Flight and Service Manual for the Sailplane Mini
Contents
1. PAL LLC Lisa SEN fuselage root rib 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 mm follow the instructions on page 48 Mini NIMBUS B Service Manual 6 10 Safety belts 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 0 Attachment Brackets on the fuselage shell and accessible through cut outs in the seat panel Shoulder harness Gadringer Schugu c Autoflug Schugu FAG 74 0 Attachment Front wing attachment tube accessible through cut outs in the upper FRP fairing Instruments m The original certification of the Mini Nimbus B was carried out using the following instruments Airspeed Indicator 30 300 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 S For the basic equipment or for cloud flying any approved instruments can be used if they meet the requirements of 2 8 page 12 56 Mini Nimbus B Service Manual 7 Determination of the empty weight C G For the determination of the empty weight C G positi2. OPERATING LIMITS Airspeed limits IAS FLIGHT MANUAL km h knots mph Maximum speed Vue Flap pos 4 7 Maximum speed Vere Flaps pos 0 8 In strong turbulence Vs Maneuvering speed VA Airplane tow Var Auto winch tow Vur Note At increasing altitudes the true airspeed TAS airspeed indicated on the AS This has no influence on the strength and loading capaci For reasons of flutter safety however the following indi should not be exceeded Altitude VNE m Et 0 0 3 000 9 800 6 000 19 700 10 000 32 800 ty of the sail 290 180 200 200 180 150 155 97 108 108 a od is higher than the AS plane cated airspeeds IAS IAS km h knots 250 135 230 135 223 120 T 96 155 112 124 124 112 93 IAS mph 155 199 139 110 Mini Nimbus B 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 0 9 m in front of the vertical tail plane 60 PS n a vH RE H Q O i u H A lt Ing 15 T7 d O ed Ci q A 50 knots 60 60 100 120 lho 160 180 200 220 240 km h sus a ee u
3. SCHEMPP HIRTH GmbH amp Co KG KIRCHEIM TECK Federal Republic of Germany FLIGHT and SERVICE MANUAL for the Sailplane Mini Nimbus B Issue July 1979 This Manual should always be carried in the Sailplane It belongs to the Sailplane Mini Nimbus B Registration Number VH OUEQB Leu Serial Number var BOG a aes us Manufacturer SCHEMPP HIRTH Owner Balaklava Gliding Club The pages 5 38 are approved by the Luftfahrt Bundesamt This page intentionally left blank Mini Nimbus B FL IGHT MANUAL Table of Contents ND NN NN N NN NN N m e L O IO O1 amp QO NH WWW w BEBE SE Sa St SH St SS SS O co 1 O O gt QQ Ns w N Amendments General Operating Limits Airspeeds Airworthiness Category Load Factors Weights Cockpit load C G Positions Weak links for Towing Minimum Equipment Acrobatics Wing and Tail Setting Control Surface Movements Emergencies Recovery from Spins Malfunction Canopy Jettison Normal Operating Conditions Page 3 O O0 U gt 10 12 15 t3 14 15 15 15 16 Daily Inspection Cockpit Lay out Check before Takeoff Takeoff Free Flight Slow Speed Flight Stalls High Speed Flight Flight with Water Ballast Cloud Flying 10 Flights below Ice Point 11 Acrobatics 12 Ap
4. 4 6 Low Speed and Stall To get familiar with the sailplane stalls should first be carried out in high altitude from straight and turning flight with about 45 bank with different flap positions The following stall speeds were measured Take off 335ko 739 lb 450kg 932 1b weight C G position 380mm 15 in 22Omm 8 7in Stall speed km h knots mph mph air brakes retracted flap positions 8 62 33 38 75 40 67 36 42 81 44 ne 42 48 48 89 air brakes extended flap position 58 36 8 Shortly before reaching the stall speed stall warning occurs with air brakes retracted at speeds of 62 to 89 km h 33 to 48 knots 38 to 55 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 3 1 mph before reaching the stall speed When pulling the stick gently back the ASI indicates again higher speeds until 31 Mini Nimbus B FLIGHT MANUAL 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 ab
5. Mini Nimbus B Service Manual m 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 3 Push the main bolt through the aligned spar bushings and secure its handle onto the fuselage shell by means of a cowling safety pin Horizontal tail plane Screw the ring bolt mounting 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 andinsert the bolt into the bearing of the attachment fitting on the lower surface of the stabilizer Remove the ring bolt Check if the two control connection 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 Mini Nimbus B Service Manual 5 3 Disassembly 1 Horizontal tail plane 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 2 Wings W
6. Mini Nimbus B FLIGHT MANUAL 4 3 Check before take off See cockpit placard on page 24 4 4 Take off Aerotow Maximum permitted speed on aerotow Vr 180 km h 97 kt 112 mph Use the C G hook for aerotow or if installed the nose tow hook The Mini Nimbus has been aerotowed using Nylon ropes of between 40 and 60 m length 130 200 ft When commencing the ground run apply the wheel brake gently so that the sailplane does not overrun the tow rope For take off set flaps at 4 and the trim to neutral for forward to middle C G positions or to nose heavy for middle to aft C G posi tions with the C G in a middle to forward position the elevator should be neutral for the ground run in the case of rear C G positions it is recommended that down elevator is applied until the tail lifts As the speed increases select flap setting 0 with middle to rear C G positions the sailplanes leaves the ground at 0 flap setting and in the case of forward C G positions or if the all up weight is high flap setting 8 should be selected to shorten the take off run After the sailplane left the ground at speeds of about 70 to 75 km h 38 40 kt 43 47 mph the trim can be set for minimum control stick loads Normal towing speed is in the region of 100 to 120 km h 54 65 kt 62 75 mph with flap setting 0 At speeds in excess of 120 km h 65 kt 75 mph the appropriate flap setting is 4 When water ballas
