Janus A
Contents
1. Adjustment of the front seat rudder pedals The adjustment device is operated by a Bowdencable with a plastic T handle at the right hand side of the control stick Adjustment backward Pull the handle and move the pedals into the desired backward position o J ANUS FLIGHT MANUAL 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 handle slightly back to unlock the mechanism and push the pedals with the heels into the desired forward position and lock as before Canopy The isa 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 knob of the locking device on the canopy frame and lift the canopy with the free hand Take care that the cord which holds the opened canopy in place is attached The jettisoning device is mounted on the right hand side of the cockpit just under the canopy frame For jettisoning open the canopy as described before then PULL BACK the red knob at the risht hand side and push off the canopy Drag parachute The operating handle with a blue knob is installed at the risht hand side of the cockpit where the molded seat is attached to the fuselage shell It should be eee with the right hand To deploy the chute push the handle forward through the gide slot up to2. Adjustable stops on the sticks firm stops in the wing Locking device in the cockpit Firm stops at the operation handles in the cockpit and on the fuselage steel tube frame 18 JANUS FLIGHT MANUAL 5 Weight and 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 weisht 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 The following empty weicht C G range aft of datum must be observed Datum Wing leading edge at root rib Leveling means Slope of rear top surface of fuselage 100 to 4 5 w C G range u C G range kg mm lbs inches 470 490 602 830 19 0 23 52 375 484 598 840 18 8 23 38 380 478 594 850 18 0 23 24 385 472 591 860 18 4 23 11 390 467 587 870 18 2 22 98 395 461 583 880 18 0 22 85 400 456 580 890 17 3 22 73 405 448 576 900 16 6 22 51 410 440 573 910 15 8 22 49 415 432 569 920 15 1 22 37 420 425 566 930 14 4 22 26 425 418 563 940 13 7 22 15 C G range in flight gross weight C G 30 mm to 300 mm 1 18 in to 11 81 in aft of datum 19 JANUS FLIGHT MANUAL Checking of the empty weicht C G position To facilitate the checking of the empty weight C G position by weighing the glider at the tail
3. 1 2 inch smaller than that under it 1 layer 92110 S layers 92140 n nnii ae fuselage shell 3 1 3 u 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 strean Better 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 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 A
4. AEAT RE MIA L 9 i Oo 00 A oo A E Scarf Y A UOU FR 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 111 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 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 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 five8layers Therefore we need larger scarfs These should for larger holes or cuts never be less than 3 18 inches wide With all fuselage shell repairs apply resin first to a layer of 92110 cloth following with feurSlayers 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
5. 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 Application En mph one Approach anc a S 5 Thermal flight 80 loo 50 62 Turbulent O thermals So loo 50 62 43 54 Best glide 90 140 49 76 Flight between _40 E 65 86 en 120 160 75 99 65 86 High speed 150 220193 137 81 119 Due to excessive stressing the airspeed at the flap positions L and 10 down must not exceed Yu 170 km h 105 mph or 92 knots sJ s JANUS FLIGHT MANUAL Longitudinal trim The spring type trimming device green knob at the left hand side of the cockpit where the seat is supported is gradually variable With the C G in a medium position the glider can be trimmed for steady flight at speeds of 75 to 170 km h 46 to 105 mph 40 to 92 knots Circling flight The increase of stick forces when pulling back during circling is clearly noticeable Opposite aileron is necessary only in turns with greater bank due to the selected aileron differential The rudder is very effective and must be held almost in neutral position during the circling flight Full rudder and aileron is necessary to roll from a 45 banked turn through an angle of 90 degrees Time taken fo
