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SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK

Ventus-2cM

FLIGHT MANUAL

1.4 Descriptive

data

The “Ventus-2cM” is a flap equipped, single-seat high performance powered
sailplane (capable of self-launching) constructed from fiber reinforced plastic
(FRP), featuring a T-tail (fixed horiz. stabilizer with elevator, fin and rudder).
It can be flown in 15 m or 18 m configuration.

Wing

The four-piece (15 or 18 m) wing with winglets is multi-stage trapezoid in plan-
form with double-panel “Schempp-Hirth” type airbrakes on the upper surface
The flaps act as full-span ailerons.

The water ballast tanks are integral compartments in the fwd. section of the
inbd. panels (174 Liter [45.97 US Gal., 38.28 IMP Gal.]) and in the 18m-outbd.
panels (28 Liter [7.40 US Gal., 6.16 IMP Gal.]).
Their total capacity is approx. 202 Liter (53.40 US Gal., 44.40 IMP Gal.).

The wing shells are a CFRP/foam-sandwich construction with spar flanges of
carbon fiber rovings and shear webs made from CFRP/foam-sandwich.
For taxiing a small wheel (available as an option) may be fitted to the outboard
wing panel(s).

Fuselage

The pilot has 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 bulkheads and glass fiber webs. The landing wheel is retract-able an
features a mechanical respective hydraulic brake; the tail wheel (or rubber skid)
is fixed or the tail wheel is optional steerable.

Horizontal tailplane

The horizontal tailplane consists of a fixed stabilizer with elevator. The stabilizer
is a GFRP/CFRP/foam-sandwich construction, the elevator halves are a pure
GFRP/CFRP shell. The automatic elevator trim is linked to the flap actuating rod
and is infinitely adjustable.

Vertical tail

Fin and rudder are constructed as a GFRP/foam-sandwich.
On request a water ballast trim tank with a capacity of 7.8 Liter (2.06 US Gal.,
1.72 IMP. Gal.) is provided in the fin.

Controls

On rigging the wing panels, the control surfaces are automatically hooked up.

November 2003
Revision --

1.4.1

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Summary of Contents for Ventus-2cM

Page 1: ...str 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 powered 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 authoritati...

Page 2: ...ighing 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: ...er Berichtigung Abschnitt Seiten Datum der Berichtigung Bezug Datum der Anerkennung durch das LBA Datum der Ein arbeitung Zeichen Unter schrift Revision No Affected section Affected page Date of issue Reference Date of Approval by LBA Date of Insertion Signature MB Modification Bulletin Änderungsblatt TN Technical Note Technische Mitteilung 0 1 2 ...

Page 4: ... TECK Ventus 2cM 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: ...nerk 3 2 LBA anerk 3 3 LBA anerk 3 4 LBA anerk 3 5 LBA anerk 3 6 LBA anerk 3 7 1 LBA anerk 3 7 2 LBA anerk 3 7 3 LBA anerk 3 7 4 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 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 N...

Page 6: ...nerk 4 5 3 8 LBA anerk 4 5 3 9 LBA anerk 4 5 3 10 LBA anerk 4 5 4 1 LBA anerk 4 5 4 2 LBA anerl 4 5 4 3 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 2...

Page 7: ...A 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 5 3 2 3 5 3 2 4 5 3 3 6 1 1 6 1 2 6 2 1 6 2 2 6 2 3 6 2 4 6 2 5 6 2 6 6 2 7 6 2 8 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 November 2003 November 2003 November 2003 November 200...

Page 8: ... 7 11 2 7 11 3 7 12 1 7 12 2 7 12 3 7 12 4 7 12 5 7 13 1 7 13 2 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 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 November 2003 ...

Page 9: ...f 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 1 8 2 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 November 2003 0 2 6 ...

Page 10: ...imitations 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 ...

Page 11: ......

Page 12: ...UGZEUGBAU GmbH KIRCHHEIM TECK Ventus 2cM 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 Ventus 2cM 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: ...tfahrt 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 825 and was issued on March 12 1997 Category of Airworthiness UTILITY Noise Certification Basis Neufassung der Lärmvorschriften für Luftfahrzeuge LVL effective on August 1st 2004 November 2003 Revision 1 2 ...

Page 15: ...at 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 R...

Page 16: ... outboard wing panel s Fuselage The pilot has 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 s...

Page 17: ...thed belt reduction drive The power plant is housed in the fuselage aft of the wing and an electrical spindle drive pivots it such that the propeller pylon extends from the engine bay In its appearance the Ventus 2cM differs from sailplane model Ventus 2c only by its engine doors with pylon retracted Flight characteristics and performances are identical with those of a corre spondingly loaded Vent...

