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Schempp-Hirth Flugzeugbau ARCUS M, Руководство по эксплуатации самолета


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SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK 

 

Arcus M 

FLIGHT MANUAL 

 
 
 

Determination of fuel contents (continued) 

 

b)  Wing tank(s) (option) 
 
 

The fuel content of the wing tank(s) is not measured. Therefore the amount of 
fuel filled into the wing tank(s) has to be determined during refuelling. 

 
 

Entering total amount of fuel filled into all tanks 

 
 

It is possible to consider the amount of fuel filled into the wing tank(s) at the 
amount of fuel displayed on the engine control unit MCU II. 

 

To do so, scroll through the display of the engine control unit MCU II with the 
Menu-button until “FUEL” is displayed while the power plant is retracted. 
Release the Menu-button shortly and then press the button again for 5 s as 
done for the calibration of the fuselage 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 for at least 5 s, the entered amount of fuel will be adopted and 
displayed on the engine control unit MCU II. 

 
 

The fuel consumption of the power plant is measured with a flow rate meter 
while the engine is running. The indicated total fuel content of wing and 
fuselage tank(s) on the MCU II considers the amount of fuel consumed while 
the engine is running. 

 
 

If the fuel content of the fuselage tank drops below 6 l, only the fuel content of 
the fuselage tank will be displayed on the engine control unit. If the fuel 
content in the fuselage tank will climb again over 6 l (because of bleeding fuel 
out of the wing tank(s) into the fuselage tank), the total amount of fuel in all 
tanks will be displayed again. 

 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
October 2011 
Revision --  

appr. 4.2.2.5 

Содержание ARCUS M

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 7: ...8 anerk 4 5 3 9 anerk 4 5 3 10 anerk 4 5 4 1 anerk 4 5 4 2 anerk 4 5 5 anerk 4 5 6 1 anerk 4 5 6 2 anerk 4 5 6 3 anerk 4 5 6 4 anerk 4 5 6 5 anerk 4 5 7 1 anerk 4 5 7 2 anerk 4 5 8 anerk 4 5 9 1 aner...

Страница 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...

Страница 9: ...7 2 1 7 2 2 7 2 3 7 2 4 7 2 5 7 2 6 7 2 7 7 2 8 7 3 1 7 3 2 7 3 3 7 3 4 7 3 5 7 3 6 7 3 7 7 3 8 7 3 17 7 3 18 7 3 19 7 3 20 7 3 21 Oktober 2011 Oktober 2011 Oktober 2011 Oktober 2011 Oktober 2011 Okt...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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