FLIGHT and SERVICE MANUAL
Contents
1. 49 Mini Nimbus C Service Manual 6 5 Damages 6 6 Before every take off especially after a longer period of storage a ground inspection should be carried out see Flight Manual page 17 Pay attention to damages as tears in the paint holes white spots in glass fiber laminate etc In case of doubt about the seriousness of the damage ask the advice of a FRP expert Smaller damages which do not impair the airworthiness of the sailplane can be repaired by the owner himself See Appendix Repair Instructions Tow release hook The tow release hook mounted on the bottom of the fuselage just in front of the landing wheel is much exposed to dirt and must be checked quite often for damages Keep it clean and lubricated It is easy to take off the tow release hook for inspection or repair Remove the seat panel disconnect the release cable and unscrew the two attachment bolts In case of belly landings the towing hook is protected by two angular fittings which are bolted onto the attachment brackets of the hook If these fittings Show an abrasion up to the heads of the attachment bolts they must be replaced When mounting the towing hook again take care to attach it onto the bracket as shown on sketch page 50 50 Mini Nimbus C Service Manual Attachment of the tow release hook in front of the landing wheel Towing hook to be attached onto the bracket by the bolt holes 3 and2. If available install the venturi and check the tubing by blowing into the venturi the connected variometer must indicate Climb Check if the attachment of the horizon tal tail plane is locked Check elevator and rudder for free and full movement trailing edges for damage attachments for excessive backlash by rocking slightly at the trailing edge See G See 3 Check the pitot tube for contamination When blowing into the tube the ASI must WOrk After heavy landings or excessive acceleration the frequency of flexural wing vibration should be checked about 160 min Carbon wii 134 min Grass Wing Mini Nimbus C FLIGHT MANUAL 4 2 l S 19 a Disassemble the sailplane and check Surfaces of fuselage wing and horizon tal tail plane If damages should be observed e g tears in the painting of the rear fuse lage and of the horizontal tail plane white spots at the spar stubs or at the root ribs in the area of bearings and attachment bolts deformation of the main bolt and of the elevator control fittings etc The sailplane is unserviceable until the damages are properly repaired Cockpit Layout Instrument panel ee With canopy opened the instruments are i well accessible The instrument compart ment cover is fastened by four screws f The instrument panel is attached onto 3 the fuselage canopy frame and is easy to remove Control stick The main landing wheel brake lever i
3. Max water ballast at different e mpty weights and cockpit loads 280 200 220 ans lb lb ve Empty weight 1b lb 480 500 520 540 560 419 419 588 At high cockpit loads care is to be taken not to exceed the max permitted weight of non load carrying structure The baggage compartment can be loaded with a weight of max 15 kg 33 lb 5 kg 11 lb are allowed to be The weight of objects which do the originally installed equipm considered when determining the permitted water ballast of which only removed not belong to ent must be maximum l O Mini Nimbus C FLIGHT MANUAL 846 0 G Range were zer eww ee 2 22 2 25 2 2 e e e e a C G range in flight gross weight C G 220 mm 8 66in to 380 mm 14 96 in at all weights Datum Wing leading edge at root rib Leveling means Slope of rear top surface of fuselage 100 to 5 1 tail down i e main landing gear wheel on the ground and tail skid jacked up about 49 cm 19 3 in Be cautious not to exceed the permitted aft C G position When a minimum cock it load pilot and parachute of 70 kg tise lb is observed it is certain to be within the limits Less weight is to be compensated with ballast on the seat see page 8 b Empty weight C G range eee eT Tange After repair work installation of additional equipment new painting etc the empty weight C G position must be checked If it should not b
4. construction methods l Inner wing panel Glass fiber foam Sandwich Foam CONTICELL 60 8 mm thick l 2 Outer wing panel pal AR Aa E Glass fiber foam sandwich Foam CONTICELL 60 6 mm thick 5 Flaps Ailerons Air brakes Pure glass fiber layup 4 Fuselage Pure glass fibex layup 5 Vertical tail piane Fin Glass fibe foam sandwich Foam CONT CELL 60 i in front of the spar 6 mm thick aft cf the spar 4 mm thick Rudder Glass fiber foam sandwich Foam CONTICELL 60 4 mm thick 6 Horizontal tail plane Ll 2281 2 plane Stabilizer Glass fiber foam sandwich Foam CONTICELL 60 6 mm thick Elevator Pure glass fiber layup If a fracture or damage occurs to the sail plane you should first inspect the damaged area to determine exactly the type of con struction and to find the appropriate method for the repair Repair Instructions for the Sailplane Mini Nimbus C In the Mini Nimbus C we find the following construction methods l inner wing panel Carbon glass fiber foam sandwich Foam CONTICELL 60 8 mm thick 2 Outer wing panel Carbon glass fiber foam sandwich Foam CONTICELL 60 6 mm thick 5 Flaps Ailerons Air brakes Pure glass fiber layup 4 Fuselage i Pure glass fiber layup 5 Vertical tail plane Fin Glass fiber foam sandwich Foam CONTICELL 60 in front of the spar 6 mm thick aft of the spar 4 mm thick Rudder Glass fiber foam sandwich Foa
5. 2050 Hamburg 80 Nicopress sleeves Tools TOST Flugzeugger amp tebau e Thalkirchnerstr 62 D 8000 M nchen 2 Towing hook ae Mini Nimbus C Service Manual 6 2 Annual Inspections Maintenance schedule See control system views on pages 58 59 60 Accessibilty of controls for inspection Wing controls Aileron drive accessible through cut outs in the rear wing spar with air brake opened and aileron dismounted Air brake drive accessible through cut outs in the rear wing spar with air brake opened Fuselage controls Drives in the fuselage accessible after removal of the seat panel and the fairing on the front steel tube frame Elevator control LT S9ueroir Accessible after disassembly of the horizontal tail plane Rudder control Accessible through the cut out in the nose with rudder deflected to the right After having cleaned the sailplane proceed as follows Check all external surfaces for holes tears scratches dents and detached laminates If the outer laminate of a sandwich shell is damaged also the inner glass cloth layer is to be inspected It is advisable to ask an expert s advice Check all accessible metal parts for damage As known from experience no damage occurs when operating the sailplan properly 46 Mini Nimbus C Service Manual If any repair should be necessary ask the advice of the manufacturer o Check all accessible met
6. Stall speed knots mph air brakes retracted flap positions 62 55 38 78 42 67 36 42 amp amp 45 77 42 48 92 49 Bae Shortly before reaching the stall speed Stall warning occurs with air brakes retracted at speeds of 62 to 92 km h 55 to 49 knots 38 to 57 mph depending on the wing loading and flap position by slight vibration of the horizontal tail plane ailerons become spongy With air brakes extended the Sailplane vibrates considerably already 5 km h 2 7 knots 5 1 mph before reaching the Stall speed When pulling the stick gently back the ASI indicates again higher speeds until 48 air brakes extended flap position 8 X Fie Mini Nimbus C FLIGHT MANUAL 4 7 with the C G in aft positions control is lost by wing dropping or with the C G in forward positions the sailplane pancakes when the control stick reaches the limit of backward travel The control stick then is to be eased forward With air brakes extended the loss of height during recovery to normal flight is about 50 m 164 ft With the C G in aft positions full rudder in a stall brings the sailplane into a spin It recovers safely from the Spin by the standard method which is defined as a apply opposite rudder i e against the direction of rotation of the Spin b pause c ease the control stick forward until the rotation ceases and the sailplane becomes unstalle