Page 18: ... 62 m 2 03 ft Height 0 81 m 2 66 ft Mass Empty mass approx 395 kg 869 lb With power plant 325 kg 345 kg removed 715 lb 759 lb Maximum all up mass 525 kg 565 kg 1157 lb 1246 lb Wing loading range 41 4 54 3 kg m 38 1 51 2 kg m 8 5 11 1 lb ft 7 8 10 5 lb ft Engine Type SOLO 2625 01 Manufacturer Solo Kleinmotoren GmbH Germany Power at 6200 RPM 37 kW 49 6 HP Propeller Type KS 1G 152 R 122 Manufacturer ...

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

Page 20: ...cator 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 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: ...tended 180 km h 97 kt 112 mph Do not exceed this speed with propeller extended VPOmax Maximum speed for extending retracting the propeller 120 km h 65 kt 75 mph VPOmin Minimum speed for extending retracting the propeller 92 km h 50 kt 57 mph Do not extend retract the propeller outside this speed range November 2003 LBA app Revision 2 2 2 ...

Page 24: ...een 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 Red line at 285 km h 154 kt 177 mph...

Page 25: ...ixture mixing proportion for CASTROL Super TT 50 1 2 Propeller manufacturer Technoflug Leichtflugzeugbau GmbH 78713 Schramberg Germany Propeller model KS 1G 152 R 122 Reduction ratio 1 3 Fuel capacity See table below Tank s in inboard wing panels Tank in fuselage starbd side OPTION port side OPTION Total capacity incl optional tank US IMP US IMP US IMP US IMP Liter Gal Gal Liter Gal Gal Liter Gal ...

Page 26: ... Normal Range Caution Range Maximum Limit Signal green Yellow red Tachometer RPM Indicator min 1 Range 2500 6200 6300 6700 6800 flashing Signal Coolant Liquid Temperature Indicator C Range 40 110 110 flashing Signal yellow 9 8 0 Fuel Quantity Indicator LTR Range tanks in wing and fuselage fuselage tank only Indicated by the ILEC multi function engine control unit November 2003 LBA app Revision 2 5...

Page 27: ...1157 lb 1246 lb Maximum permitted landing mass 525 kg 565 kg 1157 lb 1246 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 340 kg 750 lb Maximum permitted mass in baggage compartment 2 kg 4 4 lb see page 7 8 November 2003 LBA app Revision 2 6 ...

Page 28: ... in aft of datum Power plant installed 290 mm 11 41 in aft of datum Maximum rearward c g position Power plant removed or installed 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 l...

Page 29: ...HT MANUAL 2 8 Approved maneuvers The powered sailplane model Ventus 2cM is certified in category U T I L I T Y Capable of self launching only with 18m wing span November 2003 LBA app Revision 2 8 Warning Aerobatic maneuvers and cloud flying n o t a p p r o v e d ...

Page 30: ...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 31: ...L 2 10 Flight crew The Ventus 2cM 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 32: ...GmbH KIRCHHEIM TECK Ventus 2cM FLIGHT MANUAL 2 11 Kinds of operation With the prescribed minimum equipment installed see page 2 12 this powered sailplane is approved for VFR flying in daytime November 2003 LBA app Revision 2 11 ...

Page 33: ...AT with sensor when flying with water ballast red line at 2 C 35 6 F 1 Magnetic compass 1 Engine control unit indicating RPMs Coolant liquid temperature C Fuel quantity Liter Engine time Water pump failure 1 Rear view mirror 1 Four piece safety harnesses symmetrical 1 Automatic or manual parachutes or 1 Back cushions thickness approx 10 cm 3 9 in when compressed CAUTION The sensor for the OAT must...

Page 34: ...ace Maximum towing speed 180 km h 97 kt 112 mph Weak link in tow rope max 735 daN max 1620 lb Minimum length of tow rope 30 m 98 ft Tow rope material Hemp or Nylon Winch launch propeller retracted 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 735 daN max 1620 lb November 2003 LBA app Revision 2 13 ...

Page 35: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 2cM FLIGHT MANUAL 2 14 Other limitations N o n e November 2003 LBA app Revision 2 14 ...

Page 36: ...35 daN 1620 lb TIRE PRESSURE Main wheel 4 0 bar 58 psi Tail wheel 2 5 bar 36 psi 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 propeller extension retraction 120 65 75 Propeller extended speed 180 97 112 For 18 m span...

