative equipment already installed at delivery as well as for equipment later installed This directory serves as a table of contents for chapter 9 Supplements Stemme TSA M variant S6 Serial No Registration No Title Pages ...

Page 215: ...Flight Manual STEMME S6 Doc No P400 006 000 E Page 9 4 Revision Date of Issue 07 October 2008 Date of Rev page intentionally left blank ...

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