Schempp-Hirth Ventus-3M Performance Preliminary Flight Manual Download | Manualshive

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SCHEMPP-HIRTH FLUGZEUGBAU GmbH, KIRCHHEIM/TECK

Ventus-3M „Performance“

FLIGHT MANUAL

March 2019
Revision –

7.3.34

I. Power plant operating unit MCU3 BG

(cont.)

B) Functional description (cont.)

6

. Operating notifications (cont.)

Number

HINWEIS_BENZINHAHN_OEFFNEN (36)

Display

Open fuel valve

Description

The Power plant is being extended or is extended, but the fuel shut-off valve is still
closed. This condition does not prevent the engine from starting. This message is
deleted automatically as soon as the fuel shut off-valve is opened.

Text
Short text

Open fuel valve

Number

HINWEIS_TANK_RESERVE (38)

Display

Low fuel level

Description

The tank capacity falls below a type-dependent threshold (approx. 6L). This message
is repeated every 4min while the engine is running, otherwise every 20min.

Text

Low fuel tank level. Limited engine operation time.

Short text

Low fuel level

Number

HINWEIS_BATTERIESPANNUNG (39)

Display

Bat. volt. low/high

Description

The battery voltage is outside the permissible range (<11.5V or too high). This may
limit the motor running time. This message is repeated at different intervals depending
on the battery status.

Text

Battery voltage out of range. Limited engine operation time.

Short text

Bat. volt. low/high

Number

HINWEIS_WASSERTEMP_HOCH (40)

Display

Water temp. high

Description

The cooling water temperature is above its limits.

Text

High cooling water temperature. Reduce engine speed or cool engine.

Short text

Water temp. high

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Summary of Contents for Ventus-3M Performance

Page 1: ... Registr No O H 1 0 3 1 Date of issue M a r c h 2 0 1 9 Pages as indicated by appr Are EASA approved by Type Certificate EASA A 627 vom 00 Monat 0000 This powered sailplane is to be operated in compliance with information and limitations contained herein Approval of translation has been done by best knowledge and judgement In any case the original text in German language is authorative ...

Page 2: ...rd of revisions Any revision of the present manual except actual weighing data must be recorded in the following table The new or amended text in the revised page will be indicated by a black vertical line in the left hand margin The revision number and the date will be shown on the bottom left hand side of the page ...

Page 3: ...n Unterschrift Revision No Affected section Affected page Date of issue Reference Date of Insertion Signature ÄB MB Änderungsblatt Modification Bulletin TM TN Technische Mitteilung Technical Note Hinweis Nicht eingefügte Berichtigungen sind zu streichen Das Verzeichnis der Seiten ist gegebenenfalls handschriftlich zu aktualisieren Note Cross out revisions which are not included The list of effecti...

Page 4: ...Seiten List of effective pages Abschnitt Affected section Seite Affected pages Ausgabedatum Date of issue Bezug Reference 0 0 1 1 0 1 2 0 2 1 0 2 2 0 2 3 0 2 4 0 2 5 0 2 6 0 2 7 0 2 8 0 2 9 0 2 10 0 2 11 0 2 12 0 3 1 März 2019 März 2019 ÄB MB Änderungsblatt Modification Bulletin TM TN Technische Mitteilung Technical Note ...

Page 5: ...fective pages Abschnitt Affected section Seite Affected pages Ausgabedatum Date of issue Bezug Reference 1 1 0 1 1 1 1 2 1 1 3 1 1 4 1 1 1 4 1 2 1 4 1 3 1 4 2 1 5 1 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 ÄB MB Änderungsblatt Modification Bulletin TM TN Technische Mitteilung Technical Note ...

Page 6: ...22 2 2 2 CS 22 2 3 1 CS 22 2 4 1 CS 22 2 4 2 CS 22 2 5 1 CS 22 2 6 1 CS 22 2 7 1 CS 22 2 8 1 CS 22 2 9 1 CS 22 2 10 1 CS 22 2 11 1 CS 22 2 12 1 CS 22 2 12 2 CS 22 2 13 1 CS 22 2 14 1 CS 22 2 15 1 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 ÄB MB Änderung...

Page 7: ... 3 0 3 1 1 CS 22 3 2 1 CS 22 3 3 1 CS 22 3 4 1 CS 22 3 5 1 CS 22 3 6 1 CS 22 3 7 1 CS 22 3 7 2 CS 22 3 7 3 CS 22 3 7 4 CS 22 3 7 5 CS 22 3 7 6 CS 22 3 7 7 CS 22 3 8 1 CS 22 3 9 1 CS 22 3 9 2 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 ÄB MB Änderungsblatt Modification Bulle...

Page 8: ...1 4 CS 22 4 3 1 5 CS 22 4 3 1 6 CS 22 4 4 1 CS 22 4 5 1 1 CS 22 4 5 1 2 CS 22 4 5 1 3 CS 22 4 5 1 4 CS 22 4 5 2 1 CS 22 4 5 2 2 CS 22 4 5 2 3 CS 22 4 5 2 4 CS 22 4 5 3 1 CS 22 4 5 3 2 CS 22 4 5 3 3 CS 22 4 5 3 4 CS 22 4 5 3 5 CS 22 4 5 3 6 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 ...

Page 9: ... 22 4 5 6 1 CS 22 4 5 6 2 CS 22 4 5 6 3 CS 22 4 5 7 1 CS 22 4 5 7 2 CS 22 4 5 7 3 CS 22 4 5 8 CS 22 4 5 9 1 CS 22 4 5 9 2 CS 22 4 5 9 3 CS 22 4 5 9 4 CS 22 4 5 9 5 CS 22 4 5 10 CS 22 4 5 11 CS 22 4 5 12 CS 22 4 5 13 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März...

Page 10: ...ion Seite Affected pages Ausgabedatum Date of issue Bezug Reference 5 5 0 5 1 1 CS 22 5 2 1 CS 22 5 2 2 CS 22 5 2 3 CS 22 5 2 4 5 3 1 5 3 2 1 5 3 2 2 5 3 3 1 5 3 3 2 5 3 4 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 ÄB MB Änderungsblatt Modification Bulletin TM TN Technische Mitteilung Technical Note ...

Page 11: ...ist of effective pages Abschnitt Affected section Seite Affected pages Ausgabedatum Date of issue Bezug Reference 6 6 0 6 1 1 6 2 1 6 2 2 6 2 3 6 2 4 6 2 5 1 6 2 5 2 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 ÄB MB Änderungsblatt Modification Bulletin TM TN Technische Mitteilung Technical Note ...

Page 12: ...11 7 3 12 7 3 13 7 3 14 7 3 15 7 3 16 7 3 17 7 3 18 7 3 19 7 3 20 7 3 21 7 3 22 7 3 23 7 3 24 7 3 25 7 3 26 7 3 27 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März ...

Page 13: ... 32 7 3 33 7 3 34 7 3 35 7 3 36 7 3 37 7 3 38 7 3 39 7 3 40 7 3 41 7 3 42 7 3 43 7 3 44 7 3 45 7 3 46 7 3 47 7 3 48 7 3 49 7 3 50 7 3 51 7 3 52 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 ÄB MB ...

Page 14: ...11 1 7 11 2 7 11 3 7 11 4 7 12 1 7 12 2 7 12 3 7 12 4 7 12 5 7 12 6 7 13 1 7 13 2 8 0 8 1 1 8 2 1 8 2 2 8 3 1 8 4 1 8 5 1 8 5 2 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 März 2019 Mä...

Page 15: ...MANUAL 0 2 12 0 2 Verzeichnis der Seiten List of effective pages Abschnitt Affected section Seite Affected pages Ausgabedatum Date of issue Bezug Reference 9 9 0 9 1 1 9 2 1 März 2019 März 2019 März 2019 ÄB MB Änderungsblatt Modification Bulletin TM TN Technische Mitteilung Technical Note ...

Page 16: ... FLIGHT MANUAL March 2019 Revision 0 3 1 0 3 Table of contents Section General 1 Limitations 2 Emergency procedures 3 Normal operating procedures 4 Performance 5 Weight balance 6 Aircraft and systems description 7 Aircraft handling care and maintenance 8 Supplements 9 ...

Page 17: ...GmbH KIRCHHEIM TECK Ventus 3M Performance FLIGHT MANUAL March 2019 Revision 1 0 Section 1 1 General 1 1 Introduction 1 2 Certification basis 1 3 Warnings cautions and notes 1 4 Description and technical data 1 5 Three side view ...

Page 18: ...rovide pilots and instructors with all necessary information for the safe and efficient operation of the powered sailplane This manual includes at first all the material that needs to be provided to the pilot according to EASA airworthiness code CS 22 It also contains supplemental data and operating procedures which could in the manufacturer s opinion be useful for the pilot ...

Page 19: ...on basis This self launching powered sailplane model designation V e n t u s 3 M has been approved by the European Aviation Safety Agency EASA in compliance with the airowrthiness requirements contained in CS 22 vom 05 März 2009 The Type Certificate is No EASA A 627 and was issued on MONAT Category of Airworthiness UTILITY ...

Page 20: ...ans that the non observation of the indicated procedure leads to an immediate or important degradation of the flight safety CAUTION means that the non observation of the indicated procedure 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 CS 22 Pages marked ...

