Flugzeugbau Ventus-2C, Flight Manual

Page 1: ...r No Date of issue N o v e m b e r 2 0 0 3 Pages as indicated by LBA app are approved by Signature Luftfahrt Bundesamt Authority Stamp Original date of approval This sailplane is to be operated in compliance with information and limitations contained herein Approval of translation has been done by best knowledge and judgment In any case the original text in German language is authoritative ...

Page 2: ...ghing 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 indicated by a black vertical line in the left hand margin and revision number and the date will be shown on the bottom left hand side of the page 0 1 1 ...

Page 3: ...Affected page Date of issue Reference Date of Approval by LBA Date of Insertion Signature 1 0 7 0 2 5 7 2 5 März March 2006 Trimmung elevator trim 2 0 1 2 4 5 6 0 2 2 0 2 3 0 2 4 1 4 3 2 6 2 13 2 15 4 5 1 2 4 5 1 3 4 5 1 4 4 5 3 1 4 5 3 2 4 5 3 3 4 5 4 1 5 2 2 6 2 5 Mai May 2006 TM Nr 349 32 Erhöhung der max Flugmasse bei 18 m Spann weite auf 600 kg TN No 349 32 Increase of the max permitted all u...

Page 4: ... TECK Ventus 2c FLUGHANDBUCH FLIGHT MANUAL 0 2 Verzeichnis der Seiten List of effective pages Abschnitt Affected section Seite Affected pages Ausgabe Datum Date of issue Bezug Reference 0 0 1 1 0 2 1 0 2 2 0 2 3 0 2 4 0 2 5 0 2 6 0 3 1 0 2 1 ...

Page 5: ... LBA anerk 2 15 3 1 1 3 1 2 LBA anerk 3 2 LBA anerk 3 3 LBA anerk 3 4 LBA anerk 3 5 LBA anerk 3 6 LBA anerk 3 7 LBA anerk 3 8 LBA anerk 3 9 1 LBA anerk 3 9 2 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 Mai 2006 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 Mai 2006 November 2003 November 2003 November 2003 ...

Page 6: ...5 3 4 LBA anerk 4 5 3 5 LBA anerk 4 5 4 1 LBA anerk 4 5 4 2 LBA anerk 4 5 5 LBA anerk 4 5 6 1 LBA anerk 4 5 6 2 LBA anerk 4 5 6 3 LBA anerk 4 5 6 4 LBA anerk 4 5 6 5 LBA anerk 4 5 7 1 LBA anerk 4 5 7 2 LBA anerk 4 5 8 LBA anerk 4 5 9 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 Mai 2006 Mai...

Page 7: ...1 5 1 2 LBA anerk 5 2 1 LBA anerk 5 2 2 LBA anerk 5 2 3 LBA anerk 5 2 4 5 3 1 5 3 2 1 5 3 2 2 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 November 2003 November 2003 November 2003 Mai 2006 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 Mai 2006 November 2003 November 2003 Nove...

Page 8: ...6 7 3 1 7 3 2 7 4 7 5 7 6 7 7 7 8 7 9 1 7 9 2 7 9 3 7 10 7 11 7 12 1 7 12 2 7 12 3 7 12 4 7 13 1 7 13 2 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 March 2006 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 Novem...

Page 9: ...ten List of effective pages Abschnitt Affected section Seite Affected pages Ausgabe Datum Date of issue Bezug Reference 8 9 8 1 1 8 1 2 8 2 8 3 8 4 8 5 1 8 5 2 9 1 1 9 1 2 9 2 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 0 2 6 ...

Page 10: ...mitations 2 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 Aircraft and systems description 7 a non approved section Aircraft handling care and maintenance 8 a non approved section Supplements 9 0 3 1 ...

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Page 12: ...LUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 2c 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 November 2003 Revision 1 1 1 ...

Page 13: ...ilplane has been prepared to provide pilots and instructors with information for the safe and efficient operation of the sailplane This manual includes the material required to be furnished to the pilot by JAR Part 22 It also contains supplemental data supplied by the manufacturer of the aircraft November 2003 Revision 1 1 2 ...

Page 14: ...n Ventus 2c has been approved by the Luftfahrt Bundesamt LBA in compliance with JAR Part 22 effective on June 27 1989 Change 4 of the English Original Issue including additional Amendment 22 90 1 The LBA Type Certificate is No 349 and was issued on September 26 1996 Category of Airworthiness UTILITY November 2003 Revision 1 2 ...

Page 15: ...t the non observation of the corresponding procedure leads to an immediate or important degrada tion of the flight safety CAUTION means that the non observation of the corresponding procedures leads to a minor or to a more or less long term degradation of the flight safety NOTE draws the attention on any special item not directly related to safety but which is important or unusual November 2003 Re...

Page 16: ... a semi reclining position in the comfortable cockpit The one piece canopy hinges sideways and opens to the right For high energy absorption the cockpit region is constructed as a Kevlar carbon glass fiber laminate which is reinforced by a double skin on the sides with integrated canopy coaming frame The aft fuselage section is a pure carbon fiber non sandwich shell stiffened by carbon fiber bulkh...

Page 17: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 2c FLIGHT MANUAL Intentionally blank November 2003 Revision 1 4 2 ...

