STEMME S10-VT Maintenance Manual Download Page 48

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Maintenance Manual STEMME S10-VT

Date of Issue: Jan. 01, 1998

Page 3-34

Amendment Nr. 0

Date: --

A4011121_B23.doc

Doc. No. A40-11-121

Abbreviations in Fig. 3.6.a mean:

A: TEK-connection (pitot tube)

B: static

pressure

connection

(pitot-tube)

C: total pressure connection

D: static

pressure

connection

(both sides of tail boom)

E: static

pressure

connection

(optional, both sides of cockpit)

F: flask connection

Certified installations:

Device

line

remarks

Altimeter

Air speed indicator

C, D

Variometer (except for Bohli 68 PVF1 and
Bohli 68 PVF2)

A, F

jet compensated (TEK)

B, F

not compensated

E, F

not compensated

Variometer

Bohli 68 PVF1

(without

internal expansion diaphragm)

C, E, F

only, if no variometer acc. (3) installed

Variometer Bohli 68 PVF2 (with internal
expansion diaphragm)

C, E

E-variometer or gliding computer

B, C, (A)

or: C, E, (A)

line

may be required depending on

type

Coded altimeter

NOTE:

Any line must be as short as possible

The water/separator filters must always be located

in front of

the device and

in front of

any junction.

Fig. 3.6.b Pitot and Static Pressure System, Legend

Summary of Contents for S10-VT

Page 1: ......

Page 2: ...l ROTAX Maintenance Manual for the ROTAX 914 F refer to Annex E is separately revised by ROTAX The inspector confirms by his signature the correct insertion of amendments Am No pages removed pages inserted Date of amendment Date of insertion Signature 1 ii iv v 3 31 7 26 ii iv v 3 31 7 26 18 03 1998 2 ii iv v 3 55 7 33 ii iv v 3 55 7 33 23 03 1998 3 ii iv v viii 7 10 7 18 ii iv v viii 7 10 7 18 22...

Page 3: ... 17 3 19 3 21 3 37 3 38 3 40 4 1 4 3 5 2 6 9 6 13 7 9 7 17 7 23 7 32 10 1 Annex E 30 11 2007 15 iii vi 1 2 4 1 4 3 iii vi 1 2 4 1 4 3 30 11 2008 16 iii iv 4 1 4 3 iii iv 4 1 4 3 24 02 2010 17 iii iv 4 1 4 3 iii iv 4 1 4 3 10 01 2011 18 iii iv v vii 5 1 5 2 cover sheet Annex E iii iv v vii 5 1 5 2 cover sheet Annex E 07 06 2011 19 iii iv 4 1 4 3 iii iv 4 1 4 3 04 04 2012 20 iii iv 4 1 4 3 5 5 iii i...

Page 4: ...2007 3 21 14 30 11 2007 3 22 3 23 Page Am No Date 3 24 8 11 11 1999 3 25 8 11 11 1999 3 26 8 11 11 1999 3 27 8 11 11 1999 3 28 3 29 3 30 3 31 22 10 01 2014 3 32 10 14 12 2001 3 33 3 34 3 35 3 36 3 37 14 30 11 2007 3 38 14 30 11 2007 3 39 3 40 14 30 11 2007 3 41 3 42 3 43 3 44 10 14 12 2001 3 45 10 14 12 2001 3 46 3 47 3 48 3 49 3 50 1 22 10 01 2014 3 50 2 22 10 01 2014 3 51 6 15 04 1999 3 52 3 53 ...

Page 5: ... 11 11 1999 7 20 8 11 11 1999 7 21 1 8 11 11 1999 7 21 2 8 11 11 1999 7 22 8 11 11 1999 7 23 23 29 01 2015 7 24 7 25 7 26 22 10 01 2014 7 27 7 28 8 11 11 1999 7 29 22 10 01 2014 7 30 22 10 01 2014 7 31 7 32 14 30 11 2007 7 33 2 23 03 1998 8 1 8 2 8 11 11 1999 8 3 8 4 8 5 8 6 8 7 10 14 12 2001 9 1 1 13 25 05 2005 9 1 2 22 10 01 2014 9 2 22 10 01 2014 9 3 22 10 01 2014 9 4 22 10 01 2014 10 1 14 30 1...

Page 6: ...ols and Instrumentation 3 23 3 4 8 Fire Protection 3 23 3 4 9 Engine Cowlings 3 23 3 4 10Propeller Fig 3 4 10 a b c 3 24 3 4 11Power Transmission 3 27 3 4 12Front gear 3 27 3 4 13Operation Mechanism of the Propeller Folding System 3 28 3 4 14Operating Media 3 29 3 5 Landing Gear 3 31 3 5 1 Main Landing Gear Fig 3 5 1 3 31 3 5 2 Tail Wheel 3 31 3 6 Flight Control Instruments Pitot Static System Fig...

Page 7: ...5 4 6 Tail Boom 5 15 5 4 7 Empennage 5 15 5 4 8 Fuel System Components in the Fuselage 5 15 5 4 9 Engine and Engine Mountings 5 16 5 4 10Lubrication System 5 16 5 4 11Cooling System Liquid Cooling Ram Air Cooling 5 16 5 4 12Air Induction System 5 17 5 4 13Engine Controls Monitoring 5 17 5 4 14Center Fuselage Fairing Engine Cowlings and Fire Wall 5 17 5 4 15Propeller 5 17 5 4 16Drive Shaft with Fro...

Page 8: ...Bearings 7 8 7 4 Powerplant 7 9 7 4 1 Engine 7 9 7 4 2 Lubrication System 7 12 7 4 3 Cooling System 7 12 7 4 4 Air Induction System 7 13 7 4 5 Exhaust System 7 14 7 4 6 Fuel System 7 15 7 4 7 Engine Controls Monitoring 7 16 7 4 8 Fire Protection 7 17 7 4 9 Cowlings 7 18 7 4 10Propeller 7 19 7 4 11Drive Shaft System 7 23 7 4 12Front Gear Mounting and Support 7 24 7 4 13Propeller Operation 7 25 7 5 ...

Page 9: ...l Tools 10 1 11 List of Maintenance Documents for Parts Being Approved Independently from the Aircraft 11 1 Annex A Supplementary Instructions for Maintenance and Care Maintenance Instructions Annex B Service Bulletins Airworthiness Directives Annex C Documents Inspection and Operation Reports Annex D Maintenance and Inspection Forms Annex E Maintenance Manual Line Maintenance for ROTAX Engine Typ...

Page 10: ...0 Maintenance instructions for the L Hotellier quick disconnects in flight control system 11 Manufacturer s documents referring to the equipment listed in the equipment list of the corresponding S N 12 SB s published by STEMME ROTAX and manufacturer of other equipment installed 13 Maintenance Instructions from STEMME 14 Service Information s from ROTAX The amount and kind of maintenance work depen...

Page 11: ...m 1 Imp gal 4 546 l 1 sqft 0 0929 m2 1 US gal 3 785 l 100 fpm 0 5081 m s 1 p s i 0 06895 bar 1 2 Abbreviations The following abbreviations are being used for clarity a c aircraft AUW all up weight CB circuit breaker CFRP carbon fibre reinforced plastic CG centre of gravity CHT cylinder head temperature DCDI dual capacity discharge ignition GFRP glass fibre reinforced plastic KIAS knots indicated a...

Page 12: ...ansmitted via an internal gear a freewheel clutch a composite drive shaft and a front reduction gear to a foldable propeller in the fuselage nose The electrically operated variable pitch propeller with two blades can be folded and completely covered by a retractable nose cone propeller dome for soaring One fuel tank is located in each outboard area of the central wing Engine fuel supply is by two ...