7. C 2 7 2 8 M FLIGHT MANUAL Weak links for towing Winch and Airplane tow max 600 50 kg 1320 66 1b Mimimum Equipment Airspeed Indicator with a range of min 50 km h to min 270 km h min 27 knots to min 146 knots min 51 mph to min 168 mph marked as follows km h knots mph White Arc 78 180 42 97 48 112 flaps O 8 Green Arc 86 200 46 108 53 124 normal range Yellow Arc 200 250 108 155 124 155 warning range Red Radial 250 135 155 max speed Yellow Arrow 90 49 56 approach Altimeter Four piece safety belt Manual or automatic parachute or back cushion compressed 10 cm 4 in thick Placards see pages 23 25 Flight and Service Manual For Cloud Flying 0 additional to the minimum equipment Magnetic Compass Variometer Turn amp Bank The installed ASI system was found to be suitable for cloud flying EE EE E ee a a cH meh S ae a ee up Mini Nimbus C FLIGHT MANUAL 2 9 Acrobatics The Mini Nimbus C is approved for the following acrobatic maneuvers Inside loops Spins Turns Lazy eight It is recommended to install a recording accelerometer in addition to the equip ment listed under 2 8 Acrobatic maneuvers are permitted only without water ballast Loose objects are to be removed 2 10 Wing and Tail Setting E Reference Rear fuselage center line Angle of wing setting 0 77 Angle of tail setting 0 Control surface movements lt Di rrace movem
8. Pedal SE YELLOW T handle 1 Ru D p t Air brakes BLUE handle OPENING JETTISONING Canopy BED ball knobs Ventilation Water ballast 26 Mini Nimbus C FLIGHT MANUAL 4 3 Check before take off 4 See cockpit placard on page 24 Take off Airplane tow Maximum towing speed flaps 49 VAT 180 km h 97 knots 112 mph For airplane tow Perlon tow ropes of 40 to 60 m length were tested When beginning the ground run put slightly on the brake to avoid rolling over the rope Before take off adjust the trim NORMAL with the C G in forward to medium positions NOSE HEAVY with the C G in medium to aft positions Normally the take off is conducted with flaps in position 8 With the C G in aft positions high take off weight or Strong cross wind the ground run should be made with flaps in position A until the ailerons become sufficiently effec tive The flaps then can be taken back to the normal position 8 With the C G in aft positions it is advisable to hold the control stick in forward position during the ground run until the skid has ground clearance After lifting off at about 70 to 75 km h 38 to 40 knots 43 to 47 mph the trim can be adjusted so that almost no stick force is perceptible The normal towing speed is 100 to 120 km h 24 to 65 knots 62 to 75 mph with flaps ii position O9 At speeds from 120 km h 65k or 75 mph it is advisable to s
9. Sable to touch down at a minimum Speed of 60 65 km h 32 35 knots 37 40 mph Touching down at 90 km h 49 knots 56 mph instead means doubling the the energy of tiie sailplane and conside rably increases the running distance When off field landings are inevitable always extend the landing gear Flying in rain or with iced up wings means a loss of performance and aerodynamic qualities Therefore be cautious when landing Come in at a speed of about 95 100 km h 21 54 knots 59 62 mph uc Ad a Mini Nimbus C Service Manual 2 2 1 Storage Parking Ground towing The sailplane should be stored or parked in well ventilated rooms Closed weatherproof trailers should be equipped with sufficiently large vent holes Store or park always with fully drained off water tanks Take care to keep the Sailplane free from any strain especially at high temperatures The wings must be supported very carefully in the trailer either by their spar stubs or by the wing root leading edge in section true supports The outer wing panel is to be supported by the leading edge in section true supports in the area of the aileron about 2 4 m from the tip The fuselage should be Supported on a wide cradle just in front of the C G towing hook and on the tail skid Dependent on the make of the trailer the tailplane can be supported either verti cally by the leading edge on two section true cradles with a distance
10. a b Begs Destruction of the whole shell also the inner glass fiber laminate destroyed If the outer shell receives a puncture or a fracture tap to determine the extent of delamination from the foam Follow by removing the lacquer with a sanding disc or block and remove from the foam the portion of the shell which has become delaminated Around the edge of the damaged area where the shell is still firmly bonded scarf with an abrasive block or a plane blade at least 1 1 2 inches for each cloth layer about 3 4 inch is necessary After scarfing the shell blow out thoroughly the whole repair area including the pores of the foam and wash the scarf with carbon tetrachloride or acetone Now fill the hole in the foam with microballoons and simultaneously 8111 the pores of the exposed foam Then lay three patches of the 92110 cloth with diagonal weave direction pter s largest patch first over the damaged area The applied cloth must be dry and dust free Outer laminate A 5 layers 92110 diagonal a NLT a o 9 o0 o O s GC Ser 9 0 6 09 o Ee o 9 ee Microballoons Conticell 60 After hardening appr 8 hrs at 20 deg C or 68 deg F the damaged area should be smoothed filled and painted In smoothing take care that only the edges of the patches are sanded Inner laminate If there is a through hole in the sandwich shell then the inner laminate must be repaired We
11. is permitted The elevator control movement at Vyp must be even less which depends on the permitted maneuvering load factor Under normal weather conditions this Sailplane can be safely flown at high Speeds up to VNE 250 km h 135 knots or 155 mph In strong turbulence i e in wave rotors thunder clouds visible up currents or when flying over mountain ridges the airspeed Vg 200 km h 108 knots or 124 mph must not be exceeded Load Factors The following load factors should not be exceeded 5 3 2 65 at speeds of 200 km h 108 knots 124 mph air brakes 4 0 1 5 at speeds of closed 250 km h 135 knots 155 mph 3 5 air brakes extended The safety factor then is j 1 5 0 Mini Nimbus C FLIGHT MANUAL 2 4 2 5 Weights Maximum takeoff weight 500 kg 1102 1b Max weight of non lifting paris 220 kg 485 1b Max weight of water ballast kg or liters see page 9 Loading instructions Cockpit load pilot and parachute Max 110 kg 243 lb Min 70 kg 154 lb The maximum takeoff weight must not be exceeded Less weight than 70 kg 154 lb must be compensated with ballast lead or sand cushion on the seat safely attached e g onto the suspension of the seat belt C G arm of the pilot incl parachute or back cushion 220 mm 21 65 inches ahead of datum Mini Nimbus C FLIGHT MANUAL Water ballast Maximum takeoff weight with water ballast 500 kg 1102 lb
12. o2 S 47 Mini Nimbus C Service Manual Check the tire pressure of the main landing wheel 5 5 Atm or 50 psi o Inspect the static and dynamic pressure intakes the tubing and couplings for free air pass and tightness Check instruments for loose glasses o Assemble the sailplane and check the control surface movements and all control for easy and smooth operation The gap between flap air brake and aileron should be at least 2 mm 0 08 in Check the wings and control surfaces for excessive backlash of controls and attachments see paragraphs 6 3 and 6 4 Check the function of the tow release mechanism 6 3 Backlash of the controls ee ee OS With controls held fixed the backlash of the control surfaces must not exceed the following values Backlash in EET Control Measuring point surface aft of hinge axis Elevator Rudder Flaps Ailerons measured above hinge axis at fully opened air brake 48 Mini Nimbus C Service Manual 6 4 Backlash of the attachments eue tuU eS x Wings Tangential backlash movement forth and back can occur due to the wear of the washers which are pressed onto the wing attachment bolts If the movement at the wing tips exceeds 20 mm 1 3 16 additional washers of an inner diameter of 15 95 mm about 0 3 to 0 5 mm thick Should be pressed onto the bolts until the backlash is eliminated
13. original certification of the Mini Nimbus B was carried out using the following instruments Airspeed Indicator 30 200 km h marked in accord with 2 8 page 12 Winter 6FMS 4 2 Altimeter 10 1000 10000 m Winter 4 FGH 10 Magnetic Compass Ludolph FK 16 Variometer Winter St V 5 Radio Dittel FSG 40 For the basic equipment or for cloud flying any approved instruments can be used if they meet the requirements of 2 8 page 12 er 56 Mini Nimbus C Service Manual 7 Determination of the empty weight C G For the determination of the empty weight C G position the Sailplane is to be assembled with closed canopy with the permanent equipment installed and without water ballast With main landing wheel on the ground the tail skid is to be jacked up on a balance about 49 cm 19 3 in from the ground i e slope of rear 100 to 5 1 tail down or rear fuselage center line horizontal Then the weight at the tail skid is to be determined with wings held level The distances a and b are measured using a plumb or gathered from the last weight and balance report The distances a and b measured at the original weighing by the manufacturer are a 129 mm 5 1 in b 5950 mm 154 7 in Datum Wing leading edge at root rib Leveling Slope of rear top surface of means fuselage 100 to 5 1 tail down Empty weight C G position MM MM dees Wo b A W top surface of fuselage xm T
