STEMME S10 Maintenance Manual Download

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Summary of Contents for S10

Page 1: ... and conversion of technical data have been done by best knowledge and judgement In any case the original version in the German language is authoritative Model STEMME S 10 Serial number 10 Type Certificate EASA A 054 former LBA 846 Registration Non standard equipment or systems with effect to the contents of this manual if installed are entered in the table on page 1 Druck Info Datei enthält 64 Se...

Page 2: ...ual under the specified revision numbers the text passages relating to the standard version have been crossed out The necessary amendments to the text are described in further detail in the associated LBA approved Service Bulletins The procedure of amending the Manual in the case of installation of alternative equipment is described in further detail in the Service Bulletin A31 10 008 see Annex B ...

Page 3: ...s included in the text not applicable to the serial number concerned must be crossed out For further information please refer to Section 9 3 or to the Service Bulletin A31 10 008 The inspector certifies by his signature at the same time the correct transfer of the information specific to the serial number deletion of inapplicable text passages Am No Affected Sections removed Pages included Pages A...

Page 4: ...fig 6 3 a Titel 2 1 2 2 3 21 22 1 22 2 38 fig 6 3 a 1 fig 6 3 a 2 Nov 30 2007 13 0 4 2 3 21 22 1 22 2 2 3 21 22 1 22 2 Nov 24 2008 14 0 4 2 2 3 21 22 1 22 2 2 2 3 21 22 1 22 2 Feb 24 2010 15 0 5 2 2 3 23 29 2 2 3 23 29 June 07 2011 16 0 4 2 2 3 21 22 1 22 2 2 2 3 21 22 1 22 2 April 04 2012 17 0 4 2 2 3 21 22 1 22 2 2 2 3 21 22 1 22 2 Aug 13 2012 18 0 4 5 2 2 3 4 5 21 22 1 22 2 23 30 2 2 3 4 5 21 2...

Page 5: ... 3 25 18 Oct 15 2012 5 3 26 18 Oct 15 2012 5 3 27 18 Oct 15 2012 5 3 28 18 Oct 15 2012 Section Page Am No Date 5 3 29 18 Oct 15 2012 5 4 30 18 Oct 15 2012 6 1 6 3 31 Oct 1 1990 6 4 6 5 32 Oct 1 1990 6 6 33 9 April 19 1999 res 34 Oct 1 1990 7 1 7 3 35 Oct 1 1990 7 3 36 11 May 25 2005 7 3 37 Oct 1 1990 7 3 7 4 38 12 Nov 30 2007 7 4 39 Oct 1 1990 7 4 40 1 19 Jan 10 2014 7 4 40 2 19 Jan 10 2014 7 4 7 ...

Page 6: ...ller 16 3 3 11 Drive train System 16 3 4 Landing Gear 17 3 4 1 Main Landing Gear figure 3 4 1 a 17 3 4 2 Tail Wheel 18 3 5 Flight Instruments Pressure System figure 3 5 a 18 3 6 Electric System figures 3 6 a to 3 6 e 18 3 7 Communication and Navigation Equipment 19 3 8 Oxygen Equipment 19 4 Airworthiness Limitations Section 21 5 Time Limits Maintenance Checks 23 5 1 Life Limited Components 23 5 2 ...

Page 7: ...35 7 1 2 Fuselage and Cockpit 35 7 1 3 Tail Units 35 7 2 Control System 35 7 3 Powerplant 35 7 3 1 Engine 35 7 3 2 Fuel System 36 7 3 3 Oil System 36 7 3 4 Cooling System 36 7 3 5 Induction System 36 7 3 6 Controls Instruments 37 7 3 7 Fire Protection 37 7 3 8 Engine Cowlings 37 7 3 9 Propeller 37 7 3 10 Drivetrain System 38 7 4 Landing Gear 38 7 4 1 Main Landing Gear 38 7 4 2 Tail Wheel 41 7 5 Fl...

Page 8: ...Maintenance Manual STEMME S 10 Date of Issue Oct 01 1990 page 6 Amendment No Date A4010021_B19 doc Doc No A40 10 021 intentionally left blank ...

Page 9: ...powered glider STEMME S10 2 The Flight Manual for the motorglider STEMME S10 3 The Operating and Maintenance Manual Limbach L2400 and Series 4 Maintenance instructions for the L Hotellier ball and swivel joints in Appendix to this Maintenance Manual 5 Manufacturer s documents referring to the equipment listed in the equipment list of the corresponding S N The amount of maintenance work depends irr...