6. c ease the control stick forward until rotation ceases and the glider becomes unstalled d take the rudder into neutral position and allow the glider to dive out The loss of heisht in one complete rotation of the spin is 80 to 100 meters After having initiated action for recovery from the spin the glider speeds up very fast 15 JANUS FLIGHT MANUAL therefore be cautious to bring the glider out of the dive promptly but gently Flying in rain or with iced up wings means a considerable loss of performance and aerodynamic qualities The minimum speed can increase about 15 km h 9 mph 8 knots Therefore be cautious when landing Come in at a speed of about 100 to 110 km h 62 to 68 mph 54 to 59 knots Emergency exit The roomy and well faired cockpits guarantee a quick and safe bailing out in emergency Jettisoning of the canopy 1 PULL BACK the red ball knob at the left hand side of the canopy frame 2 PULL BACK the red ball knob at the right hand side of the cockpit 4 Throw off the canopy The cord which holds the opened canopy in place is released when pulling back the Knob of the jettisoning device at the right hand side of the cockpit The canopy frame on the fuselage is built of strong fiber glass without sharp edges and is well suited as a are for the pilots to jump off HE JANUS FLIGHT MANUAL Cloud Flying The sailplane has sufficient strength and stability for cl
7. damaged area to determine exactly the type of construction and to find the appropriate repair method 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 different construction methods Repairs must for this reason be Penrormed 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 a 5 32 inch thick foamed polystyrene EEE 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 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 fiber
8. function of the control surfaces Do the controls reach the limit of their travel with sufficient ease and smoothness Do the air brakes operate properly Make sure to lock them after checking Is the drag chute handle locked at the rean stop of the guide slot 28 JANUS Service Manual 4 C Is the flap position n the O or 4 position Is the canopy properly closed and locked The red knobs at the left and risht hand side must be in the front position Is the pilot s parachute properly attached re the safety belts put on and secured ls the altimeter adjusted for the equivalent altitude or for NN Is the radio frequency adjusted for the airfield and or for the air traffic control After take off Check the trim 29 x JANUS Service Manual Maintenance Take good care of the surface finish Remove all contaminations such as dust grass seeds insects eto using warm water and a soft sponge Use mild soap if necessary Use no polish which might attack the paint It is recommended to polish the glider twice a year using a buff and buffing wax By this all contamination is removed and the surface becomes less sensitive to new dust Smooth all scratches carefully with resin filler Though the glider is not very affected protect it from moisture Never try to clean the plexiglass hood with a dry cloth Use special plexiglass polish after cleaning with warm water and a so
9. the center stop where the slot is branched off Moving the handle further forward up to the front stop of the slot means jettisoning the chute gt O J ANUS FLIGHT MANUAL Do not push the handle too far forward if the drag chute should be deployed unless it is desired to jettison the chute For normal landings the use of the drag parachute s not necessary since the air brakes are very effective Deploy the parachute only in emergency Pack the drag parachute very carefully following the enclosed Operation and Maintenance Instructions of drag parachutes siga JANUS FLIGHT MANUAL Calibration of the Airspeed indicator Dynamic Pressure intake Pitot tube in the nose of the fuselage Static pressure intake Airspeed indicator Cockpit frame about and Variometer 6 cm 2 3 8 in front of the front instr panel Altimeter Rear fuselage about 1 2 m 47 in front of the vertical tail plane Equivalent airspeed V EAS Indicated airspeed V IAS V EAS V IAS V EAS V IAS V EAS V IAS km h km h mph mph knots knots Air density p 0 125 kes m JANUS FLIGHT MANUAL Flight Performances two seat a SE W S 36 5 kp m 7 48 1b ft Stall speed 70 km h 44 mph 38 knots Minimum sink 0 7 m sec 2 3 ft sec at 90 km h 56 mph 49 knots Best gliding ratio 39 5 at 110 km h Max L D 68 mph 59 knots Wing flaps The flaps have the purpose to adapt the laminar