14. place is attached such to rip immediately when throwing off the canopy The canopy frame on the fuselage is built of strong glass fibers without sharp edges and is well suited as a Support for the pilot to jump off zn ue Mini Nimbus C FLIGHT MANUAL 4 Normal Operating Conditions a b c d e a b When going around the sailplane for inspection check all external Surfaces for tears blisters or dents In case of doubt ask a FRP expert Open the canopy and check if the main bolt is installed and secured Check the cockpit controls by visual inspection Remove foreign particles Check tire pressure of the main wheel 5 5 Atm 50 psi Check condition and function of the towing hook Check ailerons for free and full movement Check air brakes for close fit and proper operation Check trailing edges of flaps and ailerons for damage Check flaps and ailerons for excessive backlash of attachments by rocking slightly at the 18 Mini Nimbus C FLIGHT MANUAL c d e b O O9 trailing edge Check the function of the gas spring with flaps in position 7 Push the flaps down at the inner root into neutral position and then release The flaps must return to the initial position 7 Check hinges for damage Check if the holes for static pressure intake under the wing are open Check if the holes for static pressure intake in the rear fuselage shell are open
15. recommended After entry to the turn apply rudder in the vertical climb at a speed of 130 km h 70 knots 81 mph Speed during recovery from the turn 180 200 km h 97 108 knots 112 124 mph Lazy Eight Entry to the maneuver at a speed of 180 km h 97 knots 112 mph followed by a climb of about 30 to 45 degrees from which a turn is initiated at a speed of 120 km h 65 knots 75 mph Speed during recovery 180 km h 97 knots 112 mph Dependent on the load factor and the angle of bank the speed in steep turns should not be less than the values given in the following table Load Angle Speed factor of bank km h knots mph 2 0 60 110 59 68 5 65 125 67 78 3 0 70 135 75 84 5 729 150 81 93 Acrobatics are permitted only when flying without water ballast 59 Mini Nimbus C FLIGHT MANUAL 4 12 Approach and Landing The very effective air brakes are a combination of spoilers and flaps and allow steep and slow approaches They do not notably increase or decrease the lift The normal flap position during the landing is 8 Pulling back the air brake handle until a clear resistance is observed means extending only the spoilers by which the sailplane can be controlled during the approach When pulling the handle further back the spoilers and flaps are cooperating The normal approach speed is about 75 80 km h 40 43 knots 47 50 mph with flaps in position 8 air brakes and lan
16. side and glue the foam thereto in order to keep the surface wave free Caution Do not apply too much heat to freshly laid cloth otherwise it causes ugly blisters and you must start over Caution On the controls minimize weight in the repair The surface should require very little filling Damage to the Fuselage LIT V CL ES ES LARS In the repair of the fuselage we save the annoying replacement of the foam We have here as already mentioned only to do with the simple glass laminate which in most places consists of five layers Therefore we need larger scarfs These should for larger holes or cuts never be less than 2 3 8 inches wide With all fuselage shell repairs apply resin first to a layer of 92110 cloth following with four layers of 92140 cloth alternating the weave lengthwise and diagonally Then you are always on the safe side Each succeeding layer should be about 5 8 to 1 2 inch smaller than that under it 4 layerg 92140 BOX E 7 layer 92110 fuselage shell For small holes or fractures the repair is no problem You sand your scarf clean well with carbon tetrachloride or acetone lay on the cloth layers and if the resin is dry can finish the whole repair with microballoons after 2 or 3 hours Caution If the room is cold or if you are hurried you should nonetheless not use a concentrated hot air Stream Better make a large tent over the area from aluminum foil and heat the space from a safe distance T
17. with Nicopress Oval Sleeves No 18 2 M or No 28 5 M using a tool No 51 M 850 and following the special instructions for making and checking the sleeves Gas springs After removal of the upper fiber glass fairing on the front steel tube frame the gas springs are accessible behind the front wing attachment tube The piston rods must be clean and without any damage If a leakage of the piston rod oil seal Should be observed the gas spring must be replaced The expansion force of the gas spring is to be checked on the assembled sailplane with flaps in position 79 It must be possible to hold the flap in this position without moving down when applying a moment of 16 to 19 Nm resp 1 6 to 1 9 mkg or 11 6 to 13 7 ft lb 442 Mini Nimbus C Service Manual s The required moment is obtained by pulling the trailing edge of the flap in the area of its root using a Spring balance or by attaching weights 225 mm P The force or the weight should be P 7 0 to 8 5 kg or 15 4 to 18 7 lb Towing hook Inspections are to be carried out in accord with the Operating and Maintenance Instructions for Special Towing Hooks S 72 and SH 72 dated May 1975 LBA approved P 4 Instruments Follow the instructions of the respective f manufacturers i Suppliers Schempp Hirth GmbH amp Co KG Krebenstr 25 D 7312 Kirchheim Teck Cables Sleeves Gas springs Main landing wheel R Lindemann Osterrade 12 D
18. 0 135 155 5000 240 130 149 6000 226 122 140 7000 214 115 1535 8000 202 109 125 9000 191 103 119 10 000 179 97 111 12 000 159 86 99 WEAR ELeil 453 2044 4 Eur ud m Mini Nimbus C FLIGHT MANUAL Pressure error at MSL Dynamic pressure intake Pitot tube in the nose of the fuselage Static pressure intake Airspeed Indicator 15 cm under the rear edge of the spar cut out Variometer In the area of the instr panel and at the rear portion of the fuselage about O 9 m in front of the vertical tail plane o 9 o N P D e 8 R S N e 42 3 SI 8 8 S Ae 7 9 Tus SR F Hm 8 3 5 o 1 R jS I 8 R 48 o g m i 8 dg 4 s f E 120 lo 160 180 200 220 240 km h EA De knots 130 120 10 00 9 0 80 0 60 50 40 40 50 60 70 80 90 100 110 120 130 140 150 mph Note All speeds stated in this Manual are indicated airspeeds IAS Der hes Mini Nimbus Cc FLIGHT MANUAL 2 2 2 3 Airworthiness Category Erano U Utility according to the LEMS Based on the Airworthiness Requirements LFSM full control movements can be applied up to the maneuvering speed V At higher speeds it is possible to overstress the sailplane therefore full control movements are not allowed at speeds exceeding 200 km h 108 knots or 124 mph At the maximum airspeed Vyp 250 km h 135 knots or 155 mph a maximum of one third of the full control movement
19. 5 OT O e aaa mr mm c m EE UC DETUR s i ERAT ERO mpm oue AEE ae em em gre 51 Mini Nimbus C Service Manual 6 7 Weights and hinge moments of the SE control surfaces After repair or a new painting the weight and hinge moment of the control surfaces must not exceed the following values Control Weight Hinge moment surface xg I 5 82129 8 42124 0 1585124 1 14129 Aileron 8 2 125 0 065312 0 473124 Elevator 0 45 If these values are exceeded a mass balance must be installed in front of the hinge axis RK Mass balance on flaps and ailerons one en ISPs A flat bar of lead or of similar heavy material is to be attached onto the inside of the nose strip between the first and second hinge fitting respectively by means of 4 mm or 5 32 counter sunk screws in a distance of 100 to 150 mm or 4 to 6 in each 52 Mini Nimbus C Service Manual Mass balance on the rudder ne HU EE Parallel to the already installed round bar a square or a round bar of the required weight is to be glued onto the inside of the nose Strip and covered with amp glass cloth layer additional mass balance Mass balance on the elevator On the elevator the mass balance is to be attached span wise onto the nose joint Strip The hinge moments must be determined on the disassembled control surfaces M Per Mass balance nr eed The control surfac
