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Page 138 " *" & %# 9 ## 1 039 ## 1 03 # 1 03 # 1 " #$ % & 4 //%...
Page 139 " #$ % & 4 //%...
Page 140 ) && & * + " + & , " + && & & & " ." & + &+ & / & * 1 + ) $* ,2 3& + ,2 ) $% &! &$ 4 & )& ) $% 3& + + &...
Page 141 """""""""""""""""""""""""""""""""""" * &! &$ 8 $ + **& + %- **& *& & 8 ++ **& + ! & *& ! * &* * &! &$ & $ 4 &$ & & ! & & " && & + &+ &...
Page 142 """"""""" + !! & & % * &! &$ & $ 4 ! & < ! &$ & & ! 7* & * &! &$ & * & !& $ & $ < - + !! & & & ! &...
Page 143 """"""""""""""""" & & * & && < && & " + < & $ && & & * & & * & & * ." ! " $% & ' - **&...
Page 144 & ! &$ & * %& + ! & * 4 & + * 4 & + ! ! & ! " $% & ' - **&...
Page 145 * &! &$ & & ! + * & + & + &$ & $ $ - % &$ * 4 & / "! < % & + !& $ &/8 $* & & & $ ! & & *& &...
Page 146 " A( :) , " A' :) , ( : " :) , #: " :) , #: " ' :) , ( : & & ! + * & & & ! ! * & & $ $ $ &...
Page 147 & + " & + + * < && & , '' $$ % &4 &+ )3 6 • % , 5 < < • & • ;"3; & * & • 3 $ 4 &8 C 2 , 6 3 8 &...
Page 148 & & ! H ** + 4 4 & " 4 &< & & * & 4 & & = 6 & "! & " 6 ! & ! 8 4 & & & & ! $ +& * & &...
Page 149 & & !& $ & @ & " & !0 "! & & $ - % $ & & 10 ( " + & & 4 & ! & 2 6G & & +- $ % !! ! % !! &...
Page 150 &8 : &8 . 8. F66 21 & • • 9 2 , 6 3 9 • I ( < , # <$, + ." • % , 5 < < <$, & * $ ." • % , 5 <...
Page 151 &8 &8 : * . 9 & > 0> ' '# ' 0( ' '# '#5' ( (0 ' 0# '''' ! " $% & ' - **&...
Page 152 < $ 7 ) & • • • & • I # < , ' <$, & * +8 % & • % , 5 < ." • 7 $ $ & @ > & & ! < & $ 7 ) &...
Page 153 & - & & < !! + & !& $ & & J + $ *& + & 8 % + $ & .& $* & & & % $ &/ + % + & 1G + 4 ! 'D . ! ' ! &...
Page 154 * &! &$ 4 & & + 4 & +- 4 &< & & ! &- + * & & ! & • • & • '' < , ''0 <$, • % , 5 < • , , ' •...
Page 155 " & during Weighing ..............6 3 " $% & 6.3.1 Logsheet for Report of Empty Mass and CG Location ....6 5 6.4.1 Mass Moments and Useful Load ..........6 9 6.4.2 Calculation of Proper Loading for Flight ........6 10 &...
Page 156 ++++++++++++++++++++++++++++++++++++ will only reach the flight performance and handling characteristics described in this operations manual if it is operated in the safe limits for loading and for the center of gravity (CG). The pilot in command is responsible for the correct loading of the aircraft within the loading limits and CG limits.
Page 157 The state of the aircraft and its equipment when weighing must be defined precisely. More information about weighing the aircraft is given in the maintenance manual (STEMME Doc. No.: P500 006.000). Installed equipment according to the current equipment list •...
Page 158 plane (RP) is located at the leading edge of the inner wing at • the wing root. It is aligned vertically to the longitudinal axis. This plane creates a reference line on the ground. Longitudinal inclination: Place a wedge 1000:42 (2,4° = 2°26‘) on the rear •...
Page 159 " $% & ++++++++++++++++++++++ The current empty mass and empty CG location must be documented chronologically in a report of empty mass and CG location (chapter 6.3.1). Every change in the empty mass or empty CG location (which might be caused by changes in equipment, repainting, repairs or similar) must be documented in this report.
Page 160 $% & (continuous report of changes to the aircraft structure and/ or equipment) Registration No.: Serial No.: Sheet No.: ....Current Empty Mass Cleared by Authorized Personnel Con. Description of Mass Lever to Moment Date action taken [lbs] RP [ft] [ft lb] 1.