Page 37: ...LIGHT MANUAL Section 3 3 Emergency procedures 3 1 Introduction 3 2 Canopy jettisoning 3 3 Bailing out 3 4 Stall recovery 3 5 Spin recovery 3 6 Spiral dive recovery 3 7 Engine failure carburetor icing 3 8 Fire 3 9 Other emergencies November 2003 Revision 3 1 1 ...

Page 38: ...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 39: ... 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 40: ...jettisoned With the canopy gone see section 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 Revisi...

Page 41: ...all differences in the stall behaviour WARNING When stalling with extended propeller engine idling or ignition off the turbulent airflow produced by the propeller superimposes the vibration in the controls so that in this case a significant stall warning is not noticeable IMPORTANT NOTE If on stalling the vibration in the controls and in the cockpit becomes more pronounced with controls getting sp...

Page 42: ...0 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 ...

Page 43: ... 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...

Page 44: ... If permitted by these factors the propeller should at least be partly retracted ignition to be switched OFF for this purpose regardless of the position of the prop blades thus achieving a considerably better glide ratio Thereafter close fuel shut off valve and set engine master switch at OFF WARNING With power plant fully extended the rate of descend increases to a value of about 2 30 m s 453 fpm...

Page 45: ... mph so that the engine revs will quickly build up with an audible prop noise then level off and reduce speed to 95 km h 51 kt 59 mph Maintain this speed until the engine has definitely fired open throttle a little The loss of height from the moment of acceleration to the point where the aircraft is leveled off is in the order of 150 m 492 ft to 200 m 656 ft Carburetor icing From experience gained...

Page 46: ...overloads on the spindle drive caused by releasing the key of the emergency switch too late will force the 12 A circuit breaker to trip In the extreme down position the spindle is stopped by the limit witch retracted and is shown by the green signal Failure of the power plant s electrical energy supply Should this happen in flight the ILEC engine control unit is out of function all signals out but...

Page 47: ...EWARE OF THE PROPELLER With engine running reconnect battery wiring b Via the optional ground service receptable Plug in special starting cable plug with 3 pins into the receptacle socket below the instrument panel on the left side Clamp negative ground strap to proper terminal of an external 12 V power source then clamp power strap to positive terminal Thereafter follow normal starting procedure ...

Page 48: ...SE fuel shut off valve Open throttle fully Leave propeller in extended position This sequence should be followed if possible a on the ground b on take off c in flight WARNING Discontinue flight and land immediately Avoid any maneuvers causing a high stressing of the fuselage November 2003 LBA app Revision 3 8 ...

Page 49: ...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 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 cab...

Page 50: ...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 51: ...ity 4 3 Daily inspection 4 4 Pre flight inspection 4 5 Normal procedures and recommended speeds 4 5 1 Methods of launching Engine starting engine run up and taxiing 4 5 2 Take off and climb 4 5 3 Flight including in flight engine stop start procedures 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...

Page 52: ...roduction 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 53: ...needs a little force to push it home Check that the spar stub tip is located correctly on the far side of the fuselage and ensure that the angular levers on the root rib are definitely 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 ...

Page 54: ...tor 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 rigging Check the controls with the aid of a helper for full and...

Page 55: ...ft 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 backwards and forwards if...

Page 56: ...ng system is found behind the front wing locating tube with the GFRP access panel removed The ON OFF switch for the additional fuel pump is on the fairing of the wing locating tube on the port side Hence only a single loose filler hose with a quick disconnect coupling is required for refueling see sketch on page 4 2 2 2 and 4 2 2 3 November 2003 LBA app Revision 4 2 2 1 ...

Page 57: ...rnal refueling system November 2003 LBA app Revision 4 2 2 2 1 2 3 4 a Fuselage tank Connect external filler hose to fitting and connect line of internal fuel pump to fitting feeding the fuselage tank see also accompanying sketch Fill fuselage tank by actuating the pump ON OFF switch 1 2 3 4 ...

Page 58: ... app Revision 4 2 2 3 4 3 6 5 1 2 b Wing tank s Connect external filler hose to fitting Disconnect wing tank fuel line from line servicing the fuselage tank and connect instead the line fed by the internal fuel pump as shown in accompanying sketch Fill wing tank by actuating the pump ON OFF switch then re connect to 5 6 3 5 6 1 2 ...

Page 59: ...ount of fuel left in the fuselage tank safety measure Data entry Depress both white button LCD on the right and CAL on the left until the letter E is displayed By depressing and releasing only the button on the right the value is increased by one Liter by depressing and releasing only the button on the left the value is reduced by on Liter Note that the total amount of fuel must be entered i e fus...