Page 10: ...Maintenance Manual STEMME S10 Date of Issue Oct 01 1990 Page 8 Amendment No Date A4010021_B19 doc Doc No A40 10 021 intentionally left blank ...

Page 11: ... gear is electrically extended and retracted and is equipped with hydraulic disc brakes The tail wheel is steered with the pedals The engine is located in the fuselage in a central steel tube framework near the aeroplane centre of gravity The engine power is transmitted via a composite material shaft and a transmission gear to an articulated propeller in the fuselage nose In soaring flight the pro...

Page 12: ...69 kW propeller STEMME 10 AP N diameter 1 61 m gear transmission ratio i 1 18 Masses see also figure 14 3 a maximum allowable mass 850 kg empty mass 640 kg maximum mass of non structural parts 570 kg total useful load occupants fuel baggage 210 kg mass of ballast For pilot masses between 55 and 70 kg including parachute the defined ballast mass of 6 kg must be attached to the right hand rudder ped...

Page 13: ...Maintenance Manual STEMME S10 Date of Issue Oct 01 1990 Page 11 Amendment No Date A4010021_B19 doc Doc No A40 10 021 intentionally left blank ...

Page 14: ...ling free access to the wing attachment control system joints and the mixed aileron flap controls Detachment of wing from the fuselage upwards Flaps over the total span of the central wing ailerons over the total span of outboard wings Articulation of flaps and ailerons on the lower side Symmetrical and asymmetrical cross connection of flap and aileron controls Two storied Schempp Hirth air brakes...

Page 15: ...ll rods to the end of the tail boom and then straight up to the elevator fitting In the tail boom the push pull rod is several times supported by linear motion ball bearings The adjustable longitudinal control stops are in the middle of the connection tube beneath the right control system cover in the cockpit Longitudinal Trim figure 3 2 a The powered sailplane is trimmed by means of a slidable sp...

Page 16: ...l rods in the wing are supported by linear motion ball bearings The fully retracted position of the airbrakes is barred by over centre locking of the elbow lever The locked position can be adjusted by a stop screw at the elbow lever The fully extended position is determined by a fix rubber stop which one end of the driving lever butts upon when this position is reached Directional Control From the...

Page 17: ...framework The connection to the fittings on the engine is realised by means of flexible hoses with metal reinforcement and a fire resistant sheathing 3 3 4 Cooling System The engine is cooled by ram air The air inlets are to the left and to the right side of the central fuselage cowlings From these inlets the cooling air flows directly to the cylinder heads A minor portion of the cooling air is bl...

Page 18: ...ted to each other and to the fuselage front section and to the tail boom by means of Camloc snap fasteners 3 3 10 Propeller The articulated propeller consists of a central part and two propeller blades hinged to this central part The articulation axle is aligned so that the propeller blades are movable in the plane of rotation of the propeller When the propeller is not running the blades are folde...

Page 19: ...ndle drives The wheel well is covered by two landing gear doors the right hand door is coupled via a spring element directly to the right gear leg The left hand door is closed via a bowden cable which is operated also by the right landing gear during the last part of its track Electric landing gear warning acoustic warning activated by switches on the air brakes control shaft beneath the left stic...

Page 20: ...lled behind the firewall All current circuits and electric instruments are protected by fuses or circuit breakers respectively Master Switch cuts all current sources from the main bus In case of failure of the main current circuit the avionics instruments are automatically switched over to the auxiliary battery if installed Subordinate Switches Engine master switch to switch ON OFF all electric ap...

Page 21: ...approval may be installed The mass limits and the centre of gravity range for equipment in the instrument board as well as the limits of current consumption are to be adhered to Locations of the antennas The radio antenna is installed in the rudder The VOR antenna is installed on the cockpit floor armada shell The transponder antenna is installed in the tail boom 3 8 Oxygen Equipment One or maximu...

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Page 25: ...irst 50 operating hours and every further 50 operating hours Type 2 after the first 100 operating hours and every further 100 operating hours Type 3 annually The items to be checked are given in the following Inspection Lists for Periodical Checks In addition special inspections which may be prescribed by the manufacturer or by the airworthiness authority are to be performed in accordance with the...

Page 26: ...e to the connector X X X 8 Check and maintain the L Hotellier quik release joints of the aileron push pull rods at the inner to outer wing attachements according to the manufacturer instructions ref to Appendix A Is a spring cotter fastened unloosable to the connector X X X 9 Remove fairings on the flap and aileron link rods and inspect the bellcrank levers and the other parts of the flap and aile...