Page 21: ...ters 34 9 US Gal 29 0 IMP Gal The wing shells are a CFRP foam sandwich construction with spar flanges of carbon fiber rovings and shear webs made from GFRP foam sandwich Fuselage The pilot has a semi reclined position in the comfortable cockpit The one piece canopy hinges forward and opens to the front The cockpit region is constructed as a Kevlar carbon glass fiber laminate in order to achieve a ...

Page 22: ...GFRP foam sandwich Optionally a water ballast trim tank with a capacity of 7 8 liter 2 06 US Gal 1 72 IMP Gal can be integrated in the fin The dumping valve of the water ballast trim tank in the vertical fin is linked to the dump valves of the wing water ballast tanks Controls Rigging the wing panels and the tail will automatically hook up the control surfaces ...

Page 23: ...he engine bay in the fuselage cone The power plant is stopped by reducing the airspeed and turning off the ignition After turning off the ignition the retraction process is conducted automatically by the power plant control unit MCU 3 With the power plant control unit MCU 3 apart from the ignition switch the RPM indicator the fuel valve and the throttle control no more controls have to be consider...

Page 24: ...ength 6 78 m 22 24 ft Width 0 62 m 2 03 ft Height 0 81 m 2 66 ft Weight mass Empty mass from approx 395 kg 870 83 lb Empty mass with power plant removed approx 345 kg 760 59 lb Maximum all up mass 600 kg 1322 77 lb Wing loading 38 3 55 4 kg m 7 84 11 34 lb ft2 Engine Model SOLO 2625 01i Power Manufacturer 45 kW at 6200 RPM Fa Solo Kleinmotoren GmbH Propeller Model Manufacturer KS 1G 152 R 122 Fa T...

Page 25: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 3M Performance FLIGHT MANUAL March 2019 Revision 1 5 1 1 5 Three side View ...

Page 26: ...n 2 2 Airspeed 2 3 Airspeed indicator 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 of operation 2 12 Minimum equipment 2 13 Aerotow and winch launch 2 14 Other limitations 2 15 Limitation placards ...

Page 27: ...n 2 1 1 2 Limitations 2 1 Introduction This section includes operating limitations instrument markings and basic placards necessary for safely operating the aircraft its standard systems and its standard equipment The limitations included in this section and in section 9 have been approved by the EASA ...

Page 28: ...1 180 km h 97 kt 112 mph Do not exceed this speed with the given flap settings VFE_L Maximum speed for flap extended on setting L 150 km h 81 kt 93 mph Do not exceed this speed with the given flap setting VRA Rough air speed 180 km h 97 kt 112 mph Do not exceed this speed while flying in strong turbulence Strong turbulence is met in lee wave rotors thunderclouds etc VA Maneuvering speed 180 km h 9...

Page 29: ...m speed for winch launch 150 km h 81 kt 93 mph Do not exceed this speed during a winch launch Vmax Maximum speed with power plant extended 180 km h 97 kt 112 mph Do not exceed this speed with power plant extended VPOmin Minimum speed for extending retracting the power plant 92 km h 50 kt 57 mph Do not extend retract the power plant outside this speed range VPOmax Maximum speed for extending retrac...

Page 30: ...tted Green arc 102 180 km h 56 97 kt 64 112 mph Normal operating range lower limit is the speed 1 1 times VS1 at maximum mass with c g in the most forward position and flaps at the neutral position upper limit is the max allowed speed in rough air White arc 94 180 km h 51 97 kt 58 112 mph Positive flap operating range Lower limit is the speed 1 1VS0 at maximum mass and in landing configuration upp...

Page 31: ...us power 45 KW 61 PS at 6200 min 1 Maximum permitted coolant Liquid temperature 115 C Fuel premium unleaded Not below RON 95 AVGAS 100LL or mixtures of the two fuels Oil lubrication Fuel oil mixtrue 1 50 2 with Castrol ACT EVO 2T or Castrol Power 1 RS 2Tor Castrol GO 2T or Castrol Super TT or Castrol TTS or other two stroke engine oils according to JASO FC or JASO FD Propeller manufacturer Technof...

Page 32: ... 13 0 3 43 2 86 39 0 10 3 8 58 Usable fuel 12 7 3 35 2 79 12 0 3 17 2 64 12 0 3 17 2 64 36 7 9 69 8 07 Non usable fuel 0 3 0 08 0 07 1 0 0 26 0 22 1 0 0 26 0 22 2 3 0 6 0 51 SN 21 after manufacture Ventus 3M SN 21 Tank in fuselage Tanks in inboard wing panels Total capacity incl optional tanks left Option right Option Liter US Gal IMP Gal Liter US Gal IMP Gal Liter US Gal IMP Gal Liter US Gal IMP ...

Page 33: ...ndicator TFT Display 40 115 C 25 bzw 95 115 C 115 C blinkend Illustration Green range Yellow range Red range red flashing display operation note Fuel Quantity Indicator Operating range 7 L 6 bis 0 L TFT Display Fuel content fuselage and wing tank s 3 Fuel content only fuselage tank flashing Illustration Red flashing display Warning message 1 If the RPM is in the area between 6250 and 6600 RPM for ...

Page 34: ...ed take off and landing mass without water ballast with installed power plant 545 kg 1202 lb with removed power plant 512 kg 1129 lb Maximum permitted mass of non lifting parts with installed power plant 365 kg 805 lb with removed power plant 320 kg 705 lb Minimum permitted take off and landing mass with installed power plant 446 kg 983 lb with removed power plant 401 kg 884 lb Maximum permitted m...

Page 35: ...orward power plant removed c g position 300 mm 11 81 in aft of datum plane power plant installed 320 mm 12 60 in aft of datum plane Maximum rearward 430 mm 16 93 in aft of datum plane c g position It is extremely important not to exceed the maximum rearward c g position which is met by observing the minimum seat load The minimum seat load is given in the loading table and is shown by a label in th...

Page 36: ... GmbH KIRCHHEIM TECK Ventus 3M Performance FLIGHT MANUAL March 2019 CS 22 Revision 2 8 1 2 8 Approved maneuvers The powered sailplane is certified in category Utility self launching Warning Aerobatic maneuvers are NOT approved ...

Page 37: ...2 Revision 2 9 1 2 9 Maneuvering load factors The following maneuvering load factors must not be exceeded o With airbrakes retracted at VA 180 km h 97 kt 112 mph n 5 3 g n 2 65 g at VNE 280 km h 151 kt 174 mph n 4 0 g n 1 5 g o With airbrakes extended at VNE 280 km h 151 kt 174 mph n 3 5 g n 1 5 g ...

Page 38: ... Revision 2 10 1 2 10 Flight crew The powered sailplane is single seated Observe the minimum seat load In case the minimum seat load can t be achieved ballast must be installed to compensate this to a permissible configuration See also section 6 2 2 Weight and Balance Record Permitted Payload Range ...

Page 39: ...rformance FLIGHT MANUAL March 2019 CS 22 Revision 2 11 1 2 11 Kinds of operation This powered sailplane is approved for o VFR flying in daytime o cloud flying up to a maximum mass of 490 kg 1080 lb with the prescribed minimum equipment installed see page 2 12 ...

Page 40: ...ith page 2 3 1 1 Altimeter 1 Outside air temperature indicator OAT with sensor when flying with water ballast red line at 2 C 35 6 F 1 Magnetic compass 1 Engine control unit with RPM indication Coolant liquid temperature indication Fuel quantity indication Engine time Warning signals 1 Rear view mirror 1 Four piece safety harness symmetrical 1 automatic or manual parachute or 1 back cushion thickn...

Page 41: ...h slip ball 1x Variometer 1x VHF Transceiver Recommended additional equipment for cloud flying 1x Artifical horizon 1x Clock Warning Cloud flying is only permissible under following conditions o without waterballast o up to a maximum mass of 490 kg 1080 lb o if permitted by the applicable national air traffic act Note From experience gained to date it appears that the airspeed indicator system ins...

Page 42: ... 97 kt 112 mph Weak link in tow rope max 660 daN max 1484 lb Minimum length of tow rope 30 m 98 ft Tow rope material Hemp or Nylon Warning Only permissible on nose tow hook and with retracted power plant Winch launch Maximum launching speed 150 km h 81 kt 93 mph Weak link in winch cable max 750 daN max 1686 lb Warning Only permissible on c g tow hook and with retracted power plant ...

Page 43: ...spection program for the extension of the allowed service time If the results of this special inspection possibly after proper repair of detected defects are satisfactory the allowed service time is increased by 3000 hours up to a maximum of 9000 hours in total Thereafter the special inspection in accordance with the above mentioned inspection program must be repeated in intervals not exceeding 10...

Page 44: ...TECK Ventus 3M Performance FLIGHT MANUAL March 2019 CS 22 Revision 2 15 1 2 15 Limitation placards possible discrepancies from this see page 6 2 2 and 6 2 3 must be registered Note For further placards refer to the Maintenance Manual Ventus 3M ...

Page 45: ...FLIGHT MANUAL March 2019 Revision 3 0 Section 3 3 Emergency procedures 3 1 Introduction 3 2 Jettisoning the canopy 3 3 Bailing out 3 4 Stall recovery 3 5 Spin recovery 3 6 Spiral dive recovery 3 7 Engine failure carburettor freezing 3 8 Engine fire 3 9 Other emergencies ...

Page 46: ...T MANUAL March 2019 Revision 3 1 1 3 Emergency procedures 3 1 Introduction This section provides check lists and recommended procedures for dealing with emergencies that may occur Emergency situations can be minimized by proper pre flight inspections and regular maintenance ...