Page 60: ...y 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 61: ...p 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 e Check condition and attachment of the wing wheel if installed 3 a Check ailerons flaperons on inbd wing panels for proper co...

Page 62: ... Check all components lines hoses pipes and wires etc for chafing marks h Check engine arresting wires and their attachment for proper condition i Check engine door actuating mechanism for proper function j Check for proper function Throttle control manual primer when squeezing rubber bulb air must be expelled through hole in lid of carburetors and prop arresting device Note With the prop arrestin...

Page 63: ...eck the line when blowing gently from the front to the probe with pneumatic valve for the TEK probe set at Power off the variome ter s connected should read climb c Check that the fin mounted PITOT tube is clear When blowing gently into this probe the ASI must register with pneumatic valve for the pitot pressure set at Power off d Check that the opening for the fuel tank vent line at the upper end...

Page 64: ...c 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 is discovered e g surface cracks in...

Page 65: ...in wing connected if installed 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 ASI switched to Pitot head in fin or nose O Canopy closed and locked O Fuel quantity checked O Function of water pump checked NO flashing red signal O ...

Page 66: ...d 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 powered 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 ...

Page 67: ...e about 150 to 160 km h 81 86 kt 93 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 required At low...

Page 68: ...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 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 ...

Page 69: ...ss than 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 ...

Page 70: ...PROCEDURE ON THE GROUND O Apply wheel brake pull stick back O Check that propeller is clear Should engine die after first ignition SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK FLIGHT MANUAL Engine run up Advance to full throttle prior to or during the take off run make sure that engine reaches a minimum speed of about 5600 to 5800 RPM and runs sound Taxiing With a wheel fitted near the tip of the...

Page 71: ...on the ground With some back pressure on the stick the aircraft lifts off at about 80 km h 43 kt 50 mph if flap setting L was used reset flaps at 2 Finally ease stick forward until the speed for best climb VY 95 100 km h 51 54 kt 59 62 mph is reached The initial climb up to a safe height may be conducted with RPMs in the yellow caution range Observe coolant liquid temperature while climbing On rea...

Page 72: ... pan cut out Then the 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 wi...

Page 73: ...atively small though the change in 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 wis...

Page 74: ...96 132 170 71 92 82 106 2 km h kt mph 155 192 84 104 96 119 167 206 90 111 104 128 155 183 84 99 96 114 170 200 92 108 106 124 S km h kt mph 192 206 104 111 119 128 206 221 111 119 128 137 183 230 99 124 114 143 200 250 108 135 124 155 Flying between thermals and high speed flying S1 km h kt mph 206 285 111 154 128 177 221 285 119 154 137 177 230 285 124 154 143 177 250 285 135 154 155 177 For a s...

Page 75: ...ng motions speed increases 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 turbulent 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 powered sailplane will drop a wing A norm...

Page 76: ...of height from 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 powered 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 characteristi...

Page 77: ...good climb rather than for high cruise the speed attained in level flight at 6200 RPM is just about 149 km h 80 kt 88 mph with flaps set at 0 At this speed the aircraft shows a stable behaviour and is easy to control Flown in a shallow drive the maximum permitted engine speed of 6800 RPM must not be exceeded November 2003 LBA app Revision 4 5 3 6 ...

Page 78: ... 500 m 1640 ft The maximum range in glide is achieved at a speed of about 100 to 110 km h 54 59 kt 62 68 mph resulting in an average speed of about 100 km h 54 kt 62 mph Should the sawtooth method be impracticable due to low cloud ceiling or because of airspace restrictions then cruising in level flight at a speed of about 149 km h 80 kt 93 mph is also possible The range however is then considerab...

Page 79: ...op until green light comes on spindle drive will automatically be cut off CAUTION Through the mirror observe the propeller retracting to check if the propeller rotate further The propeller retracts within about 11 seconds but the entire process from stopping the engine to the moment the propeller has fully retracted takes about 90 seconds and consumes a height of about 100 m 328 ft November 2003 L...

Page 80: ...ke Should a flight be planned over long distance without any acceptable landing fields the prop should be extended at a height giving sufficient time for all emergency procedures and if necessary for re retracting the propeller 2 Starting procedures see also check list on page 4 5 1 5 Power plant master switch ON Push prop arresting device handle forward Check that fuel shut off valve is open Set ...

