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DG Flugzeugbau LS8 Series Flight Manual

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Summary of Contents for DG Flugzeugbau LS8 Series

  • Page 2 EASA Date of approval 05 August 2016 This sailplane is to be operated in compliance with information and limitations contained herein. Copyright DG Flugzeugbau GmbH any copy or publishing prohibited DG Flugzeugbau Otto Lilienthalweg 2 Telefon (07251) 3020-0 76646 Bruchsal Telefax (07251) 3020-200 www.dg-flugzeugbau.de...
  • Page 3 2016 August 4-13, 4-18, 6-1, 6-4, last revisions of the initial 2016 7-11, 8-2, 8-3, 8-4 flight manuals (6-1, 6-4 text from LS8-b taken for all variants) Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 4 " June 2016 " June 2016 " June 2016 " June 2016 " June 2016 " June 2016 " June 2016 " June 2016 " June 2016 Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 5 " 4-24 June 2016 " 4-25 June 2016 " 4-26 June 2016 " 4-27 June 2016 " June 2016 " June 2016 EASA-app. June 2016 June 2016 Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 6 7-10 June 2016 7-11 June 2016 June 2016 June 2016 June 2016 June 2016 June 2016 June 2016 June 2016 June 2016 June 2016 8-10 June 2016 June 2016 Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 7: Table Of Contents

    4 Normal Procedures..............approved 5 Performance..............partly approved 6 Weight and Balance............non-approved 7 Description of Systems)............non-approved 8 Handling, Servicing and Maintenance ......non-approved 9 Supplements ................ non-approved Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 8: General

    1.1 Introduction .............. 1-2 1.2 Certification Basis ............ 1-2 1.3 Warnings, Cautions and Notes (Definitions) ... 1-3 1.4 Descriptive and Technical Data ....... 1-4 1.5 Three View Drawing ..........1-5 Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 9: Introduction

    The Type Certificate LBA No. 402 for the variant LS 8-b was issued on 13.05.2002. 15.09.2010 the variants LS8-a, LS8-b, and LS8-18 have been incorpoated into the EASA Type Certificate A.047. Category of Airworthiness: "Utility". Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 10: Warnings, Cautions And Notes (Definitions)

    Note: Draws the attention to any special item not directly related to safety, but which is important or unusual. Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 11: Descriptive And Technical Data

    When executing TN8002 (Conversion LS8-a to LS8-18) the variant LS8-a will be converted to variant LS8-18 and may be operated alternatively with 15 m or 18 m wingspan. Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 12: Three View Drawing

    Flight Manual LS8 (LS8, LS8-a, LS8-18, LS8-b) 1.5 Three View Drawing Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 13: Limitations

    2.12 Further Limitations ..........2-12 2.12.1 Operating Placards for Limitations ....2-12 2.12.2 Approved Gelcoats for Exterior Surfaces ..2-13 2.12.3 Use of Water for Ballast ....... 2-13 Issued: June 2016 EASA app. 2-1 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 14: Introduction

    Warning: Therefore, operational limits, - speeds and load factors - must be adhered to ! Issued: June 2016 EASA app. 2-2 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 15: Airspeeds (Ias)

    280 151 174 Do not extend or retract the landing gear operating speed gear above this speed. Maximum air brake 280 151 174 extension speed Issued: June 2016 EASA app. 2-3 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 16: Airspeed Indicator Colour Markings

    Without altitude related VNE markings on the dial, a VNE placard according to section 2.12 must be on the instrument panel. Issued: June 2016 EASA app. 2-4 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 17: Mass (Weight)

    Horizontal tail Water ballast (to compensate wing ballast) and battery in tail fin do not count for “non-lifting” parts, but for maximum all-up weight. Issued: June 2016 EASA app. 2-5 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 18 Warning: The vertical tail fin battery may be removed from the tail fin to reduce Minimum Cockpit Load (see entries in section 6.2 for possible combinations !) Issued: June 2016 EASA app. 2-6 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 19: Centre Of Gravity Limits

    Minimum Cockpit Load ! Maximum amounts see section 4.5.10.5. Issued: June 2016 EASA app. 2-7 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 20: Manoeuvring Load Factors