10. when putting the brake para chute into its box on the lower end of the rudder Do not put a wet parachute into the box If necessary dry it before See 2 5 The brake parachute ribbons and cords should not be entangled or twisted Stretch the chute and check its proper shape The two shroud lines adjacent to the name plate on the canopy base should run straight up to the attach ment loop without being entangled with the other shroud lines If necessary untangle the chute before putting it into the box Fold up the stretched parachute into the box in a S shape manner beginning at the top of the canopy See sketch 2 2 2 3 est 2 5 Maintenance Check the brake parachute always after having used it during flight or at lan ding Minor defects as small holes in the ribbons little wears soiling etc do not affect the serviceability of the chute If the brake parachute shows greater damages as tearing off of more than 10 of the ribbons spacers or shroud lines it must be taken out of service and be repaired before further use Brake parachutes not in use must be reviewed in intervals of about 60 days The brake parachutes must be inspected at the end of 12 months after the manufacturing inspection of the sailplane and during the annual inspections there after Storage Brake parachutes not in use should be stored in a dry and airy room at about 20 C 68 F and 65 rel humiditiy of the
11. when using a strong winch care should be taken to avoid an excessively sharp start due to the acceleration which presses the pilot back into the seat by which he unintentionally may pull the stick aft Airplane tow Maximum tow speed 170 km h 105 mph 92 knots Wing flaps should be in positions 0 u En JANUS FLIGHT MANUAL There is no tendency for the glider to ground loop With the C G in forward position the nose wheel is in ground contact The ground run should be started with stick fully pulled back Then ease the stick slowly forward until the nose wheel has ground clearance and the glider is running on the main wheel With the C G in normal positions take off should be made with stick in neutral position For pilots of light weight it is recommended to begin the ground run at the first launches with stick in forward position The glider pulls up very gently and does not show any tendency to oscillate The take off speed is about 70 to 90 km h 44 to 56 mph 48 to 48 knots Due to the T type tail plane avoid flying lower than the towing airplane because flying in its wake causes an unpleasant beating of the control stick as a result of wake turbulence Tow release Pull the release handle fully back The tow release is operated by a cable with a yellow plastic T handle in the front seat at the left hand side of the stick and in the back seat at the left hand side of the instrument panel
12. 20 75 65 Air brakes extended 220 137 119 Wing flaps Positions L or 10 N 170 105 92 Position 6 down 220 137 119 Positions O 4 7 up 220 137 119 Weights Empty weight appr 380 kg 838 lbs Maximum weicht Max weight of non load carrying structure 620 kg 1367 1bs including payload 400 kg 882 lbs Approved for cloud flying YES see comments on page 16 Category Glider Utility according to the German Glider Airworthiness Requirements LFS Weak links for towing max 600 kg Max 1520 lbs Frequency of flexural wing vibration appr 127 min JANUS FLIGHT MANUAL C G position in flight Datum Wing leading edge at root rib Leveling means Slope of rear top surface of fuselage 100 to 4 5 tail down C G range 30 mm to 400 mm aft of datum 1 18 in to 11 81 in at all weights Airspeed Indicator km h mph knots Maximum speed Vyg 220 137 119 Maneuvering speed Vy 170 105 92 1 1x stall speed 1 1 EN 75 46 40 Basic for the stall speed 1 1 VS is the following configuration a Wing flaps in position L b Air brakes retracted c Maximum weight 620 kg 1367 lbs Marking of the Airspeed Indicator km h mph knots Red Radial 220 197 119 Yellow Arc 170 220 105 137 92 119 Green Arc 75 170 46 105 40 92 White Arc 75 170 46 105 40 92 white arc marked with L and 10 at 170 km h 105 mph or 92 knots So J ANUS FLIGHT MANUAL Data and Reference placards Identificat
13. E iy o oO ee ee i 0 0 009 o Inner laminate 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 If there is a through hole in the sandwich shell then the inner laminate must be repaired We 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 1f 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 92110 X 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 at 68 deg F sand and apply the outer patches A tip on gluing the plywood plate the hoie 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 shell With additional nails or pin