Page 18: ...18 73 ft Aspect ratio 23 3 29 5 MAC 0 673 m 0 648 m 2 210 ft 2 13 ft Fuselage Length 6 78 m 22 24 ft Width 0 62 m 2 03 ft Height 0 81 m 2 66 ft Mass Empty mass approx 290 kg 310 kg 739 lb 783 lb Maximum all up mass 525 kg 600 kg 1157 lb 1323 lb Wing loading range 37 7 54 3 kg m 34 9 54 4 kg m 7 7 11 1 lb ft 7 1 11 1 lb ft May 2006 Revision 2 TN No 349 32 1 4 3 ...

Page 19: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 2c FLIGHT MANUAL 1 5 Three side view November 2003 Revision 1 5 15 0 m 49 21 ft 18 0 m 59 06 ft 6 81 m 22 34 ft 2 5 m 8 20 ft ...

Page 20: ...d 2 3 Airspeed indicator markings 2 4 reserved 2 5 reserved 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 of operation 2 12 Minimum equipment 2 13 Aerotow and winch launch 2 14 Other limitations 2 15 Limitation placards November 2003 Revision 2 1 1 ...

Page 21: ...udes operating limitations instrument markings and basic placards necessary for safely operating the aircraft its standard systems and standard equipment The limitations included in this section and in section 9 have been approved by the Luftfahrt Bundesamt LBA Braunschweig November 2003 Revision 2 1 2 ...

Page 22: ... is met in lee wave rotors thunderclouds etc VA Maneuvering speed 200 km h 108 kt 124 mph Do not make full or abrupt control movements above this speed as the aircraft structure might get overstressed VFE Maximum flap extended speed Flaps set at L 2 1 0 200 km h 108 kt 124 mph Do not exceed this speed with the given flap setting VT Maximum speed on aerotow 180 km h 97 kt 112 mph Do not exceed this...

Page 23: ...peed with flaps extended positive Green arc 102 200 km h 55 108 kt 63 124 mph Normal operating range lower limit is the speed 1 1VS1 at maximum mass c g in most for ward position and flaps at the neutral 1 position upper limit is the max permissible speed in rough air Yellow arc 200 285 km h 108 154 kt 124 177 mph Maneuvers must be conducted with caution and operating in rough air is not permitted...

Page 24: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 2c FLIGHT MANUAL Intentionally blank November 2003 LBA app Revision 2 4 ...

Page 25: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 2c FLIGHT MANUAL Intentionally blank November 2003 LBA app Revision 2 5 ...

Page 26: ...b 1323 lb Maximum permitted landing mass 525 kg 600 kg 1157 lb 1323 lb Maximum permitted take off and landing mass without waterballast mNT mFL Current weight of the wing panel mFL Maximum permitted mass of all non lifting parts mNT 280 kg 616 lb Maximum permitted mass in baggage compartment 2 kg 4 4 lb see page 7 8 May 2006 LBA app Revision 2 TN No 349 32 2 6 ...

Page 27: ...orward c g position 260 mm 10 24 in aft of datum Maximum rearward c g position 380 mm 14 96 in aft of datum It is extremely important that the maximum rearward c g position is not exceeded This requirement is met when the minimum seat load is observed The minimum seat load is given in the loading table and is shown by a placard in the cockpit A lower seat load must be compensated by ballast see se...

Page 28: ...BAU GmbH KIRCHHEIM TECK Ventus 2c FLIGHT MANUAL 2 8 Approved maneuvers The sailplane model Ventus 2c is certified in category U T I L I T Y November 2003 LBA app Revision 2 8 Warning Aerobatic maneuvers n o t a p p r o v e d ...

Page 29: ...ust not be exceeded a With airbrakes locked and at VA 200 km h 108 kt 124 mph n 5 3 n 2 65 With airbrakes locked and at VNE 285 km h 154 kt 177 mph n 4 0 n 1 5 With flaps as follows Setting L 2 1 0 1 2 S S1 km h Speed kt mph 200 108 124 285 154 177 Load factor n 5 3 4 0 b With airbrakes extended n 3 5 n 0 November 2003 LBA app Revision 2 9 ...

Page 30: ...L 2 10 Flight crew The Ventus 2c is single seated Observe the minimum seat load if necessary ballast must be installed to bring the load up to a permissible figure See also section 6 2 Weight and Balance Record Permitted Payload Range November 2003 LBA app Revision 2 10 ...

Page 31: ...s of operation With the prescribed minimum equipment installed see page 2 12 this sailplane is approved for 1 VFR flying in daytime 2 Cloud flying without water ballast for maximum masses wing span 18 m 410 kg 902 lb wing span 15 m 400 kg 880 lb November 2003 LBA app Revision 2 11 ...

Page 32: ... or 1 Back cushion thickness approx 10 cm 3 9 in when compressed Caution The sensor for the OAT must be installed in the ventilation air intake For structural reasons the mass of each instrument panel with instruments in place must not exceed 10 kg 22 lb b Cloud flying only permissible without water ballast In addition to the minimum equipment listed under a the following is required 1 Turn and ba...

Page 33: ...aximum towing speed 180 km h 97 kt 112 mph Weak link in tow rope max 765 daN max 1687 lb Minimum length of tow rope 30 m 98 ft Tow rope material Hemp or Nylon Winch launch only permissible with c g tow release in place Maximum launching speed 150 km h 81 kt 93 mph Weak link in winch cable max 765 daN max 1687 lb May 2006 LBA app Revision 2 TN No 349 32 2 13 ...