7. 2 in S N 135 279 mm 5 31 8 8 in 15 18 5 ley Ss w IE leo i 7 i 11 at 3 LEVELING MEANS Slope of rear top surface of fuselage 100 to 5 1 ie main landing gear wheel on the ground and tail skid jacked up about 49cm 19 3 inches CONTROL SURFACE MOVEMENTS Mini Nimbus B Mini Nimbus B FLIGHT MANUAL 3 EMERGENCIES Sl Recovery from a Spin 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 rudder 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 90 km h 46 to 49 knots er 53 to 56 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 stalle
8. Wing The cantilever two 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 combination of spoi m capacity of 125 liters serial no Fuselage A The one piece canopy is faired The trailing edge air brakes are a ers and flaps The ailerons have internal drive Two integral water tanks have a total up to 83 The fuselage is necked behind the wing into the fuselage and hinged at the right hand Side The fuselage shell is built ina pure glass fiber lay up and therefore has a high energy absorption The fuselage shell is stiffened by FRP foam sandwich bulkheads The pilot is seated in a semi reclined position The landing gear wheel is retractable A towing hook is installed as standard 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 rod in the cockpit The stabili click stop device on the flap operating izer 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 Mini Nimbus B
9. Check ailerons for free and full movement 3 a Check air brakes for close fit and proper operation b Check trailing edges of flaps and ailerons for damage Check flaps and ailerons for excessive backlash of attachments by rocking slightly at the Mini Nimbus B FLIGHT MANUAL c O 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 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 See Check the pitot tube for contamination When blowing into the tube the AST must work After heavy landings or excessive acceleration the frequency of flexural wing vibration should be checked about 141 min Check also the elevator drive fitting on the horizontal tail plane for tears using a fivefold magnifying lens If
10. Foam CONTICELL 60 4 mm thick 6 Horizontal tail 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 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 structures are concerned If repairs on carbon glass fiber parts should be necessary ask the manufacturer for advice Mini Nimbus B Repair Instructions Note At the construction of this sailplane Mini Nimbus B the following CIBA resin system was used Resin XB 2878 A Hardener XB 2878 B Mixing proportions by weight 100 resin to 36 hardener Curing instructions After precuring or during the cure 15 hours at 50 C 122 F or 10 hours at 80 C 176 F Recommended maximum curing temperature 100 C 212 F Repairs on this sailplane should be made using the above CIBA resin system Do not use the resin system Fpikote 162 with Laromin C 260 as specified by the repair instructions for the CIRRUS Schempp Hirth KG 7312 Kirchheim Teck W Germany Repair Instructions for the Glass Fiber Plastic Sailplane CIRRUS Construction In the CIRRUS sailplane we find three basically differe
11. 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 37 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 mir se Mini Nimbus B FLIGHT MANUAL Turns flaps in position 7 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 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 c imb 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 240 60 110 59 68 235 659 1 25 67 78 840 TOR 135 T3 84 2 5 T3 150 81 93 Acrobatics are permitted only when flying without water b
12. its steep ttitude the sailplane then could exceed he maximum permitted speed ro H OY pum Take care that the required equipment for cloud flying is installed in the sailplane see page 12 Flight below freezing point At temperatures below 0 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 B FLIGHT MANUAL s This in particular 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 33 Acrobatics without water ballast only Inside loops flaps in position 7 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 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
13. necessary the fitting should be replaced Mini Nimbus B FLIGHT MANUAL 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 2 Cockpit Layout 1 Instrument panel With canopy opened the instruments are well accessible The instrument compart ment cover is fastened by four screws The instrument panel is attached onto the fuselage canopy frame and is easy to remove 2 Control stick The main landing wheel brake lever is mounted on the control stick 3 Tow release The yellow handle at the left hand side of the control stick operates the towing hook Mini Nimbus B FLIGHT MANUAL 4 Air brakes Extension Pull back the blue handle at the left hand side Sf the cockpit Retraction Push the handle forward 5 Wing flaps 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 Gatch Tt Low speed Pull back the handle and catch it 6 Trim
