Schempp-Hirth Flugzeugbau ARCUS M, Flight Manual

Page 1: ...Registr No Date of issue O c t o b e r 2 0 1 1 Pages as indicated by appr are approved by This powered sailplane is to be operated in compliance with information and limitations contained herein Appr...

Page 2: ...g data must be recorded in the following table and in the case of approved sections be en dorsed by the responsible airworthiness authority The new or amended text in the revised page will be indicate...

Page 3: ...Lfd Nr der Berichtigung Abschnitt Seiten Datum der Berichtigung Bezug Datum der Anerkennung Datum der Ein arbeitung Zeichen Unter schrift Revision No Affected section Affected page Date of issue Refer...

Page 4: ...cus M FLUGHANDBUCH FLIGHT MANUAL 0 2 Verzeichnis der Seiten List of affected pages Abschnitt Affected section Seite Affected pages Ausgabe Datum Date of issue Bezug Reference 0 0 1 1 0 1 2 0 2 1 0 2 2...

Page 5: ...2 2 anerk 2 3 anerk 2 4 anerk 2 5 anerk 2 6 anerk 2 7 anerk 2 8 anerk 2 9 anerk 2 10 anerk 2 11 anerk 2 12 1 anerk 2 12 2 anerk 2 13 anerk 2 14 anerk 2 15 Oktober 2011 Oktober 2011 Oktober 2011 Oktob...

Page 6: ...1 anerk 4 2 1 2 anerk 4 2 1 3 anerk 4 2 2 1 anerk 4 2 2 2 anerk 4 2 2 3 anerk 4 2 2 4 anerk 4 2 2 5 anerk 4 2 2 6 anerk 4 3 1 anerk 4 3 2 anerk 4 3 3 anerk 4 3 4 anerk 4 3 5 anerk 4 4 Oktober 2011 Ok...

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Page 8: ...1 5 1 2 anerk 5 2 1 anerk 5 2 2 anerk 5 2 3 anerk 5 2 4 5 3 1 5 3 2 1 5 3 2 2 5 3 2 3 5 3 3 6 1 1 6 1 2 6 2 1 6 2 2 6 2 3 6 2 4 6 2 5 6 2 6 6 2 7 6 2 8 Oktober 2011 Oktober 2011 Oktober 2011 Oktober 2...

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Page 10: ...ges Ausgabe Datum Date of issue Bezug Reference 7 7 4 7 5 7 6 7 7 7 8 7 9 1 7 9 2 7 9 3 7 10 7 11 1 7 11 2 7 11 3 7 12 1 7 12 2 7 12 4 7 13 1 7 13 2 Oktober 2011 Oktober 2011 Oktober 2011 Oktober 2011...

Page 11: ...t of affected pages Abschnitt Affected section Seite Affected pages Ausgabe Datum Date of issue Bezug Reference 8 9 8 1 1 8 1 2 8 2 1 8 2 2 8 3 8 4 8 5 1 8 5 2 9 1 1 9 1 2 9 2 Oktober 2011 Oktober 201...

Page 12: ...an approved section Emergency procedures 3 an approved section Normal procedures 4 an approved section Performance 5 a partly approved section Weight balance 6 a non approved section Powered sailplan...

Page 13: ...LUGZEUGBAU GmbH KIRCHHEIM TECK Arcus M FLIGHT MANUAL Section 1 1 General 1 1 Introduction 1 2 Certification basis 1 3 Warnings cautions and notes 1 4 Descriptive data 1 5 Three side view October 2011...

Page 14: ...sailplane has been prepared to provide pilots and instructors with information for the safe and efficient operation of the Arcus M This manual includes the material required to be furnished to the pil...

Page 15: ...as been approved by the EASA in compliance with CS 22 effective on November 14th 2003 The Type Certificate is No EASA A 532 and was issued on XX XX XXXX Category of Airworthiness UTILITY Noise Certifi...

Page 16: ...t the non observation of the corresponding procedure leads to an immediate or important degradation of the flight safety CAUTION means that the non observation of the corresponding procedure leads to...

Page 17: ...em seats The one piece canopy hinges sideways and opens to the right For high energy absorption the cockpit region is constructed as an aramid carbon fibre laminate which is reinforced by a steel tube...

Page 18: ...ngine bay To stop the power plant turn off the ignition and reduce the airspeed After turning off the ignition the retraction process is conducted automatically by the engine control unit MCU II With...

