Flight Manual and Service Manual for sailplane type
Contents
1. Pepe od en b ae Dr x Flight Manual and Service Manual i for sailplane type DG 100 ii ELAN EST EST E God T C E Type Certificate Data Sheet No G E U i German Sailplane Data Sheet No 301 p s t un Na 5 RN pos a bo ds DORUM 5 4 N iA a bie scd EN n UM IND es ae ugue m MT L dH Dd a d 5 1 pe A a Manufacturer Glaser Dirks Flugzeugbau GmbH a 8 EN 7520 Bruchsal 4 i Im Schollengarten 19 20 ODE 1 7 vy v psa a 11 e i l i West Germany bh ee ee Ys FU dn BREVES ds Telephone 07257 1071 i FONS d oak i RENN uu 7 Owner cera Cea ae Siehe 0 Sie R e i 0 i ii SEN MN A mows Y 1 9 s cw Ww a Eu ok a DE 3 DN i VY gt i iN i Dow i bou gods qd FF UD fet Wes i 5 a WINE Si uu 188 3 This flight handbook is to be carried in the TUM o ves M M ae sailplane Vv OQ x i 0 i M 1 P De i am i i rj D l Date of issue 21 April 1975 the Pages 1 through 17 and diagrams 2 4 5 and 6 of the original German Language Flug und Betriebshandbuch DG 100 have been approved by Luftfahrt Bundesamt manual fo umenA went s hinged Canopy ed 24 April 19015 124 April 19792 102. necessary remove paint and putty to determine if cracks extend into FRP Check for white spots and delaminations around bushings Shell Compression fractures cracks blisters Spanwise hair line cracks in the leading edge near the stagnation point can be ignored Ailerons Compression fractures cracks blisters Check hinges and drives Issued April 21 1975 Service Manual DG 100 Check list Fuselage Fuselage to wing connections White spots excessive play bent tubes hard assembly Fuselage and vertical stabilizer intersection Cracks Scrape away paint and putty While moving vertical stabilizer side to side and fore and aft check for cracks extending into GFRP Stabilator mounting Excessive play Check top rib of vertical stabilizer for cracks expecially near fittings Rudder bearings Excessive play white spots in FRP bent fittings cracks in finish Tail wheel Enlarged axle hole If so fill with thick filler Fuselage shell Outside Cracks creases nicks Inside White spots sharp white zig zag lines cracks Any loose ribs Has any bulkhead become loose To check this remove also the control column boot instrument panel cover and the access cover of the tow hook compartment and check the bulkheads in this areas carefully Torsion check Hold fuselage steady and attempt to move vertical stabilizer does it move easier than usual If so are the cracks visible Landing gea
3. noti 100 T as versus EAS 80 70 VA 60 TEREE 50 Pa 0 2 0 50 9 70 30 100 110 E Af Pquivalen alr spaced The airspeed indicator utilizes the forward static ports diagram Examples for calculating the water ballast 1 2 3 kg 1b 235 518 24o 529 24o 529 Emptyweight page 21 Pilot and parachute 75 165 9o 198 5 5 1 231 6 Baggage 5 11 8 17 6 20 44 Waterballast loo 220 8o 176 5 34 75 Take off weight 415 915 418 922 399 880 M M M M Max take off weight without water ballast Max take off weight with minimum 8o kg 176 1b water ballast 4 240 529 115 253 7 3o 66 385 849 385 kg 849 1b 418 kg 922 1b Diagram 5 issued 25 10 75 Diagram 6 Placard Locations Take off check Trimm weights Parachute worn correctly Pilot seat belts and shoulder hornest fastenen Seat back and rudder pedals aajusted All controls and instruments in easy reach Altimeter Spoilers checked for operation and locked Flight controls tested Trim set Canopy properly closed and locked xo CO Un Awn 1 CS fbs Minimum weight in pilot seat wi
4. Empty Weight C G aft of datum in Minimum Weight i pilot seat 165 lbs Maximum Payload ibs Pilot with parachute water baggage 6 3 Reference Data Wing Sweep Back o Dihederal Leading Edge Line Airfoil contour break 212 mm 8 35 inches Angle of incidence 0 Wing oscillated frequency min Aircraft should rest on the wheels during the frequency measurements Issued April 21 1975 Service Manual DG 1oo Flight control Travel and Tollerance Aileron up down 46 mm 5 mm measured 188 mm from center of motion If the full travel distance is too small the short push rod on the aileron drive must be shortened Rudder 243 mm lo mm tolerance measured 460 mm from center of motion The midpoint of rudder travel can be adjusted by letting out on one cable and taking up on the other simultaneously and in equivalent amounts Stabilizer 139 2mm 66 2 mm Stabilizer position may be determined in the following manner Level the fuselage lay a straight edge across fitting I position a length of adhesive tape 85 mm below the straight edge The tape must also be level Using the tape as a referance line measure stabilizer position according to the sketch below Reference line adhesive tape Issued April 21 1975 Service Manual DG 100 Trim tab permanently adjusted at factory With the stabilizex
5. from hinge line lift rudder with small scale Tf the scale reads more than 450 g 1 1b correct by adding metal strips to mass balance until the scale reads less than 430 g 0 95 lbs Aileron Suspend the aileron freely at hinge line and lift 180 mm 7 09 in from hinge line with scale If scale reads more than 388 g 0 85 1b the mass balance must be increased Stabilator Holding the stabilator by its mounting fitting Lift with scale 181 mm 7 125 in from hinge line until surface lies level Scale must not read more than 220 g 0 48 1b 6 13 Tangential play of horizontal tailplane Tangential playis unobjectionable if it does not exceed lcm 0 4 in Measure only the play not the elastically deformation of the whole structure Check for clearance between tailplane trimtab and the access cover Enlarge clearance if necessary 1 Issued April 21 1979 Service Manual DG i o0 6 14 Play in Control Systems Alleron ith the stick fixed in a neutral position the play in the aileron 188 mm fromthe hinge line should be 1 5 mm and the aileron should be neutral With the aileron fixed the piay in the stick at the top should be 3 mm Stabilator liith the surface fixed in neutral the play at the stick at the top should be 3 mm Trim tab With the stabilator in neutral allowable pla is 0 5 mu at 116 mm from hinge line Rudder Axi
6. 22 9 80 Type certification inspector
7. 6 Be certain the wings are level 7 Measure the distance between perpendiculars through points a and b see figure next page Using the Empty Weight and the values determined above calculate the C G as follows W C G Empty X empty 2 empty x kx Repairs or alterations Gross Weight empty After the addition or deletion of equipment or accessories repairs painting or any change in the aircraft that could influence the weight and balance a new weight and balance must be computed Aircraft certificated as Standard Catagory must have the weight and balance certified by a licensed Airframe Mechanic Empty weight C G range is determined by referance to diagram no 2 If the C G is out of limits adjustments may be made by ballasting or by relocating equipment or accessories Weight includes all accessories but excludes pilot and parachute Remove loose objects from cockpit C G In Flight X 2 flight x b 5 82055 Gross weight iis 5 flight The flight weight includes empty weight items plus pilot parachute and all items needed in flight barograph camera cushions etc In addition the rudder pedais and seat back should be adjusted as in flight Issued April 21 1975 ora tae Issued April 21 1975 Service Manual DG 1loo 6 2 Weight and Balance Record Maximum allowable Flight Weight Weighed on Empty Weight Instruments Oxygen Equipment