14. 21 40 50 60 70 80 9 10 HO 120 130 knots D e A a pe 4 40 50 60 70 80 90 100 No 120 130 140 150 mph Note All speeds stated in this Manual are indicated airspeeds IAS Mini Nimbus B FLIGHT MANUAL 2 2 Airworthiness Category U Utility according to the LFMS Based on the Airworthiness Requirements FSM full control movements can be pplied up to the maneuvering speed Va t higher speeds it is possible to verstress the sailplane therefore ull control movements are not allowed speeds exceeding 200 km h 108 knots 124 mph t the maximum airspeed Vw 250 km h 35 knots or 155 mph a maximum of one hird of the full control movement is ermitted he elevator control movement at Vye ust be even less which depends on the permitted maneuvering load factor B H trep or u 5 Under normal weather conditions this sailplane can be safely flown at high speeds up to Vw 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 f 500 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 Mini Nimbus B F
15. LIGHT MANUAL 2 4 Weights Maximum takeoff weight 450 kg 992 1b Max weight of non Lifting parts 230 kg 507 1b Max weight of water ballast kg or liters see page 9 Loading instructions Cockpit load pilot and parachute Max 110 kg 243 1b Min 70 kg 154 Ib The maximum takeoff weight must not be exceeded Less weight than 70 kg 154 1b 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 550 mm 21 65 inches ahead of datum Mini Nimbus B Serial Nr up Water ballast to 82 FL IGHT MANUAL Maximum takeoff weight with water ballast 450 kg 992 1b Max water ballast at different empty weights and cockpit loads Empty weight kg 220 230 240 250 260 Empty weight lb 485 507 529 391 513 At hi non l gh cockpit loads care not to exceed the max oad carrying structure permi The baggage compartment can a wei 5 kg 1L 15 The wei to the ori ght of max are al 15 kg lowed ght of objects wh ginally must be consi maximum perm install dered when determining the 33 to ich ed is to be taken tted weight of be Ib be do loaded with of which only removed not belong equi
16. allast Mini Nimbus B Se FLIGHT MANUAL 4 12 Approach and Landing he very effective air brakes are a ombination of spoilers and flaps nd allow steep and slow approaches hey do not notably increase or he normal flap position during the ulling back the air brake handle until ear resistance is observed means ending only the spoilers by which he sailplane can be controlled during ling the handle further back lers and flaps are cooperating he normal approach speed is about 80 km h 40 43 knots 47 50 mph h flaps in position 8 air brakes landing gear extended h water ballast the speeds increase 2 a decrease the lift landing is 8 P a cl ext t the approach When pu the spoi T 75 wit and Wit up to 15 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 flaps are taken back into normal posi n loss of lift while the spoilers tio with their fu stil are drag and decrease of lift 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 p the gliding angle however promptly re
17. anual 5 ce 1 Storage Transport Assembly Storage Parking Ground towing m 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 higher tempera ures ue to their high fineness ratio the ings with leading edge down must be upported very carefully at the center of he spar stubs and in a section true ing support at a distance of about 2 4 m rom the tip he fuselage should be supported on a ide cradle just in front of the C G owing hook and on the tail skid he horizontal tail plane is to be upported with leading edge down on section true cradles which should have a distance of about 1 5 to 2 0 m In trailers the horizontal tail plane must not be supported at the attachment fittings Sailplanes which are kept assembled for longer periods must be maintained so to avoid corrosion of the attachments of the fuselage wings and tail surfaces The use of dust covers on high perfor Oe ee ase mance sailplanes 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 tail plane attachments due to vibration 40 Mini Nimbus B Servi
18. axis Mass balance on flaps and ailerons A square bar of lead or of similar heavy material is to be attached onto the in side of the nose strip between the first and second hinge fittings by means of 4 mm or 5 32 counter sunk screws in a distance of 100 to 150 mm 4 to 6 in each Mass balance on the rudder Parallel to the already installed round bar a square or round bar of the required weight is to be glued onto the inside of the nose strip and covered with a glass cloth layer additional mass balance Mini Nimbus B Service Manual 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 The control surface should be supported at its hinge axis The force P is to be measured by means of a letter or spring balance After the installation of an additional mass balance the control surface movements are to be checked for their inlimited travel Mini Nimbus B Service Manual 6 8 Maintenance of the surface finish Wash the surface 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 add washing agents to the water too often and don t use agents which are containing Silicone Clean the plexiglass hood with a
19. ce Manual 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 Adjust the flap control lever in the cockpit on high speed position 7 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 on a support e g on the tail plane support Lock the flap control lever in position 0 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 bearings on the fuselage When a distance of 1 to 2 cm between wing root rib and fuselage is reached remove the main bolt