Page 19: ...m 3 28 ft Weight mass Empty mass from approx 530 kg 1169 lb Maximum all up mass 800 kg 1764 lb 38 5 51 3 kg m Wing loading 7 9 10 5 lb ft Engine Model SOLO 2625 02 i Manufacturer Fa Solo Kleinmotoren...

Page 20: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Arcus M FLIGHT MANUAL 1 5 Three side view October 2011 Revision 1 5...

Page 21: ...tor markings 2 4 Power plant fuel and oil 2 5 Power plant instrument markings 2 6 Weights masses 2 7 Center of gravity 2 8 Approved maneuvers 2 9 Maneuvering load factors 2 10 Flight crew 2 11 Kinds o...

Page 22: ...ction 2 includes operating limitations instrument markings and basic placards necessary for safely operating the powered sailplane its standard systems and standard equipment The limitations included...

Page 23: ...et in lee wave rotors thunderclouds etc VA Maneuvering speed 180 km h 97 kts 112 mph Do not make full or abrupt control movements above this speed as the aircraft structure might get overstressed VFE...

Page 24: ...tended 180 km h 97 kt 112 mph Do not exceed this speed with propeller extended VPOmax Maximum speed for extending retracting the propeller 120 km h 65 kt 75 mph Do not extend retract the propeller out...

Page 25: ...ositive Green arc 96 180 km h 52 97 kts 60 112 mph Normal operating range lower limit is the speed 1 1VS1 at maximum mass c g at the most for ward position and flaps at the neutral 0 position upper li...

Page 26: ...il Castrol ACT EVO Propeller manufacturer Technoflug Leichtflugzeugbau GmbH D 78713 Schramberg Germany Propeller model KS 1G 160 R 120 or Propeller manufacuter Binder Motorenbau GmbH D 97645 Ostheim v...

Page 27: ...Normal Range Caution Range Maximum Limit Tachometer RPM Indicator min 1 Signal green yellow red Range 2500 6600 6600 6700 6700 5 min 6600 Coolant Liquid Temperature Indicator C Signal Range 25 115 115...

Page 28: ...4 lb Maximum permitted take off and landing weight mass w i t h o u t water ballast Power plant installed 785 kg 1731 lb Power plant removed 765 kg 1687 lb Maximum permitted weight mass of all non lif...

Page 29: ...tum power plant removed 100 mm 3 94 in aft of datum plane power plant installed Maximum rearward c g position 290 mm 11 42 in aft of datum plane It is extremely important that the maximum rearward c g...

Page 30: ...hing The following aerobatic manoeuvres are only permitted without wing water ballast up to a maximum all up mass of 690 kg 1521 lb with power plant removed a inside loops b stalled turns c lazy eight...

Page 31: ...llowing manoeuvring load factors must not be exceeded a With airbrakes locked and at VA 180 km h 97 kts 112 mph n 5 3 n 2 65 With airbrakes locked and at VNE 280 km h 151 kts 174 mph n 4 0 n 1 5 b Wit...

Page 32: ...ot in command in compliance with the following requirements All necessary control elements and instruments including engine control unit must be installed for the rear seat The priority selector switc...

Page 33: ...ZEUGBAU GmbH KIRCHHEIM TECK Arcus M FLIGHT MANUAL 2 11 Kinds of operation With the prescribed minimum equipment installed see page 2 12 the Arcus M is approved for VFR flying in daytime October 2011 R...

Page 34: ...T with sensor when flying with water ballast red line at 2 C 35 6 F 1 Magnetic compass 1 Engine control unit MCU II indicating RPM Coolant liquid temperature C Fuel quantity Liter Engine time Warning...

Page 35: ...ter 1 VHF Transceiver NOTE From experience gained to date it appears that the airspeed indicator system installed remains fully operational when flying in clouds Recommended additional equipment for c...

Page 36: ...eller Maximum towing speed 180 km h 97 kts 112 mph Weak link in tow rope max 850 daN 1911 lb Minimum length of tow rope 30 m 98 ft Tow rope material Hemp or Nylon Winch launch propeller retracted Only...

Page 37: ...lplane is extended by another 3000 hours to a total of 9000 hours first step The afore said inspection program must be repeated when the sailplane or the powered sailplane has reached a service time o...

Page 38: ...frame C1 C2 1 batt in fin F1 front seat load rear seat load LOAD ON THE SEATS crew incl parachutes 70 kg 154 lb Maximum cockpit load load on both seats may not be exceeded For seat loads below the pl...