8. EFFECTIVITY DG gliders and motorgliders S on request 5 ACCOMPLISHMENT with installation of new harness X REASON Some newer types of harnesses are not listet in the maintenance manuals of all DG types INSTRUCTIONS 1 The following newer types are accept able for installation Certification No Gadringer BAGU 5202 G 40 070 32 SCHUGU 2700 G 40 071705 rubber coated adjuster bars Autoflug BAGU FAG 12 D O 30 070 87 SCHUGU FAG 12 H O 40 071 25 t S Schroth H 01 0 104 40 073 11 x f Install the new harness similar to the i existing harness i 4 ey 2 If you install one of these types file 34e 24 OF this TN as enclosure into your aircraft M 8 6 7 Y maintenance manual we psc ou X n 3 Enter the new harness in the equipment x x list of your aircraft or write a new x equipment list 5 5 3 3 REMARKS The instructions may be executed by the 55 owner amp M They are to be inspected and entered in 4 2 N the aircraft logs by a licensed inspector Vs 0 v 9 QA Bruchsal 4 date LBA approved Jan 24 1996 The German original of this TN has been approved by the LBA under the date 0 5 Marz 0208 ana is signed by Author W Dirks Mr Fendt The translation into Eng lish has been done by best knowledge yy Ow and judgement 5 42 024
9. additional addition P cover ent Dirge 2 n2 Flight Handbook DG 10oo 4 11 Water Ballast One 4o kg or 56 ke PVC water tank in each wing Dump is accomplished thru a central valve in the fuselage and out of an opening behind the main gear On the ground each wing can be drained individually by lowering the opposite wing The dump rate in flight is about one quart per second so the amount remaining can be easily controlled Filling the Tanks Close dump valve and lower a wing Connect the supplied clear plastic tube Fill ballast tank while observing tube After the tank is full as indicated by the sight tube raise the wing and drain the water remaining in the tube Remove the fill tube and connect hose to dump valve Repeat for other wing After loading ballast level wings and check for inbalance Correct imbalance by draining the required amount from the heavy wing The PVC connections should be lubed occasionally to prevent binding Precautions Concerning Flight with Ballast Ambient temperatures of less than 0 C could cause the water to freeze so dump ballast prior to encountering these conditions Ballast raises the landing speed and increases the landing roll It is therefore recommended that ballast be dumped before landing off field Dump immediately in case of leak Maximum allowable ballast is determined by use of diagram 5 Issued April 21 1975 Service Manua
10. without much loss of altitude Rain has been found to have very little effect on stall characteristics High Speed Flight The stabilator is mounted in such a way that rough air does not transmit pitching forces to the stick The trimmable anti tab provides stability The DG 1oo may be trimmed at any speed up to maximum however the pilot should maintain a grip on the stick at all times at high speeds Maximum permissable speed of 135 kts 155 np must be observed 4 6 Spins Water ballast in both wings does not affect spin performance Spoilers should not be opened at any time to enter or recover from a spin The DG loo has no spiral dive tendency The spin performance is strongly dependent upon the C G location The following are some examples of spin characteristics for typical C G locations Issued April 21 1975 Flight Handbook DG loo Xg 7 86 in A spin is not possible with this C C location Depending upon the manner of pull up the aircraft may stall and change heading 90 180 degrees before resuming straight flight or it may simply mush straight ahead X 12 67 in A spin is possible under the eo conditions From slow flight just slightly above quickly pull back on the stick all the way and 88 apply full rudder When the rudder tends to stay in this position a steady state spin is achieved Accompanying this is a slow longitudinal pitch down tendancy which does not affect the recov
11. Issued June 1986 9a Nose up up o 000000000 9969 023 Spoilers Water ballast dump Rudder pedal adjust Ventilation Issued April 21 1975 Flight manual DG 100 4 4 Take off Take off check 1 Trim weights 2 Parachute worn correctly 3 Pilot seat belts and shoulder harnest fastened 4 Seat back and rudder pedals adjusted 5 All controls and instruments in easy reach 6 Altimeter 7 Spoilers checked for operation and locked 8 Flight controls tested 9 Trim set 10 Canopy properly closed and locked Take off Roll The location of the tow hitch in the fuselage centre line the extraordinary aileron control and the low lift off speed with its reduced ground roll all combine in a controllability that effectively reduces possibility of wing drop and ground loop These factors also enhance crosswind performance Aero tow a If only a C G release is installed then the aerotow is to be executed with this release Set trim in 12mm aft of full nose down b If an additional tow release for aerotow is installed only this release should be used for aerotow Adjust the trim for aerotow so that the indicator is 3 cm 1 2 in behind the forward position c General Hold stick in resulting position and at 75 80km h 38 43kts 44 50mph ease stick back to lift off On very rough surfaces keep a tight grip on the stick After attaining
12. in the o position and the trim con trol 3 mm ahead of the full aft position the trim tab should fair in with the stabilizer Friction adjustment is on the left side under deck of baggage area Spoilers The short push rod in the fuselage is adjusted so that the spoilers are extended evenly and are easily locked closed Extension out min 140 mm in O mm It is important that the control rod ends are not unscrewed more than a maximum of 60 mm 9 AN 6 4 Inspections x Every 200 flight hours the following items are tO be checked 1 Rudder cables for wear especially near the S shaped tube guides of the pedal adjustment mechanism Replace worn cables with the following hardware Steel wire cable 3 2 mm diameter LN 9374 with copper NICOPRESS sleeve 28 3 M use tool No 51 M 850 or 63 V XPM or 64 CGMP use M groove 2 Trim tab cable ends particularly where they connect with the aluminum levers The forward lever is located under the baggage area deck on the left side The rear lever is visible through the rudder cove bulkhead after removing the rudder 3 Check every year all screwed connections and safety de vices Check controls for sufficient lubrication and rust prevention CARD emergency release of p single piece canopy To be checked every 3 month referring to flight manual page 9a 5 Wheel brake Adjust the wheel brake occasionally This is done at the adjustment screw at the front landing gear strut abo