20. d 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 Mini Nimbus B Emergency Exit FLIGHT MANUAL 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 PULL BACK the red ball canopy frame knob at the right hand side of the cockpit just below of the side fairing Throw off the canopy 3 Q anopy uilt of strong glass nNnWOH upport for the pilot he cord which holds the opened canopy in place is attached such to rip immediately when throwing off the he canopy frame on the fuselage is fibers without harp edges and is well suited as a to jump off ee Mini Nimbus B FLIGHT MANUAL 4 Normal Operating Conditions When going around the sailplane for inspection check all external surfaces for tears blisters or dents In case of doubt ask a FRP expert a Open the canopy and check if the main bolt is installed and secured b Check the cockpit controls by visual inspection c Remove foreign particles d Check tire pressure of the main wheel 3 9 Ais SO BEL Q e Check condition and function of the towing hook
21. d winch tow 150 81 93 Maximum permitted RATS km h knots mph Altitude VNE IAS m ft km h knots mph 3000 9800 250 135 6000 19700 223 120 10000 32800 177 96 Weak links for towing 600 30 kg 1320 66 1b Landing wheel tire pressure 35 Atm 50 PSL Mini Nimbus B FLIGHT MANUAL Cockpit load Payload pilot and parachute The maximum weight must not be exceeded Minimum payload 70 kg 154 1b Less weight must be compensated with ballast on the seat 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 The following acrobatic maneuvers are permitted recommended km h knots mph entry speed Inside loops 200 108 Spins 60 32 Turns 200 108 Lazy eight 180 97 Mini Nimbus B FLIGHT MANUAL Extended Landing gear Retracted CRT 4 Trimming EEN knob Gas gt LED Tow release i el N Pedal adjustment YELLOW T handle ps lt LL Lan ects Air brakes BLUE handle JETTISON Canopy RED ball Be Ventilation Water ballast DO
22. e inspection program mentioned under section 3 If the results of this inspection are positive or if any defects found have been duly repaired the service time of the sailplane is extended by another 1000 hours to a total of 4000 hours first step The above inspection program must be repeated when the sailplane has reached a service time of 4000 hours If the results of this inspection are positive or if any defects found have been duly repaired the service time of the sailplane is extended to 5000 hours second step TECHNICAL NOTE NO 328 7 November 1985 S g re Mini Nimbus B SERVICE MANUAL When the sailplane has reached a service time of 5000 hours the above inspection program again must be repeated If the results of the inspection are still positive or if any defects found have been duly repaired the service time may b xtended to a total of 6000 hours third step For a possible service time exceeding 6000 hours procedures will be evaluated in the future 3 LBA approved Schempp Hirth 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 4 The inspection must only be done by the manufac turer or by a licensed repair station or inspec tor 5 The results of the inspections have to be record ed in an inspection test report wherein c
23. ear wing spar with air Dbrake opened and aileron dismounted Air brake drive accessible through cut outs in the rear wing spar with air brake opened e Fuselage controls Drives in the fuselage accessible after removal of the seat panel and the fairing on the front steel tube frame e Elevator control Accessible after disassembly of the horizontal tail plane e Rudder control Accessible through the cut out in the nose with rudder deflected to the right After having cleaned the sailplane proceed as follows e 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 L is advisable to ask an expert s advice e Check all accessible metal parts for damage As known from experience no damage occurs when operating the sailplane properly 46 Mini Nimbus B Service Manual If any repair should be necessary ask the advice of the manufacturer Check all accessible metal parts for corrosion If necessary remove the rust and protect the surface again by a new painting Corroded fittings push rods and levers should be thoroughly cleaned and consequently primed and painted using a special primer and Nitro paint primer and paint can be supplied by Schempp Hirth If the controls cannot be operated
24. eration he 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 with controls held fixed the backlash of the control surfaces must not exceed the following values Control Backlash Measuring point aft of hinge axis Elevator Rudder Flaps Ailerons Air brakes measured above hinge axis at fully opened air brake Mini Nimbus B Service Manual 6 4 Backlash of the attachments 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 30 mm 1 3 16 additional washers of an inner diameter of 13 95 mm about 0 3 to 0 5 mm thick should be pressed onto the bolts until the backlash is eliminated Mini Nimbus B Service Manual 6 5 Damages 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 airworthines
25. h the C G in aft positions comes to stal yet and enters unintended a spin set the flaps on negative position immediately apply opposite rudder and ease the control stick 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 valves 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 This page intentionally left blank Mini Nimbus B FLIGHT MANUAL 4 9 4 10 Cloud flying The sailplane has sufficient strength and stability Tor cloud flying It is easy to control and has stable circling qualities Nevertheless observe the following instructions Do avoid 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 ir brakes already at an indicated peed of 130 km h 70 knots 81 mph or t a load factor exceeding 29 t speeds exceeding 140 km h 76 knots 7 mph the air brakes should not be etracted again due to