Page 39: ...GHT MANUAL Section 3 3 Emergency procedures 3 1 Introduction 3 2 Canopy jettisoning 3 3 Bailing out 3 4 Stall recovery 3 5 Spin recovery 3 6 Spiral dive recovery 3 7 Engine failure carburettor icing 3...

Page 40: ...MANUAL 3 Emergency procedures 3 1 Introduction Section 3 provides check lists and amplifies procedures for coping with emergencies that may occur Emergency situations can be minimized by proper pre fl...

Page 41: ...py is to be jettisoned as follows Swing b a c k one of the red locking levers provided on the left side of the canopy frame up to the stop approx 90 and swing canopy sideways fully open The canopy wil...

Page 42: ...e person in the front seat should bend his upper body slightly forward grab the canopy coaming frame of the fuselage with both hands and lift himself up The instrument panel is pushed up by the legs T...

Page 43: ...ron b Propeller extended With the power plant extended there are no significant differences in the stall behaviour but the turbulent airflow produced by the propeller superimposes any vibration in the...

Page 44: ...ed for that flap setting is not exceeded It is recommended for positive flap settings to change the flap setting to 0 during spin recoveries With the center of gravity in the foremost position a stead...

Page 45: ...a rapid increase in speed and acceleration Recovery from a spiral dive is achieved by easing the control stick forward and applying opposite rudder and aileron WARNING When pulling out of a dive the...

Page 46: ...of the selected landing procedure is improved the propeller should at least be partly retracted regardless of the position of the prop blades Ignition OFF and press manual control switch retraction re...

Page 47: ...ise Pull up with about 2g und reduce speed to approx 95 km h 51 kt 59 mph Maintain this speed until the engine has definitely fired The loss of height from the moment of acceleration to the point wher...

Page 48: ...l The engine SOLO 2625 02i is developed with a redundancy system which has to be manually activated if the normal engine control system breaks down This system consists of a simple electronic device p...

Page 49: ...ve ground strap to proper terminal of an external 12 V power source then clamp power strap to positive terminal Thereafter follow normal starting procedure with master switch ON Caution When connectin...

Page 50: ...le fully If the engine stops master switch at OFF Leave propeller in extended position This sequence should be followed if possible a on the ground b on take off c in flight WARNING Discontinue flight...

Page 51: ...vator control is more serious The pilot however should take into consideration that the powered sailplane is still controllable to at least some extent by using its flaps for longitudinal controls Fla...

Page 52: ...the powered sailplane overshooting the boundary of the landing field in mind a decision whether or not to initiate a controlled ground loop should be made at least 40 m 131 ft away from the boundary I...

Page 53: ...spections a Daily inspection b Inspection after reinstalling the power plant 4 4 Pre flight inspection 4 5 Normal procedures and recommended speed 4 5 1 Methods of launching 4 5 2 Take off and climb 4...

Page 54: ...oduction Normal procedures associated with optional equipment are found in section 9 This section provides checklists and amplified procedures for conducting the daily and pre flight inspection Furthe...

Page 55: ...ry tilt the fuselage or move the wing gently up and down to help it home Check that the angular levers on the wing root rib are properly inserted into their corresponding funnels on the fuselage Push...

Page 56: ...ent fitting Remove rigging tool locating pin must not protrude in front of the leading edge of the fin Check whether the elevator actuating pins are really located by moving the elevator and check tha...

Page 57: ...n Horizontal tailplane Using the threaded rigging tool pull out the front tailplane attachment pin lift the stabilizer leading edge slightly and pull the tailplane forward and off Main wing panels Unl...

Page 58: ...de of the vertical stabilizer is not blocked While refuelling the fuselage and or the wing tank s monitor the fuel level of the expansion reservoir in the baggage compartment The fuselage tank is comp...

Page 59: ...mpletely filled as soon as the fuel level in the expansion reservoir is rising The vent lines of the wing tank s are equipped with a pressure relief valve Thus under normal conditions bleeding of fuel...

Page 60: ...espective wing tank with the connections in the fuselage Connect the external fuel hose to the respective fitting in the fuselage see sketch on page 4 2 2 6 Place the other end of the external fuel ho...

Page 61: ...ground with main and tail wheel wings are levelled fuselage tank is completely filled power plant is retracted limit switch for engine retracted active Scroll through the display of the engine control...

Page 62: ...elage tank to select this menu item Subsequently the total amount of fuel in the wing tank s and the fuselage tank can be entered by further pressing the menu button If the menu button isn t pressed f...