Page 47: ...vers on right and left side of canopy frame to their stops more than 90 o Lift the canopy as forward as possible with both red levers the canopy is held in its place at its rear end by the Röger Hook This process can by supported by pushing up the instrument panel with the legs o The aerodynamic forces will then lift the canopy at its front end and swing the canopy around the Röger Hook upwards to...

Page 48: ...isoning the canopy see page 3 2 1 bailing out is done as follows o Actuate release buckle of restraint system o Bend upper part of the body slightly forward Grab canopy coaming frame on fuselage with both hands and lift body Legs will tilt up the instrument panel if needed o Leave the cockpit to the left or to the right o Pull rip cord of manual parachute at a safe distance and height ...

Page 49: ...ecessary regain normal flight attitude with suitable countermeasures of rudder and aileron control Power plant extended The stall behaviour is only marginally influenced by the power plant Warning When stalling with extended power plant and ignition off or idling engine the vibration in the controls are superimposed from the turbulent airflow produced by the propeller therefore no significant stal...

Page 50: ... avoid exceeding the speed limits for positive flap settings when pulling out of the dive Spinning with the center of gravity in the foremost position is only possible with positive flap settings and very dynamic stall If stalling normally the aircraft mostly enters in a spiral dive sometimes with strong side slip angle or a side slip Recovery is done by applying the manoeuvers indicated for this ...

Page 51: ...y 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 0 and the permissible control surface deflections at VA VNE see section 2 2 must be observed In spiral dive or to stop the spiral dive airbrakes should not be extended since the permissible load factor with ...

Page 52: ...on and terrain If the safety of the selected landing procedure is improved the power plant should at least be partly retracted regardless of the position of the propeller blades with the manual control switch For retraction Ignition OFF or with the emergency system switch press DOWN Even with partly retracted power plant the glide ratio will improve considerably Thereafter Close fuel shut off valv...

Page 53: ...he engine has started Then pull up with about 2 g and reduce speed to the desired climb flight speed If possible increase the throttle carefully during the pull up with reducing airspeed to ensure sufficient lubrication of the engine CAUTION Observe the speed limits of the engine The loss of height from the moment of acceleration to the point where the aircraft is leveled off is in the order of 15...

Page 54: ...ted in the base of the instrument panel The emergency switch for the extension and the retraction of the power plant is accessible after flipping the red switching cover Rocker switch upwards Power plant extends Rocker switch downwards Power plant retracts Warning After opening the red protective cap all safety functions of the power plant control system are deactivated When the starter button is ...

Page 55: ...cockpit see section 7 2 Center the propeller as exactly as possible in the retracting position by varying the manual force on the handle of the propeller brake and hold the propeller there The power plant operating unit shows in the retracting position Retract the power plant with the emergency system CAUTION If it is not possible to hold the propeller exactly in the retracting position the power ...

Page 56: ... occur for two reasons The respective error message will be displayed on and stored in the power plant control unit 1 Failure of the generator With a defective generator the electrical power supply for the engine control system and the fuel injection is then only provided by the engine batterie in use As soon as their capacity is depleted the engine will stop and it will be impossible to retract t...

Page 57: ...tem will be ensured via the generator The power plant control unit will display the corresponding message If the electrical power supply of the power plant is provided alone by the generator the electrical power supply will collapse when the engine is stopped It s then impossible to retract or restart the engine CAUTION In case of a failure of the engine battery the nearest airport or nearest land...

Page 58: ...or the wiring in the aircraft For this reason starting the engine via an external battery is not permitted Replace the empty engine battery with a charged engine battery and then start the engine normally Proceed as follows to replace the engine battery o Open canopy remove the battery cover under the instrument panel and make the poles of the battery accessible o Replace the built in engine batte...

Page 59: ...wing steps must be carried out o CLOSE fuel shut off valve o Open throttle fully o When the engine is stopped Master switch OFF o Leave powerplant in extended position This procedure shall followed if applicable o On the ground o During take off o In flight Warning Cancel flight and land immediately Any manoeuvres which would cause high fuselage stress should be avoided ...

Page 60: ...as the heavier wing tends to drop somewhat sooner than normal apply opposite aileron Jammed elevator or flap control While jammed flaps will just result in a fixed profile flight behaviour a jammed 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 controls Flap lever ...

Page 61: ...inst an obstacle If there is the danger of the aircraft 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 o If possible always turn into the wind o As the wing tip is forced down push the control stick forward simultaneously Emergency water landing From experience gained f...

Page 62: ... inspection 4 5 Normal operating procedures and recommended speed 4 5 1 Methods of launching 4 5 2 Self launch Starting the engine runup taxiing and engine shut down on the ground 4 5 3 Flight Cross country flight propeller retracted 4 5 4 Flight Cross country flight propeller extended 4 5 5 Inflight starting of the engine 4 5 6 Inflight stopping of the engine retracting the powerplant 4 5 7 Appro...

Page 63: ...ormal operating procedures 4 1 Introduction This section provides checklists and amplified procedures for conducting the daily and pre flight inspection Furthermore this section includes normal operating procedures and recommended speeds Normal procedures associated with optional equipment are found in section 9 ...

Page 64: ...t t he water ballast connecting rod int rigging position o Insert spat stub of left wing panel forward into fuselage cut out Concentrate on lifting the trailing edge more than the leading edge also to avoid the aft locating pin get canted in the fuselage bearing o Check that the spar stub is inserted correctly on the far side of the fuselage o Ensure that the angular levers on the root rib are def...

Page 65: ...anels o Take round headed rigging tool screw it into wing pin locking lever on outbd panel and swing the latter upwards o Thereafter slide outboard panel onto spar stub of inboard panel until stub pin has just engaged in its corresponding bushing on the outboard wing panel align aileron coupling lap with slot on adjacent aileron on inbd Wing and push panel fully home o Finally swing wing pin locki...

Page 66: ...in front of the leading edge of the fin o Check whether the elevator actuating pins are really located by moving the elevator and if the horizontal tailplane is seated correctly on the fin After rigging o Check with the aid of a helper the controls for full and free movement in the correct sense Caution On the outboard wing panel do not seal the gaps between both outer ailerons between ailerons of...

Page 67: ... leading edge slightly and pull the tailplane forward and off Outer wing panels o Force the spring loaded locking pin of the winglet down with the mounting pin and pull the winglet from the outboard wing panel o Remove the covering between outer and inner wing Swing up locking lever with the aid of the mounting screw o Carefully pull off the outer wing panel Inner wing panels o Unlock airbrakes o ...

Page 68: ...he refueling system is located in the engine compartment at the top of the front bulkhead on the left hand side The toggle switch for the refueling pump is located in the cockpit above the back cover on the left side This means that only a loose fuel hose with quick disconnect coupling is required for refueling see description on the following pages and sketch on page 7 11 3 The refuelling hose us...

Page 69: ...powerplant operating unit shows the current content of the fuselage tank The fuselage tank is filled completely as soon as the expansion reservoir starts to be filled quickly The refueling has now to be stopped If the fuel tank is overfilled during refueling or if the fuel warms up fuel may spill via the ventilation pipes into the expansion reservoir in the baggage compartment As soon as the expan...

Page 70: ...l that is pumped further is automatically fed into the wing fuel tanks For accurate control of the actual amount of fuel on board it is recommended to completely empty the wing fuel tanks before refueling see page 4 2 3 8 Before refueling the wing fuel tanks ensure that the vent lines of the wing fuel tanks are also connected to the fuselage Otherwise overflowing fuel from the wing fuel tanks may ...

Page 71: ...l to overflow from the fuselage fuel tank into the wing fuel tank The associated asymmetry of the wing loading must be taken into account during take off Before self launching with wing tank s that are not or partially filled make sure that the contents of the fuselage tank is sufficient for a safe self launch If necessary keep the wings horizontal before take off until the fuselage tank is suffic...

Page 72: ...ng unit If the fuselage tank starts to empty the fuel content displayed on the operating unit flashes when the reserve quantity of 6 liter fuselage tank is reached In addition a warning tone sounds The warning can be switched off by pressing the rotary switch The warning appears again as soon as the tank capacity has been reduced by another liter Optional wing tank s In order to record the actual ...

Page 73: ...tary switch is not operated for more than 5 seconds the operating unit accepts the entered value for the fuel quantity and automatically returns to the normal operating mode If the entered value for the fuel content in the wing fuel tank s is greater than zero and the fuel content in the fuselage tank is not 6 liter or below the change in the fuel content on board during engine operation is calcul...

Page 74: ...isplay shows the new tank calibration factor e g 94 the calibration is successfully completed After returning to the main menu the display of the fuselage tank content is set to 13 L If the tank calibration factor is not displayed the tank calibration must be repeated The error message TANK CALIB FAILED Tank calibration failed occurs if the calibration would result in a tank calibration factor wit...

Page 75: ...spring loaded drain valve must be pushed inwards Wing fuel tank s Option If the fuselage fuel tank is not completely filled the contents of the wing fuel tank s may be emptied into the fuselage fuel tank To do this lift the wing with the wing fuel tank to be emptied to allow the fuel to drain quickly Alternatively it is possible to transfer the contents of a wing fuel tank to an external receptacl...