Page 13: ...el STEMME 11 AP diameter extended DPA 1 63 m 63 4 in mass of the propeller incl outer casing of needle bearing and rubber buffers mP 9350 g 20 61 lbs overall mass of propeller blade mB 650 g 10 g 1 433 lbs 0 022 lbs max propeller RPM nP 2 650 RPM propeller pitch T O position P 17 65 cruise position P 24 05 max current consumption of the resistor element Imax 10 A Weights see also figures 6 3a 6 3 ...

Page 14: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 2 3 Amendment Nr 0 Date A4011121_B23 doc Doc No A40 11 121 Fig 2 a 3 View Plan of the S10 VT ...

Page 15: ...f the outboard wings The controls of flaps and ailerons are interconnected the ailerons acting as differential flaps and the flaps acting as differential ailerons The flap deflection is reduced from the inner to the outer wing the aileron deflection is reduced from outer to the central wing and from up to down deflections Two storey Schempp Hirth air brakes are installed on the centre wing upper s...

Page 16: ...al harness Dual controls are provided Between the seats a console covers systems and the drive shaft tunnel The mushroom style panel arrangement has three separate areas LH side centre and RH side The one piece canopy is hinged at the front and held in opened position by gas springs Three canopy locks on both left hand and right hand side are operated by one locking lever on each side One lock to ...

Page 17: ...ver for parking brake valve on the floor panel console in front of the LH control stick Hydromechanical brake system The brake lever can be locked with a pin for parking 8 Trim Lever One green lever on centre console between seats To trim push down unlock and shift lever forward or aft Locking is by a spring device 9 Throttle Lever One black lever on centre console with two forward stops for max c...

Page 18: ...he cowl flaps 3 Propeller Dome Operation Black handle in the middle foot of the instrument panel to open close and lock the propeller dome linked to the engine electric master switch Unlock by lifting lock by pushing down the handle In the forward position Dome OPEN the engine master switch comes ON when the dome is LOCKED 4 Propeller Brake Black T handle on RH side of the cowl flap reduction to b...

Page 19: ...y in LH and RH wing tanks Engine elapsed time indicator These instruments are located as a rule with the exception of the engine elapsed time indicator in the RH area of the panel if not installed i e with double instrumentation in the centre area The engine elapsed time indicator is located on the centre console between the seats The red fire warning light test by pushing light for optic and acou...

Page 20: ...ch down additional battery selected up main battery selected 4 switch for auxiliary fuel pump 5 fuel selector switch positions LEFT BOTH RIGHT 6 electric master switch 7 switch for external generator 8 engine back up switch to bypass engine master switch in case of malfunction of the microswitch at the propeller dome switch is guarded with a black protecting plate for unintended operation 9 TCU em...

Page 21: ...ance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 7 Amendment Nr 0 Date A4011121_B23 doc Doc No A40 11 121 Fig 3 2 a Arrangements of Elements on Instrument Panel Related to S N Indicated on Title Page ...

Page 22: ...o a central bell crank lever beneath the connection tube of the longitudinal elevator control From this bell crank lever control inputs are transmitted via push rods to the mixing shaft in central fuselage Via this mixing shaft bell crank levers push pull rods and quick release couplings the control rods in the wing are moved Both sides of the central wing contain a straight through control rod su...

Page 23: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 9 Amendment Nr 0 Date A4011121_B23 doc Doc No A40 11 121 Einkleben Höhensteuerung und Trimmung Fig 3 3 a Pitch Control and Trim ...

Page 24: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 10 Amendment Nr 4 Date Aug 12 1998 A4011121_B23 doc Doc No A40 11 121 Fig 3 3 b Wing Flap Control in Fuselage ...

Page 25: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 11 Amendment Nr 0 Date A4011121_B23 doc Doc No A40 11 121 Fig 3 3 c Wing Flap Control in Central Wing ...

Page 26: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 12 Amendment Nr 0 Date A4011121_B23 doc Doc No A40 11 121 Fig 3 3 d Aileron Control in Fuselage ...

Page 27: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 13 Amendment Nr 0 Date A4011121_B23 doc Doc No A40 11 121 ...

Page 28: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 14 Amendment Nr 8 Date Nov 11 1999 A4011121_B23 doc Doc No A40 11 121 Fig 3 3 f Airbrake Control in Fuselage ...

Page 29: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 15 Amendment Nr 8 Date Nov 11 1999 A4011121_B23 doc Doc No A40 11 121 Fig 3 3 g Airbrake Control in Wing ...

Page 30: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 16 Amendment Nr 8 Date Nov 11 1999 A4011121_B23 doc Doc No A40 11 121 Fig 3 3 h Rudder Control ...

Page 31: ...he central fuselage the following modifications were made The most significant modification is the relocation of the turbocharger unit to the aft of the engine to stay within the outlines of the S10 VT fuselage The turbocharger unit is supported by five struts aft of the engine In between the turbocharger and the carburetors a supercharger intercooler is installed Relocation of the turbocharger un...

Page 32: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 18 Amendment Nr 0 Date A4011121_B23 doc Doc No A40 11 121 Fig 3 4 a Propulsion System ...

Page 33: ...in the LH landing gear bay The quantity of the coolant can be checked at the scale on the overflow container and must be between min and max markings The coolant lines consist of flexible coolant hoses and aluminium tubes To allow relative movements the rigid components of the system are connected by flexible hoses Ram Air Cylinder Cooling Ram air for cylinder cooling is guided from the RH cowl fl...

Page 34: ... Heavy Maintenance for ROTAX Engine Types ROTAX 912 and 914 Series section 78 Turbocharger attachment Five steel tube struts at aft engine mounts The turbocharger unit consisting of turbocharger and muffler is installed aft of the engine and supported by five struts on the crankshaft housing The turbocharger is supplied with oil by oil suction and oil pressure pipes from the engine oil pump The ex...

Page 35: ...ted to a fuel hose routed to a water separator which separates drainage and fuel supply from the respective tank The drain line is laid to the respective self sealing drain valve one for each tank installed between the lower connections of the elbow levers of the L G The supply suction line of each tank including a fine filter and a check valve is routed from the water separator to the respective ...

Page 36: ...sor Fuel Pressure Engine Compartment Fuel Pressure Regulator Airbox Sensor Airbox Presssure Fuel Cock IIII IIII Left Right Quantity Indicators ON OFF RIGHT LEFT External Generator Circuit Internal Generator Circuit Left Wing Tank Right Wing Tank Green Status Light Aux Fuel pump Aux Pump Switch Fuel Tank Selector Switch Red Warning Light Fuel Pressure Electrical Main Fuel Pump LH Electrical Main Fu...

Page 37: ...nt type N 56582 T508 and one coat of clear varnish type 4232 0303 hardener N39 1327 or N50 2509 thinner N39 3091 The fuel and oil hoses in the engine compartment are covered by fire protective sleeves Aeroquip The fire warning system is triggered by two bimetallic temperature sensors above the carburetors The fire warning is by means of a red warning light push to test function on the instrument p...

Page 38: ...e propeller blade Electrically heated expanding servo elements 15 actuate the blade pitch mechanism On achieving their activating temperature these expanding servo elements drive a piston connected to the propeller blades All components of blade angle mechanism are double redundant and mechanically interconnected by a coupling ring 12 so that both propeller blades always have identical pitch Prope...