14. Flight Janus VH GWO SCHEMPP HIRTH K G KIRCHHKIM TIiCH WEST GERMANY HG Z W AAA EA AAA W W N WN N m m Rra Flight and Service Manual for the Sailplane JANUS Translation of the German Manual Issue July 1975 This Manual should always be carried in the Sailplane It belongs to the tow place Sailplane JANUS Registration Marks VIA TOW 222 serial Number ee Giese WR Manufacturer ooooooooooo Owner Checker Sapa LBA approved November 10 1975 gt Le JANUS Flight and Service Manual EEE H G EEE 2 m u Page General O Table of contents l Amendments 2 FLIGHT MANUAL Operating data and limitations 3 5 Operating instructions 6 16 Minimum equipment 16 Wing and tail setting Table of Contents control surface movements 17 Weight and C G range 18 19 Cockpit load 20 Three sides view el Weight and balance 22 Service Manual Rigging 23 26 Check list 27 28 Maintenance 29 31 Backlash of attachments 32 33 Appendix Polar curves Repair instructions Operating and maintenance instructions for drag chutes H e JANUS FLIGHT MANUAL Amendments 3 _ JANUS FLIGHT MANUAL l Operating Data and Limitations za 3 1 2 222 ss m E AER ED zz 2 zu E Airspeed limits km h m p h knots Glide or dive 220 137 119 Max speed in rough air 220 137 119 Maneuvering speed 170 105 92 Airplane tow 170 105 92 Auto winch tow 1
15. air Protect them from vermins and do not store them together with food chemicals battery acids etc Do not expose them to strong insolation which has a detrimental effect on the ribbon fabric Drying Wet brake parachutes must be dried before further use Hang them up for airing and drying Avoid however temperatures exceeding 40 C 1040F and strong inso lation 2 6 Cleaning 2 7 Clean the brake parachute only if it is absolutely necessary Clean with lukewarm water adding little of a mild washing agent as used for Nylon fabrics Do not scrub rub and wring Greater damages see 2 1 must be repsired by the manufacturer Therefore send brake parachutes for repair only to the manufacturer of the chutes or to the manufacturer of the sailplane MED AU y EHER ne CU EHRE oe war A A e see eee a asm
16. ar The connection by the ball spring safety couplings requires some experience therefore it is advisable to get familiar with before rigging the wings Connect ailerons first and flaps thereafter taking care that the flap handle s locked in position L Each coupling should be checked after locking by pulling across with a force of about 5 kg 11 lbs in the direction of releasing Additionally make a visual inspection Horizontal Tail Plane See sketch on page 26 The horizontal tail plane should be mounted by one person only Put the plane from the front onto the fin so that the front bolt bearing fitting A is just dipping into the upper opening of the movable glass fiber fairing on the top of the fin Push the tail plane sliehtly down until its lower surface is fully sitting on the fairing Push the tail plane backwards until a clear audible CLICK indicates that the locking hooks B are engaged onto the axle C Move the locking handle D using a mounting pin of 8 mm dia in order to lock the hooks tishtly up to the rear stop Honfagestift Emm D entriegelt EIN l unlocked A Vorderer Beschlag Eront fitting 8 Vernegelungshaken Locking hook C Achse Axle D verriegelungshebel Locking handle E Einstellschraube Setting screw Hohenleitwerk Aufhangung und Antrieb JANUS Horizontal tail plane Attachment and control connection T JANUS Service Manual When taking off the horizontal tail
17. at 1300 mn 51 18 inches back seat 190 mm 7 48 inches ahead of datum negative moments MEASURING POINT REAR UPPER EDGE OF THE FIN _ e 1 ELEVATOR 40 4 UP 479 mm 185 9z In Down 724 2 mm 2 8379 in AILERONS WING FLAPS 10 A UP 80 7mm 3 15 85 in MAX UP 24t3mm 0 9479 in DOWN 4022 mm 1 57223 in Max DOWN 6227 mm 2 44293 19 UDDER 5 0 DOWN 62 N S MEASURING POINT 201m TO LEFT AND RIGHT 193m 29m N gt 255420 mm 10108 in ON THE ELEVATOR LOIN Be SSN en 300 mm 50 11 8 12 in LEVELING MEANS f SLOPE OF REAR TOP SURFACE OF FUSELAGE 100 TO 4 5 ne FUSELAGE CENTER LINE HORIZONTAL THREE SIDES VIEW CONTROL SURFACE MOVEMENTS JANUS we DD vie JANUS FLIGHT MANUAL Weight and Balance Datum Wing leading edge at root rib Leveling means Slope of rear top surface of fuselage 100 to 4 5 Akane Fu 26 i 27 Weight at landing wheel Wa Y Weight at tail skid LH areosi Empty weight W NA N oannes Distance a Jeo 164 mm Distance O a Aoise orra Wo Maximum cockpit load Gr Bt ee occ evens bl Lex CYC by 977 23 JANUS Service Manual Rigging The rigging of the JANUS can be done by three persons if a support for one wing is provided Generally four persons will do the rigging Wings Clean and lubricate the wing attachment bolts and their bearings on the fuselage Put the main bolt into the cockpit within reach Align th