Page 34: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 2c FLIGHT MANUAL 2 14 Other limitations N o n e November 2003 LBA app Revision 2 14 ...

Page 35: ...parachute Minimum load kg lb Maximum load kg lb 154 243 110 For seat loads below placarded minimum refer to Flight Manual section 6 2 70 Flap setting 1 2 S S1 285 154 177 Flap setting L 2 1 0 200 108 124 Rough air speed 200 108 124 Maneuvering speed 200 108 124 Aerotowing speed 180 97 112 Winch launching speed 150 81 93 Landing gear operating speed 180 97 112 For 18 m span 1323 lb 600 kg For 15 m ...

Page 36: ...ntus 2c FLIGHT 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 reserved 3 8 reserved 3 9 Other emergencies November 2003 Revision 3 1 1 ...

Page 37: ...T 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 flight inspections and maintenance November 2003 Revision 3 1 2 ...

Page 38: ...canopy is to be jettisoned as follows Swing red locking lever situated on the canopy frame on the left b a c k w a r d about 90 up to its stop and swing canopy sideways fully open The canopy will then be torn out from its hinges by the airstream and gets carried away November 2003 LBA app Revision 3 2 ...

Page 39: ...3 2 the pilot may bail out as follows Actuate release buckle of restraint system Bend upper part of body slightly forward Grab canopy coaming frame on fuselage with both hands and lift body legs will make the instrument panel tilt up Leave the cockpit to the left Pull rip cord of manual parachute at a safe distance and height November 2003 LBA app Revision 3 3 ...

Page 40: ...LIGHT MANUAL 3 4 Stall recovery On stalling whilst flying straight ahead or in a banked turn normal flying attitude is regained by firmly easing the control stick forward and if necessary applying opposite rudder and aileron November 2003 LBA app Revision 3 4 ...

Page 41: ... ft The recovery speeds are between 145 and 250 km h 78 135 kt 90 155 mph depending on the flap setting At positive flap settings and high all up masses a resetting of the flaps at 1 may be required so as to avoid exceeding their speed limits when pulling out of the dive With the center of gravity in the foremost position a steady spinning motion is not possible the aircraft stops rotating after a...

Page 42: ... which is indicated by 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 the dive the limiting airspeed for the various flap settings if necessary reset flaps at 1 and the permissible control surface deflections at VA VNE see page 2 2 1 must be observed November...

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Page 45: ...d elevator control is more serious The pilot however should take into consideration that the aircraft is still controllable to at least some extent by using its flaps for longitudinal control Flap lever pulled back slower Flap lever pushed forward faster This may for example allow the pilot to move over to a more favourable bail out aera Loss of directional control Should a rudder control cable br...

Page 46: ...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 about 40 m 131 ft away from the boundary If possible always turn into the wind and as the wing tip is forced down push the control stick forward simultaneously Emergency water landing From experience gained from composite sailplane landings on water followin...

Page 47: ...4 2 Rigging and de rigging 4 3 Daily inspection 4 4 Pre flight inspection 4 5 Normal procedures and recommended speeds 4 5 1 Methods of launching 4 5 2 reserved 4 5 3 Flight 4 5 4 Approach 4 5 5 Landing 4 5 6 Flight with water ballast 4 5 7 High altitude flight 4 5 8 Flight in rain 4 5 9 Aerobatics November 2003 Revision 4 1 1 ...

Page 48: ...oduction Normal procedures associated with optional equipment are found in section 9 This section provides check lists and amplifies procedures for conducting the daily and pre flight inspection Furthermore this section includes normal operating procedures and recom mended speeds November 2003 Revision 4 1 2 ...

Page 49: ...de of the fuselage and ensure that the angular levers on the root rib are defi nitely inserted into their fuselage funnels do not raise aileron Now push panel home until its locating pins have fully engaged in their corre sponding fuselage bearings and push in the main wing pin for about 30 to 40 mm 1 2 to 1 6 in so that the panel is prevented from sliding out by the GFRP lami nate covering the fr...

Page 50: ...e fin Next slide the horiz tailplane aft onto the two elevator actuating pins pull rigging tool and its pin forwards seat stabilizer nose and push locating pin home into the front tailplane attachment fitting Remove rigging tool the 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 ele vator After riggi...

Page 51: ...attachment pin lift stabilizer leading edge slightly and pull tailplane forwards and off Inboard wing panels Unlock airbrakes set water ballast control knob to the closed position unlock handle of main wing pin and set flaps at 0 With a helper at the tip of each inboard panel pull out main wing pin up to the last 20 to 30 mm 0 8 1 2 in and withdraw the starboard panel by gently rocking it backward...

Page 52: ... When walking around the aircraft check all surfaces for paint cracks dents and unevenness In case of doubt ask an expert for his advise 1 a Open the canopy and check gas strut raising the instrument panel for proper function b Check that the main wing pin is properly secured c Make a visual check of all accessible control circuits in the cockpit d Check for full and free movements of the control ...

Page 53: ...mp valves if necessary c Check outboard wing panels for proper connection locking lever must be below upper wing surface d Check that the ailerons are in good condition and operate freely Check for any unusual play by gently shaking the trailing edge Check hinges for damage 3 a Check ailerons flaperons on inbd wing panels for proper condition and free movement Check for any unusual play by gently ...