26. idenced Then the foam is further removed 3 4 inch around the hole in the innor laminate and the outer laminate scarfed as under paragraph a Now the projecting inner laminate is cleaned of any toam and feathered I We remove the outer laminate in the region of the damage w h 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 X or 2 layers 92110 X and till the hole in the foam with microballoons mixed with Styropor kernels or crumbled Styropor IT If you are not hurried let it harden 8 hrs at 68 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 Betore inserting the plywood drive through the middle of the ply a pin or nail by which it can be drawn against the inner shell 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 u Outer laminate Microb with polar Ad ac y Inner laminate Thin plywood backing 3 4 Basically it is possible to repair also larger shell parts in the foregoing manner Because ot weight you should use a plug of foam in place ot the microballoons and Styropor kernels In these cases proceed as fallows You cu
27. ied 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 fallout 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 arc method using 1 7324 0 welding rod Larger Repairs You should not attempt 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
28. ion is within the JI t Su C G range ft of datum Empty weight Tail weight kg mm kg 200 644 693 28 7 205 633 685 29 0 2 1 0 623 678 29 3 215 614 671 29 6 220 605 664 29 9 225 596 658 30 3 230 588 652 30 6 235 581 646 30 9 240 573 641 312 245 566 635 34 25 250 559 630 341 39 255 552 625 22 260 546 620 322 5 Tp inches lb 440 25 40 27 29 63 11 450 25 03 gt 27 01 63 73 460 24 67 26 75 64 37 470 24 33 26 50 65 01 480 24 00 26 26 65 65 490 23 69 26 03 66 29 500 23 39 25 817 66 93 510 23 10 25 59 67 55 520 22 82 25 39 68 20 530 22 56 25 19 68 83 540 22 30 25 00 69 46 550 22 05 24 82 70 11 560 21 81 24 64 10 73 570 21 58 24 47 7 1234 Forward empty weight C G calculated for a max cockpit load of 110 kg 243 1b Aft empty weight C G calculated for a min cockpit load of 70 kg 154 1b and a baggage compartment load of 5 kg 11 1b Mini Nimbus B FLIGHT MANUAL Leet Weak links for towing Winch and Airplane tow max 600 230 kg 1320 66 lb 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 31 mph to min 168 mph marked as follows km h knots mph White Arc 77 180 41 97 48 112 flaps 0 8 Green Arc 17 200 41 108 48 124 normal range Yellow Arc 200 250 108 135 124 155 warning range Red Radial 250 135 155 max speed Yell
29. ith air brakes unlocked and flaps in position 0 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 Mini Nimbus B 6 Maintenance 6 1 Periodic 43 Service Manual Inspections Rudder control cab les After every 200 fl annual inspection cables are to be the S shaped tubul wit The inj control cables ured worn or c permissible If a replacement o necessary to be used The thimble eye sp Nicopress Oval S No 28 3 M using a following the spec Gas springs After removal of fairing on the fr he front wing at IC Ct hould be observed e replaced Ion e w TH must be possi this position with applying a moment 6 to 1 9 mkg or cables 3 made of zinked carbon steel strands are eeves No the upper fi on he gas springs are ight hours and at every the rudder control checked in the area of ar guide on the pedals h pedals in front and aft position should be replaced if orroded A wear of single outer strands up to 25 is f the cables should be 2 mm 1 8 LN 9374 lices are made with 18 3 M or tool No 51 M 850 and ial instructions for making and checking the sleeves ber glass steel tube frame accessible behind achment tube he piston rods mu
30. ity Due to the installed baffles o noticeable shifting of the water is bserved he filling holes are closed by a cap hich has a small 5 mm dia hole for ulling 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 outboard 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 MHHOD QS S SD Mini Nimbus B 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 0 degr C 32 degr F the water must be drained off to avoid icino 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 wit
31. ld 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 factors 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 The terminal velocity in a dive with an inclination of the flight path of 45 is about 150 km h 81 knots 93 mph air brakes and landing gear extended 334 Mini Nimbus B 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 is expected or when flying in narrow thermals where highly banked circling is required the use of water ballast is not worthwhile 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 125 liter water with wings held level the tanks are 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 ust be filled with the same water uant
32. lights 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 310 mm to 380 mm 12 2 in to 15 in aft of datum The sailplane is to be weighed as des cribed on page 57 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 W2 Flight D x Flight a W W Payload Service Manual Mini Nimbus B peotried umutxzeu 3e 3SETTECQ 107EM idy202 4 by X unjzep FO 37e uotytsod 9 9 by gsr 3au6r xs Aydug 6ss 2 s nyeu ts ey y Aq ano pst ze burubr x Ab T El Fo oyeq 389ys HoT s ueTeg pue IybrsM 58 a Mini Nimbus B SERVICE MANUAL Inspection program for extension of service time 1 General The results of fatigue tests of wingspar sections have demonstrated recently that the service time of GFRP sailplanes may be extended to 6000 hours if for each individual aircraft 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 CFRP components are approved for a service time of 6000 hours 2 Dates When the sailplane has reached a service time of 3000 hours an inspection must be done in accordance with th