13. safety altitude the landing gear can be retracted with a forceful operation of the gear handle Normal tow speed is 100 120 km h 54 65 kts 62 75mph Cruising tow speed is 165 kmh 90 kts 103mph Winch Launch only allowed at the C G release All phases of the takeoff are normal After reaching a safe height the stick should be pulled back slowly so that not too much speed is gained The most comfortable winch speed is 100 110 km h 54 60 kts 62 68 mph with a minimum of 90 km h 49 kts 56 mph and a maximum of 130 km h 70 kts 81 mph Pull the tow release after reaching launch altitude Do not wait for the automatic to function Issued March 1998 TN 301 19 11 Flight Handbook DG 1oo 4 5 Free Flight Thermal Soaring Because of the long tail moment arm the DG loo has good directional stability The good roll rate 3 5 sec from 459 bank to the opposite 45 bank provides the maneuverability to immediately compensate for irregularities in thermal strength or size Quick Maneuvering at very slow speeds can be done without fear of stall Stall Characteristics When the DG foo stalls it really only mushes without a distinct stall break Full aileron control is always available Entering the stall with more speed and a sharp pull up will force the DG loo to a more distinct stall break and a roll to the side Easing up on the stick and rudder in opposition to the roll will execute a recovery
14. the fuselage boom should not be damaged 92 130 92 X Stabilator aileron rudder shell inside and Holes cracks blisters in the wings tail and outside control surfaces not in excess of the following dimensions 110 3 Trim tab x 92 ilo 2 125 amp Diameter Length Forward fuselage lloxoutside belly 3x 92 125 X Wi 1 15 ings oo mm mm 125 ft Stabilator 50 mm 8o mm Aileron 56 mm 80 mm Rudder 50 mm 80 mm Fuselage boom belly 5 1 x 92 lloXoutside r 3x 92 125 125 t The parts may not be damaged in the spar area 4 Replacement of bent fittings 4 Method of beveled repair SSS aul ti d FRP shell ex fuselage 8 f t outside FRP foam sandwich b pe inside ex wing lI fethof of FRP repairs 2 3 above 1 Remove damaged fabric bevel edges and roughen surface around hole All repairs must follow the procedure of wet over dry Special tips for handling FRP repairs are found in the Petite Plane Patch Primer Outside fabric layers can be pressed into foam before new layers are applied Issued April 21 1975 Service Manual DG loo 6 12 Control Surface Mass Balances After the repair of any control surface the mass balancing must be checked Rudder MM 1 connect control cables and lie fuselage on its side so that stabilizer is horizontal At a point 200 mm 7 87 in
15. the possibility of future retraction problems A simple hosing with water is the best cleaning method Issued April 21 1975 Flight Handbook DG 100 4 10 Hints for the Competition Pilot M HMRM A few general tips on ballast For lift of less than 2 kt 1 m s it will be profitable to fly without ballast This is also true for extremely weak weather or when working the weak evening lift Medium lift of 4 kt 2 m s will require about half ballast 40 1 or 11 US gal 9 Imp gal Use full ballast in lift of 6 kt 3 m s or more Maximum allowable takeoff gross weight must be observed The maximum ballast is determined by empty weight and fuselage payload by meaus of Diagram 5 While in flight ballast may be reduced as desired by using a dump rate of approximately one quart per second 11 sec The competition pilot will appreciate the enhanced response given by a center of gravity which lies near the aft limit To obtain maximum performance the sailplane surfaces should be clean and gaps at the wing and fuselage junction and at the tail should be sealed with tape The polar diagram 1 is valid only under these conditions An accumulation of dirt rain etc will degrade performance slightly Issued 01 06 1982 15 Flight Handbook DG loo Good instrumentation is necessary to achieve high efficiency flight In addit
16. wing Fill with the desired amount of water remove the hose and close the valve with the waterballast lever Place the other tank In case the valve leaks slightly apply some grease to the valve surfaces After filling tbe tanks check to see if the wings are balanced If one wing is heavy release enough water to balance the wings Precautions Concerning Flight with Ballast Ambient temperatures of less than O could cause the water to freeze so dump ballast prior to encountering these conditions Ballast raises the landing speed and increases the landing roll It is therefore recommended that ballast be dumped before landing off field Dump immediately in case of leak Maximum allowable ballast is determined by use of dia gram 5 Issued April 21 1979 17 Service Manual DG loo Ss Assembly and disassembly 5 1 Assembly l c2 Issued Open the canopy and open the access cover with a Screwdriver Clean and lube the pins bushings and tbe ball end of the control rod quick connects With a helper on the wingtip lead the wings into place Sight through the wing main pin bushings to determine alignment Push the main pins in as far as possible Turn the handles up to the fuselage wall Therefore pull out the white securing knob Set the knob back in its locking position Connect aileron and spoiler controls Spoilers Should be closed but not locked To check the quick disco
17. with clear water using a sponge and chamois Never use gasoline alcohol or thinner for cleaning Do not use detergent too often The surface may be pollished as often as desireable When using a power buffer care must be taken that the surface is not overheated This sailplane should be protected from moisture just like other sailplanes The surface should be protected from intense sunlight heat and ballast should not be retained for extended periods 6 8 Lubrication Periodically make a detailed inspection of the sailplane and lube all bearings Especially the 811 bearing univers jams should be cleaned and lubed Molycoat Long life These areas are involved o Aileron drive directly accessable at the wing contour break Spoiler drive in the spoiler box In this location are the spoiler bearings which should be lubed Unscrew the push rod fairing on the left bulkhead and lube the guides Remove the storage area deck Stabilizer aileron trim and water ballast control rods should be lubed Service Manual DG o00 o Open fuselage access cover Lube sopiler control and flight control quick disconnects o Remove stick mechanism cover Lube stick mechanism o Lube guide of rudder adjustment mechanism o Oil bearing points of gear struts in wheel well o Lube the guide of the gear lever with Vaselene o Clean and lube all hinges elevator rudder ailerons trim Single piece ca