18. ding 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 J 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 E b Destruction of the whole shell also the inner glass a be 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 fill the pores of the exposed foam Then lay three patches of the 92110 cloth with diagonal weave direction Bo largest patch first over the damaged area The applied cloth must be dry and dust free Outer laminate a 3 layers 92110 diagonal Fat Fe ae amp amp Po H x FR e a x u s 3 o o o o o 8 STA o O D o f O 6 4 P
19. e central fuselage push rods of ailerons wing flaps and air brakes Push the air brake operating handle up to its front stop Put the left wing fork spar root into the cut out of the fuselage until the wing attachment bolts are fully inserted into their bearings on the fuselage Insert the main bolt about 4 cm 1 5 inches into the spar bushing Push the 8 mm dia mounting pin through the bushing on the right hand Side of the fuselage and the corresponding bushing of the spar The wing now can be laid down on the Support The fuselage must not be held in place any longer Put in the right wing tongue spar root likewise into the fuselage wing attachment bolts however only partly inserted into their bearings and fork spar bolts not yet contacting their bearings in the root rib Lift the right wing until the fork spar bolts are aligned with their bearings in the root rib Then push the wing further into the fuselage by moving it slightly up and down and let the volts slide into the bearings Now take out the main bolt and pull the Wings fully together by the main bolt 2 4 JANUS Service Manual bushings using the flat end of the provided lever bar Push the main bolt fully through and secure its handle onto the fuselage shell by means of a safety cowling pin Remove the 8mm mounting pin and put into the cockpit pocket The connection of the push rods of the flaps ailerons and air brakes must be made behind the sp
20. ft clean chamois Check the safety belts frequently for cuts and stains the metal parts for rust The tow release hook mounted on the bottom of the fuselage just in front of the main 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 disconnect the release cable and unscrew the three attachment bolts When mounting the tow release hook again take care to attach it onto the bracket as shown on the sketch page 30 30 JANUS Betriebshandbuch Service Manual Befestigung der Schleppkupplung Attachment of the towing hook Kupplung mit den Bohrungen Nr 1 3 und 5 am Beschlag befestigen Towing hook attached to the bracket by the bolt holes Nos 1 3 and 5 ok ee JANUS Service Manual The landing wheel has a drum brake which is operated by a handle on the control sticks Its Bowden cable can be adjusted as usual by a setscrew on the wheel The inflation pressure of the main landing wheel should be 2 75 atm 39 psi that of the nose wheel should be for the fixed type 1 5 atm 21 psi and for the retrac table type 2 0 atm 28 psi To take off the landing wheel for inspection cleaning and lubrication disconnect the Bowden cable Remove the cotter pin and the castle nut on one side of the wheel axle and pull it out Take off the wheel by pulli
21. fter 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 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 Service and Maintenance Instructions for the Brake Parachutes on Sailplanes Model BS 1000 Model BS 1300 Model BS 1600 Date November 1968 Manufacturer Walter Kostelezki KG 7987 Weingarten Wuertt W Germany 1 2 1 Lacie Lees E e Operation Follow the instructions of the Flight Manual JANUS concerning the use of the brake parachute during flight approach and landing Following instructions should be observed