Page 39: ...0 Drive pin 11 Coupling Part 12 Synchronisation ring 13 Push rod 14 Rocking lever 15 Dilation effect actuator 16 Heating element 17 Slip ring 18 Slip ring 19 Fly weight 20 Compression spring 21 Rubber stop 22 Cam lever 23 Torsion Spring 24 Stop 25 Adjustment screw 26 Yield bolt 27 Base 28 Nut 29 Ball washer Fig 3 4 10 a Variable Pitch Propeller NOTE In order to prevent incorrect assembly all parts...

Page 40: ...ransferred to the propeller blades by slip rings The expansion elements actuate only towards the high pitch angles The propeller blades are rotated in the direction of lower pitch position by the return spring at the lever mechanism assisted by mass and aerodynamic forces on the blades When the propeller switch in the cockpit is turned to cruise the expansion elements are heated with about 50 Watt...

Page 41: ... components of the power transmission system are Centrifugal clutch in between engine and drive shaft a force transmitting clutch actuated by direction of turn and rotating speed Since the centrifugal clutch transmits torque by friction it is also an overload protection Drive shaft which is manufactured in carbon fibre reinforced composite material Flexible coupling forward and aft allowing for an...

Page 42: ...dle to and around an aluminium disc which is pivoted on the guide block of the propeller dome sliding tube in the forward cockpit When pulling the handle the disc rotates against a circumferencial spring force until reaching a screw stop which is adjustable and defines the final position of the propeller The spring is winded round the propeller dome guide block and rotates the disc towards its ini...

Page 43: ...icorrosion additives and 20 water Freezing point of this mixture is about 38 C 34 F BASF Glysantin Antikorrosion proved to be good This or equivalent coolant should be used CAUTION To minimise the risk of residues concentrated antifreezing agent without water added should only be used in case of coolant evaporation after engine shut down Pure antifreezing agent starts freezing at 18 C 0 F CAUTION ...

Page 44: ...ils are to be preferred because of the temperature stability and less residue formation CAUTION A full synthetic oil in combination with AVGAS results in abnormally high abrasion and or residues During utilisation of AVGAS only semi synthetic oils should be used a Viscosity It is recommended to use multi grade oils Viscosity of multi grade oils is less depending on temperature compared to single g...

Page 45: ...s of magnets The disk brakes on the main L G wheels are operated hydraulically The main cylinder for both the left and right wheel is located on the LH control stick on RH stick optional The pressure line from the main brake cylinder to the brake callipers of the wheel brake in the center fuselage are designed as metal shielded brake hoses The brake fluid reservoir is located in the landing gear b...

Page 46: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 32 Amendment Nr 10 Date Dec 14 2001 A4011121_B23 doc Doc No A40 11 121 Fig 3 5 1 Main Landing Gear Adjustment Data ...

Page 47: ...ic pressure measured by the bar probe may not be used for the airspeed indicator Static pressure for the airspeed indicating system is exclusively measured on both sides of the tail boom This duct is also directed to the instrument panel NOTE Some instruments e g Bohli diaphragm type rate of climb indicator need additional static ports for proper operation at the widest area of the forward fuselag...

Page 48: ...imeter B 2 Air speed indicator C D 3 Variometer except for Bohli 68 PVF1 and Bohli 68 PVF2 A F jet compensated TEK B F not compensated E F not compensated 4 Variometer Bohli 68 PVF1 without internal expansion diaphragm C E F only if no variometer acc 3 installed 5 Variometer Bohli 68 PVF2 with internal expansion diaphragm C E 6 E variometer or gliding computer B C A or C E A line A may be required...

Page 49: ...protected against mechanical damage by a spiral winding tape and is fastened at adequate distance from hot areas The components for voltage distribution and propeller blade control are installed close to the main battery in the junction box E box in the upper area of the steel tube frame outside of the fire wall To protect the battery connectors mechanically a distributor plate is installed on the...

Page 50: ...d for all avionic equipment including headsets It is installed on the RH electronic plate and connected with the fuselage steel tube framework 3 7 5 Generation of Electric Energy Electrical power sources are the main battery capacity 26 Ah the optional additional battery 7 2 Ah for supply of avionics during soaring and two engine driven generators generating 600 Watt and 250 Watt The external V be...

Page 51: ... internal generator The voltage regulator of the internal generator is installed on the lower side of the E box 3 7 7 Engine Monitoring System description Refer to Maintenance Manual Heavy Maintenance for ROTAX Engine Types ROTAX 912 and 914 Series section 76 There are two kinds of engine monitoring certain parameters are sensed and conventionally displayed on analogue instruments on the RH instru...

Page 52: ...tric master switch ON the Main Bus is connected to the battery Voltage on another bus is indicated when operating a push button If this push button is operated while the engine is not running the voltage of the optional additional battery if installed is indicated When the engine is running the additional battery is charged via relay from the Main Bus In this case the voltage indicated when the pu...

Page 53: ...B If the Main CB is pulled the battery is still charged by the external generator Avionic CB s are installed in a row on a plate below the avionics Any other CB s and fuses are installed in the E box and on the electronic plate on the RH side of the instrument panel below the panel cover 3 7 11 Switches on the Instrument Panel See also Fig 3 2 a Below the centre avionic panel a row of switches is ...

Page 54: ...tch can be bypassed in case of malfunction of the engine starter due to malfunction of the engine master limit switch The engine master limit switch is operated by the propeller dome lever and connects the engine bus to the main bus in the open and locked propeller dome position If the engine instruments do not indicate after opening and locking the propeller dome a malfunction of the engine maste...

Page 55: ...tatus Light for T O position The green Propeller Pitch Status Light is ON if the propeller blades are in T O position within very close limits fine pitch and the light is OFF in any other position The position signal is generated by a blade position module installed on the RH electronic plate This module only operates if the engine is running 3 7 13 Main Landing Gear The landing gear is controlled...

Page 56: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 42 Amendment Nr 0 Date A4011121_B23 doc Doc No A40 11 121 Fig 3 7 a Generation and Distribution of Electrical Energy pg 1 ...

Page 57: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 43 Amendment Nr 0 Date A4011121_B23 doc Doc No A40 11 121 Fig 3 7 b Generation and Distribution of Electrical Energy pg 2 ...

Page 58: ...r ont 1 2 2Q X 3A F uel Lev el 1Q X QX2 E QX9 EN F uel F low A ddition M odule L H F uel F low T r anc duc er R H F uel F low T r anc duc er F uel F low I ndic ation see Not e1 Oil P r es s Oil T em p ED2E ED3E re d QX9 EN ED4EN EK5EN EN4EN QX9 EN EN3E EN3ES EK3E EK4E EK2E EN2E 1EK 3A T ac hom et er CHT r ed r ed wh ite b la ck r ed black EW2 EN EW1 E EM1 E EM2 EN 1EN 3A 2IB I gnit ion S t art er ...

Page 59: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 45 Amendment Nr 10 Date Dec 14 2001 A4011121_B23 doc Doc No A40 11 121 Left blank ...

Page 60: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 46 Amendment Nr 0 Date A4011121_B23 doc Doc No A40 11 121 Fig 3 7 e Variable Pitch Propeller Control ...

Page 61: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 47 Amendment Nr 0 Date A4011121_B23 doc Doc No A40 11 121 Fig 3 7 f Landing Gear Control ...

Page 62: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 48 Amendment Nr 0 Date A4011121_B23 doc Doc No A40 11 121 Fig 3 7 g Landing Gear Indication and Warning ...

Page 63: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 49 Amendment Nr 0 Date A4011121_B23 doc Doc No A40 11 121 Fig 3 7 h Fire Warning ...

Page 64: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 50 1 Amendment Nr 22 Date Jan 10 2014 A4011121_B23 doc Doc No A40 11 121 Fig 3 7 i 1 Heating and Lighting optional ...