18. 09 80 DM 5 Flight m p 4 5 6 SI units 01 06 82 Wek 11 13 14 15 16 Content p la Increase of service time May 1985 Service m p 37 38 TN 301 11 7 Service m p 23 26 Emergency release of the May 1985 Service m p 29 35 Amendments TN 301 13 May 1985 36 emergency release and Flight m p 7 9a Marking of canopy June 1986 w De 301 14 ventilation pr m p 23a Airbrakes TN 301 18 Oct 1996 Flight m p 3 11 Installation of an additional March 1998 LJ N 2 Issued March 1998 2 Flight manual DG 100 1 Brief Description Single seat high performance Standard Class sailplane Construction Wings and tail GFRP foam sandwich shell GFRP roving flanged spar Fuselage GFRP shell Landing gear Retractable Main Tire and Wheel 5 00 x 5 Internal drum brake 14 5 inches circumferance The wheel well is completely sealed and isolated from the fuselage Tow Hooks CG up to ser no 32 Safety tow release Europa G72 or Europa G73 from ser no 33 on and all DG 100 ELAN Sonderkupplung SH 72 additional as an option Nose release E85 installed below the instrument console only for aerotow Cockpit Inflight adjustable rudder pedals Optional inflight adjustable backrest with provision for automatic or manual parachute Long canopy extends far down side of fuselage for excellent visibility Quick disconnect instrument console Trim landin
19. Spin Vae slow deceleration Rudder gusset Serial No SR Maximum load factor at maneuvering speed 45 3 2 65 above the tail wheal 28 ps i at never exceed speed 5 0 1 5 AIL aerobatic maneuvers including spins euet be accomplished in accordance with the approved 26 106 Flight Manual s Diagramme 7 mme Supp I 100 DG Difference in placarting for single piece canopy diagram 6 a TN 301 14 issued June 1986 Diagramm 9 24 4 33 7 88 9S 2 WEIS GLOI 9A 2 Sjosjwe aI pune Zia 2M BAG 4d addiy ranig T 8 sade smaig pun apnissny ZerN So FLEISS ji Ada 4704 AM tI gt ee WL Q rr07 5 7 S t J e102 wale 10 0 enasns2 42n p 29 DM X d Np 7 deer F NY 0 eC wy b 6 7 1 1 e 5 RS f 3 ec i 845 i 36 nje Z761 2 7 p O 006 57 10 842 9 704 40 Op renee Diagram 40 Technical note Page from 7 No 301 17 323 8 359 18 No 826 31 248 7 370 5 No 866 h 384 3 873 7 SUBJECT Seat Harness M
20. T 6 9 9 6 5 4 85 ov 9 9 5 8 5 5 6 This flight handbook is to be carried in the sailplane Date of issue April 1979 Pages 1 through 17 and diagrams 2 4 5 and 6 of the original German Language Flug und Betriebs handbuch DG loo have been approved by Luftfahrt Bundesamt Concerning DG 100 and DG 100 G with hinged canopy Dear Sir One of our customers made the experience that the opened canopy has the effect of a burning class when the sun shine is strong Especially the leatherette parts might be heated to much We recommend to keep the canopy closed or to cover it with a cloth Please file this page after the first page of your DG 100 flight and service manual Yours sincerely W Bot Bruchsal 4 2 03 1977 Flight Handbook DG loo Contents Ammendments 1 2 3 4 Brief description Operations Limitations Airspeed limits 2 Center of gravity in flight 3 Weights 4 Loading Plan 5 Safety links 6 7 8 9 Tire pressure Aerobatics Instrument flight Cloud Flying Minimum required equipment 2 2 2 2 2 2 2 2 2 Emergency Procedures 3 1 Spin recovery 3 2 Recovery from unintentional instrument flight conditions 3 3 Rain and ice Normal Operations Preflight inspection Cockpit and controls Cockpit placards Take off Free flight Spins Instr
21. al play at the upper hinge max 0 5 mm max o 5 mm Repair of the brake cable In case of replacement it is of importance that the cable should be placed between the two parallelogram armsof the sticksystem see drawing Placement of the cable outside the parallelogram might lead to a blockation of the stearing mechanism issued 7 Service manual DG 100 Instrument and equipment list Airspeed indicators Manufacturer Type Winter 6 FMS 4 10 210 10 Winter 6 FMS 5 2 10 210 3 PZL PSO 6 PZL PR 400 S The airspeed indicator must have the speed range markings see Flight manual page 6 Altimeters Manufacturer Type Winter 4 FGH 10 PZL PW 12 Four piece safety belt and shoulder harness symmetrical Manufacturer Type Gadringer BAGU IV B 40 070 16 SCHUGU I1 c 40 071 05 SCHUGU FAG 7 D O 40 070 30 BAGU FAG 7 H O 40 071 21 In addition for cloud flying Radios Manufacturer Type Dittel FSG 40 S 10 911 45 Becker AR 2008 25 10 911 48 Essued May 1985 TN 301 13 35 Service manual DG 100 Compass Manufacturer Type Bohli 46 MFK 1 PZL 8 13 KJ Ludolph FK 16 The compass is to be compensated in the glider Variometer Manufacturer Type Winter StV 55 58 Winter StV 5 80 Winter 5 StVL 10 230 11 Winter 5 StVLM 10 230 12 Winter 5 StV 10 230 13 Winter 5 StV M 10 230 14 PZL PRO 4 d 58 PZL PRO 03 d 80 Turn and ban
22. an also be found in the Petit Plan Patch Primer A list of materials for the DG loo and a check list for post accident inspecstion is found on pages 27 29 Repairs by the owner should not b attempted if the spar is damaged 2 the main fittings on the wings 2096 182 or tail are torn out or if in the immediate vicinity there are white areas in the laminations the parts are torn in such a way as to make repairs uncertain without the use of jigs or appliances the damage is so extensive that the or contour is obscured Cut away undamaged areas as necessary to gain access to damaged areas Issued April 21 1979 0 aa p 28 27 26 25 24 23 Diegram 2 DE 06 empty watght Cb range dis pa dant ypun empty weigh an of pilot weight emply weight C6 abt of datu Cio echas minintum pliet weight tinct parachute 75 ths 143 lbs 155 tbs 143 ths 470 80 430 500 510 S20 tmpty weight Fahr werk Seitensteuerung landing gear rudder control DG 100 122 S426 Diagramm 10 4 u Flight Manual and Service Manual for sailplane type DG loo ELAN Type Certificate Data Sheet No G E U German Sailplane Data Sheet No 361 Manufacturer ELAN Toverna Spotnega Orodja 64 275 Begunje Gor Jugoslawien Tel 003864 75010 Owneri 1 0 0 000 sieve ws CENE RE