    Minimum equipment see section 2-10. For USA only: Night-VFR, IFR and Flight into known icing conditions are not approved. Issued: June 2016 EASA app. 2-8 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 21: Flight Crew

    Tail battery not installed (Check with horizontal tailplane removed!) For possible combinations see Flight Manual entries in section 6 and on the Cockpit data placards. Issued: June 2016 EASA app. 2-9 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 22: Minimum Equipment List

    • Variometer: recommended: range at least ±10 m/s (2000 ft/min; 20 kt.) • Additionally ATC equipment, for instance transponder, is recommended. Approved types of equipment see Master Equipment List in Maintenance Manual section 9. Issued: June 2016 EASA app. 2-10 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 23: Aero Tow, Winch Launch And Auto Tow

    Minimum tow cable length for aero tow ....30 m (100 ft) recommended length...up to 80 m (260 ft) Caution: During motorglider tow, limitations regarding weak link and tow cable length must be obeyed. Issued: June 2016 EASA app. 2-11 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 24: Further Limitations

    Up to 10000 (32800) - 179 111 Up to 12000 (39400) - 156 Maximum baggage weight 5 kg (11 lbs) at baggage compartment (Soft items only) Issued: June 2016 EASA app. 2-12 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 25: Use Of Water For Ballast

    UP-Gelcoat Scheufler T35 white Tone similar to RAL 9010 2.12.3 Use of water for ballast Use of water for ballast restricted to clear water without any additives. Issued: June 2016 EASA app. 2-13 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 26: Emergency Procedures

    3.7.6 Emergency landing with landing gear retracted ..3-8 3.7.7 Ground loop ..............3-8 3.7.8 Emergency landing in water ........3-9 3.7.9 Flight in the vicinity of thunder storms.......3-9 Issued: June 2016 EASA app. 3-1 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 27: Introduction

    - open - Lift with arms over cockpit rim Exit push yourself away from the sailplane - preferably dive under wing, to avoid the tail Issued: June 2016 EASA app. 3-2 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 28: Stall Recovery

    When during stalled flight the angle of incidence is increased considerably by further “pulling”, then –depending on C.G. position- spinning may result from asymmetric stall. Issued: June 2016 EASA app. 3-3 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 29: Spin Recovery

    Elevator - pull cautiously Warning: During dive-out be alert not to exceed maximum permissible speed VNE = 280 km/h (151 kt.; 174 mph) inadvertently! Issued: June 2016 EASA app. 3-4 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 30: Other Emergencies

    190 km/h (103 kt.; 118 mph) – green ASI range upper limit – should not be exceeded because of possible severe turbulence. Issued: June 2016 EASA app. 3-5 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 31: Rain

    Caution: For prolonged flights below +5° Centigrade (41° F) use no water ballast. Icing Conditions: Move control surfaces continually to avoid freezing solid. Open canopy window for better visibility. Issued: June 2016 EASA app. 3-6 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 32: Flight With Asymmetric Water Ballast Loading

    In this case at least 25 Litres (6.6 US gallons, 5.5 UK gallons) –corresponding to 15 seconds of discharge time- should be dumped Issued: June 2016 EASA app. 3-7 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 33: Emergency Landing With Landing Gear Retracted

    (a) steer wingtip to desired direction onto the ground, whenever possible the windward side should be preferred. (b) simultaneously decrease tail skid load by controlled forward stick deflection. Issued: June 2016 EASA app. 3-8 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 34: Emergency Landing In Water

    Therefore, flights and especially winch launches in the vicinity of thunder storms should be avoided, as in important structures of the LS8 carbon fibres are used. Issued: June 2016 EASA app. 3-9 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 35: Normal Procedures

    4.5.16 Landing ................4-26 4.5.17 Flight in Rain ............... 4-27 4.5.18 Flight in the Vicinity of Thunderstorms ......4-27 4.6 Postflight Check ................4-27 Issued: June 2016 EASA app. 4-1 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 36: Introduction

    11. Check forward horizontal tail attachment for ball being fixed. Warning: When the ball is loose, refer to section 8.3. Issued: June 2016 EASA app. 4-2 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 37 (b) Opening of wing dump valves ? (c) Wing system completely water tight ? 17. Check control system functions using a helper. 18. Perform Daily Inspection according to section 4.3. Issued: June 2016 EASA app. 4-3 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 38 (use valve opener) Issued: June 2016 EASA app. 4-4 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 39: Daily Inspection