Page 65: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 50 2 Amendment Nr 22 Date Jan 10 2014 A4011121_B23 doc Doc No A40 11 121 Fig 3 7 i 2 Heating and Lighting optional LED version ...

Page 66: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 51 Amendment Nr 6 Date April 15 1999 A4011121_B23 doc Doc No A40 11 121 Fig 3 7 j ACL on engine cowling optional ...

Page 67: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 52 Amendment Nr 0 Date A4011121_B23 doc Doc No A40 11 121 Fig 3 7 k External Power Supply optional ...

Page 68: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 53 Amendment Nr 0 Date A4011121_B23 doc Doc No A40 11 121 Fig 3 7 l Electrical Circuit Scheme ...

Page 69: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 3 54 Amendment Nr 0 Date A4011121_B23 doc Doc No A40 11 121 Intentionally left blank ...

Page 70: ...nts due to possible influence on power consumption electromagnetic influence and structural characteristics of the instrument panel Outside Germany it must be confirmed that the equipment is certified by the local authority which certified the a c The weight limits for the equipment installed in the instrument panel without structural reinforcement engine instrumentation plus 10 kg 22 lbs and the ...

Page 71: ......

Page 72: ...ks to be done at the time of the scheduled maintenance defined by Chapter 5 Time Limits and Maintenance Checks of the Maintenance Manual Be sure to verify compliance with Chapter 4 airworthiness limitations when performing scheduled maintenance per Chapter 5 The following requirements must be adhered to consistent with applicable national regulations 4 2 1 Paint Finish To ensure that the temperatu...

Page 73: ...achment omponents STEMME 10AP V88 V76 V77 V78 VU 61 10 200 hr 400 hr 1 4 Front Gear Box cog wheels STEMME 11AG 72 10 1000 hr 1 5 Front Gear Box mounting STEMME 11AA 72 10 1000 hr 1 3 6 Front Gear Box mounting elastomer parts STEMME 11AA S 11AA 36 72 10 12 years 1 3 7 Centrifugal clutch 3 flyweights STEMME 11AK 12AK 72 10 400 hr 1 8 Driveshaft STEMME 10AS 07 10AS W 10AS F 72 10 800 hr 1 9 Flexible ...

Page 74: ...6000 h of flight time Extension of service life above 6000 h can be achieved only by alteration from replacement TBR to TBO and introduction of an additional overhaul at 6000 h and a subsequent mandated overhaul interval TBO for continued airworthiness The TBO change will be notified by a revision of this chapter The additional overhaul will include a comprehensive inspection of the airframe carri...

Page 75: ...overs unscheduled maintenance such as after hard landings prop strikes or intense turbulence Maintenance including pre flight Inspections and preventive maintenance must be carried out by qualified and appropriately authorized personnel In any case the governing national laws and regulations are obligatory Extreme environmental conditions e g arid desert or humid lowlands present added albeit diff...

Page 76: ... of removal installation or overhaul of each component should be logged in strict compliance with applicable national requirements NOTE Aircraft storage or operation under less favorable or sub normal conditions often requires more frequent inspection overhaul or replacement of components than at the intervals recommended below More frequent inspection includes careful inspection before each fligh...

Page 77: ...ntenance Manual Line Maintenance ROTAX MML 914 Edition 2 Revision 1 dated July 1 2010 or later version The recommended TBO for all rubber parts as stated in the latest revision of ROTAX MML 914 Edition 2 applies to STEMME s ROTAX 914F2 S1 engine 3 STEMME does NOT endorse operating beyond the stated engine TBO defined by ROTAX and applied by STEMME for its engine ROTAX 914F2 S1 Any decision to oper...

Page 78: ...national regulations 10 The L Hotelier connections wear with use and their security is critical to safe flight STEMME recommends that the owner and operator inspect these connectors per L Hotellier Instructions for the Maintenance L Hotellier Ball and Swivel Joints Ref IMA10 01 in the latest approved revision This technical data may be obtained from L Hotelier S A 93 Avenue Charles De Gaulle 92270...

Page 79: ...be visually and manually inspected before first engine operation after maintenance to confirm that no hose can be pulled loose from its respective fittings 5 3 Periodical Inspections The intervals for general maintenance and inspections depend upon operating conditions climate storage conditions and environmental factors More frequent inspection and maintenance would be prudent under sub normal co...

Page 80: ... every 100 200 and 600 engine operating hours They have to be carried out in accordance with the following Periodic Inspections Check List Chapter 5 4 This means that a 100 engine hr inspection shall be done every 100 hr of engine operation a 100 engine hr inspection shall be done every 200 hr of engine operation plus additional 200 engine hr checks check spark plug connectors for tight fit renew ...

Page 81: ...ion 6 for details of the aircraft generally and in section 7 for specific assemblies of the aircraft The relevant subsection is indicated for each inspection item shown on the Check List In addition special inspections may at times be prescribed by the responsible authority or may be recommended by the manufacturer those inspections must be performed as required in accordance with the issued direc...

Page 82: ...ealed damage the owner or operator is advised to contact the manufacturer or another appropriately approved maintenance person specialized on diagnosing and repairing the affected type of components or systems Unscheduled Maintenance for Propeller Assembly Engine Drive Section and Front Gear Box Components An unscheduled inspection overhaul repair or replacement is mandatory following each case of...

Page 83: ...eduled Maintenance Checks and Good Practice The owner and operator are primarily responsible for maintaining the airplane in an airworthy condition This includes compliance with all applicable Airworthiness Directives It is the responsibility of the owner and the operator to ensure that the airplane is inspected and maintained as specified in sections 43 and 91 of Federal Aviation Regulations The ...

Page 84: ...els fairings or cowlings The visual inspection shall include an examination by area component detail assembly or installation as well as any associated equipment within the immediate vicinity using any inspection aids considered necessary When performing either an Annual or a 100 hr Inspection each installed miscellaneous item not specifically covered in Section 5 1 or in Section 5 4 Checklist for...

Page 85: ... bend radius cleanliness securely installed and any other apparent damage Electrical Wiring Cleanliness loose corroded or broken terminals chafed broken or worn insulation wires and wire bundles securely installed signs of heat deterioration and any other apparent damage Bolts and Nuts Fretting wear damage stretch cross threading proper torque corrosion and locking or safety wiring Filters and Scr...

Page 86: ...er to torque values in the Maintenance Manual Line Maintenance for ROTAX Engine Type 914 Series Annex E to this AMM and Maintenance Manual Heavy Maintenance for ROTAX Engine Types 912 and 914 Series Clean or replace all filters gaskets lock washers O rings and shaft seals before reassembly or reinstallation and as required by Maintenance Check List Electrical wire condition is critical to flight s...

Page 87: ...tion of flight controls X X X 7 3 6 Check slackness of aileron flap and elevator controls X X 6 4 3 7 Check friction and forces in control system X 6 4 1 5 4 2 Wings and Fuel System Components in the Central Wing 1 Check fuel system components at spar bridge of center wing X X X 7 4 6 2 Check vent line outlets at end ribs of central wing X X X 7 4 6 3 Check function of quick release couplings supp...

Page 88: ...ation X X X 7 3 1 7 Check swaged terminals of all control rods in fuselage X X 7 3 8 Check condition and attachment of instruments switches circuit breakers fuses and wiring Check fire warning light X X X 7 2 2 9 Check flexible hoses of ventilation and heating optional equipment X X X 7 2 2 10 Check rudder pedals and cables check pedal adjustment X X X 7 3 1 11 Check condition attachment and adjus...