23. ball seat Bruchsal 4 July 15 1986 E Chakra DAL Service Manual DG loo 6 9 Material List List of materials used in the 16 Resin Shell Epikote 162 Catalyst BASF Laromin C 260 Mixing proportions looparts resin 38 parts catalyst by weight or 2 parts resin part catalyst by volume Fiberglass Fabric interglas No US No Weave Weight grams sg meter 90070 l6lo Linen 8o 92116 Twill 163 92125 Twill 280 92136 Linen 390 92145 18t i50 Unidirectional 220 All fabrics finish I 556 Rovings Gevetex EC 10 80 2400 K 43 with Silanschlichte Foam Continental Conticell 60 Color brown R hm GmbH Rohacell 51 Color white Lacquer Lesonal PE Schwabbellack Mixing ratio loo Filler The resin catalyst mixture may be thickened with chopped cotton fibers Non thickened resin and catalyst mixture is applied to the area first as a bonding layer then the thickened mixture may be used Issued April 21 1975 Service Manual DU loo 6 10 Check List After Suspected Damage Entire Aircraft Inspect the general aiignment along the longitudinal exis vertical and horizontal tail surfaces Wiug flex characteristics wing angles and measurements in agreement with previously mentioned specs Wings Spar pins Check for deformation in main pins and bushings and also white spots around bushings Wing root rib Separation between rib and wing shell or between rib and main spar
24. erloads At maximum permissible airspeed only 1 3 of full control deflection should be used Maximum permissible airspeed is based on true airspeed The airspeed indicator reads indicated airspeed The higher the altitude the greater the difference between true and indicated airspeed The following table shows the indicated airspeed for V p at altitude Muse 220 300 qup sp 5908 Altitude ft o 6000 9000 12000 15000 18000 Vwg kts IAS 140 133 126 120 113 mph 161 153 145 137 130 2 Center of gravity in flight leveling means Tail down slope of loo 3 67 measured at top surface of aft fuselage 0081 See weight sheet page 20 Issued 01 06 82 Flight Handbook DG 100o Datum d Leading edge of wing at root Forward limit 7 86 inches aft of datum 199 6 mm Aft limit 14 37 inches aft of datum 365 mm 3 Weights Empty weight approx 230 kg 500 lbs Maximum gross takeoff weight without water ballast 385 kg 849 Ibs With minimum 80 kg 176 lbs waterballast 418 kg 922 lbs Maximum weight for non lifting parts 270kg 595 lbs 4 Loading Plan Cockpit payload Pilot including parachute max 177 kg 258 lbs min 75 kg 165 lbs Pilots C G most forward position at max payload 492 mm most backward position at min payload 537 mm Maximum allowable gross takeoff weight must be observed It is essential to compensate for too little cockpit weight either by ballast in the pilots seat or trim weight in t
25. ery pull out If on recovery the rudder is only returned to neutral the aircraft will continue to rotate 3 4 of a turn Full opposite rudder will result in only 1 4 to 1 3 turn before recovery The highest recovery speed will be 81 86 kt 93 loo mph 15 2 in The pitch down in the spin is very minimal 85 is also the airspeed during pull out Recovery is normal with opposite rudder Spinning from 459 bank with rudder into the rotation simply neutralizing the rudder will not stop the spin Full opposite rudder and full back stick will result in a recovery after 3 more turns Neutral stick then full opposite rudder will cause the aircraft to make 1 turns before recovery The quickest method is full opp site rudder followed by neutral stick or slightly forward of neutral which will result in recovery after y turn 4 7 Instrument Flight Cloud Flying Fly especially smoothly One should not use a spin as a rescue measure In emergency open the spoilers and maintain approximately 108 kt 125 mph 200 km h until regaining visual flight conditions Issued April 21 1975 Flight Handbook DG loo 4 8 Aerobatics only without waterballast Only the bE o are approved If the given entry speeds are observed there will be no necessity for especially vigorous control application and high structura loads will be avoided A11 maneuvers are to be done gently The follo
26. found habe been duly repaired the service time may be extended to a total of 6000 hours third step For a possible service time exceeding 6000 hours procedures will be evaluated in the future Issued May 1985 TN 301 11 37 Service manual DG 100 LBA approved Glaser Dirks Flugzeugbau GmbH document No XXXX to be issued and approved in the future contains the structural inspection procedures and limitations to be used for extending the service life above 3000 flight hours The inspection must only be done by the manufacturer or by a licensed repair station or inspector The results of the inspection have to be recorded in an inspection test report wherein comments are required for each inspection instruction If the inspections are done outside the manufacturer s facilities a copy of the records must be sent to the manufacturer for his evalution and information The annual inspection is not affected by this inspection program Issued May 1985 TN 301 11 38 3 weight iarl parachute 29 86 assuage 1 1 EN gael Parfes TUT way pa rer or 29 Me SKYL OS os Airspeed Calibration DG 100 TAS 4 airsptecl
27. g gear and spoiler controls all on left side Parallelogram mechanism at stick for elevator control prevents PIO s and unintentional movement of stick and elevator in turbulance Spoilers Schempp Hirth type on upper wing surface only Tailplane Mass balanced all flying horizontal T tail with cockpit controlled trimmable anti tab Colour White registration numbers grey Issued March 1998 TN 301 19 3 Flight Handbook 206 1066 Technical Data Wing span 49 2 feet 15 m Wing area 118 4 square feet 11 m Aspect ratio b2 S 20 5 Length 23 feet 7 m Airfoil FX 61 184 FX 66 126 21US gaK 176 1b 80 kg or 26 US gal 220 1b loo kg 2 Operations limitations and operational values 252222 222 292 4252252325 see SSS 2222225222 58 Ss srs SS 252 25 222252 222222 mI TID 222252 252222 Water ballast Flight performance group N LFS Normal catagory 1 Airspeed Limits I A 8 Never exceed VNE Maximum speed in rough air VB 260 km h 162 mph 140 kts Maneuvering VA 165 km h 1o3 mph 89 kts On aerotow YT 165 km h 103 mph 89 kts On winch tow Vw 130 km h 81 mph 7o kts Landing gear extended 165 km h 103 mph 89 kts Spoilers 260 km h 162 mph 140 kts 260 km h 162 mph 140 kts Full control deflection is permitted at all speeds up to maneuvering speed At speeds in excess of maneuvering speed control deflection should be reduced to prevent structural ov
28. he trim weight holder 46 1 inches forward of datum One 4 9 lbs trim weight will compensate for 8 lbs missing from the pilot seat Seat ballast metal or sand bags must be securely fastened to the glider at the seat belt attachment points Baggage 3o kg 66 lbs at station 23o mm 9 1 in aft datum Waterballast Each wing tank has a capacity of log gal 88 lb 4o kg or 26 gal 110 1b 5o kg Maximum allowable ballast is determined by the empty weight and fuselage payload by means of Diagram 5 Both tanks should contain equal amounts of ballast Station 200 mm 7 9 in aft of datum 5 Safety weak links Winch launch and aero tow lloo 66 lbs 500 30 kp 6 Tire Pressure Main wheel 36 lbs 2 5 bar 2 bar 01 06 82 Flight Handbook DG 1oo DS 7 Aerobatics only without waterballast The following maneuvers are approved 1 Spins Entry Start a slow pull up When the aircraft starts to buffet apply full back stick with rudder in the desired direction of rotation Recovery Rudder in the direction opposite to rotation pause then ease the stick forward When rotation stops neutralize rudder and gently recover from dive A spin is not possible with the C G far forward therefore the C G should be mid range when attempting spins An aft C G will produce a flatter spin E ODE entry speed 92 kt 106 mph 1705 4 3 Wingovers Stall Turns Oo 4 Chandelles now E 8 Instrumen