Page 63: ...IM TECK Arcus M FLUGHANDBUCH Installed Refueling System Expansion reservoir in baggage compartment vent line wing tank fuel line wing tank On OFF switch for installed fuel pump Quick disconnect coupli...

Page 64: ...d or carried out carelessly 9 1 2 3 4 5 6 7 8 When walking around the Arcus M check all surfaces for paint cracks dents and unevenness In case of doubt ask an expert for advice 1 a Open canopy b Check...

Page 65: ...4 0 bar 57 psi j Check tow release mechanism s for proper condition and function 2 a Check upper and lower wing surface for damage b Clean and grease water ballast dump valves if necessary c Check win...

Page 66: ...ks check metal parts especially at the welding joints g Check all components lines hoses pipes and wires etc for chafing marks h Check pylon arresting wire and its attachment for proper function i Che...

Page 67: ...tly into the probe the variometer s connected should read climb c Check that the fin mounted Pitot tube is clear d Check that the opening for the fuel tank vent line at the upper end of the fin is cle...

Page 68: ...dicators must register After heavy landings or after the powered sailplane has been subjected to excessive loads the resonant wing vibration frequency should be checked its value to be extracted from...

Page 69: ...O Airbrakes checked and locked O All control surfaces checked with assistant for full and free movement in correct sense O Trim correctly set O Flaps set for take off O Canopy closed and locked CHECK...

Page 70: ...e is an increase of the lift generated on the downwind wing from the tug s prop wake which drifts with the wind Therefore it may be necessary to hold downwind aileron to start For intermediate to forw...

Page 71: ...an be chosen so that pleasant high control forces can be adjusted with the trim 1 1 1 2 1 1 2 1 1 Only small control surface deflections are normally necessary to keep position behind the tug In gusty...

Page 72: ...rmal there is no tendency to veer off or to climb excessively steeply on leaving the ground Depending on the load on the seats the Arcus M is lifted off with the control stick pushed slightly forward...

Page 73: ...the release height gained is less than 300 m 984 ft In case of doubt reduce the all up mass WARNING It is explicitly advised against winch launching with a tail wind CAUTION Prior to launching by winc...

Page 74: ...er button O Set throttle as required Ignition circuit check o Warm up engine CHT ca 40 C 104 F o Set rev to 2500 through 3000 RPM o Check both ignition circuits rev hast o drop by 50 to 100 RPM o Afte...

Page 75: ...l throttle prior to or during take off run At a minimum speed of about 6300 RPM the engine runs smoothly Taxiing If the wings are equipped with the respective wheels the powered sailplane can be opera...

Page 76: ...advanced to about 70 power particularly in the case of heavy occupants forward c g positions and or uneven fields resulting in the following take off procedure Set elevator trim at its aft range Set...

Page 77: ...creases considerably Furthermore the climb performance is adversely affected Caution If at high ambient temperatures the coolant liquid temperature rises too high the cause may also be the anti freeze...

Page 78: ...m speed range covered by the elevator trim is from about 70 km h 38 kts 43 mph flap L to about 200 km h 108 kts 124 mph flap S Flying characteristics are pleasant and the controls are well harmonized...

Page 79: ...ever they should only be used at such high speeds in an emergency or if the maximum permitted speed is being exceeded inadvertently When extending the airbrakes suddenly the deceleration forces are no...

Page 80: ...mph 132 152 71 82 82 94 150 172 81 93 93 107 2 km h kts mph 152 175 82 94 94 109 172 198 93 107 107 123 S km h kts mph 175 280 94 151 109 174 198 280 107 151 123 174 For a speed polar diagram refer to...

Page 81: ...tching motions speed increases again and will then drop to stalling speed NOTE Before reaching a stalled condition depending on C G position the ASI reading drops quickly by 5 to 10 km h 3 5 kts 3 6 m...

Page 82: ...the back pressure on the control stick There is no uncontrollable tendency to enter a spin The transition into a normal flight attitude is conducted by an appropriate use of the controls The loss of h...

Page 83: ...ow dive the maximum permitted engine speed of 6600 RPM must not be exceeded Idling only in emergency With engine idling throttle closed descending flights are only allowed for short periods Long idlin...

Page 84: ...ot be less than 500 m 1640 ft The maximum range in glide is achieved at a speed of approx 110 to 120 km h 59 65 kt 68 75 mph resulting in an average speed of about 100 km h 54 kt 62 mph Should the saw...

Page 85: ...15 until reaching its vertical position don t use the starter anymore If the propeller was not caught in its vertical position by the automatic propeller brake for the last three attempts support the...

