HPH Glasflugel 304S Manual Download | Manualshive

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Document No.: 304S/MM

Date of Issue:

08/14

1-9

H

P

H

Ltd.

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Summary of Contents for Glasflugel 304S

Page 1: ...EP PA AI IR R M MA AN NU UA AL L F FO OR R T TH HE E S SA AI IL LP PL LA AN NE E Č Čá ás sl la av vs sk ká á 2 23 34 4 2 28 84 4 0 01 1 K Ku ut tn ná á H Ho or ra a C CZ ZE EC CH H R RE EP PU UB BL LI IC C t te el l 4 42 20 0 3 32 27 7 5 51 12 26 63 33 3 f fa ax x 4 42 20 0 3 32 27 7 5 51 13 34 44 41 1 i in nf fo o h hp ph h c cz z HPHLtd ...

Page 2: ...PL LA AN NE E M Mo od de el l Glasflügel 304 S S Se er ri ia al l N No o R Re eg gi is st tr ra at ti io on n Document No 304S MM Date of Issue 08 14 Č Čá ás sl la av vs sk ká á 2 23 34 4 2 28 84 4 0 01 1 K Ku ut tn ná á H Ho or ra a C CZ ZE EC CH H R RE EP PU UB BL LI IC C t te el l 4 42 20 0 3 32 27 7 5 51 12 26 63 33 3 f fa ax x 4 42 20 0 3 32 27 7 5 51 13 34 44 41 1 i in nf fo o h hp ph h c cz...

Page 3: ... Ground Handling 2 1 2 2 RIGGING 2 2 2 3 DE RIGGING 2 3 3 MAINTENANCE 3 0 3 1 MANDATORY MAINTENANCE 3 1 3 2 REGULAR MAINTENANCE 3 2 3 3 SPECIAL INSPECTION PROCEDURE 3 4 3 3 1 After hard landing and ground loops 3 4 3 4 FREE PLAY IN THE CONTROL CIRCUITS 3 5 3 5 FREE PLAY IN WING AND TAIL PLANE ATTACHMENTS 3 6 3 6 PRIMARY AND SECONDARY STRUCTURES 3 6 3 7 DAMAGE 3 6 3 8 REPAIRS 3 7 3 9 REMOVAL AND RE...

Page 4: ...NÍ DEFINOVÁNA 4 6 OBLIGATORY INSPECTIONS 4 2 4 7 LIFE LIMITED COMPONENT SECTION 4 2 5 CENTER OF GRAVITY 5 0 5 1 CENTER OF GRAVITY POSITION 5 1 5 2 PAYLOAD RANGE 5 3 6 INSTRUCTIONS FOR REPAIRS 6 0 6 1 CHECKLIST 6 1 6 1 1 General 6 1 6 1 2 WING 6 1 6 1 3 FUSELAGE 6 2 6 2 STRUCTURE OF COMPONENTS 6 3 6 3 MATERIALS 6 4 6 4 TYPE OF WAVES 6 5 6 5 BASIC TECHNIQUES AND TOOLS 6 6 6 5 1 Fiberglass Hard foam ...

Page 5: ...08 14 ii 08 14 iii 08 14 iv 08 14 v 08 14 5 5 0 08 14 5 1 08 14 1 1 0 08 14 5 2 08 14 1 1 08 14 5 3 08 14 1 2 08 14 1 3 08 14 1 4 08 14 1 5 08 14 6 6 0 08 14 1 6 08 14 6 1 08 14 1 7 08 14 6 2 08 14 1 8 08 14 6 3 08 14 6 4 08 14 2 2 0 08 14 6 5 08 14 2 1 08 14 6 6 08 14 2 2 08 14 6 7 08 14 2 3 08 14 6 8 08 14 6 9 08 14 3 3 0 08 14 6 10 08 14 3 1 08 14 6 11 08 14 3 2 08 14 6 12 08 14 3 3 08 14 6 13 ...

Page 6: ... Any revision of this Manual must be recorded in the following table and in case of approved Sections endorsed by the responsible airworthiness authority The new or amended text in the revised page will be indicated by a black vertical line in the left hand margin and the Revision No and the date will be shown on the bottom left hand of the page Rev No Affected Section Affected Page Date of Issue ...