22. ion plate stainless steel Operation limits Airspeed limits Max mum weight Cockpit load front and back seat Weak link for towing Tire pressure of landing wheel and nose wheel Wing flap positions Symbols for operating handles or knobs Pedal adjustment front seat only Tow release Trimming control Drag parachute Deploy Jettison Canopy Opening Jettison Ventilation Air brakes Colour marking of handles or knobs Tow release Yellow handle Trimming control Green knob Air brakes Blue mark Drag chute Blue knob Canopy Opening and Jettison Red knobs JANUS FLIGHT MANUAL 2 Operating Instructions Winch launching Maximum tow speed 120 km h 75 mph 65 knots Wing flaps should be in positions O or 6 The sailplane has one tow release hookson the bottom of the fuselagell just in front of the main landing wheel li Nose Hoor Under normal conditions winch launchines are conducted without any difficulty There is no tendency to zround loop With two heavy pilots the glider tends to stand on the nose and main wheel Then the ground run should be started with stick fully pulled back until the nose wheel has ground clearance With the C G in normal positions the take off run should be made with stick in neutral position When the glider is flown by very light pilots it is recommended to make the first launches with stick in forward position Instructions for the winch driver Especially
23. light path of 45 degrees the air speed is set at Vyg 220 km h 137 mph 119 knots air brakes extended and wing flaps in the position 60 Approach and Landing The approach is normally conducted at a speed of about 90 to 100 km h 56 to 62 mph 48 to 54 knots dependent on the wing loading The air brakes are extended smoothly and are very effective Sideslip is easily controlable and can be used as landing aid also with air brakes extended VE JANUS FLIGHT MANUAL The sideslip should be initiated or recovered with air brakes retracted to avoid the influence of turbulence on the horizontal tail surface The glider touches down on the landing wheel and tail skid simultaneously The wheel brake drum brake works well It is operated by a handle on the sticks To avoid a long landing run it is advisable to touch down at a minimum speed of 70 to 80 km h 4 to 50 mph 38 to 43 knots dependent on the wing loading Landing with a speed of 95 km h 59 mph 51 knots instead means doubling the time to slow down the energy and considerably increases the running distance Emergencies The sailplane can be held in a stalling position with fully pulled stick and necessary rudder control Applying full rudder in a stall brings the glider into a spin safe recovery from the spin is effected by the STANDARD METHOD which is defined as a apply opposite rudder i e against the direction of the spin b pause
24. ng it slightly back and down in order to disengage the drum locking fitting from its guide pin on the fuselage steel tube frame Take care that no washers spacers and bushings get lost Clean all parts and lubricate the bearings bushings and the axle Lubricate the bearings when a complete overhaul is carried out except for the bolts and bearings of the wing attachments which must be cleaned anda lubricated before every rigging If there is any larger repair work to be done ask the manufacturer or his representative for advice If a new painting should be made take care that the surfaces exposed to sunlight are painted white 32 JANUS Service Manual Backlash of the attachments All attachments of a glider are wearing more or less with time In the following the permitted tolerances and the provisions of repair are stated Wing 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 50 mm 1 31 32 additional washers of an inner diameter of 17 95 mm and about 0 3 up to 0 5 mm thick should be pressed onto the bolts until the backlash is eliminated Ailerons and wing flaps A backlash of up to 5 mm 3 16 measured at the trailing edge of the inner aileron and flap roots is allowable as tested in flight If the tolerances are exceeded ask the manufacturer for instructions Ho