Page 86: ...300 m 984 ft AGL But extending the prop to restart the engine at a height of 200 m 656 ft AGL on the down wind leg to a suitable landing field is safer then e g restarting it at 500 m 1640 ft AGL abov...

Page 87: ...and level or from turning flight On stalling the turbulent airflow produced by the propeller superimposes the vibration in the controls Furthermore the noise of the propeller increases considerably W...

Page 88: ...here are no other differences in the landing characteristics Side slipping is also a useful aid for landing It is possible to maintain a straight line with the rudder deflected up to about 30 50 of it...

Page 89: ...ass 600 kg 1543 lb 800 kg 1764 lb Approach speed 95 km h 51 kts 59 mph 105 km h 57 kts 65 mph Rate of descent Approx 2 0 m s 394 fpm 2 25m s 443 fpm L D approx 13 13 However the performance though red...

Page 90: ...the landing run To avoid a long ground run make sure that the aircraft touches down at minimum speed A touch down at 90 km h 49 kt 56 mph instead of 75 km h 40 kt 47 mph means that the kinetic energy...

Page 91: ...openings are closed with plugged in filler caps having a 6 mm 0 24 in female thread for lifting and venting Lifting these caps is done with the aid of the tailplane rigging tool WARNING As the thread...

Page 92: ...D Thanks to baffles inside the ballast tanks there is no perceptible movement of the water ballast when flying with partially filled tanks When flying at maximum permitted all up mass the low speed an...

Page 93: ...nd side The other end of this hose is then connected to a suitable container which is to be filled with the required amount of clean water The fin tank has eleven 11 spill holes all properly marked on...

Page 94: ...rudder The fin tank dump valve is linked to the torsional drive for the valves in the main wing panels so that these three tanks are always emptying simultaneously The time required to dump the ballas...

Page 95: ...h water ballast if the average rate of climb expected does not exceed 1 0 m s 197 fpm The same applies to flights in narrow thermals requiring steep bank angles 4 If possible all water ballast should...

Page 96: ...28 195 105 121 6000 19685 232 125 144 10000 32808 182 98 113 Flying at temperatures below freezing point When flying at temperatures below 0 C 32 F as in wave or during the winter months it is possibl...

Page 97: ...ks will only appear in the polyester coating however with time and changing environment cracks can eventually reach the Epoxy glass cloth matrix Cracking is obviously enhanced by quick descents from h...

Page 98: ...t compared with a wet powered sailplane in calm air the sink rates encountered are higher Flight tests in rain conducted by the manufacturer did not reveal any significant differences in the stalling...

Page 99: ...ane Therefore the Arcus M will gain speed very rapidly in dive Aerobatic manoeuvres with the Arcus M should only be performed if you can handle these aerobatic manoeuvres safely with similar sailplane...

Page 100: ...establish the vertical climb and you will not have to apply the maximum permitted load factor During the vertical climb you can let the outside wing drag so to speak At an indicated airspeed of about...

Page 101: ...ull out into normal flight The loss of height during the recovery to normal flight is about 100m 300ft the maximum speed is about 180 km h With forward centre of gravity positions no stationary spinni...

Page 102: ...on 5 2 LBA approved data 5 2 1 Airspeed indicator system calibration 5 2 2 Stall speeds 5 2 3 Take off distances 5 2 4 Additional information 5 3 Additional information LBA approval not required 5 3 1...

Page 103: ...on This section provides approved data for airspeed calibration stall speeds and non approved additional information The data in the charts has been computed from actual flight tests with a Arcus M in...

Page 104: ...tail boom approx 1 02 m 40 16 in forward of the base of the fin All airspeeds shown in this manual are indicated airspeeds IAS as registered by the airspeed indicator October 2011 Revision appr 5 2 1...

Page 105: ...at S km h kts mph 90 49 56 80 2 43 1 50 1 airbrakes extended flaps at L km h kts mph 80 2 43 1 50 1 73 2 39 1 45 1 Configuration POWER PLANT EXTENDED All up mass approx 800 kg 1764 lb 800 kg 1764 lb...

Page 106: ...m ft m ft 0 0 183 600 207 679 233 764 260 853 500 1640 199 653 225 738 253 830 283 929 1000 3281 216 709 245 804 275 902 308 1011 1500 4921 235 771 266 873 300 984 335 1099 2000 6562 257 843 291 955...

Page 107: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Arcus M FLIGHT MANUAL 5 2 4 Additional information N o n e October 2011 Revision appr 5 2 4...