Page 7: ...ri ip pt ti io on n O Op pe er ra at ti in ng g M Ma ai in nt te en na an nc ce e a an nd d R Re ep pa ai ir r M Ma an nu ua al l Document No 304S MM Date of Issue 08 14 1 0 H P H Ltd 1 1 B BA AS SI IC C T TE EC CH HN NI IC CA AL L D DA AT TA A ...

Page 8: ...P H Ltd 1 1 Basic Technical data Wing Span 18 m 59 06 ft Wing area 11 8m2 127 01 ft2 Aspect ratio 27 43 Fuselage Length 6 79 m 22 28 ft Width 0 62 m 2 03 ft Height 1 48 m 4 86 ft Cockpit height 0 83 m 2 72 ft Horizontal Tail Unit Span 2 5 m 6 89 ft Area 0 99 m2 10 66 ft2 Aspect ratio 6 33 Vertical Tail Unit Height 1 25 m 3 77 ft Area 1 05 m2 9 58 ft2 Aspect ratio 1 52 Landing gear Main wheel 5 00x...

Page 9: ...on fibers and shear webs of reinforced GFRP Foam Sandwich Airbrakes are of the Schempp Hirth type Two integral water ballast tanks carry a total volume of 194 liters aprox 42 UKgal 51 USgal 1 2 3 Horizontal Tail Unit The horizontal tailplane has a stabilizer and elevators Trimming is by means of a spring on the control drive The stabilizer is of GFRP Foam Sandwich construction 1 2 4 Vertical Tail ...

Page 10: ...t ti in ng g M Ma ai in nt te en na an nc ce e a an nd d R Re ep pa ai ir r M Ma an nu ua al l Document No 304S MM Date of Issue 08 14 1 3 H P H Ltd 1 3 Sailplane systems 1 3 1 Control systems in the fuselage Elevator ailerons and air brakes control systems in the fuselage FIG 1 ...

Page 11: ...n n O Op pe er ra at ti in ng g M Ma ai in nt te en na an nc ce e a an nd d R Re ep pa ai ir r M Ma an nu ua al l Document No 304S MM Date of Issue 08 14 1 4 H P H Ltd 1 3 2 Control systems in the wing Ailerons and air brakes control systems in the wing FIG 2 ...

Page 12: ... De es sc cr ri ip pt ti io on n O Op pe er ra at ti in ng g M Ma ai in nt te en na an nc ce e a an nd d R Re ep pa ai ir r M Ma an nu ua al l Document No 304S MM Date of Issue 08 14 1 5 H P H Ltd 1 3 3 Rudder control system FIG 3 ...

Page 13: ...De es sc cr ri ip pt ti io on n O Op pe er ra at ti in ng g M Ma ai in nt te en na an nc ce e a an nd d R Re ep pa ai ir r M Ma an nu ua al l Document No 304S MM Date of Issue 08 14 1 6 H P H Ltd 1 3 4 Main landing gear system FIG 4 ...

Page 14: ...cr ri ip pt ti io on n O Op pe er ra at ti in ng g M Ma ai in nt te en na an nc ce e a an nd d R Re ep pa ai ir r M Ma an nu ua al l Document No 304S MM Date of Issue 08 14 1 7 H P H Ltd 1 3 5 Control surface deflections and dimensions FIG 5 ...

Page 15: ...strument panel It is classical Pb battery 12V 22Ah The battery containment is covered with a lid and is accessible after pressing and turning the metal knob This battery supplies all board instruments Recharging of batteries must be performed outside the glider Adequate recharging equipment according battery type should be used to ensure proper function and maximal life time of batteries MAKE SURE...

Page 16: ...n ni ic ca al l D De es sc cr ri ip pt ti io on n O Op pe er ra at ti in ng g M Ma ai in nt te en na an nc ce e a an nd d R Re ep pa ai ir r M Ma an nu ua al l Document No 304S MM Date of Issue 08 14 1 9 H P H Ltd ...