20. 7 SE pa eR DET Seiad 2na Mini Nimbus C Maintenance and Service Manual Table of Contents 5 Storage Transport Assembly ee E Bersani 2 1 Storage Parking Ground Towing 39 5 2 Assembly 40 5 3 Disassembly 42 6 Maintenance 6 1 Mandatory Maintenance 43 6 2 Regular Maintenance 45 6 5 Backlash of Controls 47 6 4 Backlash of Attachments 48 6 5 Damages 49 6 6 Dismounting and reinstalling 49 the towing hook 6 7 Control surface moments 51 6 8 Surface Treatment 53 6 9 Replacement of ball bearings 54 6 10 Safety belts 55 6 11 Instruments 55 7 Determination of empty weight 56 and gross weight C G positions Control system views 58 Appendix Polar Repair Instructions of FRP Sailplanes M armen E 5 Mini Nimbus C FLIGHT MANUAL Amendments Mini Nimbus C FLIGHT MANUAL l GENERAL The Mini Nimbus C is single seat 15 m flapped sa lplane in all fiber glass construction Wing The cantilever 5 wo piece wing has a double trapezoidal Shape It is built as a FRP foam sandwich shell with Spar caps of parallel glass fibers and shear webs of FRP foam sandwich The trailing edge air brakes are a combination of spoilers and flaps The ailerons have internal drive Two integral water tanks have a total capacity of 190 liters Fuselage 2 9 The fuselage is necked behind the wing The one piece canopy is faired into the fuselage and hinged at the right hand side The fuselage shell is b
21. ASER ASE Venom m et 57 Mini Nimbus C Service Manual The empty weight C G position must be within the limits given in the Table on page 11 of the FLIGHT MANUAL A determination of the empty weight C G position is required after the installa tion of additional equipment after repair or modifications which are changing the weight of the sailplane Changes of weight and C G position are to be entered into the log book and con firmed by a designated inspector Gross weight C G position Before conducting performance flights it is recommended to determine the true gross weight C G position in order to check if it is within the optimum range for high performance Optimum gross weight C G range 300 mm to 350 mm 11 8 in to 13 8 in aft of datum The sailplane is to be weighed as des cribed on page 56 with pilot and para chute and additional equipment as seat cushion barograph cameras etc Take care that the rudder pedals and back rest have the proper position 2 Flight gt Plight a W W Payload D I MIN NIMBUS C Querruder Bre nsklappen und L wing controls NN wie flaps T3 Arlerons Air brakes D I L9 N mco Be A XA Ae und Bremsklagpensteuerung im Furnpf d 3 HE Ki SS y TERE OF GU HS IAF di k MINI NIMBUS C Seifenste
22. SCHEMPP HIRTH GmbH ES Co KG KIRCHHEIM TECK Federal Republic of Germany FLIGHT and SERVICE MANUAL for the Sailplane Mini Nimbus C Translation of the German Manual Issue Sc tember 1978 Tais Manual sh 3 always be carried in th Sailplane It belongs to the zilplane Mini Nimbus C Registration Number ee ee Serial Number EES Echempp Mirin Fiugzougbau Grr D 7312 Kirchheim unter Teck Manufacturer e CCHC 4 CC HO SOHO HOCH OHM OO EOD Owner on The pages 5 38 ac approved by the Lu tfahrt 1 4 Mini Nimbus Cc FLIGHT MANUAT Table of Contents Page Amendments 5 1 General 4 2 Operating Limits 5 a ee ere e 2 1 Airspeeds 5 2 2 Airworthiness Category 7 2 5 Load Factors 7 2 4 Weights 8 2 5 Cockpit load 8 2 6 C G Positions 10 2 7 Weak links for Towing 12 2 8 Minimum Equipment 12 2 9 Acrobatics 13 2 10 Wing and Tail Setting 13 Control Surface Movements 14 2 Emergencies 15 3 1 Recovery from Spins 15 2 2 Malfunction 15 2 5 Canopy Jettison 16 4 Normal Operating Conditions ee ee tons 4 1 Daily Inspection 17 4 2 Cockpit Lay out 19 um 4 5 Check before Takeoff 26 4 4 Takeoff 26 4 5 Free Flight 28 4 6 Slow Speed Flight Stalls 30 4 7 High Speed Plight 31 4 8 Flight with Water Ballast EE 4 9 Cloud Flying 24 4 10 Flights below Ice Point 24 L 4 11 Acrobatics 35 Wo m d 4 12 Approach and Landing 3
23. Wings pM erp T Rovings IET Textilglas GmbH GEVETEX Type ES 10 40x 60 K 43 GEVETEX Foams PVC Rigid Foam Conticell 60 Continental AG 5 16 in thick 3 7 lb cu ft Styropor THERMOPETE Super PORON 5 58 in thick 1 lb cu ft Kunststoff Werke Resin Fillers Microballoons white Union Carbide Microballoons brown Brenntag GmbH Aerosil Degussa Wolfgang Styropor kernels 1 16 3 32 dia BASF expanded polystyrene kernels Chopped cotton wool Lacquer Lesonal Werke PE Lackvorgelat white No 5 6910 resin paint PE Hardener No 7 2050or 7 205 100 to 1 5 Mixing proportions by weight 100 parts Lackvorgelat to 10 parts hardener PE Thinner No 6 3026 PE Sr to 10 parts hardener gelat and filler can be mixed in Repair Should a fracture or damage occur to the sailplane you should first inspect the damaged area to determine exactly the extent of damage and type of construction The type and density of weave can usually be determined by sanding to the cloth If this is not possible break off a piece of the laminate and ignite it After the resin is burned the type density and direction of the weave will be evident I Damage to Wing or Stabilizer The damages which can be repaired by you fall into two Groups a Simple surface damage only the outer glass fiber laminate damaged Dx REET O ME umm 23 ERE STENT 86 PROT b
24. al parts for corrosion If necessary remove the rust 1 and protect the surface again by a new i painting Corroded fittings push rods i and levers should be thoroughly cleaned and consequently primed and painted using a Special primer and Nitro paint primer i and paint can be supplied by Schempp Hirth o If the controls cannot be operated with sufficient ease and smoothness clean and lubricate the corresponding hinges or bearings Tm ee KEE KEE o Replace bearings which have an excessive radial clearance The automatic connections of ailerons and air brakes between wing and fuselage can be adjusted free from backlash by correcting screws on the funnel type levers of the fuselage The backlash of controls and air brake drive is to be checked in accord with paragraph 6 5 o All fittings attached onto glass fiber Structure are to be checked for a tight fit Check the glass fiber structure for tears white spots and broken glass cloth laminate o If a loss of the braking effect of the Se landing wheel is observed clean the 1 brake drum inspect the brake lining replace the lining if worn Check the brake Bowden cable and the brake lever adjust if necessary Check the wheel hub for lateral clearance Follow the instruc tions of the manufacturer TOST r Check the wheel axle and landing gear Struts for deformation and the attachment fittings for damage Ee ege ve ee EET Y E e ET
25. alves with filled water tanks should leak coat the closing caps slightly with grease before the next filling pull the cap down by means of a M6 mm bolt screwed into the threaded hole in the center of the cap 34 m Mini Nimbus C FLIGHT MANUAL 4 9 4 10 Cloud flying The sailplane has sufficient strength and stability for cloud flying It is easy to control and has stable circling qualities Nevertheless observe the following instructions l Do avo d extreme airspeeds in any case To prevent the sailplane from a spiral dive do not execute spins as a rescue action It is recommended to extend fully the air brakes already at an indicated speed of 150 km h 70 knots 81 mph or at a load factor exceeding 2 g At speeds exceeding 140 km h 76 knots 87 mph the air brakes should not be retracted again due to its steep attitude the sailplane then could exceed the maximum permitted Speed Take care that the required equipment for cloud flyirg is installed in the sailplane see page 12 Flight below freezing point cei epi de RD trc a c MM9 ae i cata ant At temperatures below O degr C 32 degr F as in wave flights or during winter it is possible that the flight controls cannot be operated with sufficient ease and smoothness therefore all controls should be free from moisture to avoid icing 35 Mini Nimbus C FLIGHT MANUAL 4 11 This in part