33. 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 the repair Kirchheim Teck 26th March 1968 Schempp Hirth K G ss Klaus Holighaus Translation by F H Matteson
34. ming control 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 7 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 m The jettisoning device is mounted at the right hand side of the cockpit Just under the side fairing 21 Mini Nimbus B FLIGHT MANUAL 10 se For jettisoning open the canopy as des cribed before then PULL BACK the red ball knob Landing gear RETRACTION Unlock the black handle at the right hand side of the seat pull it back and lock EXTENSION Push the handle forward and lock 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 Pedal adjustment The adjustment device is operated by a Bowden cable with a plastic T handle at the right hand side of the contr
35. nt construction methods Repairs must for this reason be performed differently on the respective parts We differentiat 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 rind a PVC rigid roam 5 16 inch thick 3 7 1b 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 a 5 32 inch thick foamed polystyrene Styropor sheet with a specific weight of only one 1b 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 tiber 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 ixing 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 Use only alkali free E glass cloth with Volan A or I 550 finish INTERGLAS INTERGLAS U S Weave Weight Application Style Style lb sq ft 91110 Elevator amp rudder Fuselage ailerons Crosstwill stabilizer Wings amp fuselage Fu
36. ol 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 Parachute support A molded glass fiber support serving as a stowage recess for automatlc back type parachutes is attached onto the rear Mini Nimbus B 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 23 Mini Nimbus B FLIGHT MANUAL 13 Cockpit Placards Identification plate fire proof Hersteller SCHEMPP HIRTH KIRCHHEIM TECK Bau Muster OD Werknummer J nacte 7 Operating limits Max take off weight 450 kg 992 1b speeds Flaps Positions 4 or 7 250 135 155 Positions 0 or 8 180 97 112 In strong turbulence 200 108 124 Maneuvering speed 200 108 124 Airplane tow 180 97 112 Auto an
37. omments are required for each inspection instruction If the inspections are done outside the manufac turer s facilities a copy of the records must be sent to the manufacturer for his evaluation and information 6 The annual inspection is not affected by this inspection program TECHNICAL NOTE NO 328 7 November 1985 Service Manual 59 MINI NIMBUS B W lbklappe im Fl gel wing controls 4 wing flaps 2 A lerons 3 Air brakes Service Manual 60 MIN NIMBUS 8 and Ein sinninl uuninnnbnse Lu lin Fuselage Controls 2 Allerons 3 A rbrakes 4 Elevator Service Manual 61 MINI NIMBUS 8 Seitensteuerung im Rumpf Rudder control in the fuselage 60 70 80 90 100 MO 4120 490 o 160 160 170 180 0 5 10 20 a MINI NIMBUS HS7 3 0 SINK m s Repair Instructions for the Sailplane Mini Nimbus B In the Mini Nimbus B we find the following construction methods 1 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 3 Flaps Ailerons Air brakes Pure glass fiber layup 4 Fuselage 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
38. on 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 top surface of fuselage 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 129mm 5 1 in b 3930 mm 154 7 in b 3900 mm with tailwheel for FOB 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 W b Sera lU ned 57 Mini Nimbus B 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 f
39. out 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 unstalled d neutralize the rudder and allow the sailplane to dive out High 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 Vw 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 Mini Nimbus B FLIGHT MANUAL the speed must not exceed Vg 200 km h 108 knots 124 mph With the C G in aft positions Lhe required stick travel at all speeds up to Vw 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 Vez 250 km h 135 knots 155 mph Since sudden deceleration of about 2g can occur the air brakes shou
40. ow Arrow 85 46 53 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 additional to the minimum equipment Magnetic Compass Variometer Turn amp Bank The installed ASI system was found to be suitable for cloud flying Mini Nimbus B FLIGHT MANUAL 2 9 O Acrobatics The Mini Nimbus B is approved for the following acrobatic maneuvers recommended entry speeds km h knots mph Inside loops 200 108 124 Spins 60 32 37 Turns 200 108 124 Lazy eight 180 97 WE It is recommended to install a recording accelerometer in addition to the equipment listed under 2 8 Acrobatic maneuvers are permitted only without water ballast Loose objects are to be removed wing and Tail Setting Reference Rear fuselage center line Angle of wing setting 0 7 Angle of tail setting 09 Control surface movements See page 14 Pay attention to the tolerances if repair work should be necessary FLIGHT MANUAL 14 100 to 5 1 WING ELAPS 6 38 in Max UP Max DOWN u 205mm 33 5mm zm ELEVATOR Sn 2 NR BER BER Q ip di i 323mm 1532 mm ES se TER 21 03 ft UP AND DOWN 122 12in 0592 08 in Fe Bei RUDDER 25 mm 19 22 5 9 11 5 nn 19 5 24 LEFT AND RIGHT 1 93
41. pment itted water ballast Mini Nimbus B FLIGHT MANUAL 2 6 C G Range a C G range in flight gross weight C G 220mm 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 pit load pilot and parachute of 70 kg 154 1b 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 After repair work installation of additional equipment new painting etc the empty weight C G position must be checked If it should not be 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 RE ee Mini Nimbus B FLIGHT MANUAL If the determined tail weight does not exceed these values the empty weight C G posit