Page 89: ... stabilizer fittings X X X 7 1 3 8 Check connection of elevator control rod to rear fitting of elevator X X X 7 3 3 9 Check backlash in fittings of horizontal stabilizer when installed X X X 7 1 3 10 Check additional battery optional Connections tight fit and condition of mounting Check if the Equipment List and Weight and Balance Report correspond with the a c with regard to the additional batter...

Page 90: ...it X 7 4 1 15 15 Check of compression pressure X X 7 4 1 16 16 Check mountings of turbocharger muffler X X X 7 4 5 1 17 Check condition of exhaust bends incl attachment and springs X X X 7 4 5 2 18 Check heat insulation exhaust bends muffler heat protection shields renew if required X X X 7 4 5 3 19 Renew heat insulation of exhaust bends X X 7 4 5 3 20 Check of mounting points of engine housing X ...

Page 91: ...tion of ignition retarder module X X 7 4 7 6 Check function of engine instrumentation X X X 7 4 7 5 4 14 Center Fuselage Fairing Engine Cowlings and Fire Wall 1 Check condition of upper center fuselage fairing including oil service access X X X 7 4 9 2 Check condition of LH and RH Cowling X X X 7 4 9 3 Check condition of cowling fire protective painting Repair if required X X X 7 4 8 1 4 Check con...

Page 92: ...front gear fairing X X X 7 4 12 4 Check function of freewheel clutch X X X 7 4 11 5 Check attachment of freewheel clutch on engine flange X X X 7 4 11 6 Check condition and tight fit of cardanic rubber disc joint on freewheel clutch X X X 7 4 11 7 Check condition and tight fit of cardanic rubber disc joint on front gear X X X 7 4 11 8 Check condition of composite shaft X X X 7 4 11 9 Check front g...

Page 93: ...18 Tail Wheel 1 Tail wheel Check ease of operation clearance to fairing backlash X X X 7 5 2 2 Check tire condition pressure 2 8 0 2 bar 41 3 p s i X X X 7 5 2 3 Check wheel fork for cracks and deformation X X 7 5 2 4 Check bearing of tail wheel fork X X 7 5 2 5 Check spring coupling assy between tail wheel and rudder X X X 7 5 2 5 4 19 Flight Instrumentation and Pressure Systems 1 Check condition...

Page 94: ...OM equipment for proper installation and safe mounting and compare to equipment list X 7 8 2 Check function and if applicable service life limits of NAV and COM equipment refer to records of operating times Annex C X 7 8 3 Check each antenna installed X 7 8 5 4 22 Oxygen Equipment 1 Check oxygen equipment if installed Observe maintenance instructions of manufacturer refer to Annex A X X 7 9 5 4 23...

Page 95: ...ection 5 4 16 as far as applicable 3 After the propeller blades have been repaired or replaced the drive system must be dynamically balanced as laid down in A17 10AP V 2 E Dynamic Propeller Balancing STEMME S10 Maintenance Manual Annex A In the event of major damage to the propeller blades e g shortening of a propeller blade by more than 30 mm 1 18 in areas painted grey on both sides at the tips o...

Page 96: ...der is controlled by hand Supporting points for lifting the aircraft are on the wing bottom surface in the spar area about 1 m 3 3 ft from the fuselage position of the wing spar can be determined by light tapping The tail section is lifted approximately 0 5 m 1 6 ft supporting the tail wheel The wing supports for lifting must have an area of at least 200 x 300 mm 9 in x 12 in the longer side in di...

Page 97: ... load must be entered in the Weighing Logsheet and Permitted Payload Range in section 6 2 of the Flight Manual and confirmed by an authorised inspector before operating the powered glider In addition the placard on centre console in the cockpit must be corrected accordingly Definitions Reference datum is the plane that is touching the leading edge of the centre wing and is perpendicular to the upp...

Page 98: ...ired weight of the ballast can be calculated m m x x x x Ballast alt neu alt Ballast neu where malt and xalt are empty weight and CG prior to the modification xneu the target for CG at empty weight and xBallast the arm of the ballast weight in front or aft of RP It must be observed that the maximum weight which can be installed at the rear web of the vertical fin is structurally limited to 2 7 kg ...

Page 99: ... kg Allowable CG empty aft of Datum mm Nose heavy CG range tail heavy CG range allowable CG range Fig 6 3 b Range of Empty Weight CG as a Function of Empty Weight and Minimum Load WARNING The additional battery has a major effect on the aircraft CG The Equipment List and the Weight and Balance Report must correspond with the a c with regard to the additional battery otherwise the airworthiness exp...

Page 100: ... 2 19 85 522 7 20 58 530 20 87 537 3 21 15 544 7 21 44 552 21 73 660 1455 503 19 8 522 3 20 56 529 7 20 85 537 21 14 544 3 21 43 551 6 21 72 662 1459 4 501 7 19 75 522 20 55 529 3 20 84 536 6 21 13 543 9 21 41 551 2 21 7 664 1463 9 500 5 19 7 521 7 20 54 529 20 83 536 3 21 11 543 5 21 4 550 8 21 68 666 1468 3 499 3 19 66 521 4 20 53 528 7 20 81 535 9 21 1 543 2 21 39 550 4 21 67 668 1472 7 498 1 1...

Page 101: ...ute 110 kg 243 lbs max Baggage load in baggage compartments 22 kg 48 5 lbs but maximum is also the difference between max cockpit load and max weight of both occupants 180 kg 397 lbs When loads are below Minimum Loads as stated in the Flight Manual section 6 2 the difference of minimum load and actual load must be compensated by ballast The manufacturer has prepared a fix point for ballast attachm...

Page 102: ...left wing flap right wing flap right aileron Position Position mm in 10 neutral 31 4 1 22 0 16 31 4 1 22 0 16 5 neutral 15 4 0 6 0 16 15 4 0 6 0 16 0 left neutral right 48 4 1 89 0 16 0 2 0 0 08 27 3 1 06 0 12 0 2 0 0 08 0 2 0 0 08 27 3 1 06 0 12 0 2 0 0 08 48 4 1 89 0 16 5 neutral 15 4 0 6 0 16 15 4 0 6 0 16 10 neutral 31 4 1 22 0 16 31 4 1 22 0 16 L 16 neutral 51 4 2 0 16 51 4 2 0 16 6 4 1 2 Fri...

Page 103: ...to 4 7 10 36 200 1 47 to 272 1 99 11 6 2 61 to 15 8 3 55 at operating rod r 17 2 cm 6 77 in Elevator 0 75 1 65 to 0 92 2 0 28 0 21 to 32 5 0 24 2 0 0 45 to 2 7 0 61 at inner end rib 0 92 2 0 to 1 15 2 5 28 0 21 to 37 5 0 27 r 14 0 cm 5 51 in Rudder 2 6 5 73 to 4 0 8 82 182 1 33 to 224 1 64 4 3 0 967 to 5 3 1 19 at bottom rear corner r 42 5 cm 16 7 in left and right measured separately 6 4 3 Free P...

Page 104: ...l surface bearings except rudder bearings are coated and normally greasing is not required However greasing may be necessary in aggressive environmental conditions when bolts show first signs of corrosion In this case use MoS2 free grease The rudder hinges must be greased depending on the degree of exposure to contamination specially the lower hinge Connection of the Propeller Extension Shaft to t...

Page 105: ...ease any rigging and Inspection Type 3 6 Shear fittings inner outer wing grease any rigging and Inspection Type 3 7 Forward and rear horizontal tail fitting grease any rigging and Inspection Type 3 8 L Hotellier connection aileron control rod grease only ball any rigging and Inspection Type 3 see also manufacturer instruction Annex A 9 Spring parts of landing gear doors oil any scheduled maintenan...