Page 17: ... io on n O Op pe er ra at ti in ng g M Ma ai in nt te en na an nc ce e a an nd d R Re ep pa ai ir r M Ma an nu ua al l Document No 304S MM Date of Issue 08 14 2 0 H P H Ltd 2 2 H HA AN NG GA AR RI IN NG G T TR RA AN NS SP PO OR RT T R RI IG GG GI IN NG G ...

Page 18: ...sling Fuselage is correctly stored in a wide fuselage molding in front of the C G release and supported by the tail wheel The Tailplane is stored in two profile true slings separated 1 5 2m 5 6 6 ft and with the L E pointing downward Under no circumstances attach the tailplane into the trailer by using the tailplane main attachment fittings Sailplanes which stay rigged for the whole year or longer...

Page 19: ...al position and are actually engaging into the opposing socket fittings on the fuselage 4 Rig Starboard wing with the same lever settings as Port wing and pull together with rigging tool Ensure correct engagement of control as with Port wing 5 Momentarily remove main wing spar pin Level main pin bushes by moving wintips up and down When bushes line up push pin in and lock 6 Rig both wing extension...

Page 20: ...f Issue 08 14 2 3 H P H Ltd 2 3 De rigging 1 Pull front tailplane connection pin out with the help of the tool and lift up tailplane 2 Unlock and remove connecting pins of the wingextensions and apply the hand force to take the wingextension out of the wingtip 3 Lift wingtips and remove main pin 4 With the help of the rigging tool or by pulling on the wingtips separate the wings from the fuselage ...

Page 21: ...e es sc cr ri ip pt ti io on n O Op pe er ra at ti in ng g M Ma ai in nt te en na an nc ce e a an nd d R Re ep pa ai ir r M Ma an nu ua al l Document No 304S MM Date of Issue 08 14 3 0 H P H Ltd 3 3 M MA AI IN NT TE EN NA AN NC CE E ...

Page 22: ...unction with Nicopress clamps No 28 3 M and tool 51 M 850 or 63 V XPM or 64 CGMP whereby always the M groove should be used Only the correct tool must be used in conjunction with these clamps The works and inspection instructions corresponding to the tool should be adhered to After every 200 operating hours and during every yearly inspection the metal lip at the flap operating lever must be checke...

Page 23: ...ers of the sandwich are damaged the inner layers should also be checked Seek the help of an experienced person Check all metal parts for corrosion and if necessary clean up and preserve again steel fittings pushrods and levers should be primed with Zincromite and conserved with Nitro lacquer If control runs with excessive friction the bearings and joints should be cleaned and lubricated Lubricate ...

Page 24: ...nt and that the fiberglass bearings on the wheel box are not damaged Check pressure of main and tail wheel Main wheel Takeoff weight lbs 837 992 1102 Tire size kg 380 450 500 p bar 3 5 4 0 5 0 5 00 5 psi 51 58 72 Tail wheel p 2 5 bar 36 p s i Check static and pitot inlets lines as well as line quick connectors for free flow and leak Ensure there are no loose instrument face glasses On the rigged a...

Page 25: ...ead 03 check upper and lower part trailing fork of landing gear check folding struts and dumper rings 04 check fuselage to wing joint shear pins carry through tubes and their integration into the fuselage shell 05 check bulkhead below rear carry through tube 06 check upper and lower wing shells for wrinkles and cracks 07 check spar tunnel floor below spar in the fuselage between forward and rear m...

Page 26: ...cuits With fixed controls the following free play on the control surfaces must not be exceeded Aileron 2 5 mm measured 102 mm behind control hinge line Flaps 3 mm measured 122 mm behind control hinge line Airbrakes 2 mm measured 190mm above upper surface with full employed airbrakes Elevator 1 8 mm measured 138 mm behind control hinge line The rudder control circuit is an open circuit operated dir...

Page 27: ...ns of the fuselage the empennage and control surfaces crew seat Damage that compromises the structural integrity of any of these can result in loss of control of the aircraft with no ability to make a safe landing or very severe hazards to pilot Another term for them is Critical Load Bearing Structures Secondary structures would be those components that do not bear flight loads and are not directl...