26. board aileron root The water is drained off through a hole in the lower wing surface next to the root rib With the dump valve operating knob at the right hand side of the cockpit pushed back dump valve closed the connection of the water ballast System of the wing to the fuselage is made automatically when attaching wings 44b Mini Nimbus C FLIGHT MANUAL Pushing the knob forward opens the dump valve in the wings moving the knob down locks it in that position When flying at temperatures lower than O degr C 32 degr F the water must be drained off to avoid icing Drain off the water before landing to reduce the approach speed and therewith the landing run Full water tanks are drained off within about 4 minutes In the improbable case that the water tanks should be unequally drained off or only one sided stalls are to be avoided and an adequate margin of safety in the lower speed range should be observed When the glider with the C G in aft positions comes to stall yet and enters unintended a spin set the flaps on negative position immediately apply opposite rudder and ease the control stic forward Dive out gently when rotation has ceased During the landing run care is to be taken of the tendency for the glider to ground loop due to the earlier ground contact of the heavier wing Never park the sailplane with filled water tanks Drain off the water open the caps and let the tanks dry If the dump v
27. d d neutralize the rudder and allow the sailplane to dive out High Speed Flight speed Flight When flying at high speed observe the maximum limiting speeds for the respec tive flap positions as marked on the ASI by corresponding colors Full control movements are permitted at Speeds up to Va 200 km h 108 knots 124 mph only At a speed of Vue 250 km h 135 knots 155 mph only one third of the full control movements is allowed Avoid sharp elevator control movement in any case In strong turbulence e g in wave rotors thunder clouds visible vertical whirl wind or when flying over mountain ridges EE 2 Mini Nimbus C FLIGHT MANUAL the speed must not exceed Vg 200 km h 108 knots 124 mph With the C G in aft positions the required stick travel at all speeds up to VNE is relatively small the change of speed however is clearly noticed by a change of the stick force The air brakes can be extended at speeds up to VNE 250 km h 155 knots 155 mph Since sudden deceleration of about 2 g can occur the air brakes should be used only in emergencies or when exceeding unintentionally the maximum permitted speeds see page 5 Take care that the safety belt and the Shoulder harness have a tight fit Do not push inadvertently the control Stick when extending the air brakes Avoid loose objects in the cockpit With air brakes extended do not pull out too rapidly but gently see load fact
28. ding gear extended With water ballast the speeds increase up to about 20 The gliding angle is about 1 4 5 In the approach pull out arc or Shortly before landing at speeds less than 70 km h 38 knots 43 mph the air brakes must not be Slowly retracted but rapidly and fully otherwise only the idend flaps are taken back into normal posi tion loss of lift while the Spoilers with their full drag and decrease of lif are still fully extended Rapid and full retraction of the air brakes does not considerably change the lift and longitudinal inclination of the sailplane the sinking speed resp the gliding angle however promptly improve 38 Mini Nimbus C FLIGHT MANUAL With semi retracted air brakes the Mini Nimbus pancakes Landings always should be carried out with fully extended air brakes for this configuration ensures the lowest touch down speed Steep approaches e g in strong ground turbulence or over high obstacles should be made with fully extended air brakes while the gliding angle is corrected with elevator control only Excessive height can be reduced without gaining much speed by easing the control Stick forward The sailplane touches down on the landing wheel and the tail skid simultaneously The wheel brake drum brake is suffi ciently effective The brake lever is mounted onto the control stick To avoid a long landing run it is advi
29. e MEE ROARS Four ball bearings GL 14 are installed at the ends of the wing attachment tubes of the fuselage steel tube frame These bearings are to be checked for cracks after heavy landings If a replacement of the bearings should be necessary the repair is to be done as follows Turn the inner ball about 90 across and hammer the bearing out of its seat from the opposite side using a bar of about 12 to 14 mm diameter Insert a new ball bearing GL 14 with the lead in grooves to the inside in the direction of the wing chord Peen over or punch the outer bearing race at three spots lead in grooves inside fuselage root rib me Mount the wings and check the clearance of the wing attachments If the backlash is exceeding the permitted tolerance i e if the movement at the wing tips is exceeding 30 mr follow the instructions on page 48 lead in M aye EC e aE RES RAL NM ef an cea tre 53 Mini NIMBUS Service Manual 6 10 Safety belts 6 11 A four piece safety belt is required Following makes and models are approved Seat belt Gadringer Bagu IV D or IV E Autoflug Bagu FAG 7F O Attachment Brackets on the fuselage shell and accessible through cut outs in the seat panel Shoulder harness Gadringer Schugu II C Autoflug Schugu FAG 7H O Attachment Front wing attachment tube accessible through cut outs in the upper FHRP fairing Instruments The
30. e should be supported at its hinge axis The force P is to be measured by means of letter or spring balance After the installation of an additional mass balance the control surface movements are to be checked for their unrestricted travel l ve 955 ze Mini Nimbus C Service Manual 6 8 Maintenance of the surface finish 0 Wash the surfaces with clean warm water using a soft sponge and wipe dry with a Soft clean chamois Never use gasoline alcohol or thinner for cleaning Do not addwashing agents to the water too often and don t use agents which are containing Silicone Clean the plexiglass hood with a special cleaning agent for plexiglass or in needs with lukewarm water Use only soft clean chamois for wiping dry Never try to clean with a dry cloth The sailplane should be protected from moisture If water should be soaked into inner compartments disassemble the sailplane and let the components dry while turning them over frequently Do not expose the sailplane to extreme sunlight and avoid unnecessary permanent Strain Take care that all external portions of the sailplane which are exposed to sunlight are painted white Other colors than white would excessively heat the FRP structure which may impair the strength qualities of the tpLane Ger bue Mini Nimbus C Service Manual 6 9 Replacement of the ball bearings for ere din ta wing attachment bolts on the fuselage a E e
31. e within the limits compensating weight must be added If the limits of the empty weight C G are followed it is certain that the gross weight C G is also within the permitted range To facilitate the checking of the empty weight C G position the following table shows besides of the C G range for different empty weights also the max permitted tail weight calculated for the corresponding aft empty weight C G position gt Mini Nimbus C ll C G position is with C G range aft of datum Empty weight FLIGHT MANUAL If the determined tail weight does not exceed these values the empty weight in the limits Tail weight kg mm kg EU NE 200 644 695 28 7 205 655 685 29 0 210 625 678 29 3 215 614 671 29 6 220 605 664 29 9 225 596 658 50 5 250 588 652 50 6 255 581 646 30 9 240 573 641 31 2 245 566 635 31 5 255 552 625 32 2 260 546 620 52 5 lb inches lb 440 25 40 27 29 63 11 450 25 03 27 01 63 73 460 24 67 26 75 64 57 470 24 55 26 50 65 01 480 24 00 26 26 65 65 490 23 69 26 03 66 29 500 23 39 25 81 66 95 520 22 82 25 539 68 20 550 22 56 25 19 68 85 550 22 05 24 82 70 11 560 21 81 24 64 70 73 570 21 58 24 47 71 37 Forward empty weight C G calculated for a max cockpit load of 110 kg 245 1b Aft empty weight C G calculated for a min cockpit load of 70 k a baggage compartment load o f 154 1b an 5kg 11 lb Mini Nimbus
32. empt to make larger repairs of the following types If the wing fuselage or controls are broken apart If the spar flanges are damaged If the main fittings at the root rib fuselage or in the controls are broken out If in the area of the fittings the laminate shows white areas or cracks When you cannot guarantee tl epair Kirchheim Teck 26th March 1968 Schempp Hirth K G ss Klaus Holighaus Translation by F H Matteson