Page 106: ... by stone strike Check all labels and repair or renew if necessary specially national flag and registration Additional remarks about identification of structural damage specially in force transfer areas etc can be found in section 7 1 in relevant subsections for components According to the type approval data sheet the surface may only be coloured in white except for registration and areas for warn...

Page 107: ...23 doc Doc No A40 11 121 6 7 Drainage and Ventilation Holes The following position plan shows positions of the drains and ventilation holes except for propeller Any drains and ventilation bores should be checked for blockage during any scheduled inspection Positions of Drainage and Ventilation Holes ...

Page 108: ...d propeller flange of the engine without 22 16 2 M10 connecting clutch and flexible disk drive shaft 243 35 25 8 3 M10 connecting flexible disk and forked sleeve of the drive shaft 243 35 25 8 4 M10 connecting drive shaft and flexible disk front gear 243 35 25 8 5 M10 connecting flexible disk and front gear 243 35 25 8 6 M8 connecting front gear in the gear suspension 221 16 11 8 7 M8 fastening sc...

Page 109: ...g see position plan in section 6 7 7 1 1 3 Wing fittings Check backlash of the wing fittings by moving wing tips forward and aft and up and down If excessive backlash is found or in case of doubt the bolts and fittings must be measured by means of a micro meter Clearance of Wing Fuselage Attachments Axial maximum 0 4 mm 0 016 in Radial maximum 0 15 mm 0 006 in Clearance of Inner to Outer Wing Atta...

Page 110: ... at the vertical tail root Check the lower sides of front fuselage and tail boom for damages from stone strike Deep damages of the coating which may allow water to penetrate into the composite structure should be repaired See also section 6 6 and Annex A Minor repair to components of fibrous composite material 7 1 2 2 Drainage holes Check holes for cleanness clean if necessary Positions see positi...

Page 111: ...ck condition of rudder fittings stainless steel specially check lower fitting for cracks and deformation Check tight fit of screw connections and rivet connection of bearings friction in bearings observe section 6 5 Lubrication and backlash The axial backlash of the rudder should be minimum washer D125 08 must be installed between lower bearing and lower hinge bolt Check condition of split pin Mov...

Page 112: ... screw stop Check backlash of the horizontal tail fitting move horizontal tail tip forward and aft and up and down take hold of the mid section of the horizontal tail fin push up and down If excessive backlash is found the bolts and fittings must be measured Maximum Backlash of Horizontal Tail Fittings forward fitting vertically 0 15 mm 0 006 in horizontally 0 1 mm 0 004 in rear fitting vertically...

Page 113: ...elease gas spring Force of Gas Spring compressed 150 30 N 34 7 lbf 7 2 1 3 Re installation of the canopy Unscrew the ball head bolted joint of the pneumatic springs which hold the canopy open Loosen the M8 nuts on the fuselage side of the canopy hinge by two revolutions Use a punch to brace the gas spring within the hinge opening spring and push the head half way under the side wall so that the sp...

Page 114: ...ck instrument panel for loose screws Check condition and attachment of instruments switches circuit breakers fuses and wiring Press fire warning light to check it for acoustical and optical function 7 2 2 3 Air hoses Check ventilation air hoses for condition holes crinkles and proper attachment to the air vents and the air inlet at the bottom front fuselage NACA Inlets Heating air hoses optional r...

Page 115: ...ustment clean sliding guide with alcohol if required Check all control rods and levers including slides for rudder cables in centre fuselage for tight fit of all joints proper condition of bearings damage scratches and deformation NOTE Do not use grease or oil to improve smooth operation of pedal adjustment Check condition and attachment of rubber stops on centre steel frame Check function proper ...

Page 116: ...rudder stop screws on lower rudder fitting left right for rated values according section 6 4 1 1 Elevator Control Connection Check control link in rear horizontal tail fitting for condition tight screw connection low friction of bearing observe section 6 5 Lubrication To check bell crank lever of the elevator control in the base of the vertical fin remove two stoppers from inspection holes LH side...

Page 117: ...vice centres indicated by ROTAX refer to www rotax aircraft engines com Service of modified components are carried out by STEMME only as well as delivery of modified spar parts For identification of components affected by the modifications and in any case of doubt it is recommended to contact STEMME STEMME AG Flugplatzstrasse F2 Nr 7 D 15344 Strausberg 49 0 3341 3612 0 49 0 3341 3612 30 e mail ser...

Page 118: ...onents See Maintenance Manual Line Maintenance for ROTAX Engine Type 914 Series section 12 00 Annex E 7 4 1 7 Check of Waste Gate Deviating from the figures in the ROTAX manual the waste gate control of the ROTAX 914 F2 S1 has been modified according to the following figure The servo cable and the spring are now attached to an additional swiveling lever which is mounted on the original lever of th...

Page 119: ...System and Maintenance Manual Line Maintenance for ROTAX Engine Type 914 Series section 12 00 subsection 6 1 Annex E 7 4 1 13 Check of V Belt Tension See Maintenance Manual Line Maintenance for ROTAX Engine Type 914 Series section 12 00 subsection 2 7 Annex E 7 4 1 14 Renewal of Spark Plugs The radiator on LH side can be removed prior to renewal the spark plugs See Maintenance Manual Line Maintena...

Page 120: ...nes to and from turbocharger specially close to the collar nut connections and the line support to frame for tight attachment CAUTION Check operating time of lubricant hoses Refer to section 4 Airworthiness Limitations Section See also Maintenance Manual Line Maintenance for ROTAX Engine Type 914 Series section 12 00 subsection 2 2 2 3 Annex E 7 4 2 2 Oil Level Check Oil specification see section ...

Page 121: ...th and open cap slowly Sudden opening of the cap would provoke exit of boiling coolant and in consequence scalds Coolant specification see section 3 4 14 7 4 3 2 Rinsing of Cooling System See Maintenance Manual Line Maintenance for ROTAX Engine Type 914 Series section 12 00 subsection 3 3 Annex E 7 4 3 3 Coolant Renewal Additionally to instructions of Maintenance Manual Line Maintenance for ROTAX ...

Page 122: ...2 in Check condition of support plate on lower engine mounting frame below engine and tight connection of bend to the support plate 7 4 5 3 Heat Insulation Check of Heat Insulation Tape on Exhaust Bends Check condition of glass fibre heat insulation tape on exhaust bends specially close to spring clamps Renew if fibre tape is brittle fibres fall off when touched holey or fray Check condition of sp...

Page 123: ...cess and remove the coarse filters 7 4 6 2 Fuel System in the Fuselage See also Maintenance Manual Line Maintenance for ROTAX Engine Type 914 Series section 12 00 subsection 2 3 Annex E Check condition and function of quick release couplings in supply lines Check condition routing sufficient supports clearance to moving components kinks tight fit of clamp connections of supply return and drain lin...

Page 124: ... lever on 115 spring on both carburetors must keep a small tension Check stop positions of 115 and idle via corresponding positions of both carburetor throttle valve levers Check of Trottle Lever Stops Adjust throttle lever to forward stop end of gate throttle valve lever on both carburetors must reach 115 stop Adjust throttle lever to aft idle stop throttle valve lever on both carburetors must re...

Page 125: ...st undergo a functional check after a failure during engine start To perform the following check remove instrument panel cover The module is mounted on the electronics CB plate on the RH side of the panel Correct function can be examined by means of two LED s mounted on the circuit board discernible through an opening in the module housing Disconnect the control line from the starter relay located...