Page 76: ...occur when these daily inspections are neglected or carried out carelessly When walking around the aircraft check all surfaces for paint cracks dents and unevenness In case of doubt ask licensed maintenance personnel for advice o Open the canopy and check the function of the gas strut for opening the canopy o Check that the main pin is secured o Check all control elements in the cockpit by visual ...

Page 77: ...age o Clean and grease water dump valves if necessary o Check outboard wing panels for proper connection locking lever must be below upper wing surface and its cover must be installed and sealed o Check the flaperons of the outer wing panels for proper condition and free movement Check for unusual play by gently shaking the trailing edge Check hinges for damage o Check the flaperons of the inner w...

Page 78: ...lon and both signal generators on the upper belt pulley which are needed for the automatic retraction process o Propeller brake Check easy movement of brake lever and clearance to brake bell in inactive position condition of brake lever with attachments of Bowden cables wear of brake pad Check condition of brake servo and Bowden cable from brake servo to brake lever Check condition and function of...

Page 79: ... and rear spindle drive mounting o Check the exhaust manifold exhaust joint exhaust coupling and silencer for damage and cracks o Pay attention to scuffing marks on components and cables o Check arresting wire and the respective attachments o Check the function of the engine door kinematics o Turn the propeller several times by hand Check for abnormal noise or stiffness in the engine o Actuate the...

Page 80: ...il wheel 2 5 bar 36 PSI o Mount the TEK probe if present and check TEK line When blowing from the front onto the probe the connected variometers must indicate climbing If equipped with tail tank optional o Check that fin tank spill holes are clear o Check water ballast level in fin tank In case of doubt discharge ballast o Check dump valve of the tail tank at the fin bulkhead for cleanness 5 ...

Page 81: ...y should be checked its value is 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 After a ground loop especially the rear part of the fuselage tube and the transition to the vertical tail has to be checked for damage and detached bulkheads To do so support the wing...

Page 82: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 3M Performance FLIGHT MANUAL March 2019 CS 22 Revision 4 4 1 4 4 Pre flight check ...

Page 83: ...ard c g positions Knob forward to first third of its 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 aircaft 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 th...

Page 84: ...0 to 150 km h 70 81 kt 68 93 mph for higher all up masses At higher towing speeds and 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 propelle...

Page 85: ... to climb excessively steeply 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 position slightly pushed forward in case of c g in central 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 att...

Page 86: ...erfect condition are available Furthermore there is not much point in launching by winch for a soaring flight if the release height gained is less than 300 m 984 ft In case of doubt reduce all up mass by dumping water ballast 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 using seat cushions it must ...

Page 87: ...d Ignition circuit check o Warm up engine CHT ca 40 C 104 F o Set rev to 4000 RPM o Select Automatic ignition circuit Check AUTO or Manually select both ignition circuits MANUAL LEFT RIGHT The drop in rev has to be smaller than 300 RPM o After returning to both ignition circuits the engine should return to primarily RPM b Runup Increase speed to full throttle before starting or when starting up Fu...

Page 88: ...r to achieve a narrow turning circle d Engine shut down on the ground If the engine is stopped on the ground with the ignition switch the powerplant control system will switch into the process for the automatic positioning of the propeller But on the ground the automatic retraction of the powerplant is not possible without manual help To avoid unnecessary power consumption of the powerplant contro...

Page 89: ... its aft range o Set flaps at 0 position or at 1 in crosswind conditions o Pull control stick fully back o Apply full throttle briskly When accelerating to full throttle take care that the tail wheel just remains on the ground for better directional control o On reaching a speed of about 40 km h 22 kt 25 mph reset flaps to 2 on soft ground forward C G to L and adjust the elevator control only so t...

Page 90: ...igh ambient temperatures the coolant temperature rises too high the cause may also be the anti freeze proportion being too much for such temperatures The effectiveness of coolant liquid with less anti freeze is significantly better Caution Even if you re not going to take off with own power but it is possible to put the engine into operation later in flight it is strongly recommended to carry out ...

Page 91: ... the stick while flying between 115 and 125 km h 62 67 kts 71 77 mph in flap setting 0 With mid point c g positions the trim range is from approx 80 km h flap position L to approx 230 km h flap position S1 Flying characteristics are pleasant and the controls are well harmonised Turn reversal from 45 to 45 can be accomplished without any noticeable skidding Ailerons and rudder may be used to the li...

Page 92: ...the full deflection range is permissible Avoid especially sudden elevator control movements In strong turbulence i e in wave rotor thunderclouds visible whirlwinds or when crossing mountain ridges the speed in rough air VRA 180 km h 97 kt 112 mph must not be exceeded With the c g at an aft position the control stick movement from the point of stall to maximum permissible speed is relatively small ...

Page 93: ...t speeds above maneuvering speed the pilot should actively try to slow down the extension movement of the airbrakes Aerodynamic forces will strongly such out the airbrakes Attention should be paid that in a dive with the airbrakes extended the aircraft should be pulled out less abprubtly than with retracted airbrakes see section 2 9 A dive at VNE 280 km h 151 kt 174 mph with the airbrakes fully ex...

Page 94: ...lways well suited to the actual flying speed For smooth thermals flap setting 2 is recommended In turbulent thermals which require a quick aileron response flap setting 1 is advantageous Near the lower end of the optimum thermalling speeds the pilot may even use flap setting L especially at high all up masses or in updrafts with hardly any variation in flying speed For a speed polar diagram please...

Page 95: ...ns speed increases again and will then drop to stalling speed Note Befor reaching stalling speed the ASI reading drops quickly depending on the c g position The ASI starts oscillating because of the turbulent airflow affecting the pitot pressure probe When reaching a stalled condition with the c g in rearward positions the aircraft can be maintained in this condition with the stick fully pulled ba...

Page 96: ...its nose or wing Normal flying attitude is regained by applying corresponding control deflections The loss of height from the beginning of the stall until regaining a normal level flight attitude depends on the time of correction of the stalled flight condition and can be between 60 m and 150 m 200 500 ft Influence of Water Ballast Apart from higher stall speeds caused by the higher mass in flight...

Page 97: ... 100 km h 54 kt 62 mph o a glide in clean sailplane configuration Thereby the height to be consumed in glide should not be less than 500 m 1640 ft The maximum range in glide is achieved at a speed of approx 115 km h 62 kts 71 mph resulting in an average speed of around 110 km h 59 kts 68 mph In addition the range of course also depends on the amount of water ballast carried and decreases with high...

Page 98: ...to stalling from turning flight to the stalling behaviour with the power plant retracted Stall speeds see page 5 2 2 When the engine is running ignition ON there is a strong increase in the engine noise when stalling Warning When stalling with extended power plant and engine idling or with ignition off the turbulent airflow produced by the propeller superimposes the vibration in the controls so th...

Page 99: ...a suitable landing field at 200 m 656 ft AGL than eg starting it at 500 m 1640 ft AGL above a forest or similar Should a flight be planned over long distance without any acceptable landing fields the power plant should be extended at a height giving sufficient time for all emergency procedures and if necessary for re retracting the power plant 2 Starting the Engine in Flight See also check list on...

Page 100: ...movement of the propeller close to the retraction position can be accelerated by pressing the starter button electronically controlled pulse operation of the starter Caution The starter control interrupts the impulse operation as soon as the propeller is approx 15 in front of the retraction position The further movement of the propeller to the retraction position is only done by the aerodynamic fo...

Page 101: ...the manual propeller brake again o Observe the propeller in the rearview mirror By varying the manual force on the handle of the propeller brake center the propeller as precisely as possible in the retraction position with the aid of the aerodynamic forces and then hold on tight In retraction position the power plant operating unit unit shows o Retract the engine with the manual control switch Cau...

Page 102: ...ly and repeatedly If it is not possible to retract the power plant completely and there is still sufficient flight altitude then the power plant must be extended again to start the retraction process again o To repeat the retraction process and return to automatic mode first fully extend the power plant again using the ignition switch note the position displayed on the power plant operating unit o...

Page 103: ...trim Caution For the approach or for the landing especially at cross wind the flaps can also be set to 2 or 1 to improve the effectiveness of the ailerons and the handling of flaps for approach and landing The approach speed quoted previously should then be increased by at least 5 km h 3 kts 3 mph Side slip Side slipping is very effective landing aid please also see page 4 5 7 2 Side slips in 18 n...

Page 104: ... and increased yaw angle a slow pitch 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 airbrakes 3 During side slip with not completely filled water ballast tanks a shift of the water ballast can arise which can change the flight behaviour Slips with water ballast are therefor not...

Page 105: ... up mass 525 kg 1157 lb Approx sink rate 2 75 m s 540 ft min At IAS 115 k mh 62 kt 71 mph Approx L D 1 11 6 Because of the reduced performance the approach has to be started at a significantly higher altitude in order to perform the landing approach with the same procedure as in glider condition Warning 1 Be cautious when extending the airbrakes Due to the additional drag with the extended power p...

Page 106: ... the flap may be set at 0 for improved aileron response during 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 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 unnecessarily The landing run may be ...

Page 107: ... water only through 4 round openings in the upper wing surface The openings are closed with filler caps provided with thread The filler caps have a slit and may be opened with the help of the rigging tool or a coin A hole in the filler caps serves for venting the tank The hole features a valve preventing the loss of bigger amount of water when the wings are i e placed on the ground Warning The hol...