33. ents See page 14 Pay attention to the tolerances if repair work should be necessary 6 37 in WING FLAPS Max UP Max DOWN 350 mm ELEVATOR amu m nisma hem a pa i 1 4 2 RUNDE lt 210 1 30 2 In UP AN 3 3mm 5t2mm RUDDER 49 5 mm 22 12 in 0 59 1 08 in LEFT AND RIGHT 1 93 2 160 20 mm 6 3 4 8 IN 6 3 40mm i 3 46 ies besar E iy e E S D Ge cs E Lengt nei fe AA OP ou MS me YS NRI LEVELING MEANS Slope of rear top surface of fuselage 100 to 5 4 g i ie main landing gear wheel onthe ground and i CONTROL SURFACE MOVEMENTS l 2 skid Ji 49 cm 12 3 inches tail skid jacked up about cm 19 3 inches MES ECH C WING FLAPS AILERONS SEH Pr em 350mm ELEVATOR UP DOWN pedi SE 13 8 n EEN 210 30 2 n UP AND DOWN To Mr RUDDER 15 mm SCH LEFT AND RIGHT 493 2 160 20 mm 6 32 2 in e Wo 86 140mm 3 46 5 8 75 Gi LEVELING MEANS Slope of rear top surface of fuselage 100 to 5 tail skid jacked up about 49cm 19 3 inches 2 E Mini Nimbus C u 15 Mini Nimbus C FLIGHT MANUAL 3 EMERGENCIES 3 1 Recovery from a Spin eee RE das 3 2 If the sailplane with the C G in medium or aft positions enters unintentionally into a spin ease the control stick for ward immediately and apply opposite rudde
34. et the flap into position AH With water ballast the normal towing 0 Should be increased about 20 96 Mini Nimbus C FLIGHT MANUAL s 27 series Neen mmn The landing gear can be retracted during the tow however not in low altitude 1 for gripping the control stick while actuating the landing gear may change the attitude behind the towing airplane For release pull the release handle at the left hand side of the stick fully through pull several times and make sure that the rope is released before turning off Winch tow Maximum towing speed Vwr 150 km h 81 knots 93 mph Before take off adjust the trim NORMAL with the C G in forward to medium positions NOSE HEAVY with the C G in medium to aft positions The normal take off flap position is 48 Put slightly on the brake when beginning the ground run to avoid rolling over the rope The sailplane has a normal behaviour during the ground run and lifts off without tendency to enter an excessively steep climb Depending on the trim adjustment the control stick should be held inslight for Ward position during the take off with the C G in aft positions and slightly F pulled with the C G in forward positions When a safety height of about 50 m 164 rc is reached the sailplane can be brought into a steeper climb by pulling the stick If pitching oscillations are observed during the last stage of the tow ease the cont
35. ght hand side of the seat pull it back and lock EXTENSION Push the handle forward and lock 9 Water ballast Black knob at the right hand side of the cockpit just under the side fairing Knob in aft position Dump valve closed Knob in front position and locked Dump valve open 10 Pedal adjustment The adjustment device is operated by a Bowden cable with a plastic T handle at the right hand side of the control stick Adjustment backward Pull the cable and move the pedals into the desired back ward position Give the pedals a slight forward push with the heels not with the toes until the locking pin engages self acting with a clear clicking noise Adjustment forward Pull the cable slight ly back to unlock the mechanism and push the pedals with the heels into the desired forward position and lock as before ll Parachute support A molded glass fiber support serving as amp Stowage recess for automatic back type parachutes is attached onto the rear 22 Mini Nimbus C FLIGHT MANUAL 12 part of the seat by means of four screws When using a manual long back pack parachute it is advisable to take it off Cockpit ventilation The ventilator is closed by pulling the small black knob at the right hand side of the instrument panel In addition the sliding window of the canopy or its air scoop can be opened s 23 a Mini Nimbus C FLIGHT MANUAL 15 Cockpit Placards Identifica
36. here is little likelihood of blisters but overheating can occur and the resin may become brown If you do not have a source of hot air put a sheet of foil over the applied cloth and use a heat pad or hot water bottle For larger holes in the tailcone not accessible from the inside we must again fabricate a backing on which to contour the repair cloth This can be retained as dis cussed previously with the aid of plywood a nail and a little Patex It cannot later fall out the cloth being directly on the plywood and so is bonded thereto After the plywood backing is secured proceed as previously discussed Lacquer Work After sanding the edges of the patch or the area filled with microballoons until the original contour is attained the puttying can be abandoned and the lacquer PE Vorgelat or PE Vorgelat and filler in 1 to 1 proportion applied directly with a brush not sprayed After hardening sand the area and wet sand with 360 grit wet or dry paper If at no place the weave shows then final sanding can be done with 600 grit wet or dry Polish with rubbing compound If the weave shows repaint with lacquer Repairs to Fittings At the appearance of a damage to a fitting the cause of which is not known contact the factory Welding should be carried out only by an approved aircraft welder All weldments made by the factory are by the Argon are method using 1 7324 0 welding rod Larger Repairs You should not att
37. icular applies to the AIR BRAKES Experiences have shown that it is very advantageous to coat the full Span of the top covers on the air brakes with Vaseline to avoid jamming by icing Flaps and control surfaces are to be moved frequently When flying with water ballast observe the instructions on page 255 Acrobatics without water ballast only Inside loops flaps in position 79 The maneuver should be entered at speeds not less than 180 km h 97 knots 112 mph A speed of 200 km h 108 knots 124 mph is recommended l The speed during recovery is 180 km h 97 knots 112 mph Spins flaps in position 8 or 0 Steady spins are possible only with the C G in the aftmost position With the C G in forward positions the Sailplane goes into a spiral dive Recovery then must be initiated imme diately by neutralizing all controls and diving out Entry to the spin is initiated from dynamic stall by applying rudder in the direction of rotation just before stalling out Ailerons neutral Speed during entry to the spin 60 km h 32 knots 27 mph Speed during recovery from the spin 120 150 km h 65 81 knots 75 93 mph Action for recovery from the spin is initiated by applying opposite rudder and easing the control stick forward 36 Mini Nimbus C FLIGHT MANUAL Turns flaps in position a9 Entry to the turn at speeds not less than 180 km h 97 knots 112 mph A speed of 200 km h 108 knots 124 mph is
38. l from a 45 degrees banked turn through an angle of 90 degrees is 3 seconds 29 Mini Nimbus C FLIGHT MANUAL Flight performances W S 33 kg m 6 76 1b sq ft Stall speed flap position 8 61 km h 33 knots 38 mph Minimum sink flap position 8 0 57 m sec 1 87 ft sec at 80 km h 45 knots 50 mph Best gliding ratio 1 41 at 95 km h E E 0 D RE p 29 mph Wing flaps The flaps have the purpose to adapt the laminar bucket of the wing airfoil to the respective airspeed in the best way Since the laminar buckets of the applied airfoil are covering eachother widely the following flap positions can be accepted Normal flight three positions Landing one position High speed flight one position Airspeed Application knots mph Approach see page 37 AA NEN 80 120 43 65 50 75 thermals 4 1110 170 59 92 68 With water ballast the speeds increase about 20 Best glide Flight between mp O on EE Eom Mini Nimbus C FLIGHT MANUAL 4 6 Low Speed and Stall To get familiar with the Sailplane stalls should first be carried out in high alti tude from straight and turning flight with about 45 bank with different flap positions The following stall speeds were measured ete 335 kg 759 1b 500 kg 1102 1b C G position 580mm 15 in z20 mm 12 6in
39. m CONTICELL 60 4 mm thick 6 Horizontal tail plane Stabilizer Glass fiber foam sandwich i Foam CONTICELL 60 6 mm thic Elevator Pure glass fiber layup If a fracture or damage occurs to the sail plane you should first inspect the damaged area todetermine exactly the type of construc tion and to find the appropriate method for the repair Repairs can be carried out as described by the enclosed instructions for the Cirrus as far as glass fiber structure are concerned If repairs on carbon glass fiber parts should be necessary ask the manufacturer for advice Mini Nimbus C Repair Instructions Note At the construction of this sailplane Mini Nimbus C the following CIBA resin System was used Resin XB 2878 A Hardener XB 2878 B Mixing proportions l by weight 100 resin to 36 hardener Curing instructions After precuring or during the cure 15 hours at 50 C 1220F or 10 hours at 80 C 1769F Recommended maximum curing temperature 100 0 212 F EE M S Repairs on this Sailplane should be made using the above CIBA resin System Do not use the resin System Epikote 162 with Laromin C 26C as specified by the repair instructions for the CIRRUS Schempp Hirth KG 7312 Kirchheim Teck H Germany Repair Instructions for the Glass Fiber Plastic Sailplane CIRRUS M Construction In the CIRRUS sailplane we find three basically different construction methods Repairs must for thi