Page 161 $% ++++++++++++++++++ Only operate the aircraft within the loading limits and limits for the CG location. The current operating mass and operating CG can only be calculated by determining the useful load for the planned flight. To determine the operating mass and operating CG graphically and/or through calculations, use the tables and diagrams given in the following chapters: 6.4.1 Mass Moments and Useful load: Loading diagram •...
Page 162 %ward in flight C.G. for the aircraft is reached for loading configuration ”Fuel Tank empty“. So the critical case to be checked is with landing gear retracted (most rearward C.G. limit). If the most forward in flight C.G. limit is exceeded for this case the aircraft loading has to be adjusted clearly rearward.
Page 163 & Revision: Date of Issue: 18. November 2011 Date of Rev.: . .
Page 164 & STEMME S6 RT Calculation of the proper loading for Reg. No.: .... flight Mass Moment [lbs] [ft lb] Empty Mass and Empty Mass Moment (from current Report of Empty Mass and CG Location) Lever: ........... Pilot and Copilot Lever (mean value):...
Page 165 When calculating the CG position without including the change of fuel mass during flight, the CG must be within the following limits: 454 78 5 5 6 7 5"69 (behind RP). ( 78" 9 (6: 7 ""9 " #$ % &...
Page 166 ++++++++ quipment list is a list of all certified equipment which can be installed in the STEMME S6 RT. The installed equipment list is a list of all equipment which is actually installed in the aircraft. All equipment items actually installed in the aircraft are marked with “X”...
Page 167 & Serial No.: Reg. No.: Date: Lever Manu Description Type Spec. No. Mass [ft] facturer [lbs] + or Altimeter Winter 4FGH40 Altimeter Unit. Instr. 5934 Ser. Air speed Winter 7FMS443 Indicator Compass Airpath C2400 Variometer Winter 5STVM5 2 Soaring Computer LX 166 incl.
Page 168 Lever Manu Description Type Spec. No. Mass [ft] facturer [lbs] + 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...
Page 169 Serial No.: Reg. No.: Date: Lever Manu Description Type Spec. No. Mass [ft] facturer [lbs] + or COM/NAV/GPS Garmin GNS 430W Electronic Flight Dynon EFIS Information Sys. D 10A Transponder Garmin GTX 330 Audio Panel Garmin GMA 340 Radio Becker AR 4201 Transponder Becker...
Page 170 Lever Manu Description Type Spec. No. Mass [ft] facturer [lbs] + or Seat Belts Gadringer Stall Warning STEMME Cabin Heating STEMME not applicable Aerotow Tail Tost for S6 RT Clutch not applicable Tow Bar STEMME for S6 RT not applicable...
Page 171 Serial No.: Reg. No.: Date: Lever Manu Description Type Spec. No. Mass [ft] facturer [lbs] + or M 24 M 25 M 26 M 27 M 28 M 29 M 30 M 31 M 32 M 33 PPPPPPPPP.PPPPP PPPPP.. Clearance Installed Equipment List Date Revision: Date of Issue: 18.
Page 172 7.2.1 Fuselage ................. 7 4 7.2.2 Wing System ................7 4 7.2.3 Empennage ................7 4 ! " 7.3.1 Ailerons ................... 7 5 7.3.2 Elevator ................... 7 5 7.3.3 Rudder and Nose Wheel Steering .......... 7 6 7.3.4 Flaps ..................7 6 7.3.5 Adjustable Rudder Pedals ............
Page 173 " 7.11.1 Engine and General Information ........... 7 26 7.11.2 Propeller ................7 27 7.11.3 Operation of the Engine ............7 29 7.11.4 Turbocharger and Control System ........7 30 7.11.5 Fire Warning ................. 7 32 7.11.6 Engine Cooling System ............7 33 7.11.7 Lubrication System ...............
Page 174 There are also user notes for each system. The description of installed non standard systems is given in section 9. Additional explanations of the components and systems of the Stemme S6 RT are given in the Maintenance Manual (Stemme Doc. No.: P500 006.000).
Page 175 111111111111111111111111111111111111111 ! " The front section of the fuselage – including the cockpit – is constructed from carbon fiber composites. For additional stiffness and a decrease in mass, it is reinforced with longitudinal stringers and circular frames. The midsection is made of a steel tube framework with fairings made of carbon fiber composites.