Page 108: ...ower than filling the inner and outer tanks individually as the flow through the separation point between the inner and outer tanks is reduced When filling the tanks it must be ensured that the maximum water ballast is not exceeded see 6 2 2 and 6 2 3 Dumping the water ballast The operating handle for dumping the water ballast is located on the right hand side of the cockpit It is guided in a slid...

Page 109: ... of the aircraft is slightly different from its behaviour without water ballast The stall speeds are higher see section 5 2 2 and for correcting the flight attitude larger control surface deflections are required Furthermore more height is lost until a normal flight attitude is regained Warning In the unlikely event of the tanks emptying unevenly recognized by having to apply more opposite aileron...

Page 110: ...or venting Also with completely filled tank the uppermost spill hole 7 8 kg Liter 2 06 US Gal 1 72 IMP Gal always must be open The ballast quantity to be filled depends on the water load in the wing tanks see loading table on section 6 2 5 Filling is done with rigged or de rigged horizontal tailplane as follows o Before filling the tank always tape closed one hole less than the load required measu...

Page 111: ... valves are avoided thereafter with valves closed pulling the drain plugs home with the threaded tool used to attach the tailplane o There is little point in loading much 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 angles of bank o If possible all water ballast is to be dumped before conducting a...

Page 112: ...AS This difference does not affect the structural integrity or load factors but to avoid any risk of flutter the following indicated values IAS must not be exceeded Altitude IAS m ft Km h kts mph 0 0 280 151 174 1000 3281 280 151 174 2000 6562 280 151 174 3000 9843 280 151 174 4000 13123 266 143 165 5000 16404 252 136 156 6000 19685 239 129 148 7000 22966 226 122 140 8000 26247 214 114 133 9000 29...

Page 113: ... 4 5 9 Warning For the preservation of a proper surface finish free from cracking the manufacturer strongly advises against high altitude flights with temperatures below 20 C 4 F A steep descent with the airbrakes extended should only be conducted in case of emergency instead of the airbrakes the undercarriage may also be extended to increase the rate of sink Caution From many years of experience ...

Page 114: ...mass in which it s raining is also descending so that compared with a wet aircraft in calm air the sink rates encountered are even 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 as caused by snow ice or heavy rain may result in h...

Page 115: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 3M Performance FLIGHT MANUAL March 2019 CS 22 Revision 4 5 13 4 5 13 Aerobatics Aerobatics are not permitted ...

Page 116: ...5 5 Performance 5 1 Introduction 5 2 Data structured according to CS 22 5 2 1 Airspeed indicator system errors 5 2 2 Stall speeds 5 2 3 Take off distances 5 2 4 Additional information 5 3 Data not structured according to CS 22 5 3 1 Demonstrated crosswind performance 5 3 2 Flight polar 5 3 3 Range 5 3 4 Noise data ...

Page 117: ... Revision 5 1 1 5 Performance 5 1 Introduction This section provides approved data for airspeed calibration stall speeds and additional information The data in the charts has been computed from actual flight tests with a powered sailplane in good condition and using average piloting techniques ...

Page 118: ...s in the indicated airspeed IAS caused by the measurement of Pitot Static pressure may be read from the following calibration chart This chart is applicable to free flight PITOT pressure source Fuselage nose cone STATIC pressure source Fuselage tail boom approx 0 8 m 31 5 in in front of the fin All airspeeds shown in this manual are indicated airspeeds IAS as registered by the airspeed indicator ...

Page 119: ...ed Flaps at L hm h kts mph 74 3 40 1 6 46 1 9 72 5 39 2 7 45 3 Airspeed indication is oscillating with rearward c g positions The loss of height from the beginning of the stall until regaining a normal level flight attitude is up to 110 m 360 ft Configuration Powerplant extended Full throttle Wingspan 18 m All up mass approx 600 kg 1322 lb 600 kg 1322 lb C G position aft of datum 320 mm 13 in 430 ...

Page 120: ...5 C 59 F 30 C 86 F m ft m ft m ft m ft m ft Ground run distance until lift off 0 500 1000 1500 2000 0 1640 3281 4921 6562 191 208 226 246 268 616 682 741 807 879 216 235 256 279 304 708 771 839 915 997 243 265 288 313 342 797 869 944 1026 1122 272 296 322 351 382 892 971 1056 1151 1253 Total distance over 15m 50 ft obstacle 0 500 1000 1500 2000 0 1640 3281 4921 6562 303 330 359 391 426 994 1082 11...

Page 121: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 3M Performance FLIGHT MANUAL March 2019 CS 22 Revision 5 2 4 5 2 4 Additional information None ...

Page 122: ...entus 3M Performance FLIGHT MANUAL March 2019 Revision 5 3 1 5 3 DATA not structured according to CS 22 5 3 1 Demonstrated crosswind performance The maximum crosswind velocity at which take offs and landings have been demonstrated is 20 km h 11 kts ...

Page 123: ...speed of 90 km h 48 kts 56 mph Best L D At an airspeed of 120 km h 65 kts 75 mph Speed polar diagram see page 5 3 2 2 not yet measured Powerplant extended Ignition OFF Flap position 2 Wingspan 18 m All up weight 600 kg 1322 lb Sinken 2 46 m s 484 ft min 4 8 kts At airspeed 115 km h 62 kts 71 mph Maximum Power applied Flap position L Wingspan 18 m All up weight 525 kg 1157 lb 600 kg 1322 lb Best cl...

Page 124: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 3M Performance FLIGHT MANUAL March 2019 Revision 5 3 2 2 Speed polar diagram not yet measured ...

Page 125: ... km 78 nm b The following values are based on the sawtooth method see page 4 5 4 and the following parameters Climbing with maximum continuous power All in weight 530 kg 1168 lp climbing speed 98 km h 53 kts 61mph Climbing from 500 m 1640 ft MSL to 1500 m 5000 ft MSL Gliding at the speed of the L D Fuel consumption approx 22 5 ltr h 5 9 US Gal h 4 9 IMP Gal h This results in an average cruising sp...

Page 126: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 3M Performance FLIGHT MANUAL March 2019 Revision 5 3 3 2 ...

Page 127: ... Noise data The noise level limit according ICAO Appendix 16 Volume I for the powered sailplane Ventus 3M equipped with the SOLO engine 2625 01i is 65 9 dB A Noise level limit 70 8 dB A and is thus far below the noise level limit It is nevertheless recommended to wear headphones when flying with the engine running ...

Page 128: ... and balance 6 1 Introduction 6 2 Weight mass and balance record and permitted payload range 6 2 1 Seat load of less than the required minimum 6 2 2 Weight and balance log sheet power plant installed 6 2 3 Weight and balance log sheet power plant removed 6 2 4 Wing water ballast load 6 2 5 Water ballast load in fin tank optional ...

Page 129: ...rcraft may be safely operated Procedures for weighing the aircraft the calculation method for establishing the permitted payload range and a comprehensive list of all equipment available are contained in the Ventus 3M Maintenance Manual The equipment actually installed during the last weighing of the aircraft is shown in the equipment list of the weight and balance report see also section 6 2 2 an...

Page 130: ... sand cushions in the pilot seat The ballast lead or sand cushion must be attached firmly to the lap belt mounting brackets The ballast weight is added to the payload in the seat o Ballast by means of Lead plates optional A trim ballast mounting provision is provided in the fuselage nose forward of the rudder pedal assembly The ballast mounting provision holds up to three 3 lead plates with a weig...

Page 131: ...Fin tank installed YES NO 3 Inspector Signature Inspector s stamp 1 Installed batteries see section 7 12 M one battery under the instrument panel C one or two batteries near the undercarriage are optional S one battery in the vertical fin optional At least one battery must be installed as the battery for the power plant 2 Fuel in wing tanks counts as water ballast and does not need to be respected...

Page 132: ... Signature Inspector s stamp 1 Installed batteries see section 7 12 M one battery under the instrument panel C one or two batteries near the undercarriage are optional S one battery in the vertical fin optional If the battery for the power plant has been removed any electrical consumer i e bug wipers connected to this battery may no longer be functional 2 Fuel in wing tanks counts as water ballast...

Page 133: ...6 kg 57 lb Note The inner wing tanks can be filled either directly or through the outer wing tanks Wing water ballast load When determining the max permitted wing water ballast load mWB_Wing the following data are helpful o Maximum all up mass with water ballast mmax kg o Empty mass of the aircraft mempty kg see sections 6 2 2 and 6 2 3 o Payload in cockpit mCockpit kg o Fin water ballast mFT kg s...

Page 134: ... the fin tank mFT is done with the aid of the diagram shown on the next page The maximum capacity of the fin tank is 7 8 kg litre 17 2 lb 2 06 US Gal 1 72 Imp Gal 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 Chosen Wing water ballast 90 kg 198 lb The diagram on the following pa...

Page 135: ...rformance FLIGHT MANUAL March 2019 Revision 6 2 5 2 Table Water Ballast Overview Caution Fill always full liters in the fin tank At the discontinuity of the diagram vertical axis wing water ballast the corresponding fin water ballast Full liters can be filled ...

Page 136: ...tems 7 1 Introduction 7 2 Cockpit description 7 3 Instrument panel 7 4 Undercarriage 7 5 Seat and restraint systems 7 6 Static pressure and total pressure system 7 7 Airbrake system 7 8 Baggage compartment 7 9 Water ballast system s 7 10 Power plant system 7 11 Fuel system 7 12 Electrical system 7 13 Miscellaneous equipment removable ballast oxygen ELT etc ...