Page 54: ... placard b Should a total energy compensation probe be used mount it and check the line when blowing gently from the front into the probe the variometer s connected should read climb c Check that the fin mounted PITOT tube is clear When blowing gently into this tube the ASI must register Should a water ballast fin tank be installed option d Check that the fin tank spill holes are clear e Check wat...

Page 55: ...he ASI must register with pneumatic valve set at POWER ON After heavy landings or after the aircraft has been subjected to excessive loads the resonant wing vibration frequency should be checked its value to be extracted from the last inspection report for this serial number Check the entire aircraft thoroughly for surface cracks and other damage For this purpose it should be de rigged If damage i...

Page 56: ... installed O Loading charts checked O Parachute securely fastened O Safety harness secured and tight O Seat back and pedals in comfortable position O All controls and instruments easily accessible 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 ...

Page 57: ... travel other c g positions Knob to the middle of its travel As the tow rope tightens apply the wheel brake gently by actuating the stick mounted lever to prevent the sailplane from overrunning the rope In crosswind conditions the aileron control should be held towards the downwind wing i e in winds from the left the stick should be displaced to the right This is to counteract the lift increase on...

Page 58: ...nd low all up masses i e above about 160 km h 86 kt 99 mph flap setting 1 or 2 should be used see diagram below With these settings speeds up to VT are covered by the elevator trim Only small control surface deflections are necessary to keep station behind the tug In gusty conditions or when flying into the propeller slip stream of a powerful tug correspondingly greater control stick movements are...

Page 59: ...y on leaving the ground Depending on the load on the seat the aircraft is lifted off with the control stick almost fully pushed forward in the case of aft c g positions and slightly pulled back with the c g in a forward position After climbing to a safe height the transition into a typical steep winch launch attitude is effected by pulling the control stick slightly further back At normal all up m...

Page 60: ...an 300 m 984 ft In case of doubt reduce all up mass by dumping water ballast Winch launching with high ballast loads is not recommended if the head wind is less than 20 km h 11 kt WARNING It is explicitly advised against winch launching with a tail wind CAUTION Prior to launching by winch it must be ensured that the pilot is properly seated and able to reach all control elements Particularly when ...

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Page 62: ...he aircraft is practically always well trimmed for all other flap settings and for optimum performance within their speed range With a mid point c g position the speed range covered by the trim is from about 65 km h 35 kt 40 mph with flaps set at L to about 240 km h 130 kt 149 mph with flaps set at S1 The controls are well harmonized reversing a turn from 45 to 45 is possible without any skidding ...

Page 63: ...n speed will be noticed through a perceptible change in control stick loads The airbrakes may be extended up to VNE 285 km h 154 kt 177 mph However they should only be used at such high speeds in emergency or if the maximum permitted speeds are being exceeded inadvertently On extending the airbrakes high deceleration forces will occur WARNING Consequently it is wise to check in advance that the ha...

Page 64: ... 96 132 170 71 92 82 106 2 km h kt mph 140 173 76 93 87 108 155 192 84 104 96 119 172 212 93 114 107 132 145 172 78 93 90 107 155 183 84 99 96 114 170 200 92 108 106 124 S km h kt mph 173 186 93 100 108 116 192 206 104 111 119 128 212 228 114 123 132 142 172 215 93 116 107 134 183 230 99 124 114 143 200 250 108 135 124 155 Flying between thermals and high speed flying S1 km h kt mph 186 285 100 15...

Page 65: ...peed in creases again and will then drop to stalling speed NOTE After reaching stalling speed the ASI reading drops quickly by 5 to 10 km h 3 5 kt 3 6 mph and starts oscillating because of the turbu lent airflow affecting the pitot pressure head When reaching a stalled condition with the c g in rearward positions the stick reaches the stop or the sailplane will drop a wing A normal flight attitude...

Page 66: ... the beginning of the stall until regaining a normal level flight attitude is approx up to 80 m 262 ft With the c g in foremost position the sailplane just stalls without dropping its nose or a wing Influence of water ballast Apart from the higher mass in flight i e a higher stalling speed water ballast in the wing tanks has no aggravating influence on the stall characteristics The loss of height ...

Page 67: ...he pilot some reserve for the case of an approach over an obstacle being too short as he may reset the flaps at L thus gaining temporarily some additional height after touch down the flaps are then set at 1 or 0 Side slip behaviour Side slips are a very effective landing aid Side slips in 15 m configuration may be conducted in a straight line up to about 90 of the rudder travel resulting in a yaw ...

Page 68: ...itch down movement arise though the stick is pulled followed by an increase of speed To stop this movement lessen the yaw angle by reducing the rudder deflection or retract the airbrakes 3 During side slip with water ballast some water escapes through the vent holes of the water tank filler caps of the lower wing Prolonged slips with water ballast are therefore not recommended WARNING Both the per...

Page 69: ...eously After touch down the flaps may be set at 0 for improved aileron response during the landing run To avoid a long ground run make sure that the sailplane touches down at mini mum speed A touch down at 90 km h 49 kt 56 mph instead of 80 km h 43 kt 50 mph means that the kinetic energy to be dissipated by braking is increased by a factor of 1 26 and therefore the ground run is lengthened unneces...