Page 176 ! " 1111111111111111111111111111111111 The control forces are transmitted to the flight controls with control rods or control cables. Control brackets – made of rust proof coated steel – are laminated into each flight control. The bearings are prepared for easy movement at all times.
Page 177 " Design: CFC Sandwich Mounting: Rudder mounted on top and bottom, 1 control connector on bottom Operation: The rudder movement is transmitted in the front section and midsection of the fuselage by control cables. In the rear section this changes to control rods. The rudder is operated by the rudder pedals.
Page 178 %! 3 The position of the rudder pedals can be adjusted. This allows for a safe and comfortable operation of the rudder pedals, even if the seating position and size of the pilot changes. 6 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.
Page 179 % & 11111111111111111111111111111111111111 The Schempp Hirth style airbrakes are located at the inner section of the outer wing. Design: Airbrake designed as aluminum section, sealing plates made of CFC, placed at top ends of airbrakes. Mounting: 2 rotational shafts in each airbrake box Operation: Operated with control rods, the airbrakes lock at the wing joint.
Page 180 Manual as well as in the Maintenance Manual. For operation instructions of the installed equipment refer to the Maintenance Manual of the STEMME S6 / S6 RT (STEMME Doc. No.: P500 006.000) and to the operation manuals of the manufacturer provided for the installed equipment.
Page 181 6 (2 2 8 & 7 10 Revision: Date of Issue: 18. November 2011 Date of Rev.: . .
Page 182 Canopy Locks White handles on left and right side of canopy frame (additional rear canopy hook at upper rear middle of canopy end) Airbrake Lever Blue lever on left cockpit wall and on left side of center console. Cabin Ventilation Black pull button, one at each seat to control cabin ventilation.
Page 183 6 (2 2 8 & (14) Fuel Valve Red rotary handle on the rear center console at the upper canopy frame, behind head position of the pilot. (15) Handle Black pull handle, next to fuel valve, pulling of the Emergency Extend handle opens the hydraulic valve for emergency extend by bowden cable.
Page 184 ! 111111111111111111111111111111111 The illustration shows the layout and position of the most important control elements and instruments on the instrument panel in the standard configuration. !9 S/N IIIIII 7 13 Revision: Date of Issue: 18. November 2011 Date of Rev.: . .
Page 185 Instruments and indicators on the instrument panel: Airspeed Indicator (15) Manifold Air Pressure Gauge Spare (opt. Soaring Computer) (16) ASI (optional Fuel Flow Indicator) Electronic Flight Information (17) Fire Warning System (EFIS) VOR/ ILS Indicator (CDI) (18) Oil Temperature Gauge Garmin Vertical Speed Indicator/ (19) Cylinder Head Temperature, left...
Page 186 Ciruit breakers for avionics: (A1) Alt Field (A10) Spare (A2) Ldg. Gear Control (A11) Audio Panel (A3) Stall Warning (A12) ELT (A4) Voltmeter (A13) Spare (opt. Soaring Computer) (A5) Pitch Control for Propeller (A14) NAV/ GPS (A6) 12 V Socket (A15) EFIS (not certified as a primary instrumentation) (A7) Trim...
Page 187 Circuit breakers/ switches of the instrument panel: (S1) Auxiliary Fuel Pump (S5) POS Lights (S2) Fuel Transfer Pump (for optional (S6) Landing Light left tank) (S3) Instrument Light (S7) Avionics Master Switch (S4) Anti Collision Light 7 16 Revision: Date of Issue: 18. November 2011 Date of Rev.: .
Page 188 " - 111111111111111111111111111111111111 The landing gear is a retractable tricycle configuration with nose wheel steering. In the retracted configuration, all three landing gear legs are completely covered by landing gear doors. The landing gear mechanics for retraction and extension is driven by hydraulic actuation system. "...
Page 189 extended end position, the supporting drag strut is locked by a deadlock blocking and additional springs independent from hydraulic pressure. " - All three landing gear legs are equipped with separate gear doors, covering each of the landing gear legs and landing gear bays completely and aerodynamically.
Page 190 A red control light is integrated to the push button in the landing gear bay to signalize a drop of storage pressure below 90 bar / 1305 psi ±8%. For further information refer to the Maintenance Manual of the STEMME S6 RT (STEMME Doc. No.: P500 006.000).
Page 191 " - " In order to prevent a landing with unintentionally retracted landing gear the S6 RT is equipped with an acoustical landing gear warning. The acoustical warning comes up, if the airbrakes are operated with landing gear retracted and it is activated by a switch at the airbrake lever.