29. heck the surface for small depressions bubbles and other uneveness This could be a signal that something is not right Contact the manufacturer immediately and if possible send a photo of the damage and a report by a licensed airframe mechanic The manufacturer will be able to supply the correct advice and a repair program saving you the time and troubles of quesswork and bad tries Minor surface damage such as scratches gouges and cracks in the finish may be repaired by a licensed airframe mechanic See also page 31 Knowledgeable advice can also be found in the Petite Plane Patch Primer A list of materials for the DG 1oo and a check list for postaccident inspection is found on pages 27 29 Repairs by the owner should not be attempted if The spar flange is damaged The main fittings on the wings fuselage or tail are torn out or if in the immediate vicinity there are white areas in the laminations The parts are torn in such a way as to make repairs uncertain without the use of jigs or appliances The damage is so extensive that the original shape or contour is obscured Or if it would be necessary to cut away undamaged areas to gain access to damaged areas Sept 24 1980 24 Issued April 21 975 Service Manual DG loo 6 7 Service and Care You have chosen a sailplane made of fiberglass which though elegant is enormously strong and robust A few tips for care of the surface Wash the surface only
30. ing speeds and stall speeds are only slight ly affected Otherwise there is no discernable influence in flight characteristics due to rain or light icing 2 Water ballast installation Freezing of the water is a possibility at ambient temperatures of 0 C 329 F or below so it is advisable to dump the ballast prior to encountering these conditions Canopy emergency release bail out a Two piece canopy To bail out open the canopy a few inches and it will be blown open and tear off in the airstream i Single piece canopy Open the canopy opening lever and pull then the emergency release knob The low sides of the cockpit allows for a quick push off exit Issued June 1986 Flight Handbook DG loo Normal Operations 222 222 222 222 222222 2 222 2 2 2222 Preflight Inspection Daily Inspection The aircraft surface must be free from uneveness or irregularities blisters depressions or cracks in the finish See also 6 6 All control system quick disconnect fittings and assembly pins are to be inspected See also part 5 Check for any kind of extraneous matter or objects Check aileron and rudder connections Check all control elements for security and freedom of movement Tow release check Function and free of dirt Visual check of landing gear wheels and tires Dirt in the forks of the main gear may cause later retraction problems Issued A
31. ion to a variometer one certainly should have a combination instrument which displays airspeed vertical velocity and Mc Cready values Several Sollfahrtgeber instruments are available from German manufacturers The following Mc Cready values are computed for still air m S kt 5 9 lbs 29 kg m 6 8 1bs33 kg m wing loading E f su f airspeed kts 0 o Sl 597 95 54 621 900 gph km h 1 2 68 78 125 7o 81 130 2 4 78 91 145 84 97 155 3 6 9o 103 1653 96 110 175 4 8 98 112 180 161 117 165 It is easily seen from the above table that the combination instrument will yield values of sufficient accuracy at medium wing loadings Connection of the Sollfahrtgeber Venturi 1 pressure Capacity 1 7 m s apillary 0 3 mm 33 kts Length about 4 in 5 100 mm Pitot pressure Issued 01 06 1982 Flight Handbook DG 100 4 11 Water Ballast One eleven gallon 50 1 PVC water tank in each wing Dump is accomplished thru two valves one in each wings bottomside near the fuselage On the ground each wing can be drained individually by opening only one valve The dump rate in flight is about one quart per second so the amount remai ning ca be easily controlled Filling the Tanks For filling the Waterballast pull back the lever top right tank bottom left tank in the cockpit Place one wingtip on the ground Attach the hose connec tion in the water outlet on the undersurface of the
32. k indicators Manufacturer Iype Apparatebau Gauting AOA WZ 402 31 12 V 10 241 8 PZL EZS 3 or a certified artificial horizon Issued May 1985 TN 301 13 36 Service manual DG 100 E Inspection Procedure For Increase Of Service Time t General The results of fatigue tests of wingspar sections have demonstrated recently that the service time of GFRP gliders may be extended to 6000 hours if for each individual glider in addition to the obligatory annual inspections the airworthiness is demonstrated according to a special multi step inspection program particularly with regard to the service life Dates When the glider has reached a service time of 3000 hours an inspection must be done in accordance with the inspection program mentioned under point 3 If the results of this inspection are positive or if any defects found have been duly repaired the ser vice time of the glider is extended by another 1000 hours to a total of 4000 hours first step The above inspection program must be repeated when the glieder has reached a service time of 4000 hours If the results of this inspection are positive or if any defects found habe been duly repaired the ser vice time of this glider is extended to 5000 hours second step When the glider has reached a service time of 5000 the above inspection program again must be repeated the results of the inspection are still positive or if any defects
33. l DG 100 6 5 Removal of Ballast Tanks At the wing root near the main spar you will find a cord Attach another cord of strong synthetics about 3 mm in diameter and 5 meter in length Loosen the 4 machine screws in the FRP cover plate Carefully withdraw tank Remove cords from tank and attach to new tapk Puli new tank into place with cord Replace FRP cover plate Secure plate and cord with bolts Test system 6 6 Repair of Damage Before every flight and especially after a period of non use a thorough ground check should be carried out Visually check the surface for small depressions bubbles and other une veness This could be a signal that something is not right Contact the manufacturer immediately and if possible send a photo of the damage and a report by a licensed amp irframe mechanic The manufacturer will be able to supply the correct advice and a repair program saving you the time and troubles of quesswork and bad tries Minor surface damage such as scratches gouges and cracks in the finish may be repaired by a licensed airframe mechanic See also page 31 Knowledgeable advice can also be found in the Petite Plane Patch Primer A list of materials for the 26 166 and a check list for post accident inspec tion is found on pages 27 29 Repairs by the owner should not be attempted if the spar flange is damaged the main fittings on the wings f sdlare or tail are torn out or if in the immediate vicinity the