42. proach and Landing 17 19 26 26 28 30 gi 32 34 34 35 SH Mini Nimbus B Maintenance and Service Manual Tab le of Contents Oo OY OY OY OY OY OY OY O ooo 01 w N YAO BWNE WO Storage Transport Assembly Storage Parking Ground Towing Assembly Disassembly Maintenance Periodic Inspections Annual Inspections Backlash of Controls Backlash of Attachments Damages Tow Release Hook Weights and Hinge Moments of the Control Surfaces Maintenance of Surface Finish Replacement of Wing Attachment Bearings 10 Safety Belts 11 Instruments Determination of the Empty Weight and Gross Weight C G Position Weight and Balance Log Sheet Inspection program for extension of service time Exploded Views of Flight Controls and Attachments Appendix Polar Curves Page 39 40 42 43 45 47 48 49 49 5l DS 54 SD 55 56 58 58a b 59 Repair Instructions for FRP Sailplanes November 1985 Mini Nimbus B FLIGHT MANUAL Amendments Item Modificat on of water ballast tanks in the wing Modif Bulletin No 328 8 Additional inspection of the elevator drive fitting Supplementary take off and towing instructions Flap settings TN 328 7 Mini Nimbus B FLIGHT MANUAL 1 GENERAL The Mini Nimbus B is a single seat 15 m flapped sailplane in all fiber glass construction
43. s imp rove Mini Nimbus B 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 ouch down speed t Steep approaches e g in strong ground turbulence or over high obstacles should be made with fully extended air Dbrakes 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 sUfficiently effective The brake lever is mounted onto the control stick rm To avoid a Long landing run it is advisable to touch down at a minimum speed of 60 65 km h 32 35 kts 37 40 mph Touching down at 90 km h 49 knots 56 mph instead means doubling the energy of the sailplane and considerably increases the running distance Landings have been demonstrated with cross winds up to 20 km h 11 knots 12 mph 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 51 54 knots 59 62 mph 39 Mini Nimbus B Service M
44. s a puncture or a fracture tap to determine th xtent 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 blowout 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 fill the pores of the exposed foam Then lay three patches of the 92110 cloth with diagonal weave direction stepwise largest patch first over the damaged area The applied cloth must be dry and dust free Outer laminate 3 layers 92110 diagonal a ee AZ fu te ty le w ES P z x a ot 8 8 o Ff 6 D Uran so gt o o Dep be ve a Microballoons Conticell 60 After hardening appr 8 hrs at 20 deg C or 68 deg F he damaged area should be smoothed filled and painted n smoothing take care that only the edges of the patches are sanded Inner laminate Hr f there is a through hole in the sandwich shell then the nner laminate must be repaired hich is no longer bonded to the foam and enlarge the ole in the foam and inner laminate until good bonding to the foam is ev
45. s effected by easing the control stick back If pitching motions occur during the last stage of the tow ease the control stick slightly forwards Climbing take offs and low towing speeds must be avoided TECHNICAL NOTE NO 328 7 November 1985 Mini Nimbus 25 B 20 FLI GHT MANUAL with normal cockpit load and without water bal not be less than 90 km h 56 mph with water bal 100 km h 54 knots 62 When using engines with limitat towing with the wind with filled water bal sure that reserve to towing speed maintai ast the towing speed should 49 knots last not less than mph low powered winches or ion of RPMs in calm air or last tanks make the winch has enough power n the required minimum when Normal towing speed km h knots mph without water ballast 100 54 62 with water ballast 115 62 Er When reaching the maximum towing height the tow rope is released automatically nevertheless pull the release handle several times Free Flight with fl in safe alti tude Test the effectiveness of the air brakes observe the loss of height at different speeds and get fami flaps liar with t Since the trim FTE Eat m ther f The sailpl is to be adj strai is comb he operation of the wing ined with the flaps us
46. s of the sailplane can be repaired by the owner himself See Appendix Repair Instructions 6 6 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 51 Mini Nimbus B 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 and 5 51 Mini Nimbus B Service Manual 6 7 Weights and hinge moments of the 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 bp Elevator Rudder If these values are exceeded a mass balance must be installed in front of the hinge
47. selage uni directional I Wings Rovings GEVETEX Type ES 10 40x 60 K 43 Textilglas GmbH GEVETEX Foams PVC Rigid Foam Conticell 60 Continental AG 5 16 in thick 337 Lb cu ft Styropor THERMOPETE Super PORON 5 32 in thick 1 Ip Zeus 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 ss Gl Lackvorgelat white No 3 6910 resin paint PE Hardener No 7 2050 ixing proportions by weight 100 parts Lackvorgelat to 10 parts hardener PE Thinner No 6 3026 lt 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 ot the laminate and ignite it After the resin is burned the type density and direction ot 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 b Destruction of the whole shell also the inner glass fiber laminate destroyed a If the outer shell receive