40. na support e g on the tail plane support Lock the flap control lever in position OO and extend fully the air brake Put in the right wing tongue spar root up to a distance from the fuselage of about 10 cm Open fully the air brake Push in the wing with aileron in neutral position while moving the wing tip Slightly back and forth and lifting the trailing edge a little to avoid a tilting of the attachment peerings on the fuselage When a distance of 1 to cm between wing root rib and fuselage is reached remove the main bolt v eg ee dus qu GR E GA A aee au edu eq in WA DATA IT a mra a TEY 4l Mini Nimbus Cc Service Manual 5 6 7 Take the provided assembly tool push it through the main bolt spar bushings and pull the wings together Take care of the proper connection of the controls as described by the instructions No 5 Push the main bolt E the aligned Spar bushings and secure its handle onto the fuselage shell Ki means of a cowling safety pin Horizontal tail plane Screw the ring bolt EEN aid provided in the side pocket of the cockpit into the front attachment bolt on the fin Put the horizontal tail plane onto the two control connection bolts pull the Spring loaded front bolt by means of the ring and insert the bolt into the bearing of the attachment fitting on the lower surface of the EVR ent Eyer Remove the ring bolt Check if the two control connec
41. of 1 5 to 2 0 m or horizontally in section true Supports which are attached onto the ceiling of the hinged cover as on the Komet trailer In trailers the tailplane must not be Supported at the attachment fittings Sailplanes which are kept assembled for longer periods must be maintained so to avoid corrosion of all main attachments The use of dust covers should be taken for granted When towing the sailplane by car always use a tail dolly to avoid excessive stress and therewith wear of the tailplane attachments due to vibration i 20 5 Mini Nimbus C Service Manual 5 2 1 2 3 4 When towing off by hand do not push at the wing tips but at the wing root area Assembly Wings Clean and lubricate the attachment bolts and bearings i Adjust the flap control lever in the cockpit on high speed position 70 the air brake control lever and the dump valve operating lever on position CLOSED Put the left wing fork spar root with the flap in position 7 and lifting it slightly into the cut out of the fuse lage up to a distance from the fuselage of about 1 cm unlock the air brake control lever push the wing fully in and insert the main bolt into the front fork spar bushing only Be cautious that the bell cranks on the root rib are safely engaged into the funnel type fittings on the fuselage and that the flap control is catching properly the torsion drive tube The wing then can be laid down o
42. opor kernels In these cases proceed as follows You cut or sand a plug of foam Conticell 60 to fit the hole spread the inner side thinly with microballoons to close the pores and lay on it the inner laminate The inner laminate must harden before doing further work If the hardening is complete or at least progressed so that the laminate does not separate from the foam then glue the plug in the hole with thickened resin chopped cotton wool micro balloons The foam with laminate on one side is flexible so that it can be fitted to the wing contour if necessary warn the foam with a hairdryer and bend Once the foam is glued it can be smoothed puttied with microballoons and the outer laminate applied Caution Avoid strong heat otherwise air bubbles form Outer laminate TTT EE Puttied microb surface o O C O OO E Lgs ME ae p o o o 9 0 Ze d 9 Q k AA Ze Inner laminate Replacement piece Conticell 60 Damage to the Controls Basically the same procedure can be used as on the wing Only in place of the PVC foam a polystyrene foam layer Styropor Thermopete Super 5 32 inch thick is used The Styropor piece need not be coated with microballoons the cloth adheres very well with pure or slightly ERE ea de ee get EE III 5 thickened resin which must not harden in any case before doing further work However with larger replacement pieces you should let the laminate harden on one
43. ors page 7 Due to the steep flight attitude the air brakes should not be retracted at speeds exceeding 140 km h 76 knots 87 mph l The terminal velocity in a dive with an inclination of the flight path of 459 is about 190 km h 102 knots 118 mph with air brakes and landing gear extended and at maximum weight 444 _Mini Nimbus C FLIGHT MANUAL 4 8 Flight with water ballast When an average climbing speed of less than 1 5 m sec 3 knots or 5 ft sec ls expected or when flying in narrow thermals where highly banked circling is required the use of water ballast is not worthwhile i Before filling water into the wing tanks the maximum permitted water ballast is to be determined following the instruc tions on page 9 The wing tanks have a total capacity of about 190 liter water With wings held level the tanks are i filled through a hole in the upper surface next to the station of the inboard aileron root Do not fill under high pressure e g directly from the water main Both tanks must be filled with the same water quantity Due to the installed baffles no noticeable shifting of the water is observed The filling holes are closed by a cap which has a small 5 mm dia hole for pulling it out by means of the provided pin The hole in the cap serves also as a vent hole and therefore must be kept open The tanks have an additional vent by means of plastic tubing leading through the wing with outlet at the out
44. r until rotation ceases It is very important to ease the control stick forward in order to avoid a rotation to the opposite direction when applying opposite rudder Malfunction Takeoffs by winch or airplane tow on uncutted grass fields should not be con ducted If a wing is caught in the grass release immediately to avoid a ground loop and therewith damage To prevent the sailplane from unintentio nal and unnoticeable stall in an emergen cy release in low altitude a Speed of 85 to 95 km h 46 to 51 knots or 55 to 59 mph depending on the wing loading and flap position should be maintained in a straight flight In a turning flight the speed is to be increased corresponding to the angle of bank If slight oscillations are observed or if the controls become Spongy the sail plane is stalled though the ASI indicates 65 to 85 km h 35 to 46 knots or 40 to 53 mph dependent on the wing loading and flap position The control stick then is to be released forward immediately erer E tee Ee Sie ss Mini Nimbus FLIGHT MANUAL 5 5 Emergency Exit The roomy and well faired cockpit warrants a quick and safe bailing out in emergency Jettisoning of the Canopy PULL BACK the red ball knob at the left hand side of the canopy frame PULL BACK the red ball knob at the right hand side of the cockpit just below of the side fairing Throw off the canopy The cord which holds the opened canopy in
45. remove the outer laminate in the region of the damage which is no longer bonded to the foam and enlarge the hole in the foam and inner laminate until good bonding to the foam is evidenced Then the foam is further removed 3 4 inch around the hole in the inner laminate and the outer laminate scarfed as under paragraph a Now the projecting inner laminate is cleaned of any foam and feathered If the hole in the foam is smaller than a fist then glue with Patex a thin plywood or polyester plate from the inside to the laminate lay on the inner laminate 1 layer 92125 or 2 layers 921103 and fill the hole in the foam with microballoons mixed with Styropor kernels or crumbled Styropor II 4 If you are not hurried let it harden 8 hrs at68 deg F Sand and apply the outer patches A tip on gluing the plywood plate the hole in the inner laminate should always be a bit oblong so as to insert the plywood backing plate Before inserting the plywood drive through the middle of the ply a pin or nail by which it can be drawn against the inner sholl With additional nails or pins it is in this manner possible to close very large holes to the proper contour to lay the cloth patch on E Outer laminate Microb with 753 m n Inner laminate Basically it is possible to repair also larger shell parts in the foregoing manner Because of weight you Should use a plug of foam in place of the microballoons and Styr