Page 70: ... with a plugged in filler cap having a 6 mm 0 24 in female thread for lifting and venting Lifting the filler caps is done with the aid of the tailplane rigging tool WARNING As the threaded hole in the filler caps also serves for venting the tank it must always be kept open Each tank has a capacity of about inboard wing tank 87 Liter 22 98 US Gal 19 14 IMP Gal outboard wing tank 14 Liter 3 70 US Ga...

Page 71: ...anks there is no perceptible movement of the water ballast when flying with partly filled tanks When flying at maximum permitted all up mass the low speed and stall behaviour of the sailplane is slightly different from its behaviour without water ballasts The stall speeds are higher see section 5 2 2 and for correcting the flight attitude larger control surface deflections are required Furthermore...

Page 72: ...is than connected to a suitable container which is to be filled with the required amount of clear water The fin tank has for every Liter spill holes all properly marked on the right hand side of the fin which indicate the water level see accompanying sketch The venting of the tank is through the uppermost 7 8 kg Liter hole which always remains open even with a full tank The ballast quantity to be ...

Page 73: ...o the rudder The fin tank dump valve is linked to the torsional drive for the valves in the wing panels so that all three tanks are always opened simultaneously The time required to dump the ballast from a full fin tank is about 90 seconds i e draining the fin tank always takes less time than discharging full wing tanks Continued on page 4 5 6 5 November 2003 LBA app Revision 4 5 6 4 ...

Page 74: ... up equally Leaking dripping valves are avoided by cleaning and greasing the plugs and their seats with valves opened Thereafter with valves closed the drain plugs are pulled home with the threaded tool used to attach the tailplane WARNING 5 Never pressurize the tanks for instance by filling them directly from a water hose and always pour in clear water only 6 On no account whatsoever must the sai...

Page 75: ...02 119 5000 16404 240 129 149 10000 32808 180 97 112 see limitations placard page 2 15 too 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 possible that the usual ease and smoothness of the control circuits is reduced It must therefore be ensured that all control elements are free from moisture so that there is no ...

Page 76: ... only appear in the polyester coating however with time and changing environment cracks can reach the Epoxy Carbon cloth matrix Cracking is obviously enhanced by steep descents from high altitudes at associated very low temperatures WARNING Therefore for the preservation of a proper surface finish free from cracking the manufacturer strongly advises against high altitude flights with associated te...

Page 77: ...th such measurements Often the air mass containing the moisture is also descending so that compared with a wet aircraft 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 behaviour or stalling speeds It cannot be excluded however that excessive alterations of the airfoil section as caused b...

Page 78: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 2c FLIGHT MANUAL 4 5 9 Aerobatics Aerobatic maneuvers are n o t permitted November 2003 LBA app Revision 4 5 9 ...

Page 79: ... 5 1 Introduction 5 2 LBA approved data 5 2 1 Airspeed indicator system calibration 5 2 2 Stall speeds 5 2 3 reserved 5 2 4 Additional information 5 3 Additional information LBA approval not required 5 3 1 Demonstrated crosswind performance 5 3 2 Flight polar Range November 2003 Revision 5 1 1 ...

Page 80: ...oduction This section provides LBA 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 sailplane in good condition and using average piloting techniques November 2003 Revision 5 1 2 ...

Page 81: ...of base of fin and 15 cm 5 9 in below main spar cut out All airspeeds shown in this manual are indicated airspeeds IAS as registered by the airspeed indicator November 2003 LBA app Revision 5 2 1 80 43 50 60 32 37 100 54 62 all up mass 412 kg 908 lb VNE 285 km h 154 kt 177 mph 177 154 285 ρ0 1 226 kg m3 0 076 lb ft3 CALIBRATED AIRSPEED CAS INDICATED AIRSPEED IAS mph kt km h 174 151 280 149 130 240...

Page 82: ...ll speed airbrakes closed flaps at 2 km h kt mph 66 36 41 69 5 37 3 43 3 77 5 42 3 48 3 67 5 36 3 42 3 flaps at 0 km h kt mph 70 38 43 75 5 40 3 47 3 85 5 46 3 53 3 68 5 37 3 42 3 flaps at S1 km h kt mph 74 40 46 81 5 44 3 50 3 91 5 49 3 57 3 77 5 42 3 48 3 airbrakes extended flaps at L km h kt mph 76 41 47 75 5 40 3 47 3 88 5 47 3 55 3 74 5 40 3 46 3 Airspeed indication is oscillating with rearwa...

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Page 84: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 2c FLIGHT MANUAL 5 2 4 Additional information N o n e November 2003 LBA app Revision 5 2 4 ...

Page 85: ...ECK Ventus 2c FLIGHT MANUAL 5 3 Non LBA approved additional information 5 3 1 Demonstrated crosswind performance The maximum crosswind velocity at which take offs and landings have been demonstrated is 20 km h 11 kt November 2003 Revision 5 3 1 ...

Page 86: ... span m 15 18 kg 395 423 All up mass lb 871 933 kg m 40 7 38 5 Wing loading lb ft 8 3 7 9 m s 0 59 0 49 Minimum sink rate fpm 116 96 km h 80 80 kt 43 43 at a speed of mph 50 50 Best L D approx not measured 50 km h 100 110 90 95 kt 54 59 49 51 at a speed of approx mph 62 68 56 59 A speed polar diagram is found on page 5 3 2 2 November 2003 Revision 5 3 2 1 ...