Page 81: ...when the aircraft stalls from straight and level or from turning flight When stalling with running engine full power the noise of the power plant increases considerably WARNING When stalling with extended propeller with engine idling or with ignition off the turbulent airflow produced by the propeller superimposes the vibration in the controls so that in this case a stall warning is not noticeable...

Page 82: ...at 1 offers the 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 in 15 m configuration are a very effective landing aid and may be conducted in a straight line up to about 90 of the rudder travel resulting in ...

Page 83: ...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 84: ...oach speed 115 km h 62 kt 72 mph Rate of descent approx 2 75 m s 541 fpm L D approx 11 6 The reduced performance however requires significant more altitude to conduct approaches with the same techniques as in clean configuration WARNING 1 Be cautious when extending the airbrakes Due to the additional drag of the extended propeller more forward stick must be applied for maintaining the above approa...

Page 85: ...r held neutral to avoid an undesired turn around 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 powered sailplane 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 a...

Page 86: ... 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 87: ...re 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 powered 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 88: ... 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 89: ...to 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 90: ...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 powered...

Page 91: ...102 119 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 92: ...will 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 associate...

Page 93: ...ed with 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 cau...

Page 94: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 2cM FLIGHT MANUAL 4 5 9 Aerobatics Aerobatic maneuvers are n o t permitted November 2003 LBA app Revision 4 5 9 ...

Page 95: ...tion 5 2 LBA approved data 5 2 1 Airspeed indicator system calibration 5 2 2 Stall speeds 5 2 3 Take off distances 5 2 4 Additional information 5 3 Additional information LBA approval not required 5 3 1 Demonstrated crosswind performance 5 3 2 Flight polar Range 5 3 3 Noise data November 2003 Revision 5 1 1 ...

Page 96: ...tion 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 powered sailplane in good condition and using average piloting techniques November 2003 Revision 5 1 2 ...

Page 97: ...80 cm 31 5 in forward 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 INDICATED AIRSPEED IAS ρ0 1 226 kg m3 all up mass 500 kg 1102 lb flap setting 1 propeller retracted 177 154 285 VNE 285 km h 154 kt 177 mph CALIBRATED AIRSPEED CAS all up mass 500 kg...

Page 98: ...h kt mph 74 40 46 81 5 44 3 50 3 88 5 47 3 55 3 75 5 40 3 47 3 airbrakes extended flaps at L km h kt mph 76 41 47 75 5 40 3 47 3 85 5 46 3 53 3 72 5 39 3 45 3 Airspeed indication 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 60 m 197 ft Configuration PROPELLER EXTENDED FULL POWER Wing span 18 m All...

Page 99: ...332 390 458 539 932 1089 1279 1502 1768 concrete runaway Total distance over 50 ft obstacle 0 500 1000 1500 2000 0 1640 3281 4921 6562 362 425 499 588 693 1187 1394 1637 1929 2273 421 495 581 683 804 1381 1624 1906 2240 2637 487 570 670 787 926 1597 1870 2198 2581 3037 557 653 766 900 1059 1827 2142 2512 2952 3474 Ground run distance till lift off 0 500 1000 1500 2000 0 1640 3281 4921 6562 220 258...

Page 100: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 2cM FLIGHT MANUAL 5 2 4 Additional information N o n e November 2003 LBA app Revision 5 2 4 ...

Page 101: ...CK Ventus 2cM 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 102: ...59 0 50 Minimum sink rate fpm 116 98 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 b Propeller extended Maximum power kg 525 565 All up mass lb 1157 1246 m s 3 25 3 00 Max rate of climb fpm 640 591 km h 95 100 kt 51 54 at a speed of mph 59 62 At a spee...

Page 103: ...POLAR DIAGRAM AIRSPEED CAS RATE OF SINK all up mass 565 kg 1246 lb all up mass 490 kg 1080 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 104: ... The following values are based on the sawtooth method see page 4 5 3 7 at an all up mass of 485 kg 1069 lb and the climb effected at max power Average cruising speed approx 100 km h 54 kt 62 mph Fuel consumption approx 21 50 Liter h 5 68 US Gal h 4 73 IMP Gal h Fuel supplied from Usable fuel US IMP Liter Gal Gal fuselage tank optional starboard wing tank optional port wing tank Endurance climb ti...

Page 105: ... 11483 3500 0 0 98 10 197 295 394 492 590 20 30 40 ALTITUDE above MSL CLIMB TIME min RATE OF CLIMB CLIMB TIME min for 485 kg 1069 lb RATE OF CLIMB m s fpm for a mass of 485 kg 1069 lb 689 787 886 ft m 9843 3000 8202 2500 6562 2000 4921 1500 3281 1000 1640 500 0 0 5 1 0 1 5 2 0 2 5 3 0 3 5 4 0 4 5 m s fpm ...