Page 192 Activate master switch (Batt) and wait until hydraulic system pressure (90 bar / 1305 psi ±8%) is reached and hydraulic pump deactivates automatically For further information refer to the Maintenance Manual of the STEMME S6 RT (STEMME Doc. No.: P500 006.000). 7 21 Revision: Date of Issue: 18.
Page 193 11111111111111111111111111111 The seats are made of cushioned seat pans, which are integrated into the cockpit floor. Their positions are adjustable at the top and bottom (optional), so that they can be positioned ergonomically. The upper sections of each backrest are designed as head rests. Optionally, the backrest can also be adjusted at the bottom.
Page 194 . "" " # 111111111111111111111111111 The baggage compartment is located at the front of the tail boom, just behind the connector frame between the midsection and rear section of the fuselage. A maximum load 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.
Page 195 & 11111111111111111111111111111 The canopy is made of plexiglas and framed by a thin canopy frame made of CFC. This setup allows for good all round visibility. The canopy is hinged at the front of the cockpit and opens in a forward direction. A convenient entry is therefore possible.
Page 196 The method of entry varies individually and depends on the size and agility of the pilot. The following procedure is a convenient and comfortable method of entering the aircraft: Stand with your back facing the cockpit. Place one hand on the leading edge of the wing near the wing root. Place the other hand on the cockpit frame.
Page 197 " 11111111111111111111 " The installed engine is a model ROTAX 914 F2: 4 cylinder 4 stroke Otto engine in opposed cylinder design including turbocharger with electronic manifold air pressure (MAP) control and integrated reduction gear Liquid cooled cylinder heads and ram air cooled cylinders Electronic dual magneto capacitator ignition Two CD carburetor, one on each engine side Flanged reduction gear and overload clutch...
Page 198 The installed MT propeller is a model MTV 7 A / 170 51 with constant speed control unit. Electrically adjustable 3 Blade Constant Speed Propeller, continuously adjustable from T/O setting to glider setting, electronic constant speed control, control unit: P120 A (DB) Forged/milled hub made of light alloys.
Page 199 $6 # > !! !! ? The standard position of the left flip switch is ”AUTO“, for the right flip switch it is “STOP“. The propeller RPM set with the rotary switch will be held constant during the flight. If the left flip switch is set to ”MANU“ and the right flip switch is set to ”HIGH RPM“...
Page 200 "6 Before rotating the propeller by hand (for example to pump oil through the engine before a cold start), REMOVE the ignition key and set the master switch to OFF! "6 Do NOT turn the propeller against its regular direction of motion! 6 Avoid high propeller RPM on the ground.
Page 201 6 The throttle settings of 100% and 115% power can be set without looking at the throttle. 100% power is set once the first detent is reached. To set 115% power, the throttle needs to be pushed past the first detent and against the forward stop.
Page 202 The inducted air is compressed (and warmed to some extent) in the turbo charger. Therefore, a carburetor heat system is not necessary because ice will not form in any flight conditions. "6 Just before reaching the setting for take off power (between 108% and 110% power), the target MAP will rise in a step.
Page 203 " The engine compartment of the STEMME S6 RT is equipped with a fire detecting system which in case of an engine fire gives a clear warning signal by a red warning light in combination with an acoustic alarm signal.
Page 204 " ! " The heat dissipation of the liquid cooling system for the cylinder heads occurs in a aluminum gill radiator. An oil cooler for the lubrication circuit is placed below the aluminum gill radiator. Both coolers are placed below the engine and are supplied with ram air from the central NACA inlet between the main landing gear legs on the bottom of the fuselage.
Page 205 Information about the Liquid Cooling System: The following illustration shows the schematics of the liquid cooling system: ! " > !! % 3(@ B? & The expansion tank (1) is located at the top of the engine. It has a overpressure valve and breather valve which lead to the overflow bottle (4).
Page 206 The coolant circuit is a closed system. A camshaft driven water pump circulates the coolant through the system. To allow coolant to escape into the overflow bottle when warming up, an overpressure valve is installed. When the coolant contracts again during the cool down phase, coolant is sucked into the circuit again.
Page 207 The ROTAX 914 F2 is lubricated by a pressurized dry sump lubrication system. Its main oil pump has an integrated pressure control mechanism. Additionally, a suction pump is installed. Both oil pumps are driven by the camshaft. " C , % >...