Page 137: ... its systems 7 1 Introduction This section provides a description of the aircraft including the operation of its systems For details concerning optional and not standard systemy and equipment refer to section 9 Supplements For further descriptions of components and systems please refer to section 1 of the Maintenance Manual for the Ventus 3M ...

Page 138: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 3M Performance FLIGHT MANUAL March 2019 Revision 7 2 1 7 2 Cockpit Description ...

Page 139: ...on control a A small black ball knob on the right side of the instrument panel controls the amount of air for the canopy ventilation Open ventilation pull Close ventilation push b Adjustable ventilation nozzle on the right hand side of the cabin CLOSE nozzle turn clockwise OPEN nozzle turn counterclockwise For additional ventilation either the sliding window or the ventilation inlet in it can be o...

Page 140: ...ackward adjustment Pull handle back until pedals have reached the desired position Shortly pushing forward with the heels engages the locking device with an audible click Control handle for tow release mechanism s The yellow handle actuating the nose and or the c g tow release whichever is installed is to be found on the instrument panel Tow release s open pull Tow release s close release Undercar...

Page 141: ...me Canopy locked forward position Canopy unlocked rearward position To open the canopy swing both levers backwards Then lift the canopy by the levers with a little jerk or push the canopy upwards This will release the spring loaded lock in the rear area of the canopy frame Canopy jettisoning Red lever with white marking on the right and left side of the canopy frame Pull both levers back to jettis...

Page 142: ...opened rearward position Airbrakes lever Blue lever on the left hand side of the cockpit to operate the airbrakes Airbrakes locked forward position Airbrakes unlocked pulled by approx 40 mm 1 inch Airbrakes fully extended rearward position Flap lever Black lever on the seat pan mounting flange on the left for flap operation The crank guiding the lever features several positions to engage for an ap...

Page 143: ... the left side Adjustment of backrest The backrest is adjustable and pivot mounted on the seat pan It is longitudinally and inclinally adjustable to allow each pilot an optimal seating position Longitudinal adjustment not illustrated Three positions through three holes each on the right and left in the seat pan Insert the backrest with the fixed bolt into the selected hole and snap the spring load...

Page 144: ...the right side of the cockpit inner skin above the landing gear operation Fuel shut off valve OPEN forward position Fuel shut off valve CLOSED rearward position Rear view mirror The rear view mirror is mounted on the instrument panel cover and is intended to enable the pilot to visually monitor the power plant Starter button Red button on top of control stick Operate starter motor Push button Stop...

Page 145: ...pply brake Pull handle Release brake Release handle With the powerplant control unit manual operation of the propeller brake is only required if the automatic operation of the propeller brake via the brake servo is defective As long as the handle is pulled and held the mechanical propeller brake slows down the power plant at the small belt pulley The manual propeller brake may only be actuated whe...

Page 146: ...H KIRCHHEIM TECK Ventus 3M Performance FLIGHT MANUAL March 2019 Revision 7 3 1 7 3 1 Instrument Panel A description of the marked components I VII can be found on the following pages A description of the instruments is not included ...

Page 147: ...ion see page 7 3 5 ff II Pneumatic valve Optional toggle switch in the instrument panel for changing the variometer display TE tube to TE probe STATIC Static pressure or TE tube to TE probe TE dampened Tube to TE probe with constrictor III Outside air thermometer When flying with water ballast the outside temperature must not fall below 2 C 36 F ...

Page 148: ...tarter motor can be operated in any position of the power plant and independent of the engine speed see page 7 3 47 ff 2 Pulse Mode for propeller positioning After the power plant has been switched off the alignment of the propeller in the retraction position can be supported by pressing the starter button The propeller is then slowly turned with the starter motor until just before the retraction ...

Page 149: ... of the front engine compartment wall In the event of strong heat development in the engine compartment e g as a result of a fire the fire warning LED starts flashing when the temperature exceeds approx 140 C Caution When the power plant control system is switched on the fire warning LED flashes briefly for a self test VI Emergency system Description see page 7 3 47 ff VII Fuse panel Description s...

Page 150: ...e FLIGHT MANUAL March 2019 Revision 7 3 5 I Power plant operating unit MCU3 BG No Meaning 1 TFT Display All messages 2 Ignition switch with yellow cap 3 Memory Card SD Card Slot Data exchange Updates 4 Manual operation switch 5 Rotary selector switch with push button ...

Page 151: ... messages are displayed by the power plant operating unit If necessary the pilot can manually extend and retract the power plant manual operation The powerplant control system of the Ventus 3M consists of two main components 1 The MCU3 BG Power plant operating Unit is located in the instrument panel see page 7 3 1 It contains important control elements for controlling the power plant and displays ...

Page 152: ...ng circuit breakers must be closed o Master switch power plant Master switch Power plant o Power plant control system circuit breaker Power plant control Note After switching on the main switch of the power plant and the circuit breaker for the power plant control system a warning tone can be heard and a short moment of a completely white screen can be seen If the circuit breakers for the spindle ...

Page 153: ...ved away from its default position and there is no further interaction with the operating unit the screen and the cursor return to the default state after 20 seconds when in gliding mode In power plant operation mode this happens after 10 seconds The return is announced by a rotating hourglass Display in gliding mode Display during power plant operation Company Logo Aircraft Type Date Time Screen ...

Page 154: ...ssages and their meanings can be found in chapter I B 3 on page 7 3 31 Example for a critical error message Example for an operating notification Sensors for propeller position optional Direction of power plant movement Power plant travel modus automatic manual Power plant extended blinking during extension Warning Power plant retracted blinking during retraction Default position Main menu Ignitio...

Page 155: ... cooling water pump is switched off when the cooling water temperature has fallen below 60 C Note When the power plant reaches the fully extended position with ignition ON but is not started after a short period of time the electrical fuel pump and the cooling water pump will be shut off energy saving mode As soon as the starter button is pressed both devices are switched on again 3 Memory Card Sl...

Page 156: ...ration turned off Retraction of the power plant as long as the switch is held Spindle drive stops by itself when the power plant is fully retracted and the limit switch is reached c The manual control switch can be used to extend and retract the power plant in the following cases i on the ground recommended for pre flight inspection and maintenance ii when in flight the automatic operation of the ...

Page 157: ... the automatic propeller brake is opened and releases the propeller if the automatic propeller positioning has already started the process will be aborted e Return from manual mode to automatic mode i To continue the extension in automatic mode Ignition OFF and back to ON Continuation of the automatic extension process ii To continue retraction in automatic mode or automatic propeller positioning ...

Page 158: ...ing rotary selector switch navigate in the menu and function structure of the operating unit enter data Special characteristic If functional data are entered e g time or contents of wing fuel tanks this is done by pushing in the rotary selector switch and simultaneously turning it Turning it clockwise increases the value turning it counter clockwise decreases the value If the rotary selector switc...

Page 159: ...hapter I B 1 5 on page 7 3 28 1 3 Screen menu The rotary selector switch can be used to rotate the cursor to the various functions and to select the function by pressing the rotary selector switch The Motor battery voltage field 7 cannot be selected Further explanations can be found in this chapter under On Screen Menu on page 7 3 20 1 4 Coolant water temperature The coolant water temperature is d...

Page 160: ...sages various operating notifications Diverse 1 6 Power plant retracted The power plant retracted display appears statically as soon as the power plant is fully retracted and has actuated the limit switch If the symbol 6 flashes the power plant is retracting and has not yet reached the limit switch The limit switch for the retracted position of the power plant is located in the engine compartment ...

Page 161: ...nted numerically in revolutions per minute with a resolution of 50 rpm and also as a pointer on a colour scale in which the operating ranges are colour coded in accordance with section 2 5 If the corresponding limit values are exceeded the corresponding warning message appears on the TFT display The speed values are transmitted from the Trijekt engine control system to the operating unit RPM numer...

Page 162: ...e the generator does not supply any energy All electrical loads in the circuit of the main power plant switch are then supplied only by the engine battery b The symbol disappears with the main power plant switch closed if the following occurs Ignition is OFF or a charging voltage is present at the charge controller while the engine is running In this case the battery is charged if the generator wi...

Page 163: ...power plant system and maintains the power supply via the engine battery until the engine battery is exhausted 2 12 Power plant extended The display power plant extended appears statically as soon as the power plant is fully extended and has actuated the limit switch If the symbol 12 flashes the power plant is in the extension movement and has not yet reached the limit switch The limit switch for ...

Page 164: ...atus of the propeller position sensors P1 and P2 and the propeller stopper S can be displayed here This display can be activated or deactivated in Menu Setting Prop sensors 3 15 Direction of power plant movement The filled triangle shows the current direction of movement 3 16 Power plant travel modus In normal operation the power plant is automatically retracted and extended when the ignition swit...

Page 165: ...u If the cursor is moved to this position with the rotary selector switch and pressed the main menu is opened The main menu is described on page 7 3 21 4 19 Ignition circuit test Selecting this menu item starts the ignition circuit test function The MCU3 operating unit no longer has its own switch to test the individual ignition circuits This can be done in this function via the rotary selector sw...

Page 166: ...nd then pressing the rotary selector switch one of the offered functions is selected and started 1 1 Warning list All currently existing error messages are listed chronologically here and can be read in case of doubt It turned out that the error messages are confirmed quickly in the heat of the moment without having read the message The sense of this error message is then lost The messages are dis...