25. oud flying Nevertheless observe the following instructions a b c a b Do avoid extreme airspeeds in any case Make t a rule to extend the air brakes already at speeds about 150 km h 93 mph 8l knots Cloud flying is permitted only when the following approved instruments are installed 1 Airspeed Indicator 2 Altimeter 4 Turn and Bank 4 Variometer 5 Magnetic Compass The installation of an artificial horizon a clock an accelerometer and a radio is recommended Take care to follow the official regulations about cloud flying Minimum Equipment Z Z S Z 2 a Airspeed Indicator 250 km h 160 mph Altimeter 140 knots Four piece safety belt Back cushion or parachute Operating Instructions Flight and Service Manual Placards indicating operation limits JANUS 17 FLIGHT MANUAL 4 Wing and tail setting Control surface movements Angle of wing setting 2 6 Reference Fuselage center line Angle of tail setting 250 Reference Wing chord at root rib For control surface movements see page el Pay attention to the tolerances if repair work is necessary The travel of controls is limited by stops Rudder Elevator Ailerons _ Wing flaps Air brakes Adjustable stops on the back side of the fuselage steel tube frame Firm stops at the lower rudder hinge Adjustable stops on the sticks and their attachment bulkheads setscrews
26. plane it is advisable to do it from the rear Unlock the hooks B by pushing the locking handle D forward using the 8 mm dia pin Push the plane simultaneously forward about some mm one inch whilst knocking against the trailing edge until the bolt is disengaged from the bearing fitting A Take off the plane After rigging Check the function of the controls Seal the joints of the wing and fuselage with an adhesive tape Seal also the access hole for the locking handle of the horizontal tail plane The sealing is very important to ensure good flight qualities T s JANUS Service Manual Check List GT 2 zz u m A After rigging l Ce 3 4 B La De Is the handle of the main bolt secured to the fuselage by the safety cowling pin Are the push rods of the ailerons flaps and air brakes safely connected by their ball spring couplings and checked Are the joints of the wing and fuselage and the hole for the locking handle of the horizontal tail plane sealed Does the tow release mechanism function properly Does the wheel brake function properly Is the tire pressure of the main landing wheel and nose wheel checked Main landing wheel 2 75 atm 39 psi fixed 1 5 atm 21 psi Nose wheel retractable 2 0 atm 28 psi Is the horizontal tail plane safely attached i e are the locking hooks tightly snapped onto the axle up to the rear stop Before Take off Check the
27. r this motion with flaps in position 69 is 5 seconds at a speed of 100 km h 62 mph 54 knots Stalling characteristic Stalls from straight flight Depending on the wing loading and wing flap position stall warning occurs at speeds of 65 to 85 km h 40 to 53 mph 35 to 46 knots by a slight oscillation of the horizontal tail plane and the ailerons become sloppy By pulling the stick gently back the glider stalls When pulling the stick sharply back or under gusts the glider pitches down or depending on the position of control surfaces a wing may drop Speed is increasing very fast 2 13 JANUS FLIGHT MANUAL Stalls from turning flight Pulling the stick slowly back in a turning flight requires increasing opposite aileron and rudder control i e against the direction of the turn In the fully stalled condition the glider pitches down by the lower wing It recovers promptly from this attitude by easing the control stick forward Normal unstalled flight is restored by opposite rudder and aileron Behaviour at high speeds Neglecting the influence of the high flight loads the controls are easy to be handled at high speeds Excessive control movements however should be avoided When flying at high speeds in gusty air care is to be taken that the safety belts are firmly attached due to the high acceleration which acts upon the pilot Hold the control stick well fixed In a flight with an inclination of the f
28. rizontal tail plane see sketch on page 26 If tangential backlash should be observed i e if the tail plane can be moved at the tips excessively back and forth the setting screws E must be adjusted Take off the tail plane Screw out the setting screws little by little until the tail plane cannot be locked any longer Then the setting screws are to be screwed in about a quarter turn Tighten the lock nut using a 5 5 mm socket wrench When mounting the plane thereafter the locking hooks B should snap tightly onto the axle C 33 m JANUS Service Manual It may be possible that the adjustment of one setting screw must be different from the other This is the case if there is still a backlash existing though the locking mechanism has a very tight fit The setting screws then must be adjusted gradually until both locking hooks are catching the axle with the same tight fit Rudder Due to the continuous control cables no backlash of the rudder control occurs 4 94 23 ANOrs KAN gt 53759 Kors i rys LUNVERDIONS ur nn rn SELECTA As 2104297 m Uy O b R e su f K x HAHH ERRI EN en TI TE IT RE 2 se U LA eo E ES i E E a ret HEHE ENTE x E DT ee in PH HEHE i EE HERE rg are Hinnan an Ei succes j iHi AH ee LH Tiest see a