34. nnects be sure the latch extends through the rod and protrudes on the other side The hole must be visible It is recommended to fit a diameter 1 mm split pin or a safety needle in the hole disconnected connected hole for split pin T Close fuselage access door Mount stabilizer letting it rest for the moment on the locking pin Attach the trim tab fork to the trim drive The cockpit control should be in the full backward position Pull out locking pin Seat stabilizer completely and secure locking pin Attach stabilizer control quick disconnect See step 4 above Attach cover plate screwdriver Check flight control movement Check Main tire pressure 2 5 bar 36 psi Tail wheel 2 bar 28 psi Check instruments Sept 24 8o 18 Service Manual DG loo Stabilator Lock j l Ball iock pir PA S na Service Manual DG loo 6 Maintenance and Inspection Service Manual DG loo Datum d Leveling line Aft fuselage boom slope Wing leading edge loo 3 67 tail down near M 6 1 Weight and Balance Method of weighing your DG Ino I Assemble the glider completely with gear down 2 Place a scale under the cailwhell 3 The fuselage must be leveled so that the top of the aft fuselage boom has a tail down slope of loo 3 67 4 Water ballast tanks should be empty 5 Read weight of tail wheel W 2
35. nopy o Take off the canopy and clean and grease the locking mechanism After reinstalling the canopy check the pilot force needed for emergency release with the red ball handle using a sprina balance The force should not exceed 200 N 44 lbs o Check the canopy emergency release referring to flight manual page 9a Issued May 1985 TN 301 12 26 Glaser Dirks Flugzeugbau GmbH Service Information 1 86 Im Schellongartaa 19 20 Te 7257 1071 7520 BRUCHSAL 4 Untergrombach Subject Hotellier control quick connects Concerning DG 100 G DG 100 G ELAN DG 200 DG 200 17 DG 200 17C DG 400 all ser al no s Reason The sliding latch of the quick connect may loose its nonreversibility due to lubricants This is most important for the airbrake control hook up Measures 1 When servicing the Hotellier quick connects be careful only to grease the ballseat 2 Clean the sliding latch with Aceton or similar degreasing agent Operate the latch several times to make sure that no lubricant rests at the latch Repeat this measure at least one time a year and after greasing the ballseat 3 For your own safety t is recommended to fit a diameter 1 mm spring pin 500 30 771 into the control hole At older aircraft it may be necessary to enlarge the control hole with a diameter 1 2 mm drill 4 Please file this service information next to the greasing programme in the manual of your DG critical surface control Aole
36. pril 21 1975 Flight Handbook DG 1loo Cockpit and Controls i Instrument console eee removalle after Canopy ta toh bed Fe lease of Catches closed l zu Spoilers C ue Ri e ud close d open inr Ven ti lation ntilation N closes H open ON ope nd N 6 dump Trim weight hetder Rudder peral adjust gear down i Chlack bleach opera fe Vigorous ly Tow release yellow Trim green Raste fo ws nose Back pest adjust air bul Issued April 21 1979 aaa ve 16 100 Manual Single piece canopy engaged canopy jettison bolt Canopy jettison knob red pull to open Canopy latch red Canopy jettison 1 Open canopy latch 2 Pull canopy jettison knob The spiral spring installed in the front hinge will lift the canopy as far as necessary to be blown open by the airstream l Ground function test of the canopy jettison Pull canopy jettison knob The spring must lift the canopy 1 to 2 cm in the front even if the canopy latch is in its closed position Reassemb ly of the canopy Pull canopy jettison knob to fully open position Pull the canopy hinge to its opened position Insert the jetti son spring Take the canopy one person in front one person at the rear Attach the canopy on the hinge and press it down Push the canopy jettison bolt with one hand into its forward engaged position
37. r Check for straight axle bent struts alignment ease of operation over center locking is dirt in the forks of the forward strut White spots or cracks in the wheel well bulkheads Remove deck of storage area and inspect wheel well Gear lever condition Tow hook Especially afer a belly landing check for dirt function and if housing loosened or separated from fuselage Issued May 1985 TN 301 13 29 Service Manual DG 100 Seat back rest bulkhead Cracks Shoulder strap connection Seat belt Check for white areas near fuselage attachments Stick Check suspension Excessive play Controls Condition and proper operation of all flight controls and all other operating devices instruments Function Dirt in the pitot plenum For further checks see page 23 Issued April 21 1975 a NN Service Manual DG loo 3 The following overlap dimensions are to be maintained Service Manual DG 6 11 Repair instructions 1 8 These dimensions apply to all phases of the repair I The following can be repaired work 1 All damage to paint and putty Part Overlap b cm Fabric Layers and 2 Holes on the belly of the fuselage if the maximum Type diameter does not exceed the following Wing shell outside Wing shell inside 1 Forward fuselage 86 mm Me Aft boom 4o mm Cracks in the belly maximum length Forward fuselage 120 mm Aft boom 8o mm The blind glue joints of
38. re are white areas in the laminations the parts are torn in such a way as to make repairs uncertain without the use of jigs or appliances the damage is so extensive that the original shape or contour is obscured Cut away undamaged areas as necessary to gain access to damaged areas Issued April 21 1975 Service Manual DG 100 ET 5 Removal of Ballast Tanks Tie a piece of nylon cord 3 mm diameter and at least 5 m long to the nylon cord sticking out of the wing root rib Remove the tbree allen key screws securing the dump valve Pull the tank and valve out carefully Unknot the tank tie on the new tank and pull it into place Screw the valve and cover plate in place Check for waterthightness 6 6 Repair of Damage Before every flight and especially after a period of non use a thorough ground check should be carried out Visually check the surface for small depressions bubbles and other une veness This could be a signal that something is not right Contact the manufacturer immediately and if possible send a photo of the damage and a report by a licensed airframe mechanic The manuf ct rer will be able to supply the correct advice and a repair program saving you the time and troubles of quesswork and bad tries Minor surface damage such as scratches gouges and cracks in the finish may be repaired by a licensed airframe mechanic See also page 31 Knowledgeable advice c