Page 126: ...ion of camlock fasteners on upper centre fuselage fairing and engine cowlings Check tight connection of camlock fittings in the composite structure of fairing cowling and counter parts in fuselage Upper Centre Fuselage Fairing Check condition and proper fit of the upper fuselage fairing Check condition function and tight attachment of oil service access Engine cowlings Check condition and proper f...

Page 127: ... its subsidiary assemblies after an operational interruption may only be performed by the manufacturer or by a facility authorised by the manufacturer Balancing the variable pitch propeller or its assemblies may only be performed by the manufacturer or by an authorised and licensed FBO according to the specific instructions and using appropriate equipment Balancing weights have to be applied for s...

Page 128: ...secured to facilitate finding the original position NOTE A counter balancing weight washer may be attached to the inside of the fork by means of an M5 bolt This washer must be re installed at the same place on re assembly Loosen both bolts M6 with secure washers to separate the variable pitch mechanism from the hub centrepiece 18 Remove the variable pitch mechanism to the front Loosen the six M8 b...

Page 129: ...cond blade 1 Unscrew the union nut of the hollow axle using a flat size 30 nut wrench approx 4 5 mm 0 18 in thick while holding the hollow axle fast with a flat size 22 nut wrench approx 4 5 mm 0 18 in Do NOT unscrew the castellated nut 2 Twist the hollow axle in an anti clockwise direction until the spring is no longer pre loaded approx 1 turns and then press it out Make sure the blade does not d...

Page 130: ...of the propeller pitch e g to achieve correspondence between both propeller blades is accomplished by means of two adjustment screws 25 During adjustment the drive lever is only set loosely M5 screw and M8 nut are not fully tightened Tighten the M5 bolt and the M8 nut Tighten the adjustment screw and counter Check tightening torque of the M8 nut 20 Nm 14 7 lbf with a torque wrench Re check the set...

Page 131: ...his the propeller should be put in the cruise setting with the push button Maintaining this setting the contact bolts should be adjusted so that the contact screw just is in contact with the contact plate use an ohmmeter more than once Finally secure contact screw Adjusting the take off setting switch allow the elements to cool down and check if the pitch change mechanism is at the stop in the tak...

Page 132: ...iscs and observe rubber surface Removal of Drive Shaft The propeller shaft can be removed together with front gear and the propeller in one step Remove the propeller dome lift off left and right leg room coverings in the cockpit loosen clamping screw at the guide block of the propeller dome pull out locking screw with dome spring disconnect flexible hoses disconnect the antenna connection to trans...

Page 133: ... due to little oil vapour leakage through the shaft sealings is normal With front gear removed Check condition of front gear housing Check the front gear for leakage specially the screwing of both halves of the gear housing and the shaft sealings Check condition of the milled aluminium suspension cracks and its connection to the front gear Check condition and tight fit of the shock mount assemblie...

Page 134: ... components Operate propeller positioning several times from different starting points Check smooth operation and proper alignment of propeller in its end position Check spring retraction of the T handle and locking clip of the handle observe section 6 5 Lubrication Propeller Brake Check condition and proper installation of components Check smooth function of propeller brake handle and test brake ...

Page 135: ...tion of sprung linkage of the RH door Check cable mechanism of the LH door for condition and proper installation of cables springs pulleys and pulley guides and roller strut With the gear extended the closing cable must have a minimum pre load just without slack If required adjust the pre loading pressure spring of the closing cable Check clearance between tires and doors to be at least 10 mm 0 4 ...

Page 136: ...racted then disconnect the arm linking the operating cable to the left LG door take care that the cable and arm do not jam as the right leg is retracted Check if the leg contacts surrounding components Brake hose must have regular bends must not jam The stop switch must contact the centre of the landing gear tube Joint heads of the operating elbow lever must not be jammed Articulation between the ...

Page 137: ... N 22 5 to 45 lbf The landing gear legs must remain in the extended position function of spring clips on the elbow levers remounting of the elbow lever joints to the spindles landing gear switch DOWN move the spindles by means of the stop switches on the elbow levers until their relative position to the articulations is correct introduce latch lever and shift it into the operating position introdu...

Page 138: ...venting valve at the LH brake calliper Open venting valve at the RH brake calliper With continuous refilling of brake fluid to the brake fluid reservoir as required pump the brake fluid through the hydraulic brake system by operation of the RH brake lever until the brake fluid passing through the transparent flexible hose at the venting valve of the RH brake calliper is free of bubbles Close venti...

Page 139: ...ed brake lining can now be replaced by new ones 7 5 1 7 Removal and installation of landing gear legs Loosen all attachments to the frame Remove locking screws in front of the main bearings Push the bearing bolts out to the front and to the rear respectively Installation is carried out in the reverse order 7 5 2 Tailwheel Description See section 3 5 2 Lubrication See section 6 5 Support tail cone ...

Page 140: ...ing flap position 5 landing gear and air brakes retracted throttle 100 propeller pitch T O wings level not above 1000 m 3300 ft MSL Maintain a speed of 83 km h 45 kts Turn adjustment screw until the acoustic warning is actuated Check several times Second check configuration Change wing flap position to L and throttle to IDLE the warning must operate at 83 km h 3 km h 45 1 5 kts 7 6 2 Maintenance o...

Page 141: ...age drop of a charged main battery as new at approximately 15 C during starter operation 2 V For maintenance on the batteries please refer to the manufacturer s instructions Annex A WARNING During any maintenance on the electrical system should if battery energy is not required for test purposes the negative connection to the battery should be disconnected To remove the battery disconnect the nega...

Page 142: ... according to the equipment lists in section 9 are installed Only these devices have been approved during certification and a faultless operation with respect to certification requirements are granted by the airframe manufacturer Further more in countries other than Germany equipment to be installed and operated must be certified in the country in which the aircraft is registered Upon changing of ...

Page 143: ...98 Page 8 1 Amendment Nr 0 Date A4011121_B23 doc Doc No A40 11 121 8 List of Placards and their Positions This sections shows placards and their location Positions of Placards in the Cockpit Front Hier entsprechendes Bild mit geänderten Pos Nummern einkleben ...

Page 144: ...se Heavy Trim Tail Heavy ft MSL kts 10 000 139 13 000 132 16 500 125 19 500 118 26 000 105 33 000 93 39 500 81 Nationality and registration Fuel Press Aux Pump MAP TCU Ext Gen Int Gen L G Indicator Placards in the Cockpit Front L 10 5 0 5 10 4 1 2 3 5 6 7 8 Master Generator Land Gear Main Fuel Pumps Left Right Aux Fuel Pumps Left Right 9 ...

Page 145: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 8 3 Amendment Nr 0 Date A4011121_B23 doc Doc No A40 11 121 Placards in the Cockpit Front continued ...

Page 146: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 8 4 Amendment Nr 0 Date A4011121_B23 doc Doc No A40 11 121 Placards in the Cockpit Front continued ...

Page 147: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 8 5 Amendment Nr 0 Date A4011121_B23 doc Doc No A40 11 121 Positions of Placards in the Cockpit Rear ...

Page 148: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 8 6 Amendment Nr 0 Date A4011121_B23 doc Doc No A40 11 121 Placards in the Cockpit Rear ...

Page 149: ...Maintenance Manual STEMME S10 VT Date of Issue Jan 01 1998 Page 8 7 Amendment Nr 10 Date Dec 14 2001 A4011121_B23 doc Doc No A40 11 121 Fireproof Type Placard on Rear Cockpit Wall ...