Page 167: ...time of the aircraft can be read Tot time There is also a Trip time which can be reset manually To do this select the Reset trip time item in the engine menu using the rotary selector switch and push it The Trip time value jumps back to 0 00 hours The additional parameters in the Engine menu show the current values of the generator charging current Gen Curr A the water pump current Pump curr A and...

Page 168: ...ay be to recalibrated To do this the fuel tank must be completely filled With the function Calib Main tank in the Fuel menu the calibration can be carried out Select the function with the rotary selector switch and press to select If a calibration has been carried out successfully a new value is entered for Tankfactor The calibration is now complete After a few moments the fuel content is correcte...

Page 169: ...nput for the contents of the wing fuel tanks safety measure The menu item Wing tank L is displayed in grey and cannot be selected The entry is made by selecting the function with the rotary selector switch By pressing down the rotary selector switch and simultaneously turning it the value for the wing tank to the right of Wing tank L is changed The displayed fuel content and its decrease are calcu...

Page 170: ...bol on the screen menu or by selecting Ignition test from the main menu First of all o Warm up the engine CHT approx 40 C o Set engine speed to approx 3000 RPM The automatic test AUTO carries out the test independently and displays the speed differences numerically To do this select and confirm the AUTO function The engine s speed may drop by max 300 RPM when switched to left or right ignition cir...

Page 171: ...t operating unit MCU3 BG cont B Functional description cont 1 4 Ignition circuit test cont The manual test is similar o Warm up motor CHT approx 40 C o Set engine s speed to approx 3000 rpm Select MANUAL and switch off the left ignition circuit by turning the rotary selector switch one position to the left and select LEFT ...

Page 172: ...rn to the right by one position then switches on both ignition circuits again a further position to the right switches off the right ignition circuit One position back to the left switches on both ignition circuits again The change in the engine s speed is automatically recorded and displayed The measurement is terminated by pressing the rotary selector switch and the ignition circuit test menu is...

Page 173: ...n the rotary selector switch and turn it in the pressed state Turn clockwise to increase a value turn counterclockwise to decrease it Date Time is used to set the battery buffered real time clock Brightness is used to adjust the brightness Auto dimming sets the time after which the display goes into energy saving mode and darkens slightly As soon as a switch or the rotary selector switch is operat...

Page 174: ...eries is displayed Analog meas shows the input voltage the voltage of the internal battery the raw value of the temperature sensor and the CPU temperature Boot menu is a menu for firmware updates and service settings that may only be performed by qualified personnel In the Boot Menu you can also download the log file of the operating unit 1 Retract power plant completely limit switch must be actua...

Page 175: ...ng notifications Operating notification should inform the pilot if individual steps in the process flow of an operation were not executed or not completely executed and if corrective measures have to be taken by the pilot to safely finish the current process For these reasons the operating notifications are sometimes combined with warning alerts to draw the pilot s attention to the display ...

Page 176: ...ive the corresponding switch must first be released and reset e g ignition off on or on off Text Engine movement paused Switch ignition off and back on or vice versa Short Text Engine move paused Number INFO_STARTER_BLOCKIERUNG 17 Display Engine start blocked Description Case 1 On turning on the operating unit the ignition is ON the power plant is fully extended and the starter button is pressed s...

Page 177: ...HOCH 25 Display RPM too high Description The propeller speed is in the red range This can normally only occur during a dive as the engine power is automatically throttled before reaching the red range Text Engine RPM too high Reduce flight speed Short text RPM too high Nummer HINWEIS_PROPELLER_AUSFAHREN 30 Display Extend engine Description Attempt to start engine with power plant not fully extende...

Page 178: ...high engine speed Retraction is prevented Text RPM too high to retract engine Short text RPM too high to retract engine Number HINWEIS_SPINDELSICHERUNG_AUSGELOEST 34 Display Spindle fuse triggered Description Manual automatic spindle travel attempt with spindle drive fuse triggered Text Spindle fuse triggered Engine movement not possible Short text Spindle fuse triggered Number HINWEIS_NOTBETRIEB_...

Page 179: ...ption The tank capacity falls below a type dependent threshold approx 6L This message is repeated every 4min while the engine is running otherwise every 20min Text Low fuel tank level Limited engine operation time Short text Low fuel level Number HINWEIS_BATTERIESPANNUNG 39 Display Bat volt low high Description The battery voltage is outside the permissible range 11 5V or too high This may limit t...

Page 180: ...e Text Battery supply malfunction Engine restart and retraction may be impossible Short text Battery malfunction Number HINWEIS_DAUER_GELBEDREHZAHL 42 Display RPM yellow 5min Description The yellow speed range has been exceeded for more than 5min Text Engine RPM too high Reduce RPM to green range Short text RPM yellow 5min Number HINWEIS_MOTOR_GANZAUSGEFAHREN 43 Display Motor fully extended Descri...

Page 181: ...orrective measures have to be taken by the pilot to end the unsafe condition in flight The cause of the fault must be determined and eliminated before the next power plant operation if the pilot is required to pay increased attention to the operation of the power plant due to the fault For these reasons error messages are always associated with warning displays to draw the pilot s attention to the...

Page 182: ...er FEHLER_SCHALTER_EINGEFAHREN 51 Display Retract sw malfunc Description Retract limit switch defective see FEHLER_SCHALTER_AUSGEFAHREN Text Retract end switch not detected Engine position unknown Short text Retract sw malfunc Number FEHLER_MAIN_FUSE 52 Display Main fuse trig Description No voltage at the power supply input probably because the external main fuse for the power plant Master switch ...

Page 183: ...e for position and speed sensors has tripped self resetting The fuse is automatically reset if possible No action of the pilot is necessary Without functional position sensors neither the automatic propeller stop nor an automatic spindle drive movement is possible Text Position sensors malfunction Automatic propstop and Power plant extend retract disabled Short text Pos sensor malfunc Number FEHLE...

Page 184: ... operation time Short text Cool pump malfunc Number FEHLER_WASSERPUMPE_STROM 61 Display Cooling malfunction Description Current consumption of the water pump too high or too low Possible causes Pump sucks air pump is blocked water pipe is blocked or broken water level is too low Text Engine cooling malfunction Overheat possible Limited engine operation time Short text Cooling malfunction Number FE...

Page 185: ...ation of the operating unit Text Emergency mode activated Normal operation disabled Short text Emerg mode activated Number FEHLER_POSITION1SENSOR 66 Display Prop sensor malfunc Description Propeller position sensor 1 has failed no signal Automatic retraction is not possible unit switches to manual operation The pilot must bring the propeller with the manual brake into the retraction position and r...

Page 186: ...s indicates a defective generator charge regulator or a tripped generator fuse Possibly the pilot can close a triggered generator fuse again Text Unusual battery discharge Limited engine operation time Short text Battery discharge Number FEHLER_LOW_CURRENT 69 Display Low generator curr Description The generator output current is too low to supply all consumers therefore the battery is discharged e...

Page 187: ...ing defect or the Trijekt fuse tripped the engine might still run Engine operation is not possible with a Triject defect Text Engine control malfunction CAN Short text Engine malfunc Number FEHLER_MOTORSENSOR 75 Display Engine malfunc 75 Description Error signal from the Trijekt Engine control unit Crankshaft sensor defective No engine operation possible Text Engine malfunction 75 Crankshaft senso...

Page 188: ...e valve malfunction Motor start not possible Apply full throttle Short text Throttle malfunc Warning If THROTTLE malfunc Is displayed during critical flight segments apply full throttle immediately Number FEHLER_SW_CRC 81 Display SG prog corrupt Description The program memory of the power plant control unit is damaged The program is stopped permanently for safety reasons The power plant control un...

Page 189: ...topper is extended even if this may destroy the propeller stopper Text Propellerstopper still in place Acknowledge to start anyway Short text Propstop in place Number FEHLER_PROPSTOPPERSCHALTER 84 Display Propstop malfunc Description Malfunction of the propeller stopper limit switch or the propeller stopper servo Automatic retraction is also possible without propeller stopper Text Propellerstopper...

Page 190: ... only limited engine operation is possible Text Supply switch malfunction Engine operation may be restricted Short text Supply sw malfunc Number MCU3_BG_ERROR_SG_OFFLINE 201 Display Com malfunc Description The data transmission from the power plant control unit to the operating unit is disturbed This indicates a defective wiring or a defective control unit Since there is no information on the cool...

Page 191: ...unit Serial 19 0018 Serial number Year continuous number HW version 2 1 0 Hardware version HW options Hardware options none here SW version 2 1 7 Software version SW options Software options none here SW date Jan 15 2019 Creation date of the software here 15 1 2019 BL version 2 1 7 Bootloader version BL date Jan 15 2019 Creation date of the bootloader here 15 1 2019 SG Separation line for Control ...

Page 192: ...rcuit breaker spindle drive Spindel drive o Fuse emergency system Emergency System The emergency system is already activated when the red switch flap is folded up operating notification Emergency mode activated in the operating unit The emergency switch which controls the spindle drive for the movement of the power plant is then accessible under the red switch flap Toggle switch UP Power plant ext...

Page 193: ...nowledge the operating instructions on the operating unit by pressing the rotary selector switch to confirm the warning message o Stop the propeller with the manual propeller brake handle left front in the cockpit see section 7 2 o By varying the manual force on the handle of the propeller brake the air stream can be used to center the propeller as precisely as possible in the retraction position ...