Page 28: ...rrying fiber reinforced parts primary structures e g a hole in the wing shell belong to this class Major repairs are allowed to be carried out only in aircraft repair services which dispose of appropriate equipment qualified and skilled staff and finally hold the necessary approvals to carry out such repairs The sailplane manufacturer can provide to the repair services technical data spare parts a...

Page 29: ...e whereby attention should be paid that the correct bolts and pins are used and that the earth cable is attached To dismantle the aerotow release the rudder foot control is removed by removing the bolt at the rear end of the lower guide tube and pulling back the foot control Thereafter the bolts of the diaphragm are removed The diaphragm which is sealed off with a sealant is then carefully pulled ...

Page 30: ... 0 66 kgcm Flap m 3 8 4 88 kg M 1 2 1 8 kgcm Should these values be exceeded mass ballast is to be attached to the control surfaces in front of the hinge line This ballast should be distributed evenly over the whole length in the case of the elevator and only in areas where ballast is attached already as in the case of the aileron and rudder After installing additional lead strips check that the c...

Page 31: ...1 Placards and markings in the Cockpit See also the Sailplane Flight Manual Section 2 and 7 Type Glasflügel 304 S Serial No 003 S Production year 2007 Producer KUTNÁHOR A CZECH R EPU BLIC EXPERIMENT AL Ltd VENTILATION BACKREST ADJUSTMENT MAX 10 kg INCL INSTAL LED EQUIPMEN T MAX LUGGAGE COMPARTEMENT CANOPY LOCK CANOPY JETT ISON AIRBRAKES WATER BALLAST UNDERCARIAGE WHEEL BRA KE TOW RELEASE RUDDER PE...

Page 32: ...ap additives in water should not be used too often Polish as often as you wish but take care not to heat up the surface when using a polishing machine as otherwise the surface quality will suffer Exposure to moisture should be avoided as with all other sailplanes Protect from intensive sun radiation heat and unnecessary permanent load Please note that the surface of all parts which are exposed to ...

Page 33: ...cted by felt seals and these also are maintenance free over a long period The linear ball race guides of the control rods must not be greased The accessible parts of the control rods moving in the ball race guides must kept clean The canopy locks must be kept well greased Clean and maintain dirty tow release coupling according to manufacturer instructions Before rigging all shear pins and bushings...

Page 34: ...imum permissible torques for bolts M5 Nm 6 4 M6 Nm 11 M8 Nm 27 M10 Nm 53 M12 NM 92 3 15 Safety Harness For the Glasflügel 304 S a 4 point safety harness is required The following types are approved LAP STRAPS GADRINGER Bagu 5202 or latter approved versions Attachment points On GRP loops through seat tray SHOULDER STRAPS GADRINGER Schugu 2700 or latter approved versions Attachment points On forward...

Page 35: ...d with the following pressure ports as standard Pitot tube in the fuselage nose and on the top of the fin Source of the pitot pressure can be selected by the pilot Static ports in fuselage tail boom both sides aft engine doors Air Speed Indicator and altimeter have to be connected to the ports mentioned above TEC probe mounting at the top of the fin This mounting can also be used to fit a multi pr...

Page 36: ...ar or Mercury scales can be used providing the instrument will measure altitudes up to at least 20000 feet Suitable altimeters Winter 4 FGH 10 Winter 4 FGH 20 Winter 4 HM 6 PZL W 10 SC PZL W 10 SA PZL W 12 SA and their latter approved versions 3 17 3 Variometers Any approved variometer for use in aircraft with a range of at least 5m s 1000 ft min can be installed provided it is approved also for c...

Page 37: ...ed Suitable transceivers Dittel ATR 720 FSG 40 S FSG 50 S FSG 60 S Becker AR 2008 25 AR 3201 AR 4201 Microair Electronics Pty Ltd and their latter approved versions Radio transceiver antenna is mounted inside the top part of vertical fin 3 17 7 Transponders Any approved electric transponder 12V powered for use in aircraft can be used Suitable mode S transponders Becker 6401 Garrecht VT01 Funkwerk ...