Page 106: ...LVL the measured noise level of the Ventus 2cM equipped with the Solo engine 2625 01 is 61 7 dB A noise level limit 70 0 dB A and is thus far below 8 3 dB A the noise level limit The Ventus 2cM therefore complies with the Noise Regulation for Aircraft LVL dated August 1 2004 It is recommended to wear a head set while the engine is running November 2003 Revision 5 3 3 ...

Page 107: ...ECK Ventus 2cM 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 108: ...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 and 6 2 4 refer to November 2003 Revision 6 1 2 ...

Page 109: ... aid of the last valid weighing report the required data and diagrams are found in the Maintenance Manual Both loading charts weight balance log sheets are only applicable for this particular powered 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 ...

Page 110: ...eights only usable with battery removed 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 ba...

Page 111: ...ion mm aft of datum 15 m Max kg Seat load pilot incl parachute Min kg Max useful load in fuse lage incl fuel load kg Inspector Signature Stamp NOTE Maximum seat load Maximum useful load in Pilot parachute fuselage less fuel load in 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 fi...

Page 112: ...dated 18m Empty mass c g position mm aft of datum 15 m Max kg Seat load pilot incl parachute Min kg Max useful load in fuse lage kg Inspector Signature Stamp NOTE The Maximum seat load Pilot with parachute must not exceed 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 ...

Page 113: ... max permitted wing water ballast load allowance 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 November 2003 Revision SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK FLIGHT MANUAL WING SPAN 15 m 49 21 ft Water ballast load Maximum all up mass inc...

Page 114: ...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 115: ...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 116: ... 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 117: ...it 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 Power plant system 7 11 Fuel system 7 12 Electrical system 7 13 Miscellaneous equipment removable Ballast oxygen ELT etc November 2003 Revision 7 1 1 ...

Page 118: ...on provides a description of the powered sailplane including the operation of its systems For details concerning optional systems and equipment refer to section 9 Supplements For further descriptions of components and systems refer to section 1 of the Maintenance Manual November 2003 Revision 7 1 2 ...

Page 119: ...H KIRCHHEIM TECK Ventus 2cM FLIGHT MANUAL 7 2 Cockpit description November 2003 Revision 7 2 1 RPM V TEM LI T O N O FF BAT RPM RES 1 2 WP CAL LCD 6100 70 0000803 50 7 5 15 5 15 2 11 8 3 1 7 10 16 5 4 12 6 13 17 15 2 9 18 19 20 21 2 ...

Page 120: ...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 121: ... 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 ...

Page 122: ...opy 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 posit...

Page 123: ...h Forward position High speed range Rearward position Low speed range 13 Elevator trim Knurled green knob on the left mounted on the flap actuating tube The spring loaded trim is infinitely adjustable by freeing the knurled knob sliding it to the desired position and tightening the knob again Forward position Nose heavy Rearward position Tail heavy A neutral position of the trim at flap setting 0 ...

Page 124: ... 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 slide it forward and let knob engage 16 Propeller arresting device Grey lever on cockpit inner skin on the right Handle fully forward Arresting device released power on Handle in backward position Arresting device applied for arresting...

Page 125: ...the stick 20 Throttle Pivoting lever on the port side of the cockpit Fully forward position Full throttle Fully backward position Idle 21 Primer Black rubber bulb on the port seat pan mounting flange Bulb squeezed with ignition switched ON Fuel is injected into carburetors November 2003 Revision 7 2 7 ...

Page 126: ...strument panel November 2003 Revision 7 3 1 RPM V TEM LI T ON OFF BAT RPM RES 1 2 WP CAL LCD 6100 70 0000803 50 7 5 15 5 15 2 I II III IV V VI VII VIII For a description of items No I VIII refer to the following pages A description of the instrumentation is not deemed necessary ...

Page 127: ... for low fuel level in fuselage tank 04 Signal for ignition 05 Signal for propeller not fully extended 06 Signal for prop arresting device applied 07 Signal for prop fully extended 08 Prop extension retraction switch 09 Signal for prop fully retracted 10 Display selector button fuel entry 11 Engine hour meter 12 Fuel entry 13 Ignition switch 14 Display for either engine speed RPM and coolant liqui...