Page 194: ...vibrations during flight with idle power setting a regular readjustment of the spindle drive is to prevent creeping retraction of the powerplant This function is performed automatically by the powerplant control system during normal operation When operating with the emergency system this tracking function is not applicable Note If the circuit breaker for the power plant control system is still clo...

Page 195: ...table fuse 1 Master switch Power plant MAIN SW Circuit breaker 50 A Power plant The master switch power plant interrupts the power supply via the engine battery Batt E Caution If the power plant master switch is opened the power plant system is supplied by the generator via the supply switch 2 Master switch Avionic MAIN SW Circuit breaker 7 5 A Avionic The master switch avionic disconnects the ins...

Page 196: ...indel drive Circuit breaker 12 A Protection of the spindle drive for extend and retract the power plant 5 Powerplant control system fuse Power Plant syst Circuit breaker 7 5 A Protection of the operating and control unit for the power plant control without starter motor The following loads are individually protected by self resetting fuses within the control unit cooling water pump engine speed se...

Page 197: ...he position of the throttle valves the cooling water temperature the air pressure and the air temperature 8 Fuel pump fuse fuse 7 5 A Fuel pump Protection of the fuel pump of the engine control system and of the built in refuelling pump 9 Relay fuse Relay fuse 7 5 A Protection of relays for ignition 10 Fuse for avionic when switched to battery E Avionic E Fuse 6 3 A Separate protection of the avio...

Page 198: ...ercarriage The Ventus 3M has a retractable main wheel with hydraulic disc brake and a steerable or rigid optional tail wheel The extension retraction process is described on page 7 2 3 For technical descriptions of the retractable landing gear system with wheel brake see section 1 in the Ventus 3M Maintenance Manual ...

Page 199: ...olted to the mounting flanges provided on both sides of the cockpit The seat features a backrest with integrated headrest that is adjustable during flight The lap straps are anchored to the seat pan The shoulder straps are attached to the front main bulkhead of the fuselage steel frame Permitted seat belts see section 7 in the Ventus 3M Maintenance Manual ...

Page 200: ...ox 0 8 m 30 in front of the base of the fin These pressure ports are determined for altimeter and airspeed indicator and are optionally also suitable for other devices 7 6 2 Pitot pressure sources o At the nose of the aircraft This pressure port is determined for the airspeed indicator and also optionally for other devices 7 6 3 Additional pressure source o At the fin This pressure probe features ...

Page 201: ...d are very effective the change in trim is just noticeable When unlocked the airbrakes might get slightly sucked out by their spring loaded cover strips which in this position may then oscillate within their travel causing some rattling and or banging This is immediately stopped by further extending or retracting the airbrakes The control of the glider is not affected A view of the airbrake system...

Page 202: ...gage compartment is not provided soft objects like jackets etc may be placed on the removable panel covering the control linkage behind the main spar stubs Such baggage must be taken into account when determining the permissible load on the seat Maximum mass of the baggage compartment is 2kg 4 4 lb The head rest obstructs a great part of the access opening ...

Page 203: ... For serial numbers V3M 021 and V3M 031 the torsion drive is actuated via a cable drive The water ballast is dumped through an opening on each side of the lower wing surface The opening is located at half wing span of approx 1 8 m see page 7 9 2 The torsion drive for the wing dump valves is automatically connected during wing assembly The operating knob in the cockpit must be in the CLOSED positio...

Page 204: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 3M Performance FLIGHT MANUAL März 2019 Revision 7 9 2 ...

Page 205: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 3M Performance FLIGHT MANUAL March 2019 Revision 7 9 3 ...

Page 206: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 3M Performance FLIGHT MANUAL March 2019 Revision 7 9 4 ...

Page 207: ...er plant control system The corresponding operating unit for the pilot is mounted in the instrument panel See page 7 3 5 and following for further description of the power plant control system As additional control elements for the power plant the pilot must also operate the fuel shut off valve the throttle lever and if necessary the manual propeller brake After the engine has been stopped in flig...

Page 208: ... valve a strainer the electrical fuel pump and a filter element to the injection system which is connected to the engine The fuselage tank is drained via the externally accessible drainage valve on the left side behind the gear Venting The vent line of the fuselage tank is connected to the expansion reservoir via a pressure relief valve and a non return valve From there a line leads to the outlet ...

Page 209: ...l tanks must be entered into the operating unit by the pilot see section 4 2 3 Built in refuelling system The connection of the refueling system is located in the engine box on the left side direction of flight of the front wall of the engine box The toggle switch for the electric fuel pump is mounted in the cockpit on the left side of the back cover The electric fuel pump of the refueling system ...

Page 210: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 3M Performance FLIGHT MANUAL March 2019 Revision 7 11 3 ...

Page 211: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 3M Performance FLIGHT MANUAL March 2019 Revision 7 11 4 ...

Page 212: ...trical power source Additional equipment is connected to the power supply Electrical System Avionics see page 7 12 3 and 7 12 4 and according to the manufacturer s instructions for the respective equipment Power is supplied by the engine battery or one of up to 3 optional additional batteries which can be selected with the battery selector switch see pages 7 12 3 and 7 12 5 Separate main switches ...

Page 213: ...be powered from the engine battery by means of the battery selector switch The engine features an AC generator which recharges the battery via a rectifier regulator With the main switch Power plant ON and the fuse of the power plant control system ON the displays and values of the power plant control system are visible on the operating unit In order to prevent an engine failure in case of a failur...

Page 214: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 3M Performance FLIGHT MANUAL March 2019 Revision 7 12 3 ...

Page 215: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 3M Performance FLIGHT MANUAL March 2019 Revision 7 12 4 ...

Page 216: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 3M Performance FLIGHT MANUAL March 2019 Revision 7 12 5 ...

Page 217: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 3M Performance FLIGHT MANUAL March 2019 Revision 7 12 6 ...

Page 218: ...re attached to the FRP frame by means of a wing nut For information on influence on the minimum seat load refer to section 6 2 1 Oxygen system option The oxygen system will be mounted in the baggage compartment Caution After installation and de installation of an oxygen system it is necessary to re establish the empty mass and the c g position of the aircraft The modified loading plan must be ente...

Page 219: ...2 7 13 Miscellaneous equipment cont ELT installation The emergency transmitter can be installed at the following points in the fuselage according to the instructions of Schempp Hirth Flugzeugbau GmbH o on the baggage compartment floor A list of currently approved ELT s can be found in the maintenance manual ...

Page 220: ...EIM TECK Ventus 3M Performance FLIGHT MANUAL March 2019 Revision 8 0 Section 8 8 Handling care and maintenance and 8 1 Introduction 8 2 Inspection periods 8 3 Alterations or repairs 8 4 Ground handling road transport 8 5 Cleaning and care ...

Page 221: ...er handling and servicing It also identifies certain inspection and maintenance requirements which must be followed if the powered sailplane is to retain that new plane performance and dependability Caution It is recommended to follow a planned schedule of lubrication and preventive maintenance to be repeated more often if rough climate and flying conditions are encountered see section 3 of the Ve...

Page 222: ...ittings is done only if the control system becomes heavy to operate in fuselage and wing i e airbrake actuating linkage Cleaning and greasing the wheel s as well as the nose tow coupling and C G tow coupling depends on accumulation of dirt Rudder cables After every 200 operating hours and at each annual inspection the rudder cables are to be inspected at the point where they feed though the S shap...

Page 223: ...ce a year in accordance with the instructions given in the propeller manual Engine Maintenance work on the engine is required after every 25 hours of engine operation time or at least once a year in accordance with the information given in the engine manual For the remaining parts of the power plant pylon pivoting mechanism fuel system etc maintenance work is also required according to the specifi...

Page 224: ...cerned complies with an approved version Amendments of the approved sections of the Flight and or the Maintenance Manual must in any case be approved be the responsible airworthiness authority Repairs Abreviations CFRP carbon fibre reinforced plastic GFRP glass fibre reinforced plastic Before every take off and especially after the aircraft has not been used for a while it should be checked on the...

Page 225: ...f 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 Dust covers should be regarded as essential for the powered sailplane Tie down kits common in trade may be used to anchor the aircraft The water ballast tanks and the wing fuel tanks must always be left completely empty due ...

Page 226: ...d momentarily only thinners of any kind are not recommended o Never use chlorine hydrogen 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 drilling or polishing machine Hard wax is applied against the rotating disc or liquid wax is applied to the surface to be polished Then the polishing machine distributes the wax lengthwise...

Page 227: ...raft should always be protected from the wet If water is found inside the components should be stored in a dry environment and turned frequently to eliminate the water o The aircraft should not be exposed unnecessarily to intense sunlight or heat and should not be subjected to continual mechanical loads Warning All external portions of the aircraft exposed to sunlight must be painted white with ex...

Page 228: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 3M Performance FLIGHT MANUAL March 2019 Revision 9 0 Section 9 9 Supplements 9 1 Introduction 9 2 List of inserted supplements ...

Page 229: ...tus 3M Performance FLIGHT MANUAL March 2019 Revision 9 1 1 9 Supplements 9 1 Introduction This section contains appropriate supplements necessary to safely and efficiently operate the aircraft when equipped with various optional systems and equipment ...

Page 230: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 3M Performance FLIGHT MANUAL March 2019 Revision 9 2 1 9 2 List of inserted supplements Date Section Title of the inserted supplements ...

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