Page 38: ... a Operating Instructions for the Tost release E22 latest approved version b Operating Instructions for the Tost release G88 latest approved version c Beringer MOUNTING MAINTENANCE MANUAL 5 and 6 light WHEELS and BRAKES latest approved version d Gadringer Component Maintenance Manual with Instruction Manual No BAGU 5 latest approved version e Operating and maintenance instructions for instruments ...

Page 39: ...ti io on n O Op pe er ra at ti in ng g M Ma ai in nt te en na an nc ce e a an nd d R Re ep pa ai ir r M Ma an nu ua al l Document No 304S MM Date of Issue 08 14 4 0 H P H Ltd 4 4 A AI IR RW WO OR RT TH HI IN NE ES SS S L LI IM MI IT TA AT TI IO ON NS S ...

Page 40: ... additional inspection will be repeated if the sailplane reach 4000 flight hours In the case of positive test result respectively after repair of observed insufficiencies than the service life could be increased for total of 5000 flight hours 2 step After reach of 5000 flight hours the additional test inspection should be carried out If the test result is steady positive respectively after repair ...

Page 41: ...f the corresponding manufacturer see 3 19 Instructions are delivered with each new glider or component If the component is installed in another aircraft or if it is installed from another aircraft then the number of takeoffs and the months of operating life already expired must be recorded by a qualified inspector in the log of the aircraft which is the object of installation Refer to 3 9 for inst...

Page 42: ... cr ri ip pt ti io on n O Op pe er ra at ti in ng g M Ma ai in nt te en na an nc ce e a an nd d R Re ep pa ai ir r M Ma an nu ua al l Document No 304S MM Date of Issue 08 14 5 0 H P H Ltd 5 5 C CE EN NT TE ER R O OF F G GR RA AV VI IT TY Y ...

Page 43: ... The empty weight of the sailplane is established through weighing m1 the main wheel weight During weighing of m1 must be the rear fuselage cone angled down towards the rear wedge pattern 100 8 77 measured between the horizontal plane and fuselage rear upper surface with the wing leveled Sailplane empty weight mempty m1empty m2empty Empty sailplane C G X empty m2 empty x b m empty a The aircraft i...

Page 44: ...ws to pilot maintain the flight cg position at optimum range Adding this ballast limits the minimum pilot s weight Minimum pilot s weights relevant to the added permanent water ballast should be approved and recorded into the operating documents see Flight Manual ch 6 3 on the base of the minimum pilot weight without ballast 1 kg 2 2 lbs of the water ballast increases the minimum pilot weight for ...

Page 45: ... ep pa ai ir r M Ma an nu ua al l Document No 304S MM Date of Issue 08 14 5 3 H P H Ltd 5 2 Payload Range 4 00 4 50 5 00 5 50 6 00 6 50 7 00 25 0 2 70 29 0 3 10 33 0 3 50 37 0 E M P T Y C G P O S I T I O N m m SA IL P L A N EE M P T YW E IGH T T R IMPLA N G 304S N O R M A L m ax 12 5k g m in 7 0kg m in 75kg m in 8 0kg m in 85k g m in 90kg ...

Page 46: ...pt ti io on n O Op pe er ra at ti in ng g M Ma ai in nt te en na an nc ce e a an nd d R Re ep pa ai ir r M Ma an nu ua al l Document No 304S MM Date of Issue 08 14 6 0 H P H Ltd 6 6 I IN NS ST TR RU UC CT TI IO ON NS S F FO OR R R RE EP PA AI IR RS S ...

Page 47: ...latest inspection report For annual inspections the datum points and other requirements are obtained from chapter 3 Maintenance 6 1 2 WING FIG 11 1 Aileron Full travel Rips nicks dents or cracks in surface Play in hinges Close well 2 Flaps 3 Dive Brakes 4 Main wing connection Check for hairline cracks at spar root root ribs Check condition of pins ball bearings their housings and the main wing pin...

Page 48: ...tion Check for white or cracked areas around fittings excessive play 3 Horizontal stabilizer Check for excessive play white spots near hinges 4 Elevator 5 Tailboom Vertical Stabilizer Junction Torsion test Hold fuselage near front and push sidewise on fin Twists easier than usual 6 Fuselage Skin Check these places especially Check in and outside for dents rips white areas or cracks in green fiberg...