Page 87: ...POLAR DIAGRAM AIRSPEED CAS RATE OF SINK all up mass 565 kg 1246 lb all up mass 400 kg 882 lb 43 38 70 50 43 80 56 49 90 62 54 100 68 59 110 75 65 120 81 70 130 87 76 140 93 81 150 99 86 160 106 92 170 112 97 180 118 103 190 124 108 200 mph kt km h 37 32 60 130 113 210 137 119 220 98 0 5 197 1 0 295 1 5 394 2 0 492 2 5 590 3 0 fpm m s ...

Page 88: ...ECK Ventus 2c 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 ballast in fin tank November 2003 Revision 6 1 1 ...

Page 89: ...perated Procedures for weighing the aircraft and the calculation method for establishing the permitted payload range and a comprehensive list of all equipment available are contained in the Maintenance Manual The equipment actually installed during the last weighing of the aircraft is shown in the equipment list to which page 6 2 3 refer to November 2003 Revision 6 1 2 ...

Page 90: ...rt the required data and diagrams are found in the Maintenance Manual Both loading charts weight balance log sheets are only applicable for this particular sailplane the serial number of which is shown on the title page A seat load of less than the required minimum is to be compensated by ballast there are two methods 1 By attaching ballast lead or sand cushion firmly to the lap belt mounting brac...

Page 91: ...llast weights The ballast mounting provision holds up to three 3 lead plates with a weight of 2 2 kg 5 0 lb each and allows a reduction of the placarded minimum seat load as shown in the following table Difference as compared with placarded minimum Number of lead plates required up to 5 kg 11 lb less 1 up to 10 kg 22 lb less 2 up to 15 kg 33 lb less 3 Lever arm of trim ballast plates 1740 mm 68 50...

Page 92: ...aft of datum 15 m Max kg Seat load pilot incl parachute Min kg Max useful load in fuselage kg Inspector Signature Stamp NOTE Maximum seat load Maximum useful load in Pilot parachute fuselage but not more than 110 kg 242 5 lb For the determination of water ballast in the wing tanks refer to page 6 2 5 For the determination of water ballast in the fin tank refer to page 6 2 6 through 6 2 8 November ...

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Page 94: ...owance must be made for water ballast in the fin tank see page 6 2 6 and 6 2 7 i e this load must be added to the empty mass shown on the above table Empty mass as per page 6 2 3 fin ballast as per page 6 2 7 May 2003 Revision 2 TN No 349 32 SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK FLIGHT MANUAL WING SPAN 15 m 49 21 ft Water ballast load Maximum all up mass including water ballast 525 kg 1157...

Page 95: ...s done with the aid of the diagram shown on page 6 2 7 resp 6 2 8 Notes concerning the use of the fin tank are given on page 4 5 6 3 IMPORTANT NOTE When determining the useful load in the fuselage the quantity of water ballast in the fin must not be taken in account because of flight mechanic reasons Example Assumed ballast load in wing tanks 80 0 kg Liter Permissible ballast load fill only full L...

Page 96: ...r the lower amount of ballast may be used maximum wing water ballast mFT water ballast in fin tank max fin tank capacity 1 0 26 0 22 3 0 79 0 66 5 1 32 1 10 7 1 85 1 54 7 8 2 06 1 72 Liter US Gal IMP Gal 2 0 53 0 44 4 1 06 0 88 6 1 59 1 32 44 4 53 4 202 38 5 46 2 175 33 2 39 9 151 27 9 33 5 127 22 7 27 2 103 17 2 20 6 78 11 9 14 3 54 6 6 7 9 30 IMP US Ltr Gal Gal 42 9 51 5 195 38 3 46 0 174 32 3 3...

Page 97: ...NOTE Always full Liters are to be filled Where value jumps either the higher or the lower amount of ballast may be used maximum wing water ballast mFT water ballast in fin tank max fin tank capacity 1 0 26 0 22 3 0 79 0 66 5 1 32 1 10 7 1 85 1 54 7 8 2 06 1 72 Liter US Gal IMP Gal 2 0 53 0 44 4 1 06 0 88 6 1 59 1 32 38 3 46 0 174 33 0 39 6 150 27 5 33 0 125 22 0 26 4 100 16 5 19 8 75 11 0 13 2 50 ...

Page 98: ... Cockpit description 7 3 Instrument panel 7 4 Undercarriage 7 5 Seat and restraint system 7 6 Static pressure and Pitot pressure system 7 7 Airbrake system 7 8 Baggage compartment 7 9 Water ballast system s 7 10 reserved 7 11 reserved 7 12 Electrical system 7 13 Miscellaneous equipment removable Ballast oxygen ELT etc November 2003 Revision 7 1 1 ...

Page 99: ...ection provides a description of the sailplane including the operation of its systems For details concerning optional systems and equipment refer to section 9 Supplements For further descriptions of components and systems refer to section 1 of the Maintenance Manual November 2003 Revision 7 1 2 ...

Page 100: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 2c FLIGHT MANUAL 7 2 Cockpit description November 2003 Revision 7 2 1 11 8 3 1 7 2 9 5 4 12 6 13 2 10 ...