Page 27: ...ing area for embrittlement or crack initiation axial and peripherical direction check fork terminals for cracks particulary the fork terminals where the root turns into the webs X X 8 Inspect condition and attachment of instruments switches circuit breakers fuses and wiring X X X X 9 Flexible hoses of ventilation heating and instruments Check condition and installation X X 10 Inspect and if necess...

Page 28: ...ge 1 Check vertical stabiliser VS and rudder surface for damage and cracks look out for signs of hidden structural damage check nationality and registration marks renew if necessary check drain outlets X X 2 Inspect rudder supports for firm attachment check especially the lower support for cracks and deformation Check play of the hinges Check split pin lock X X X 3 Inspect connection of the antenn...

Page 29: ...X X 10 Throttle choke control make sure that the extreme positions in the carburettors are achieved Check attachment of bowden cables and sleeves Check condition of the return springs on the carburettors X X X 11 Check powerplant instruments for improper functioning X X X 12 Check fire wall steel sheets for improper condition and looseness X X X 5 3 8 Propeller The hours given in this list are eng...

Page 30: ...eck of trailing arm link suspension X X 6 Wheel bearings check for ease of operation and slackness X X X 7 Inspect brake master and wheel cylinders Check brake hoses and pipes for proper guidance chafe marks and leakage X X X 8 Inspect brake discs and brake linings min 06 in 1 5 mm X X 9 Check brake fluid level replace fluid once in two years X X X 10 Check efficiency of brakes X X X X 11 Clean an...

Page 31: ... main battery for poor condition check drop in voltage during starter operation For battery maintenance refer to manufacturer instructions X 5 3 14 Radio and Navigation Equipment 1 Inspect radio and navigation equipment refer to the Equipment List for poor condition improper operation and if applicable service life limits X 2 Check each antenna installed X 5 3 15 Oxygen System 1 Inspect oxygen sys...

Page 32: ... be carried out by a knowledgeable person or in case of doubt concerning the extent of damage by an inspector holding appropriate rating The inspection program is to be requested from the manufacturer 5 4 2 Inspection following an Impact to the rotating Propeller Following an inpact to the rotating propeller caused by touching the ground or obstacles the propulsion system is to be subjected to a c...

Page 33: ...ness with a felt layer of 6 to 8 in 15 to 20 mm thickness or something adequate is to be used The support under the plywood sheet center must be flexible so that the wing rests evenly upon the plywood sheet The stands must be capable of reliably carriing the aircraft mass and be sufficiently stable The slabs to support the wing must be non skid Warning Ensure that the wing stands are evenly lifted...

Page 34: ... tolerances are exceeded the manufacturer is to be contacted The allowable masses and moments of the control surfaces are stated in fig 6 4 2 a Masses and Moments of Control Surfaces The sheet also contains the procedures to determine the moments 6 4 3 Slackness of Control System Bearings For each control surface a maximum slackness between the cockpit control and control surface is permitted It i...

Page 35: ...he splined joint is protected by a coating on delivery and is thus maintenance free Do not grease Canopy Lock Always keep well greased MoS2 free lubricant since rod bearing within the canopy frame is made of brass 6 6 Tightening Moments for Screw Joints These data apply to standard screw joints Differing data however given for the assemblies e g propeller and engine are to be adhered to in any cas...

Page 36: ...Maintenance Manual STEMME S10 Date of Issue Oct 01 1990 page 34 Amendment No Date A4010021_B19 doc Doc No A40 10 021 intentionally left blank ...

Page 37: ... jettisoning procedure in accordance with the instructions in the Flight Manual The canopy is to be checked smoothly by two assistants standing in front of the aircraft to the left and to the right Up to S N 19 the reinstallation of the canopy is to be performed by means of a special tool to facilitate the compression of the gas spring in the canopy hinge For later S N the installation procedure i...

Page 38: ...ions A indication for high wear and the necessary replacement are cracks in the outer surface For replacement of the fuel hoses after expiration of the allowable time in service remove or lift the upper parts of the fire wall 7 3 3 Oil System Warning When tightening the screw joints of the oil hose fittings retain the oil tubes to avoid twisting and thus shutting off of the flexible hoses in the f...