    Note: If a 5“ wheel is installed to a LS8-b this is a conversion to the variant LS8- sb and the “LS8-s and LS8-sb“ flight manual is effective. Issued: June 2016 EASA app. 4-5 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 40 6,2 bar/90 psi (d) Water drain orifices in front of tail skid or tail wheel free from clogging (e) Tail skid, if fitted, for proper adhesion Issued: June 2016 EASA app. 4-6 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 41 (i) Movement of tail control surfaces unobstructed and free from play (j) Condition of gap sealing: sealing strips should not protrude upward - danger of reduced control surface effectivity Issued: June 2016 EASA app. 4-7 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 42 Warning: When parking, remember that under a certain sun angle from the rear into the opened canopy this may result in fire hazard due to convex lens effect. Issued: June 2016 EASA app. 4-8 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 43: Pre-Flight Check

    (12) Check paperwork (C of A, logbook etc.) complete and valid (13) Landing gear locking without play (14) Check wheel brake operation (15) Before take-off, perform Cockpit-Checklist procedure, see section 4.5.1 Issued: June 2016 EASA app. 4-9 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 44: Normal Procedures

    11. Lock air brakes 12. Check trim position 13. Check release system 14. Lock canopy xxx ist he designation of the variant e.g. -a Issued: June 2016 EASA app. 4-10 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 45: Adjustment Of Rudder Pedals

    (1) the guide tube must also be removed (it may obstruct an emergency exit) (2) Additionally, an adjustable headrest according to drawing 3BR-101 must be installed. Issued: June 2016 EASA app. 4-11 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 46: Retractable Landing Gear

    Baggage compartment load counts for useful load and must therefore be included, when checking loading conditions. For permanent installation of batteries, barographs, ELT etc. see Maintenance Manual section 11. Issued: June 2016 EASA app. 4-12 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 47: Balancing Of Pilots

    Warning: Item d) Re-installation is permissible only - when the C.G. weighing included the tail battery in this position - when it had been removed for trimming afterwards. Issued: June 2016 EASA app. 4-13 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 48: Water Ballast

    (h) Filling sequence: always tail tank first, then wing tanks. Warning: Wing water ballast always must be compensated by tail tank water according to table in section 4.5.10.5. Issued: June 2016 EASA app. 4-14 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 49: Vertical Tail Fin Tank Loading Procedure

    4.5.10.5. Otherwise, keeping to the maximum approved rear C.G. position cannot be guaranteed. Warning:Filling funnel meshing is mandatory to guarantee tail fin tank valve function. Issued: June 2016 EASA app. 4-15 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 50: Wing Tank Loading Procedure

    Warning:Check proper dumping, tail fin system must start dumping together with wing system to avoid C.G. shifting backwards. See also section 3.7.3 for freezing / icing. Issued: June 2016 EASA app. 4-16 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 51 Warning: Check proper dumping, tail fin system must start dumping together with wing system to avoid C.G. shifting backwards. See also section 3.7.3 for freezing / icing. Issued: June 2016 EASA app. 4-17 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 52: Loading Plan For Water Ballast

    Wing water ballast must always be compensated by tail tank water ballast according to table in section 4.5.10.5; showing tail tank water amount in relation to wing water ballast amount. Issued: June 2016 EASA app. 4-18 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 53: Maximum Wing Water Ballast (Table)

    Warning: Wing water ballast must always be compensated with tail fin water ballast according to tables in section 4.5.10.5. Note: The values in italic letters can’ t be reached with variant LS8. Issued: June 2016 EASA app. 4-19 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 54: Maximum Tail Fin Water Ballast (Table)

    (see further directions see 358.3 -384.7 14.3 372.6-399.0 section 4.5.9) 385.8 -412.3 15.4 401.2-427.7 413.4 -418.9 16.5 429.9-435.4 Warning: See also Inadvertent Freezing / Icing, section 3.7.3 Issued: June 2016 EASA app. 4-20 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 55: Dumping Of Water Ballast