29. s 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 1b sq ft Elevator amp rudder Fuselage ailerons Crosstwill stabilizer Wings fuselage Fuselage 181 150 directional Wings Eu Rovings er Textilglas GmbH GEVETEX Type ES 10 40 x60 K 43 GEVETEX Foams PVC Rigid Foam Conticell 60 Continental AG 5 16 in thick 3 7 1b cu ft Styropor THERMOPETE Super PORON 5 32 in thick 1 1b 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 3 6910 resin paint PE Hardener No 7 2050 or 7 2051 100 to 1 5 Mixing proportions by weight 100 parts Lackvorgelat to 10 parts hardener PE Thinner No 6 3026 PE Filler white No 62 507 2 6115 PE Hardener No 7 2050 or 7 2051 100 to 1 5 Mixing proportions by weight 100 parts filler to 10 parts hardener Resin paint Lackvorgelat and filler can be mixed in one to one or other proportions 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 san
30. s it is in this manner possible to close very large holes to the proper contour to lay the cloth patch on Outer laminate Microb with ye Styropor kernels psn Scarf UT UT om y X Ea er s 2a o O DOS oO 8 A a fo A I E CN aL Ore Lora a ae E 2 8 2 S A A BER c INES g O E gt 6 G C o A oo re a on 0 e Sr Se T oe ae Inner laminate Thin plywood backing 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 Styropor 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 warm 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 Putti Scarf y ttied microb surface SIERT O 0 O DR AS Be O RE ST ng gt so FDEN
31. skid with fuselage in horizontal position i e main landing wheel on the ground and tail skid jacked up about 42 cm 16 5 in from the ground the following table shows the permitted maximum weicht at the tail skid for different empty weights incl equipment If these tail weichts calculated for the corresponding limits of the extended aft empty weisht C G are not exceeded it is certain that the empty weight C G position is within the limits We Empty weight incl equipment CG a Extended aft empty weight C G calculated for a min front cockpit load of 70 kg 154 3 lbs 563 W t Permitted maximum weight at tail skid We CG a W t We CG a W t kg mm kg lbs inches lbs 370 602 50 6 830 23 52 68 0 375 598 30 7 840 23 38 68 2 380 gt 94 2050 850 25 24 68 5 385 991 91 0 860 25 11 68 8 390 587 ll 870 22 98 69 0 395 583 S 880 22 89 69 3 400 580 31 4 890 22 73 69 5 405 576 91 5 900 2 61 69 8 410 573 31 6 910 22 49 70 0 415 569 31 7 920 22 37 70 3 420 566 21 9 930 22 26 70 5 425 32 0 940 22 15 70 8 20 JANUS FLIGHT MANUAL 6 Cockpit load Pilots incl parachutes ae z Be load Less weight than 70 kg 154 lbs in the front seat must be compensated with ballast The ballast lead or sand cushion is to be safely attached e g onto the suspension of the seat belt The maximum weight of 620 kg 1367 lbs must not be exceeded C G arm of the pilots incl parachute or q back cushion front se
32. ssess Sa H HT dal saransh lsenagbf esgesse FE StH HEHE EB raat ER I RTT Ben HD T eh HEHE se R E SAS EHE I T T a up P R Eh so EHE EHEN 1 E EET H ik T nn n o a pipe o E ed Alo GL H HEHE ERBEN AE A ae S E HHH jin Hilde I nlik A BEH H Rania T Ha i a A a HEHE Sn Hitt PU a oe ae BI HG Es m H S ERIA gr je S R oo a BEI E az ERE bet 4 T ast Hi URETA ER E ELAS VE Ud MADE RJ GERMAN Y Repair Instructions for the JANUS The construction methods on the JANUS are almost the same as used on the OPEN CIRRUS Therefore repairs can be performed in the same way as described in the enclosed instructions for the CIRRUS In the JANUS we find the following construction methods Wing and Horizontal Tail Plane Glass fiber plastic foam sandwich i e foam CONTICELL 60 8 mm thick bonded on both sides with glass cloth Wing Flaps and Ailerons Glass fiber plastic foam sandwich i e foam CONTICELL 60 6 mm thick bonded on both sides with glass cloth Rudder Glass fiber plastic foam sandwich i e foam CONTICELL 60 4 mm thick bonded on both sides with glass cloth Vertical Tail Plane Fin Glass fiber plastic foam sandwich i e foam CONTICELL 60 in the front of the spar 6 mm thick in the rear of the spar 4 mm thick Fuselage Pure glass fiber plastic layup If a fracture or damage occurs to the glider you should first inspect the
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