Page 101: ...py opened 2 Ventilator control Knurled gold coloured knob on the cockpit inner skin on the left in the front Ventilator closed Knob in backward position Ventilator opened Knob in forward position Adjustable bull eye type ventilator on the starbd cockpit inner skin Turned clockwise Ventilator closed Turned anti clockwise Ventilator opened Additionally the sliding window or the air scoop in the wind...

Page 102: ...nearest notch with an audible click The pedals may be adjusted on the ground or in the air 5 Control handle for tow release mechanism s Yellow T shaped handle on the left at the base of the instrument console actuating the nose and or the c g tow release whichever is installed The aerotow rope winch cable is released by pulling this handle 6 Undercarriage Retracting Disengage black handle on the r...

Page 103: ...py 9 Canopy detachment Sliding black knob on the cockpit inner skin on the right Forward position Canopy locked To remove the canopy pull knob backwards 10 Control knob for dumping water ballast from wing tanks and optional fin tank Black knob in the middle of the cockpit inner skin on the right Forward position Valves closed Rearward position Valves opened The knob is locked in the extreme positi...

Page 104: ...rim is mounted on the left on the flap actuating tube a Green knurled screw The spring loaded trim is infinitely adjustable by freeing the knurled knob sliding it to the desired position and tightening the knob again b Green ball shaped knob optional The spring loaded trim is stepwise adjustable by canting the knob to the right moving it in the desired position and canting it back to the left into...

Page 105: ...into desired notch then engage spring loaded pin on the far side Additionally it is resettable in flight for an upright or reclining position with the aid of a black knob situated beneath the cockpit inner skin on the right Adjustment More reclining Unlock knob by moving it downward pull it back and let it engage in notch nearest to desired position More upright Unlock knob by moving it downward s...

Page 106: ...BAU GmbH KIRCHHEIM TECK Ventus 2c FLIGHT MANUAL 7 3 Instrument panel November 2003 Revision 7 3 1 III II I For a description of items No I III refer to page 7 3 2 A description of the instrumentation is not deemed necessary ...

Page 107: ...Ventus 2c FLIGHT MANUAL I Main switch Panel mounted ON OFF switch UP ON DOWN OFF II Reserved III Outside air temperature indicator When carrying water ballast the outside air temperature OAT must not drop below 2 C 36 F November 2003 Revision 7 3 2 ...

Page 108: ...mechanical resp hydraulic drum brake Instead of the standard rubber tail skid a pneumatic wheel is available on request The extension retraction process of the main wheel is described on page 7 2 3 For a technical description of the retractable undercarriage including wheel brake refer to section 1 of the Maintenance Manual November 2003 Revision 7 4 ...

Page 109: ...ither side of the cockpit A seat back with integrated head rest adjustable in flight for an upright or reclining position is standard The lap straps are anchored to the seat pan the shoulder straps are attached to the front wing suspension tube A list of approved restraint systems is found in section 7 1 of the Maintenance Manual November 2003 Revision 7 5 ...

Page 110: ... the horizontal plane and 0 15 m 5 9 in below the fuselage to wing fillet to be used for airspeed indicator etc b On request a special static pressure probe can be installed near the top of the fin for further instruments except ASI Pitot pressure sources The Pitot pressure head is near the top of the fin to be used for airspeed indicator and other instruments November 2003 Revision 7 6 ASI ALTIME...

Page 111: ...ed the airbrakes might get slightly sucked out by their spring loaded cover strips which In turn way then oscillate within their travel causing some rattling and or banging This is immediately stopped by further extending the airbrakes The control of the Ventus 2c is not affected With airbrakes extended the indicated stalling speed is higher depending from mass and C G position see page 5 2 2 A vi...

Page 112: ...ment is not provided soft objects like jackets etc may be deposited on the removable panel covering the control linkage behind the main spar stubs the head rest obstructs the access opening to a large extent Such baggage however must be taken into account when determining the permissible load on the seat November 2003 Revision 7 8 ...

Page 113: ...d in the extreme positions For notes on how to fly with water ballast refer to section 4 5 6 For water ballast loading tables refer to page 6 2 5 and the following A view of the wing water ballast system is provided on page 7 9 2 Fin tank option A steel cable connects the torsional drive in the fuselage center to the dump valve of the fin tank hence the knob in the cockpit controls all tanks A des...

Page 114: ...pening on inboard wing panel with strainer 2 Water tank filler opening on 18m outboard wing panel with strainer 3 Water dump valve control for inboard wing panel 4 Water dump valve control for 18m outboard wing panel 5 Water dump valve actuation for inboard wing panel and 18m outboard wing panel 4 2 Vent hole 15m outbd wing panel without water tank Strainer ...

Page 115: ... November 2003 Revision 7 9 3 1 3 4 5 6 7 2 8 WATER BALLAST SYSTEMS 1 Torque drive for wing tanks dump valves 2 Connection of fin tank dump valve actuating cable 3 Fin tank dump valve 4 Vent holes 5 Filler tube opening 6 Water ballast dump hole 7 Drain hole 8 Spill holes ...

Page 116: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 2c FLIGHT MANUAL Intentionally blank November 2003 Revision 7 10 ...

Page 117: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 2c FLIGHT MANUAL Intentionally blank November 2003 Revision 7 11 ...