39. t Flight Cloud Flying Approved if properly equipped see below 9 Minimum Required Equipment Airspeed indicator 27 162 kt 31 187 20 300 km h green arc 35 89 kt 4o 103 mph 65 165 km h yellow arc 89 140 kt 103 162 mph 165 260 km h red radial line 140 kt 162 mph 260 km h Airspeed indicator is to be installed so as to utilize the forward static ports 4 piece safety belt Altimeter Magnetic Compass Automatic or manual parachute or back cushion about 3 i ches thick Cockpit placards check list data placards flight handbook and service manual Additional for instrument flight cloud flying Radio in working order Compass properly compensated Variometer Turn and bank indicator or gyro horizon Experience so far has proven the airspeed indicator installation suitable for instrument flight cloud flying Issued 01 06 82 Flight Handbook DG l1oo Emergency procedures 3 1 Spin Recovery aileron neutral Rudder in the direction opposite to rotation pause then ease the stick forward When rotation stops neutralize rudder and gently recover from dive Recovery from unintentional Flight in Instrument Conditions Cloud Flight Open the spoilers fully and maintain a speed of approximately 108 kt 125 mph until regaining visual flight conditions Spinning should not be used as a rescue measure Rain and Ice 1 Influence on flight characteristics Land
40. thout trim weights Glaser Dirks Fi Model DG loo faximum airspeeds zeugbau GmbH Factory No 160 kes Hever exceed Vy 260 kofh 162 aph In rough air 260 km h 162 mph 140 kts Maneuvering V4 165 ka h 103 mph 59 kes Placards he r ba On aero tow Vy 165 kab 103 mph B9 kta on fue rear Read fire proved placard Serial No RU Baggage max 66 Lbs on the left gear door tire pressure 36 psi rated load 1166 lbs 130 km h 81 mph 70 kts 165 km h 103 uph B9 kts Landing gear extended 260 kojh 152 mph 140 kts Spoilers E Gross weight 418 kg 922 1b including vater ballast If cha pilot s weight with the parachute is below 75 kg 165 1b ballast waigh twat be installed in the tria weight holder or in the seat Sea Flight Manual Operating Limitations ES The sailplana must ba operated in compliance with the operating limitations as stated in the farm of mark nga placards and Flight Manual Front surface of main wing spar Serial No FL left FR right Cloud flying is only permitted when the following instruments are installad Aileron inner main spar surface airspeed indicator altimeter magnetic compass turn and slip indicator and i Serial No QL left vartoneter 5 OR right approved aerobatic naneuvere Recommended entry speed um stabilizer actuating arm Looping chandell 12 170 ku h 6 Ep Mec Wi ping andells stall turn 70 106 uph 92 kes
41. ument flight Aerobatics Approach and landing Hints for the competition pilot Waterballast REPRE REP PERE RES ONE cM TO Issued April 21 1975 CO Cn Un Gn Un E Flight Handbook DG 100 Assembly Maintenance and inspection a is re aed Weight and Balance Weight and Balance Record Reference Data Inspections Removal of Ballast Tanks Repair of Damage Service and Care Lubrication Material List Check List after Suspected Damage Repair Instructions Control surface massbalances Play of tailplane Play in controlsystems 605 00 e e 2 O000000000050 fon Equipment List Inspectionprocedure for increase of irent ado service time Diagrams Polar Empty Weight C G 3 view drawing Airspeed Calibration Ballast chart Placards Circling rate of sink polar Elevator control Aileron and airbrake control Rudder control landing gear Issued May 1985 301 11 18 19 19 21 21 23 24 24 25 25 27 28 31 33 33 34 35 37 gt ps Flight manual DG 100 Amendments O Deom 1 Seat landing gear aileron 19 09 80 Diagr 2 control stops Flight m p 9a Single piece canopy 24
42. ve the wheel brake lever Landing gear Clean after soft field landings see 4 9 Tow release Clean tow release After a gear up landing check cable deflectors Damaged parts must be replaced bezore the next take off Issued M y 1985 TN 301 12 23 Service Manual DG 100 Inspections In addition to the inspections listed in item 6 4 the following inspections have to be accomplished Airbrake torque tube in the fuseiage On every annual inspection the airbrake torque tube in the fuselage must be inspected according to TN 301 18 working instruction no 2 Airbrakes On every annual inspection the airbrakes must be inspected according to TN 301 18 working instruction no l Issued Oct 1996 TN 301 18 23a Service Manual DG loo 6 5 Removal of the Water Ballast Tanks Tie a piece of nylon cord 3mm diameter and at least 5 m long to the nylon cord sticking out of the wing root rib linscrew the screw cap of the valve Pull the valve body with the tank out of its suspension in direction of the wing tip Tben pull the valve body and tank out of the wing through the opening in the root rib Unknot the nylon cords from the tank and open the hose clamp at the valve Attach the new tank and install it analogous Fill the tank and check for watertightness 6 6 Repair of Damage Before every flight and especially after a period of nonuse a thorough ground check should be carried out Visually c
43. wing maneuvers are approved 1 Spins entry speed 2 Loops 170 km h 92 kt 106 mph 3 Wingovers Stall Turns 92 kt 166 mph 4 Chandelles tou 92 kt 106 mph The wingover is especially graceful when not only rudder is used but also a little aileron in the direction of turn The amount of aileron should be reduced at the top of the maneuver 4 9 Approach and Landing Final approach speed in smooth air is 44kt 5 mph 90km h Good short field landing capability due to the high rate of descent possible with the Schempp Hirth spoilers The DG 1oo slips well and this can be used as an approach aid Low speed controllability is such that landings in even strong crosswinds are simple and routine The approach speed should be increased by approximately the wind velocity to protect against low level wind Shear This extra speed can be reduced just prior to touch down Additionally in gusty conditions the approach speed should be increased and this extra speed should be carried to touchdown The docile nature of the FX 61 184 airfoil will permit even a tail whell first touchdown without the subsequent hard drop in Landings in very soft fields with the landing gear down are possible if the stick is held back during roll out Only for landings in very short fields should the landing gear be left retracted After a soft field landing it is important to remove dirt or other foreign matter from the retraction cables to prevent
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