    Warning: Check thermometer regularly during flight. Dump water at +5° Centigrade <41°F>; ballast water in wing shell and tail tank should never freeze solid. (See also section 3.7.3). Issued: June 2016 EASA app. 4-21 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 56: Winch Launch / Auto Tow

    120 km/h <65 kt., 74 mph> (e) Recommended tow cable length: 30 - 80 m <100 – 260 ft> Warning: The C.G. hook is not approved for aero tow. Issued: June 2016 EASA app. 4-22 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 57: Free Flight

    When temperature is decreasing, dump water at least at +5° Centigrade <41° F> to ensure proper dumping and avoid structural damage at wing shell and vertical tail fin shell (Integral tanks). Issued: June 2016 EASA app. 4-23 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 58: High Altitude Flight

    6000 8000 10000 12000 6500 9800 13100 19700 26200 32800 39400 Max.permissible Speed km/h km/h km/h km/h km/h km/h km/h 97 kts 84 kts Issued: June 2016 EASA app. 4-24 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 59: Side-Slip

    Pressure pick-ups: Vertical tail fin pitot pressure Forward fuselage lower side static pressure (5) Partial water ballast yields unimportant difference in side-slip handling. Issued: June 2016 EASA app. 4-25 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 60: Landing

    20 km/h <11 kt., 12 mph>. Warning: Side-slip with air brakes extended is not recommended for landing, because nose heavy moment of air brakes allows no slow side-slip. Issued: June 2016 EASA app. 4-26 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 61: Flight In Rain

    Keep all water valves open for ventilation of wing water tanks and tail fin water tank. Unlock wing air brake system. For cleaning and care, see section 8.5. Issued: June 2016 EASA app. 4-27 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 62: Performance

    Data in the charts has been computed from actual flight tests with the sailplane in good condition and using average piloting techniques. Issued: March 2016 EASA app. 5-1 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 63: Approved Data

    The diagram shows airspeed indicator error due to position of pressure ports: Pitot pressure........at vertical tail fin about 3/4 up Static pressure ........at lower forward fuselage sides Issued: June 2016 EASA app. 5-2 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 64: Stalling Speeds

    <1157 lbs> 5.3 Additional Information 5.3.1 Demonstrated Crosswind Performance Aero Tow: ....20 km/h <11 kt., 12 mph> Winch Launch: ..30 km/h <16 kt., 19 mph> Issued: June 2016 EASA app. 5-3 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 65: Flight Polar

    Polaren 18 m bei 33 und 46 kg/m² Insects and raindrops on wing decrease performance and handling, see also section 4.5.16, Landing. Conversion table for Airspeed and Sink Rate: Issue: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 66: Weight And Balance

    Maintenance Manual section 2. In addition, section 6.3 lists guiding values for modification of Minimum Cockpit Load, as well as data for exact C.G. calculation. Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 67 Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 68 Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 69 Entries in section 6.2 refer to this basic condition. Caution: Simplified variation values are always on the safe (nose heavy) side. For more exact calculation use provided lever arms. Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 70 7.8.3 Emergency Locator Transmitter........... 7-11 7.1 Introduction This section provides description of the sailplanes operating systems, instrumentation and other information necessary for the safe operation of the sailplane and its systems. Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 71: Cockpit Controls

    G with TN8019 executed: Air brake and wheel brake Pedal adjustment Landing gear Water ballast Rudder pedals and wheel brake (feet operated) L with TN8019 executed: Only rudder pedals Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 72 G with TN8019 executed: Air brake and wheel brake Pedal adjustment Landing gear Water ballast Rudder pedals and wheel brake (feet operated) L with TN8019 executed: Only rudder pedals Only LS8-b: Dummy lever (petrol valve) Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 73: Air Brake System

    Loading possible after rigging. Equipment (for instance batteries) must be installed according to instructions in Maintenance Manual, section 11. Not permanently fixed, soft items count for cockpit load. Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 74: Water Ballast System And Operation

    Use as clean water as possible to avoid damage of seals due to foreign matter and clogging of draining and ventilation tubes. 7.5.1 Wing water ballast system Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 75 5 Draining tube of outer tank 6 Drain valve for both tanks 7 Drive lever 8 Cable to valve of outer tank 9 Additional ventilation of outer tank 10 Internal ventilation Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 76: Fuselage Water Ballast System