Page 128: ... 5 03 Signal for low fuel level With less than 8 Liters 2 11 US Gal 1 76 IMP Gal left in the fuse lage tank a yellow light comes on 04 Signal for ignition On depressing the starter button with the ignition switched OFF a flashing red signal comes on and automatically the starter motor is cut off On actuating the propeller retraction switch with ignition still ON the flashing red light comes on and...

Page 129: ...WN position and pressure maintained the propeller retracts A limit switch cuts off the spindle drive when prop has fully retracted NOTE With ignition switched ON the prop may be extended but N O T retracted 09 Signal for propeller fully retracted With prop fully retracted a green light comes on 10 Display selector button Fuel entry While depressing this button the display shows battery voltage and...

Page 130: ... 10 the values for the battery voltage and fuel contents are indicated Note concerning the fuel quantity indicator The number of Liters indicated depends on the rating of the fuel used The standard setting of the indicator is for AVGAS 100 LL If premium gasoline is used the reading is 20 more A re calibration with fuselage tank filled 12 Liter 3 17 US Gal 2 64 IMP Gal for another rated full is ach...

Page 131: ...ide air temperature indicator When carrying water ballast the outside air temperature OAT must not drop below 2 C 36 F V Stick mounted starter button The starter motor is cut off with propeller not fully extended watch signal with ignition switched off watch signal with prop arresting handle not in fully forward position watch signal with an engine speed exceeding 1200 RPM VI Fire warning signal w...

Page 132: ...s green extended signal permanently on Key held down Propeller pylon retracts The extreme pylon positions are recognized as follows Extended Pivoting motion of pylon is stopped by arresting wire watch rear view mirror and the circuit breaker will trip If spindle drive circuit breaker trips reset it instantly Retracted On reaching the extreme position the green retracted lights comes on Spindle dri...

Page 133: ...s circuit breaker must always be depressed otherwise the power plant batteries located in the fuselage nose cone will not be recharged by the generator November 2003 Revision 7 3 8 50 7 5 15 5 12 2 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 Circuit breaker 50A power plant master switch Circuit breaker 7 5A avionic main switch Circuit breaker 15A generator Circuit breaker 12A spindle drive Circuit breaker...

Page 134: ...BREAKER 4 A It protectes the charging socket for the avionic battery 11 CIRCUIT BREAKER 4 A This protects the charging socket for the power plant batteries and protects the fire warning device 12 CIRCUIT BREAKER 6 3 A It protects the gliding avionics when fed from the power plant batteries 13 BATTERY SELECTOR SWITCH By switching from AVIONIC to POWER PLANT power to operate the gliding avionics is ...

Page 135: ... 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 136: ...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 137: ...uselage 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 a The Pitot pressure head provided near the top of the fin is to be used in glide b The Pitot pressure head provided in the fuselage nose cone is to be used when flying power on November 2003 Rev...

Page 138: ...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 2cM 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 v...

Page 139: ...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 140: ...ed 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 de...

Page 141: ...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 142: ... 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 143: ...lectrical spindle drive anchored to the fuselage deck and linked to the pylon extends and retracts the latter in a rotary motion about the pivot pins in the fuselage The doors of the engine compartment are automatically opened and closed by a linkage while the pylon extends retracts A panel mounted ILEC engine control unit combines a number of functions requires for opening the power plant a descr...

Page 144: ...nected to the carburetor on the engine Total fuel contents in fuselage and wing tank s are displayed by the ILEC control unit its fuel quantity indicator is resettable The vent line of the fuselage tank are routed to an expansion tank from which one line extends overboard at the top of the fin on the starbd side WARNING In order to prevent an engine stop due to the lack of the fuel the opening of ...

Page 145: ...ision 7 11 2 9 1 15 18 8 14 7 3 12 2 10 16 6 5 11 4 14 17 16 17 13 5 4 18 16 16 FUEL SYSTEM with optional wing tanks M03 RT 970 tank vent line to top of fin shut off valve control expansion reservoir 0 7 Liter to engine Parts listed on page 7 11 3 loop routed to upper canopy coaming frame ...

Page 146: ...L 11 mod WALTHER SHK 12 1 Hose coupling LP 004 0 SL mod WALTHER SHK 11 1 T connector T5 NORMA 10 1 Expansion reservoir Nr 265 GRAUPNER 9 1 Hose coupling LP 004 0 2 SL WALTHER 8 1 Fuel valve control HM5 10 284 SHK 7 1 Shut off valve 4932 08 13AC LEGRIS 6 1 Flow meter DFM 1 ILEC 5 2 Fuel pump 40 105 FACET 4 2 Filter element 99 106 8 100 CARCOMA 3 1 Drain valve TORO 2 1 Fuel level transmitter TF 0 00...