Page 108: ...TECK Arcus M FLIGHT MANUAL 5 3 Non approved additional information 5 3 1 Demonstrated crosswind performance The maximum crosswind velocity at which take offs and landings have been demonstrated is 20...

Page 109: ...s mph aircraft performance not yet measured b Power plant extended iginition switched OFF engine not running All up weight mass 800 kg 1764 lb Rate of sink approx 2 25 m s 443 fpm at a speed of approx...

Page 110: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Arcus M FLIGHT MANUAL October 2011 Revision 5 3 2 2...

Page 111: ...35 nm b The following values are based on the sawtooth method see page 4 5 3 7 at an all up mass of 800 kg 1764 lb and the climb effected at max continuous power Average cruising speed approx 100 km h...

Page 112: ...uire ments LSL the measured noise level of the Arcus M equipped with the Solo engine 2625 02i is xxx dB A and is thus far below dB A the noise level limit of 73 4 dB A The Arcus M therefore complies w...

Page 113: ...TECK Arcus M FLIGHT MANUAL Section 6 6 Weight mass and balance 6 1 Introduction 6 2 Weight mass and balance record and permitted payload range Determination of Water ballast in wing tanks Water ballas...

Page 114: ...or weighing the powered sailplane and the calculation method for establishing the permitted payload range and a comprehensive list of all equipment available are contained in the Arcus M Maintenance M...

Page 115: ...the required minimum is to be compensated by ballast there are three 3 methods 1 By attaching ballast lead or sand cushion firmly to the lap belt mounting brackets Optional trim ballast mounting prov...

Page 116: ...each Plates are made to fit only into this tray Lever arm of trim ballast plates 2153 mm 7 06 ft ahead of datum b Trim ballast mounting provision on front stick mounting frame on the starboard side Th...

Page 117: ...cupants max Water ballast fin tank installed YES NO Front seat load regard less of load on rear seat min 1 Inspector Signature Stamp Note 1 If fin tank installed the pilot must either dump all water b...

Page 118: ...upants max Water ballast fin tank installed YES NO Front seat load regard less of load on rear seat min 1 Inspector Signature Stamp Note 1 If fin tank installed the pilot must either dump all water ba...

Page 119: ...4 100 26 4 22 0 80 21 1 17 6 70 18 5 15 4 510 1101 185 48 9 40 7 185 48 9 40 7 185 48 9 40 7 170 44 9 37 4 150 39 6 33 0 130 34 3 28 6 110 29 1 24 2 90 23 8 19 8 70 18 5 15 4 60 15 9 13 2 520 1147 185...

Page 120: ...nose heavy moment of loads on the aft seat with the aid of the diagram shown on page 6 2 8 Note When using fin ballast to compensate for the nose heavy moment of wing ballast and loads on the aft sea...

Page 121: ...t in the fin tank must also be taken into account when determining the maximum allowable ballast quantity for the wing tanks Example Assumed ballast load in wing tanks 40 kg Litres 88 lb 10 6 US Gal A...

Page 122: ...1 2 91 2 42 Liter US Gal IMP Gal Max fin tank capacity Wing water ballast m WT 4 40 5 28 20 IMP Gal US Gal Liter 8 58 10 30 39 12 76 15 32 58 17 16 20 61 78 21 34 25 62 97 25 52 30 64 116 29 92 35 93...

Page 123: ...Description 7 3 Instrument panels 7 4 Undercarriage 7 5 Seats and restraint systems 7 6 Static pressure and Pitot pressure system 7 7 Airbrake system 7 8 Baggage compartment 7 9 Water ballast system s...

Page 124: ...provides a description of the powered sailplane including the operation of its systems For details concerning optional systems and equipment refer to section 9 Supplements For further descriptions of...

Page 125: ...MPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Arcus M FLIGHT MANUAL 7 2 Cockpit Description October 2011 Revision 7 2 1 1 2 4a 3a 4b 5 6 8 12 14 9 15 16 17 18 19 20 21 1 2 3b 4b 5 6 8 14 15 16 17 18 19 20...

Page 126: ...ront instrument panel with two bolts The rear panel is mounted to the steel tube transverse frame between the seats Both instrument panels and their glare shields are easily detached after removing th...

Page 127: ...eached desired position Forward pressure with heels not the toes engages pedals in near est notch with an audible click An adjustment of the rudder pedals is possible on the ground and in the air 3b R...

Page 128: ...ke A wheel brake handle is mounted on either control stick 6 Airbrake levers Levers with blue marking projecting downwards below cockpit inner skin on the left Forward position Airbrakes closed and lo...