Page 39: ...ission gear mounting maximum difference of 0 012 in 0 3 mm between both joints Track of propeller blade tips maximum difference of 0 12 in 3 mm between the blades Play of blade tips in flight direction maximum of 0 16 in 4 mm total Unbalance Basic Balancing by the manufacturer Precission balancing by a knowledgeable person by adjusting the compensation masses at the blade root by a maximum of 1 13...

Page 40: ...ont Disconnect the control cable of the propeller brake on the transmission gear Loosen four fastening screws on the transmission gear supports loosen balancing spring on top of the transmission gear Pull out transmission gear with propeller shaft The engine side clutch remains on the engine Removal by loosening of the attachment screws on the engine flange Installation In the opposite order as re...

Page 41: ...peration of gear doors Fit of gear doors Clearance between gear doors and wheels 0 4 to 0 6 in 10 15 mm retract landing gear with the upper cowling of the central fuselage mounted Check clearance between the drive spindles and the cowling the bowden cables of the emergency release system may not be buckled or get stuck endurance test retract and extend the landing gear ten times at intervals of 2 ...

Page 42: ...r inspection A clear pressure point has to identifiable during operation Otherwise repeat ventilation procedure Reinstall brake lever if applicable Remove transparent flexible hose and check final brake fluid level at brake fluid reservoir Perform functional check of brake system with pre flight check according Flight Manual Ch 4 Adjustment and Ventilation of the Wheel Brake System Hydromechanical...

Page 43: ...0 2014 A4010021_B19 doc Doc No A40 10 021 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 ...

Page 44: ...ng is actuated In flight calibration Fly with a center of gravity position in the rear range with a total mass of 1874 lbs 850 kg Configuration for the calibration Wing flap position L landing gear and air brakes retracted engine running at 3000 rpm horizontal flight not above 3300 ft 1000 m MSL Fly at a speed of 45 kts 83 km h Turn adjustment screw until the acoustic warning is actuated Recheck s...

Page 45: ... in accordance with the instructions by the manufacturer see Equipment List in this case service records 7 8 Oxygen Equipment Oxygen System Mounting Check the oxygen system mounting if installed as optional equipment for condition and tight fit of components Oxygen System Perform maintenance on the oxygen system in accordance with the instructions of the manufacturer see Annex A ...

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Page 54: ...s Airpath C2300 PZL B 13 FD19 77 Ludolph FK16 10 410 3 Ludolph FK5 10 410 1 Hamilton HI400 TSO C7c Type 1 Presesion Aviation Inc PAI 700 TSO Stall Warning System Westerboer Speed Control Revolution Counter VDO 333 230 009 1 up to 4000 min 1 Engine hour meter Winter FSZM TS GW 1510 VDO 331 811 010 2 Oil pressure meter VDO 350 271 031 7 up to 10 bar Oil temp meter VDO 310 274 082 1 up to 150 C Fuel ...

Page 55: ...andard text of the Maintenance Manual Here the rule applies that associated information is added to the corresponding passage of the standard text with the original text if any and the amended text appearing in square brackets each A reference number following the closed bracket is identical with the current revision number the letter following the reference number indicates whether the text passa...

Page 56: ...ent 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 al...

Page 57: ...ame Collision warning system various various VHF NAV VOR various various all approved TSO ETSO equipment with 57 mm 2 in standard ring cutout Contact TC holder before installation of any TSO ETSO equipment with different size design Horizon various various all approved TSO ETSO equipment which is fix mountable to the instrument panel due to its own chassis or due to a suitable installation frame T...

Page 58: ...supplementary procedures If installation requires additional instructions an installation instruction is provided If flight operation requires additional information supplements to the Flight Manual are provided Information required for maintained airworthiness are published as maintenance instructions to be inserted in the Annex A of this Maintenance Manual and added to the list of maintenance in...

Page 59: ...s Torque wrench Gauge for moment of ignition Valve clearance gauge Sparking plug wrench chucking appliance for wing flap relief spring P N 00SW RMF 11 List of Maintenance Documents for Parts being approved independently from the Aircraft Operating and Maintenance Manual Limbach L 2400 and series flight engine for powered sailplanes and very light aircraft ...

Page 60: ...ly 1 1993 A4010021_B19 doc Doc No A40 10 021 12 Figures referring to the previous Sections The number of an illustration corresponds to the number of the section containing the first reference to the illustration If several illustrations relate to one section they are marked by a b etc ...

Page 61: ...Maintenance Manual STEMME S10 Date of Issue Oct 1 1990 Fig 2 a Amendment No Date A4010021_B19 doc Doc No A40 10 021 Fig 2 a 3 View Plan STEMME S10 ...