Page 147: ...ctless and a generator charging the12 V power plant batteries The latter situated in the fuselage nose as shown on page 7 12 3 ELECTRICAL SYSTEM POWER PLANT are only necessary for operating pylon spindle drive starter motor and ILEC control unit with RPM indicator The power plant batteries are controlled by a circuit breaker 50 A their voltage is displayed by the ILEC control unit By using a selec...

Page 148: ...TERY MOUNTING POSITIONS BATT AVIONIC C1 E Circuit breaker 6 3A mounted on battery F Fuse board description on page 7 3 7 G Bus bar e G AMP Terminal H Main switch Power plant Main switch Avionic J Battery selector switch K Consumer load fuse e G VHF Transceiver E Vario etc L VHF Transceiver M Antenna N PTT button O Boom mike P Speaker Q Headset connector R Rotary multipoint switch Option Low voltag...

Page 149: ...els Version 2 Batteries Battery installation in accordance with position of CG Version 3 Batteries Battery installation in accordance with position of CG Version 4 Batteries Battery installation in accordance with position of CG Selector switch for 2 batteries Rotary multip switch for 3 or 4 batteries Solar panels to be wired at the main power supply only by regulator with Vmax 13 8V OPTION Electr...

Page 150: ...6 3A 1410 G111 P2F1 ETA F 1 Fuse board M03 RE 072 SHK G 1 Bus bar e G AMP Terminal SHK H 1 Circuit breaker 50A Engine 413 K14 LN2 ETA I 1 Circuit breaker 7 5A Avionic 412 K14 LN2 ETA J 1 2 Micro switch 9040 0101 Marquardt K 1 Circuit breaker 2 4A 1410 G111 P2F1 ETA M 1 Antenna K 100 Filser N 1 PTT button LJ1 ST200 Secme O 1 Boom mike with cable Holmco or Peiker P 1 Speaker KL1 4 Ohm Std Peiker acu...

Page 151: ...nal with test button I Electrical fuel pump J Electrical fuel pump refueling K Pump ON OFF switch refueling L Fuel flow meter M Fuel level transmitter N Rectifier regulator O Starter relay P Ground connector module Q Relay spindle ext retr R Spindle drive S Limit switch prop ext T Limit switch prop retr U Fire detector V Option Ext power receptacle with relay W Water pump relay and resistance X Em...

Page 152: ... system Attachment 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 ma...

Page 153: ...ation of an Emergency Locator Transmitter is possible in the following places and must comply with the relevant instructions provided by Schempp Hirth on a panel covering the main spar stubs A list of ELTs currently approved by the LBA is found in the Maintenance Manual November 2003 Revision 7 13 2 ...

Page 154: ...IRCHHEIM TECK Ventus 2cM 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 155: ...Ventus 2cM 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 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 156: ...vy to 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 throu...

Page 157: ...tions given in the propeller manual Engine Maintenance work on the engine is required after every 25 hours of engine time or at least once every year and must comply with the instructions given in the engine manual For all other power plant accessories engine pylon pivoting mechanism fuel system etc maintenance work is also required after every 25 hours of engine time or at least once every year N...

Page 158: ...ght and or Maintenance Manual must in any case be approved by the Luftfahrt Bundesamt LBA Repairs Before every take off and especially after the powered 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 t...

Page 159: ...nt temperatures c Tie down In the case of a powered sailplane remaining rigged permanently it is important that the maintenance program includes rust prevention for the fittings on fuselage wing panels and tailplane Tie down kits common in trade may be used to anchor the aircraft Dust covers should be regarded as essential for the powered sailplane d Preparing for road transport As the wing panels...

Page 160: ...aterials 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 161: ...e 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 powered 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 powered sailplane exposed to sunlight must be painted white with the excepti...

Page 162: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 2cM FLIGHT MANUAL Section 9 9 Supplements 9 1 Introduction 9 2 List of inserted supplements November 2003 Revision 9 1 1 ...

Page 163: ...HT MANUAL 9 1 Introduction This section contains the appropriate supplements necessary to safely and efficiently operate the Ventus 2cM when equipped with various optional systems and equipment not provided with the standard aircraft November 2003 Revision 9 1 2 ...

Page 164: ...SCHEMPP HIRTH FLUGZEUGBAU GmbH KIRCHHEIM TECK Ventus 2cM FLIGHT MANUAL 9 2 List of inserted supplements Date Section Title of inserted supplement November 2003 Revision 9 2 ...

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