Page 129: ...ack lever on the front seat rest on the right Forward position dump valves closed Backward position dump valves opened The lever is held in the respective final positions Fin tank option The fin tank...

Page 130: ...re that the cable restraining the open canopy is properly hooked up 13 Canopy locking and jettisoning levers not illustrated Lever with red grip for either seat on the canopy frame on the left Forward...

Page 131: ...ght pull it back and lock in rear recess Extending Disengage handle push it forward and lock in front recess 16 Flap lever Black lever projecting upwards on cockpit inner skin on the left Swing lever...

Page 132: ...t off valve Black knob on cockpit inner skin on the right for either seat Forward position Valve opened Rearward position Valve closed 19 Rear view mirror This is provided in the front cockpit on the...

Page 133: ...nt panels Front panel For a description of components No I through VII refer to the following pages 7 3 2 through 7 3 18 A description of the instrumentation and an illustration of the rear instrument...

Page 134: ...on regarding the most important operational parameters of the engine The operational state of the engine and the position of the power plant and the propeller are determined processing the information...

Page 135: ...r operating instructions if limitations are exceeded for error messages At the same time the LCD Display shows the respective information or error message and an audible warning signal sounds buzzer 3...

Page 136: ...de DOWN The power plant retracts while the switch is held down rocker switch The spindle drive is cut off by a micro limit switch in the fully retracted position of the power plant Note When the engin...

Page 137: ...iod elapsed time counter Start calibration of fuel capacity indication Input of complete fuel capacity fuselage and wing tank s 7 Ignition switch UP Ignition ON Power plants extends completely automat...

Page 138: ...stopped and on the LCD Display the message BRAKE appears If this message is confirmed by pushing the Menu push button the automatic retraction process will be continued Note To retract the power plant...

Page 139: ...readouts and control elements 8 Test switch for Ignition circuits I II Rocker switch for testing both ignition circuits In upper position ignition circuit 1 is active in lower position ignition circu...

Page 140: ...d elapsed time minute counter 83 09M S min and sec in decimal notation actual calibration factor for fuel quantity indication fuselage tank 100 ___ With completely retracted power plant sailplane mode...

Page 141: ...the variometer s is steadier IV Outside air temperature indicator When carrying water ballast the outside air temperature OAT must not drop below 2 C 36 F V Stick mounted starter button The starter mo...

Page 142: ...tor switch 12 Priority switch 13 Emergency switch 10 1 ENGINE MASTER SWITCH CIRCUIT BREAKER 50 A This circuit breaker disconnects the power plant wiring from its power source battery M For the gliding...

Page 143: ...indle drive actuated via the emergency system 7 Circuit breaker Injection system 7 5 A Protection of Trijekt Injection system 8 Circuit breaker Fuel pump 7 5 A Protection of fuel pump 9 Circuit breake...

Page 144: ...ne will stop running With power off the priority may only be changed if the ignition on both control units is OFF in order to prevent the ignition from being switched on inadvertently 13 Emergency swi...

Page 145: ...retracted lights comes on Spindle drive is cut off by limit switch Note that when extending the power plant via emergency switch some measures against operating errors while starting are still in wor...

Page 146: ...The nose wheel if installed and tail wheel or skid are fixed The extension retraction process of the main wheel is described on page 7 2 7 cockpit description The operation of the main wheel brake is...

Page 147: ...adjustable in flight see also page 7 2 5 concerning the procedure for its adjustment For each seat the lap straps are anchored to the seat pan While the shoulder straps for the front seat are attached...

Page 148: ...6 in forward of the base of the fin b On request a special static pressure probe can be installed near the top of the fin for other instruments besides the ASI c On request additional static pressure...

Page 149: ...IM TECK Arcus M FLIGHT MANUAL 7 7 Airbrake system Schempp Hirth type airbrakes are employed on the upper surface of the main wing panels A schematic view of the airbrake system is given in the Mainten...

Page 150: ...7 8 Baggage compartment An enclosed baggage compartment is not provided For soft objects like jackets etc however there is space above the spar stubs Any such items must be taken into account when det...

Page 151: ...k and a further steel cable to the torque tube actuating the wing tanks see page 7 9 3 On rigging the main wing panels the torque tube in the fuselage is automatically hooked up to the torsional drive...

Page 152: ...NUAL WATER BALLAST SYSTEM WING 1 2 Water tank filler opening with strainer and vent hole Water dump valve actuation for wing coupled with dump valve actuation for fin tank 2 1 vent hole strainer to wa...