46. rol stick slightly forward Avoid climbing take offs and low towing Speed a amm et m a eRe tt 28 Mini Nimbus C FLIGHT MANUAL 4 5 With normal cockpit load and without water ballast the towing speed should not be less than 90 km h 49 knots 56 mph with water ballast not less than 100 km h 54 knots 62 mph When using low powered winches or engines with limitation of RPMs when towing with the wind in calm air or with filled water ballast tanks make Sure that the winch has enough power reserve to maintain the required minimum towing speed Normal towing speed km h knots mph without water ballast 100 54 62 with water ballast 115 62 71 When reaching the maximum towing height the tow rope is released automatically nevertheless pull the release handle Several times Free Flight Test the effectiveness of the air brakes in safe altitude observe the loss of height at different speeds and get familiar with the operation of the wing flaps Since the trim is combined with the flaps it is to be adjusted for zero stick force in straight flight at 110 to 120 km h 59 to 65 knots or 68 to 75 mph with flaps in position 0 The sailplane then is trimmed for all other flap positions over the optimum speed range except of high speeds The sailplane has well balanced flight characteristics and controls With flaps in position O and at a speed of 1 4 the time taken to rol
47. s mounted on the control stick Tow release The yellow handle at the left hand side of the control stick operates the towing hook DO Mini Nimbus C FLIGHT MANUAL 4 Air brakes Extension Pull back the blue handle at the left hand side of the cockpit Retraction Push the handle forward Wing flaps l Tilt the grey handle at the left hand side of the seat inward and choose the desired position High speed Push the handle forward and catch it Low speed Pull back the handle and catch it Trimming control MEE de The spring loaded trimming control green knob is mounted onto the flap control rod at the left hand side of the cockpit It is gradually adjustable Tilt the knob slightly inward choose the position and lock Nose heavy Push forward Tail heavy Pull back Canopy The one piece plexiglass hood is attached by flush hinges at the right hand side of the fuselage It is opened at the left hand side of the cockpit PULL BACK the red ball knob of the locking device on the canopy frame and lift the canopy Take care that the cord which holds the opened canopy in place is attached The jettisoning device is mounted at the right hand side of the cockpit just under the side fairing 2 Mini Nimbus C FLIGHT MANUAL For jettisoning open the canopy as des cribed before then PULL BACK the red ball knob 8 Landing gear RETRACTION Unlock the black handle at the ri
48. s reason be performed differently on the respective parts We differentiate 1 Wing and stabilizer 2 Rudder elevator and ailerons 3 Fuselage 1 Wings and stabilizer are built in a ribless glass fiber plastic foam sandwich construction This means in event of damage that we find a PVC rigid foam 5 16 inch thick 3 7 lb cu ft bonded on both sides with a glass cloth laminate 2 The controls likewise consist of a sandwich construction However here the supporting core is not PVC rigid foam but amp 5 52 inch thick foamed polystyrene Styropor sheet with a specific weight of only one lb cu ft 3 The fuselage in contrast to the above parts is not in sand wich construction but in a pure approximately 1 16 to 3 32 in thick glass fiber plastic layup which is reinforced at two locations with bonded in foam rings The following materials apply to all parts Resin Shell Epikote 162 Hardener BASF Laromin C 260 Mixing proportions by weight 100 resin to 38 hardener by volume 2 resin to 1 hardener After proportioning stir until striations disappear Add filler after stirring Glass fibers and cloth pm Use only alkali free E glass cloth with Volan A or I 550 finish INTERGLAS INTERGLAS Weave Weight Application Style lb aq ft Elevator amp rudder Fuselage ailerons Crosstwill stabilizer Wings amp fuselage uni 181 150 directional U S Style Fuselage
49. tion bolts are properly inserted into their bearings by moving the elevator After assembly Check the function of all controls Seal the joints of the wing and fuselage with an adhesive tape Seal also the hole in the fin for the front attachment bolt and the joint of stabilizer and fin The sealing is very important to ensure good fight qualities 42 Mini Nimbus C Service Manual 5 5 Disassembly 1 Horizontal tail plane 2 Pull the front attachment bolt using the ring bolt Lift slightly the leading edge of the stabilizer and take off the tail plane in forward direction Wings With air brakes unlocked and flaps in position O load the wings and pull out the main bolt Disconnect the wing attachment by pulling thoroughly at the wing tips and take off the wings Aas E EE 7 o CA Mini Nimbus c Service Manual 6 6 1 Maintenance Periodic Inspections Rudder control cables After every 200 flight hours and at every annual inspection the rudder control cables are to be checked in the area of the S shaped tubular guide on the pedals with pedals in front and aft position The control cables should be replaced if injured worn or corroded A wear of single outer strands up to 25 9 is permissible If replacement of the cables should be necessary cables 5 2 mm 1 8 LN 9274 made of zinked carbon steel strands are to be used The thimble eye splices are made
50. tion plate fire proof Hersteller SCHEMPP HIRTH KIRCHHEIM TECK Bau Muster Werknummer CTT el Operating limits Max take off weight 500 kg 1102 1b EE SE Maximum pernitted speeds I A S km h knots mph E Flaps Positions 4or 7 250 135 155 Positions Oor 8 180 97 112 In strong turbulence 200 108 124 Maneuvering speed 200 108 124 Airplane tow 180 97 112 Auto and winch tow 150 81 93 Weak links for towing 600 2 20 kg 1320166 1b Landing wheel tire pressure 3 5 Atm 50 psi ES D MEE e LI MEAS EAE S RS ACE ARE Un ee 24 Mini Nimbus C FLIGHT MANUAL Cockpit load o OOOO Payload pilot and parachute tN Ee ANG parachute be exceeded Minimum payload 70 kg 154 1b with ballast on the seat The maximum weight must not Less weight must be compensated Check List before take off Parachute put on properly Strapped in safely Back rest and rudder pedals in comfortable position Operating handles and instruments well accessible Air brakes locked after having checked the function Movement of control surfaces checked Flight controls unrestricted Trim adjusted properly Wing flaps in take off position Canopy closed and locked 25 Mini Nimbus C FLIGHT MANUAL Extended Landing gear Retracted Trimming GREEN knob ae Tow release T
51. uerung im Rumpf Rudder contro in the fuselage EEF DU M op CH uj Es EE Er L 1 SE Se EN sst ll BE l 4 MADE IN GERMANY IN Wo yg Repair Instructions for the Sailplane Mini Nimbus C The construction methods on the sailplane Mini Nimbus Q are similar to those on the OPEN CIRRUS Therefore repairs can be carried out in the same way as described by the enclosed instructions for the Cirrus In the Mini Nimbus C we find the following
52. uilt in a pure glass fiber lay up and therefore has a high energy abs rotion The fuselage shell is stiffened by RP foam sandwich bulkheads The pilot is sessed ina Semi reclined position The landing gea wheel is retractable A towing hook is installed as Standard ee just in front of the landing wheel Horizontal Tail Plane The horizontal tail plane is of a T type with stabilizer and elevator The elevator is trimmed by a spring loaded click stop device on the flap operating rod in the cockpit The stabilizer is built ina FRP foam sandwich the elevator in pure FRP Vertical Tail Plane Fin and rudder are built in a FRP foam sandwich construction The rudder has an internal drive f o Mini Nimbus C FLIGHT MANUAL 2 OPERATING LIMITS 2 1 Airspeed limits IAS km h knots mph Maximum speed VNE 250 135 155 Flap pos 4 7 Maximum speed Veg 180 97 112 Flap pos 0 8 In strong turbulence Vg 200 108 124 Maneuvering speed VA 200 108 124 Airplane tow Varn 180 97 112 Auto winch tow Vwp 150 81 93 Note At increasing altitudes the true airspeed TAS is higher than the air speed indicated on the ASI IAS This has no influence on the strength and loading capacity of the sailplane For reasons of flutter safety however the following indicated airspeeds should not be exceeded Height IAS IAS IAS m km h knots mph ee 0 250 135 155 1000 250 135 155 T 2000 250 135 155 n 5000 250 155 155 4000 25
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