    (TN 8006) (6) Draining valve for both tanks (7) Drive lever (8) Cable to valve of outer tank 7.5.2 Fuselage Water Ballast System: Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 77 Flight Manual LS8 (LS8, LS8-a, LS8-18, LS8-b) 7.5,2 Fuselage Water Ballast System continued LS8-a and LS8-18: LS8-b Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 78: Electrical System And Operation

    1 A quick acting for electrical variometers and turn and bank indicators Cross section of cables: Battery cable min. 1 mm² (corresponds to AN 20 wires) Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 79: Pneumatic System

    When connecting an electrical variometer with electronic compensation, coupling boom statics (yellow) with upper forward statics (white 6 mm) near the instrument is being recommended. This results in better compensation. Issued: June 2016 7-10 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 80: Various Equipment

    After installation, cockpit loading limit values must be checked according to Maintenance Manual section 2. Caution: When installing a 406 MHZ ELT proceed according to TN DG-G-08. Issued: June 2016 7-11 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...

  • Page 81: Introduction

    3. The serial number can be found on the type placard, on the right side of the main bulkhead. 4. A Maintenance Manual is issued with each sailplane. Issued: March 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 82 (f) Life limited parts, such as tow release system components or seat belt harness may require other inspections. See Maintenance Manual section 0.4. Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 83 During repairs, never pull pushrods out of longitudinal motion bearings as all balls will leave their cage. To re-install them, a cut-out near each bearing must be cut and closed afterwards! Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 84 When the ball becomes loose (for instance by deliberate action or inadvertently) the attachment may be damaged during horizontal tail assembly due to non-alignment of ball and corresponding pin. Warning: Ask DG Flugzeugbau for special advice if this has happened. 8.4 Ground Handling / Road Transport a) Ground Towing...
  • Page 85 Supporting Area to lift whole Sailplane 1. Under wing spar near fuselage, never under nose section 2. Under fuselage shell in front of wing (main bulkhead) 3. Fuselage shell at tail skid Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 86 At any place, minimum width of support 8 cm <3.2 in>. Tail Unit: Note only for LS8-a, LS8-18 and LS8-b: Always keep wing discharge orifices open for ventilation during trailer storage. Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 87 For Canopy (Plexiglas) care never use dry cloth because of resulting static charge, consequent collection of dust particles and scratching. Cleanse with clear water and clean chamois leather, use anti-static fluid (for instance Plexiklar) afterwards. Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 88 Completely - Trichlorethylene unsuitable: - Carbon tetrachloride or similar hydrocarbon chlorides These liquids destroy the gelcoat. Other over the counter products must be tested before being used! Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 89 These bearings are used throughout the wing control systems, in the fuselage for the elevator-, aileron- and landing gear systems. Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 90 3.1 and blank inspection forms in section 14. (b) Inspect inside of fuselage for small animals (Mice, birds etc.) and/or nests. (c) Check compass deviation and update deviation table. Issued: June 2016 8-10 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 91 9.2 List of Supplements Included Date of Document No. Title of the inserted Supplement Insertion ---- Issued: June 2016 Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited...
  • Page 94 CENTRAGE PAR WB DE DERIVE en fonction de la charge cockpit (pilote + parachute + bagages + batterie(s) dans soute à bagages) BATTERIE DE DERIVE EN PLACE Masse d’eau Charge Nombre de cockpit gueuses de dans ballast de (kg) 2,45 kg dérive (kg) (1) (1) : Masse d’eau (facultative, pour obtenir un centrage arrière) pour équilibrage de la charge cockpit...
  • Page 95 LS8-18 : PROCEDURE DE BALLASTAGE (pour procédure complète, voir FLIGHT MANUAL § 4.5.10) Préalables :  Utilise l’eau la plus p op e possi le, sa s au u additif  Avec les WB pleins, la pression de la roue principale doit être gonflée à 4 bars ...
  • Page 96 LS8-18 : PROCEDURE DE MONTAGE ET DEMONTAGE (pour procédure complète, voir FLIGHT MANUAL § 4.2.) MONTAGE LS8-18 :  V ifie ue les ou ho s d’ ve ts en caoutchouc situés à l’e pla tu e des ailes 2 t ous pa aile, à...

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