Page 153: ...4 5 6 7 8 2 WASSERBALLASTSYSTEM SEITENFLOSSENTANK 1 2 3 4 5 6 7 8 Wasserabla bet tigung Fl gel Wasserabla Verbindungsstange Wasserabla antrieb Seitenflossentank Abla ventil Entw sserungsbohrung Einf...

Page 154: ...ylon An electrical spindle drive anchored to the fuselage deck and linked to the pylon extends and retracts the latter The doors of the engine compartment are automatically opened and closed by a link...

Page 155: ...lement and the shut off valve to the injection system which is connected to the carburetors on the engine Total fuel contents in fuselage and wing panel s are displayed by the engine control unit MCU...

Page 156: ...TH FLUGZEUGBAU GmbH KIRCHHEIM TECK Arcus M FLIGHT MANUAL October 2011 Revision 7 11 2 21 20 shut off valve control FUEL SYSTEM M09 RT 882 1 2 3 4 4 16 5 6 6 7 8 9 11 10 23 12 11 14 15 18 17 13 19 19 2...

Page 157: ...ppel LP 002 1 SL006 23 WALTHER 14 1 Schlauchkupplung SP 006 0 2 SL006 11 2 WALTHER 13 2 Zugentlastung SHK 12 1 Fl geltank re 1500 x 250 HFK W TLF HEIMANN 11 1 Ausgleichsbeh lter 1 Liter SHK 10 1 T St...

Page 158: ...ble to the normally used sealed lead acid batteries there has to be an intern protection against short circuit that reacts in a short time interval approx 100 ms if the electric current is too high 40...

Page 159: ...ed by the power plant master switch 70 A circuit breaker and its voltage is displayed by the engine control unit MCU II By using a selector switch this battery may also be used for the gliding avionic...

Page 160: ...batteries may be used if they meet the respective demands ELECTRICAL SYSTEM AVIONIC M09 RE 880 Master switch Battery selector switch OPTION additional Battery selector switch see 7 12 3 Fuse board VH...

Page 161: ...ront seat load refer to section 6 2 Oxygen systems Attachment points for the mounting brackets for oxygen bottles are provided on the fuselage skin above spar joint on the left and right sides To prev...

Page 162: ...installation of an Emergency Locator Transmitter is possible in the following places and must comply with the instructions obtained from Schempp Hirth In the region of the rear seat on either seat pa...

Page 163: ...RCHHEIM TECK Arcus M FLIGHT MANUAL Section 8 8 Handling care and maintenance 8 1 Introduction 8 2 Inspection periods 8 3 Alterations or repairs 8 4 Ground handling road transportation 8 5 Cleaning and...

Page 164: ...d sailplane It also identifies certain inspection and maintenance requirements which must be followed if the powered sailplane is to retain optimal performance and dependability CAUTION It is wise to...

Page 165: ...e heavy to operate lubricate those places in the fuselage and in the wing panels where plain bearings are used sliding control rods like u c and airbrake linkage Cleaning and greasing the wheels and t...

Page 166: ...th the instructions given in propeller manual Engine Maintenance work on the engine is required after every 25 hours of engine time or at least once every year and must comply with the instructions gi...

Page 167: ...any case be approved by the Luftfahrt Bundesamt LBA Repairs Abbreviations CFRP carbon fibre reinforced plastic GFRP glass fibre reinforced plastic Before every take off and especially after the powere...

Page 168: ...e case of a powered sailplane remaining rigged permanently it is important that the maintenance program includes rust prevention for the fittings on fuselage wing panels and tailplane Tie down kits co...

Page 169: ...ners of any kind are not recommended o Never use chlorine hydrogen i e Tri Tetra Per etc o The best polishing method is the buffing of the surface by means of an edge buffing wheel fitted to a drillin...

Page 170: ...e wet If water is found inside the components should be stored in a dry environment and turned frequently to eliminate the water o The powered sailplane should not be exposed unnecessarily to intense...

Page 171: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Arcus M FLIGHT MANUAL Section 9 9 Supplements 9 1 Introduction 9 2 List of inserted supplements October 2011 Revision 9 1 1...

Page 172: ...HT MANUAL 9 1 Introduction This section contains the appropriate supplements necessary to safely and efficiently operate the Arcus T when equipped with various optional systems and equipment not provi...

Page 173: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Arcus M FLIGHT MANUAL 9 2 List of inserted supplements Date Section Title of inserted supplements 9 2...