Page 150: ...ng on the altitude up to 180 mph up to 160 kts up to 160 kts and vNE depending on the altitude Winter 7FMS4 TS10 210 19 up to 300 km h up to 300 km h and vNE depending on the altitude up to 180 mph up to 160 kts up to 160 kts and vNE depending on the altitude Altimeter Winter 4FGH10 TS10 220 46 up to 10 000 m up to 30 000 ft Winter 4FGH20 TS10 220 47 up to 10 000 m up to 30 000 ft Winter 4FGH40 TS...

Page 151: ...inter FSZM TS GW 1510 VDO 331 811 010 2 Oil pressure meter Oil temperature meter Filser SR004 10 bar 150 C Westach 2DA3 203KV 7 bar 150 C Fuel contents meter LH RH Filser SR002 Westach 2DA4 67 CHT meter Filser SR003 2 150 C Westach 2DA8 24 Volt ampere meter Westach 2DA10 78 30 0 30 A 7 17 V Four point seat belt Gadringer BaGu 5203 SchuGu 2700 40 070 32 40 071 05 Schroth Automatic Shoulder belt lef...

Page 152: ...eserved 9 3 Additional Equipment and Systems Different equipment and systems may be installed in the powered glider S10 VT which are not part of the minimum or supplementary equipment and which normally are not series standard Basically the cases Additional Equipment and Optional Systems have to be distinguished and treated differently 9 3 1 Additional Equipment In addition to the minimum and supp...

Page 153: ...rument panel due to its own chassis or due to a suitable installation frame TELEX Pro Com 4 Sigtronics SPA 400 TSO Flightcom 403 MC Flightcom ATC 2 Transponder various various all approved TSO ETSO equipment with 57 mm 2 in standard ring cutout or 159 mm 6 in standard rectangle cutout Contact TC holder before installation of any TSO ETSO equipment with different size design Encoder various various...

Page 154: ...R C Allen RCA15AK 2 Fire Warning System STEMME Series equipment Voltmeter Ammeter Filser SR001 Series equipment 9 3 2 Optional Systems Optional systems are not normally included in the Maintenance Manual To each of these systems delivered by STEMME a Service Bulletin approved by the LBA is assigned providing the information necessary for correct installation and inspection e g Serial No s Document...

Page 155: ...ight a c Precision protractor for propeller blade adjustment Torque wrench Gauge for moment of ignition Valve clearance gauge Sparking plug wrench Endoscope Micro meter Spring scale up to approx 250 N 56 lbf TCU Communication Program ROTAX Monitoring Kit refer to Maintenance Manual Heavy Maintenance for ROTAX Engine Types 912 and 914 Series section 76 00 subsection 3 1 1 Further tools and devices ...

Page 156: ...r indicated on the title page Procedural instruction Dynamic balancing of the STEMME S 10 powered glider propeller in the S10 V and S10 VT models A17 10AP V 2 E Minor repair to components of fibrous composite material a repair guide by the STEMME Company for the S10 Instructions for the maintenance of L Hotellier ball and swivel joints Maintenance instructions for equipment delivered by STEMME mus...

Page 157: ...us composite material a repair guide by the STEMME Company for the S10 Instructions for the maintenance of L Hotellier ball and swivel joints Maintenance instructions by STEMME as entered in the list below This list must comprise at least those Maintenance Instructions relating to the additional equipment installed refer to the record of accomplished SB s AD s under Annex B Maintenance Instr No Su...

Page 158: ...lletins Airworthiness Directives This Annex comprises The List of Airworthiness Directives and Service Bulletins issued by the manufacturer for the aircraft type STEMME S10 document no A31 10 000 The record of accomplished SB s AD s for this serial number All Service Bulletins already accomplished as well as those still to be accomplished ...

Page 159: ...s X last Certificate of Inspection for continued airworthiness Avionic X latest records of conformity inspection or inspection for continued airworthiness X latest records of Avionik Inspection or inspection for continued airworthiness Avionic X Release Certificate engine X Release Certificate propeller X Inspection Certificate for any instruments installed according to the equipment list except f...

Page 160: ... Issue Jan 01 1998 Page D Amendment Nr 0 Date A4011121_B23 doc Doc No A40 11 121 Annex D Maintenance and Inspection Forms This section provides patterns of maintenance and inspection forms relevant to maintenance according to sections 6 and 7 ...

Page 161: ...powered glider is performed The canopy has to be closed during weighing 5 If weight and moment arm of additionally installed or removed items is known exactly the new CG may be determined numerically see point 4 2 2 Overview of Component Weights and Weight Limits Component Weights from Separate Weighing kg lbs kg lbs Weight Limits kg lbs Central Wing Maximum All Up Weight incl Fuel 850 1874 Right ...

Page 162: ... on the powered glider Install Removal Item Weight m kg lbs Moment Arm x mm in Moment M mm kg in lbs Sum mzus Sum Mzus NOTE Count weight installed positive weights removed negative Count moment arms aft of datum positive in front of datum negative x m x M m S neu alt alt zus neu mm in xS _______________________ mm in 5 Definition of Minimum Load Required With Empty Weight determined kg lbs and the...

Page 163: ...l Surface Deflections Positive values indicate full control surface deflections downward or left negative Values indicate deflections upward or right Elevator Measuring point is trailing edge of inner rib of elevator 140 mm 5 51 in from hinge line Full Deflection 48 2 5 mm 1 89 0 08 0 2 in mm in 48 5 2 mm 1 89 0 2 0 08 in mm in Rudder Measuring point is lower rear corner of control surface 420 mm ...

Page 164: ...f the ground 25 5 8 N 5 6 1 1 1 8 lbf N lbf 4 Pilot Forces Following forces must be measured on ground Measuring points for airbrake and wing flap forces are the respective handles for down spring trim spring forces the uppermost finger notch of the control stick handle Airbrake over centred lock and unlock 150 50 N 34 11 lbf with 20 C N lbf with C Wing Flap Counter force in position L 125 25 N 28...

Page 165: ...t M F r Wherein F is the force measured at the trailing edge of the control surface and r is the horizontal distance between trailing edge and hinge axis F may be measured with a spring balance or another suitable scale with an error in measurement not exceeding 2 5 The friction of the hinge bearing should be less than 2 5 of the maximum permissible hinge moment If the detached control surface is ...

Page 166: ...____________ No Item or Inspection to be Performed Inspection Results Performed Checke d 1 Center of Gravity mm in Mass g dr and Radial Mass Moment g mm dr in 2 Needle Bearings Inner Rings and Needles 3 Balance Weight Washers Number and Type Units general Delete as applicable m g dr z mm in Jz g mm dr in x mm in y mm in Propeller Blade 1 blank 1 AP VB finished Propeller Blade 2 blank 1 AP VB _____...

Page 167: ...xial Position of Both Blades a at folding joint maximum 0 3 mm 0 012 in mm in b at Blade tips maximum 3 mm 0 12 in mm in 7 Propeller Fork Incidence Angle Blade 1 Blade 2 red Side a T O Setting Rated 3 18 5 10AP V Rated 2 30 5 11AP V b Cruise Setting Rated 3 6 10 10AP V Rated 3 54 10 11AP V 8 Static Return Force when Blade Rotated to Cruise Position Blade in 90 Position Measuring point on blade tip...

Page 168: ...ype 914 Series This Annex comprises the original Maintenance Manual Line Maintenance for ROTAX Engine Type 914 Series current issue As far as not stated differently in this Maintenance Manual of the powered glider S10 VT it is valid for the modified engine ROTAX 914 F2 S1 installed in the powered glider This Maintenance Manual is subject to changes by the manufacturer of the original engine ROTAX ...

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