Page 118: ...is to be wired as shown on page 7 12 2 through 7 12 4 and must comply with the manufacturer s instruction of the relevant instrument Power for the avionics is supplied by one or more batteries located as follows Upper end of fin option R h s of main wheel housing option Base of instrument pane November 2003 Revision 7 12 1 ...

Page 119: ...om mike M Rotary multipoint switch N Option Charging socket O Option Circuit breaker 2A P Option Low voltage indicator ELECTRICAL SYSTEM AVIONIC S08 RE 840 1 I G AWG 18 AWG 18 C to battery and to battery in fin B C A battery in fin J H K G L D antenna cable A F F F BATT AVIONIC BATT FIN BATT AVIONIC BATT AVIONIC BATT in SFL BATTERY MOUNTING POSITIONS BATT AVIONIC Parts listed on page 7 12 4 B1 B2 ...

Page 120: ...G Option Charging socket Option Charging socket Option Charging socket Option Charging socket Option Charging socket Option Charging socket Option Charging socket Option Charging socket Main switch Selector switch Main switch Selector switch Selector switch Main switch OPTION Electrolytic capacitor as a voltage buffer for Logger E Vario Electr capacitor 22000µF 25V Other additional equipment to be...

Page 121: ...3 pole 11156 MS 500 M Apem Setron D3 1 Selector switch 4 pole 11166 MS 500 P Apem Setron E 1 2 Micro switch 9040 0101 Marquardt F 2 4 Circuit breaker 6 3A 1410 G111 P2F1 ETA I 1 Antenna K 100 Filser J 1 Speaker KL1 4 Ohm Std Peiker acustic K 1 PTT button LJ1 ST200 Secme L 1 Boom mike with cable Holmco od Peiker M 1 Rotary multipoint switch 9030 01 Marquardt N 1 4 Option Charging socket Cinch 73855...

Page 122: ...t points for the mounting brackets of an oxygen cylinder are provided on the starboard fuselage skin aft of the canopy coaming frame for the neck and further aft on a panel covering the spar stubs for the body Drawings for the installation of an oxygen system may be obtained from Schempp Hirth NOTE After installation of an oxygen system it is necessary to re establish the empty mass c g position o...

Page 123: ...mitter is possible in the following places and must comply with the relevant instructions provided by Schempp Hirth in the region of the fuselage centre frame next to the wheel housing on a panel covering the main spar stubs A list of ELT s currently approved by the LBA is found in the Maintenance Manual November 2003 Revision 7 13 2 ...

Page 124: ...KIRCHHEIM TECK Ventus 2c 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 transport 8 5 Cleaning and care November 2003 Revision 8 1 1 ...

Page 125: ...the Ventus 2c It also identifies certain inspection and maintenance requirements which must be followed if the sailplane is to retain that new plane performance and depend ability CAUTION It is wise to follow a planned schedule of lubrication and preventative maintenance based on climate and flying conditions encountered see section 3 2 of the Maintenance Manual November 2003 Revision 8 1 2 ...

Page 126: ...o operate lubricate those places in the fuselage and in the wing panels where plain bearings are used undercarriage flap and airbrake actuating linkage Cleaning and greasing the wheel s and the tow release mechanism s depends on the accumulation of dirt Rudder cables After every 200 flying hours and at every annual survey the rudder cables are to be inspected at the point where they feed through t...

Page 127: ... Flight and or Maintenance Manual must in any case be approved by the Luftfahrt Bundesamt LBA Repairs Before every take off and especially after the sailplane has not been used for a while it should be checked on the ground as shown in section 4 3 Check for any sign of a change in the condition of the aircraft such as cracks in the surface holes delamination in the CFRP GFRP structure etc If there...

Page 128: ...emperatures c Tie down In the case of a sailplane remaining rigged permanently it is important that the maintenance program includes rust prevention for the fittings on fuse lage wing panels and tailplane Tie down kits common in trade may be used to anchor the aircraft Dust covers should be regarded as essential for the sailplane d Preparing for road transport As the wing panels have a thin airfoi...

Page 129: ...terials may be used Petrol and alcohol may be used momentarily only thinners of all kinds are not recommended Never use chlorine hydrogen i e Tri Tetra Per etc The best polishing method is the buffing of thesurface by means of an edge buffing wheel fitted to a drilling or polishing machine Thereby hard wax is applied to the rotating disc and distributed crosswise over the surface WARNING To avoid ...

Page 130: ... the wet If water has found a way in the components should be stored in a dry environment and turned frequently to eliminate the water The sailplane should not be exposed unnecessarily to intense sunlight or heat and should not be subjected to continual loads in a mechanical sense WARNING All external portions of the sailplane exposed to sunlight must be painted white with the exception of the are...

Page 131: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 2c FLIGHT MANUAL Section 9 9 Supplements 9 1 Introduction 9 2 List of inserted supplements November 2003 Revision 9 1 1 ...

Page 132: ...HT MANUAL 9 1 Introduction This section contains the appropriate supplements necessary to safely and efficiently operate the Ventus 2c when equipped with various optional systems and equipment not provided with the standard aircraft November 2003 Revision 9 1 2 ...

Page 133: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 2c FLIGHT MANUAL 9 2 List of inserted supplements Date Section Title of inserted supplement November 2003 Revision 9 2 ...