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Page 78: ...losed during weighing 1 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 Hand Outer Wing Maximum Weight of Non Lifting Pa...

Page 79: ...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 neu S x mm in 5 Definition of Minimum Load Required With Empty Weight determined kg lbs and the empty weight CG aft of datum mm in the Minimum Load Required is kg lbs Units cross ou...

Page 80: ...9 656 1446 2 506 19 92 523 20 59 658 1450 6 504 19 84 522 20 55 660 1455 1 503 19 80 522 20 55 662 1459 5 502 19 76 522 20 55 664 1463 9 501 19 72 522 20 55 666 1468 3 499 19 65 521 20 51 668 1472 7 498 19 61 521 20 51 670 1477 1 497 19 57 521 20 51 672 1481 5 496 19 53 520 20 47 674 1485 9 495 19 49 520 20 47 676 1490 3 493 19 41 520 20 47 678 1494 7 492 19 37 519 20 43 680 1499 1 491 19 33 519 2...

Page 81: ...istance to hinge axis 420 mm left 220 15 mm mm right 220 15 mm mm Wing Flaps and Ailerons Flap lever position Stick position Measuring points aileron inner end rib of the control suface Distance to hinge axis 163 mm wing flap inner end rib of the control suface Distance to hinge axis 175 mm left ail mm left flap mm right flap mm right ail mm 10 neutral 31 4 31 4 5 neutral 15 4 15 4 0 left neutral ...

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Page 84: ...mponents of fibrous composite material a repair guide by the STEMME Company for the S10 Information on service actions for UP Vorgelat T30 UP Vorgelat T35 a guide to the preventive care of aircraft surfaces by MGS Scheuffler 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 M...

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Page 88: ...ECK OF THE LINK BETWEEN DRIVE ROD AND SWIVEL VERIFICATION DE LA LIAISON ENTRE LA COMMANDE ET L EMBOUT 2 7 SWIVEL ASSY OPERATION CHECK VERIFICATION DU FONCTIONNEMENT DE L EMBOUT ASSEMBLE INSTRUCTION FOR THE MAINTENANCE OF L HOTELLIER BALL AND SWIVEL JOINTS INSTRUCTIONS DE MAINTENANCE DES EMBOUTS ET ROTULES L HOTELLIER APPROBATION APPROVAL REV DATE OBJET DE LA REVISION REASON FOR REVISION REDACTEUR ...

Page 89: ...nimum Il est donc indispensable de lubrifier l ensemble rotule embout Cette lubrification doit être réalisée après nettoyage et avant tout assemblage à l aide d une graisse non figeant à froid EXEMPLE LMX GREASE CASTROL caractéristiques NLGI 2 Viscosité 180 cSt plage d utilisation 30 C 150 C Il est impératif de vérifier après chaque mise en place que la connexion de la rotule dans l embout est réa...

Page 90: ...e dessus 2 3 BALL THREAD CHECK VERIFICATION DE L ETAT DU FILETAGE DE LA ROTULE No thread damage is acceptable During reassembly the collar must be perfectly set on its base It is mandatory to fix the ball in position with an adequate locking device Aucun filet ne doit être endommagé Au remontage la collerette doit venir parfaitement en appui de son support Il est indispensable d assurer une immobi...

Page 91: ...requirement is to verify the efficiency of the automatic take up clearance Ce dépassement doit demeurer 2 mm Le but de cette mesure est de vérifier l efficacité du rattrapage automatique de jeu For the light serial swivel joints verify that the screw is not to the extreme position in his oblong groove side ball joint Pour les embouts série légère vérifier que la vis n est pas en butée dans sa rain...

Page 92: ...er reason is acceptable If after these verifications one of the above checks is out of tolerance it is mandatory to replace both ball and swivel Nevertheless it is mandatory to replace this assembly every 10 years or every 3000 flight hours whichever comes first Il ne doit exister aucun blocage dû à l oxydation ou autre du siège et du verrou Si à l issue de ces vérifications un des 7 points ci des...

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Page 94: ...Service Bulletins 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 95: ...X last Certificate of Inspection for Continued Airworthiness X latest records of production inspection or inspection for continued airworthiness X Inspection Certificate engine X Inspection Certificate propeller X Inspection Certificate for any instruments installed according to the equipment list except for engine instruments and other instruments not subject to certification X log sheets for eng...

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