Page 208 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.
Page 209 " The power transmission between the engine and the front drive is realized with a long shaft made of carbon fiber composites (CFC). It runs from the front end of the fuselage through a tunnel in the center console to the output gear of the engine.
Page 210 1111111111111111111111111111111111111 " The main tank is the integral tank in the front area of the right wing. It has a fuel capacity of 17.2 US gal / 65 l, of which 2.1 US gal / 8 l are designed as a separate feeder compartment.
Page 211 6 Keep the aircraft leveled during fueling! Also, do NOT fill the tanks to the top edge in warm weather conditions (keep in mind the thermal expansion of the fuel). Else fuel might leak through the fuel tank vents. The fuel tank vents end at the wing joints between the inner wing and outer wings.
Page 212 )6 , 7 41 Revision: Date of Issue: 18. November 2011 Date of Rev.: . .
Page 213 If the optional left fuel tank is installed, then fuel can be moved from the left auxiliary tank to the right main tank by operating the fuel transfer pump. Operation of the fuel transfer pump is monitored by the amount of fuel in the right tank (automatic fuel transfer): If the amount of fuel in the right tank is more than 2/3 3/4 of its maximum capacity and is above the low fuel warning, then no fuel is transferred.
Page 214 11111111111111111111111111111111 The rated voltage of the electrical system is 12V. The starter battery is designed as a maintenance free lead battery with AGM technology. The required minimum capacity is 16 Ah. The battery mounting is located in the rear area of the engine compartment, outside of the fire wall. If the engine is running, the electrical system is supplied by a 600 W alternator.
Page 215 : supplies all avionics and is connected to the main bus with the “Avionics“ isolation switch. The avionics bus is made up of the circuit breakers A4 – A10 (Ill. 7 3). supplies main fuel pump independently from the remaining electrical system. The internal generator bus is designed as a distribution box with fuses and is located on the control board in the engine compartment (at the rear of the fire wall).
Page 216 Oil Temp. / CHT R Low Fuel Caution Light Cons. int. Generator Fuel Pressure Difference Gauge Tachometer Ignition Delay Fuel Flow Gauge Fuel Gauge L Fuel Gauge R Fuel Transfer Pump Auxiliary Fuel Pump Avionics Bus The ratings of the circuit breakers used depend on the information given by the manufacturers of the installed equipment.
Page 217 the battery or external alternator. This switch is mechanically coupled to the ”Batt“ Master Switch. To turn ON the engine bus with the ”Eng“ Master Switch, the “Batt“ Master Switch also needs to be turned ON. To turn OFF the ”Batt“ Master Switch, the engine bus also needs to be turned OFF.
Page 218 Internal Generator Caution The yellow light goes ON if the output voltage of Light (yellow) the generator controller is below the battery voltage (failure of the controller or the generator). External Alternator The red light goes ON if the output voltage of the Warning Light (red) belt driven external alternator falls below the battery voltage (failure of the external alternator).
Page 219 1111111 A tubular probe measures the total pressure, static pressure and total energy compensated pressure (TEC pressure). It is located at the left wing joint between 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.
Page 220 !! 0 " 111111111111111111111111111111111111 If the airspeed 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.
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Page 232 " 44 ! 2 %2 0 ) % J #0 0 %! %# & 0 . I $ % 0% $ # "! %25 0 %! %# < ) ! % & ! " #$ % &...
Page 233 Flight Manual STEMME S6 RT Doc. No.: P400 006.001 FAA Page: 9 1 Revision: Date of Issue: 18. November 2011 Date of Rev.: . .
Page 234 Flight Manual STEMME S6 RT This section gives supplemental information about supplemental or alternative equipment installed in the aircraft, which has not been covered in the previous text of the Flight Manual (chapters 1 through 8). This information is also needed for a safe operation of the A/C.
Page 235 Flight Manual STEMME S6 RT The following list contains all approved supplements that in the case of installation of equipment and systems in addition or as an alternative to the standard configuration are valid. These supplements contain additional information and instructions on the content of the basic Flight Manual (sections 1 through 8) or replace them if necessary.
Page 236 Flight Manual STEMME S6 RT Supplements %& ' ($ Title Pages Revision Date Inst. Check Note * mark as appropriate Doc. No.: P400 006.001 FAA Page: 9 4 Revision: Date of Issue: 18. November 2011 Date of Rev.: . .

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