48. 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 m 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 sailplane 54 Mini Nimbus B Service Manual 6 9 Replacement of the ball bearings for wing attachment bolts on the fuselage 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 m urn the inner ball about 90 across and ammer the bearing out of its seat from he 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 HS
49. st be clean and without ny damage f a leakage of the piston rod oil seal the gas spring must he expansion force of the gas spring is o be checked on the assembled sai ith flaps in position 7 ble to plane hold the flap in out moving down when of 16 to 19 Nm resp 11 8 TO Tost Ls 44 Mini Nimbus B Service Manual 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 The force or the weight should be P 7 0 to 8 5 kg er 15 7 to 18 7 Ib 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 Instruments Follow the instructions of the respective manufacturers 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 2050 Hamburg 80 Nicopress sleeves Tools TOST Flugzeugger tebau Thalkirchnerstr 62 D 8000 M nchen 2 Towing hook 45 Mini Nimbus B Service Manual 6 2 Annual Inspections Maintenance schedule See control system views on pages 59 60 61 Accessibilty of controls for inspection e Wing controls Aileron drive accessible through cut outs in the r
50. t is carried the normal towing speed should be increased by up to 15 TECHNICAL NOTE NO 328 7 November 1985 Mini Nimbus B FLIGHT MANUAL The undercarriage may be retracted during the aerotow this is not however recommended at low altitude as changing hands on the control stick could easily cause the sailplane to lose station behind the tug When releasing the rope pull the yellow cable release handle fully several times and confirm that you have released successfully before turning Winch launch Maximum permitted winch launch speed Vw 150 km h 81 kt 93 mph For winch launching only the C G hook must be used The flaps are set at 0 or at 8 if the all up weight is more than 400 kg 882 Ib Before taking off the trim should be set to neutral for forward to middle C G positions or to nose heavy for middle to aft C G posi tions AS the cable tightens apply the wheel brake gently to prevent the sailplane overrunning the cable Ground run and take off are normal there is no tendency to climb excessively steeply on leaving the ground At the moment of lift off depending on the C G the control stick should be held in a well forward position in the case of att C G positions or slightly pulled back in case of forward C G positions After climbing gently to a safety height of about 50 m 164 ft the transition to a typical winch launch climbing attitude i
51. t or sand a plug of toam Conticell 60 to fit the hole spread th inner side thinly with microballoons to close the pores and lay on it the inner laminate The inner laminate must harden betore doing further work If the hardening is complete or at least progressed so that the laminate does not separate from the toam 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 it necessary warm the foam with a hairdryer and bend Once the toam is glued it can be smoothed puttied with microballoons and the outer laminate applied Caution Avoid strong heat otherwise air bubbles form Outer laminate Puttied microb surface Inner laminate Replacement piece onticell 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 mlcroballoons the cloth adheres very well with pure or slightly TJ T 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 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 ugl
52. ted for zero stick force ght flight with flaps in position lap positi peed range he sai 23000 lplane has well balanced fl haracteristics and controls aps in position 0 and at a Of 1 4 Vstal the time taken to roll a 45 degr lane then is trimmed for all ions over the optimum except of high speeds ight speed from banked turn through an angle of 90 degrees is 3 seconds OG Mini Nimbus B FLIGHT MANUAL Flight performances W S 33 kg m2 6 76 lb 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 43 knots 50 mph Best gliding ratio 1 41 at 95 km h Max L D 51 knots flap position 0 59 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 four positions Landing one position High speed flight one position Airspeed Appl tion Flaps Ha km h knots mph Approach see page 37 Thermal flight 8 70 90 Best glide 80 120 Flight between 110 170 thermals High speed 160 250 With water ballast the speeds increase about 15 5 bus Mini Nimbus B FLIGHT MANUAL
53. with sufficient ease and smoothness clean and lubricate the corresponding hinges or bearings 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 3 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 If a loss of the braking effect of the landing wheel is observed clean the 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 Check the wheel axle and landing gear struts for deformation and the attachment fittings for damage Mini Nimbus B Service Manual Check the tire pressure of the main landing wheel 3 5 Atm or 50 psi e Inspect the static and dynamic pressure intakes the tubing and couplings for free air pass and tightness Check instruments for loose glasses Assemble the sailplane and check the control surface movements and all controls for easy a TI nd smooth op
54. y 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 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 3 8 to 1 2 inch smaller than that under it 1 layer 92110 4 layers 92140 x X ste 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 Detter make a large tent over the area from aluminum foil and heat the space from a safe distance There 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 appl
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