Page 49: ...ion from external to internal layers is valid for the layers order Let the repaired area to cure for at least 24 hours and to temper within 50 55 C for at least 15 hours Wing 1x 90070 1x ECC 763 1x ECC 763 Divinycell H60 8mm 1x ECC 469 Ł 1x 92 110 Ł Fuselage cockpit area Fuselage aft cone 1x92110 1x92110 1x92110 1x ECC 450 Ł 1x ECC 601 Ł 1x ECC 450 1x ECC 450 1x ECC 450 Ł 1x ECC 601 Ł 1x ECC 450 1...

Page 50: ...2 110 Interglas Finish I 550 or FK 144 92 125 Interglas 92 140 Interglas 92 145 Interglas 90 070 Interglas Carbon cloth 98140 Interglas Style 450 ECC Style 763 ECC Style 469 ECC Carbon aramid cloth 98355 Interglas Style 601 ECC Glass Roving EC 09 756 k43 Gevetex P185 OCV Carbon Roving HTA 5131 800tex 12000f Tenax T700S 800tex 12000f Toray Cotton flocks Type FL 1 f Schwarzw Textilw Gel coat T 30 wh...

Page 51: ...r direction Such cloth is used in the outer wing skin INTERGLAS 92 145 ECC Style 763 FIG 33 Twill weave This weave commonly has equal fiber content in warp and weft but its special weave over one under two makes it conform well to rounded places and compound curves INTERGLAS 92 110 92 125 92 140 98355 ECC STYLE 601 FIG 34 Plain weave Over one under one Warp and weft have about the same number of f...

Page 52: ...ools jigs or moulds you are not able to restore their exact shape or position 4 If it is unavoidable to remove undamaged laminated areas in order to carry out a repair 5 If you can t guarantee that your repair will be technically perfect and airworthy 6 If it s less expensive to purchase a replacement part 7 If areas with load carrying reinforcements are damaged as in most cases the number of glas...

Page 53: ...of the glass cloth is visible about 6 mm 1 4 in around the rim of the hole FIG 39 FIG 40 Fill the hole in the foam with epoxy putty which is made from normal epoxy mixed with microballoons FIG 41 Grind off the excess resin flush with the sound foam Remove part of the outer skin so that the glass is exposed for about 25 mm around the rim The exposed glass should be ground tapered so that it goes s ...

Page 54: ...10 The 92145 weave can t be blended too well Thoroughly wet the patches and the area with freshly mixed epoxy and lay them in place Saturate all with epoxy FIG 43 Cover the area with a film of polyethylene etc and squeeze and work the air bubbles out of the area Be careful not to shift the glass it will be nearly invisible if it is well wetted Let harden FIG 44 When epoxy is surely hard pull off t...

Page 55: ...aces of the support material are covered thoroughly with epoxy mixture Then cover the bottom of the foam piece with glass cloth and saturated with epoxy FIG 48 Cover the prepared area of the shell with epoxy and insert the fitted part Apply light pressure with weights or sand bags The next steps follow as explained on Figure 42 and following The support material balsa or foam should be replaced ev...

Page 56: ...m under the inner skin to hold it in place while new fabric is glued to it Dress the inside surface of the inner skin to a clean tapered surface as shown on Figure 50 Gloves will protect the hands from sharp edges FIG 50 Cut out a platform piece of foam or other light material big enough to overlap the hole by about 50 mm 2 in all around Sand off its top surface so that it is a fairly good fit to ...

Page 57: ...al l Document No 304S MM Date of Issue 08 14 6 11 H P H Ltd The re established inner layer is now sanded off and one can lay in a piece of foam and proceed as shown in picture B 2 4 and continued as on Figure 55 FIG 55 This support platform remains forever inside and we must insure that it remains there in fact and also does not interfere with any steering mechanism ...

Page 58: ...und away taper on each side for a distance equal to the length of the rip but at most about 50mm 2 in on each side of the rip and also at each end Lay on resin and properly oriented glass cloth After this is hard grind off the inside surface of the rip and lay on a single layer of fabric inside as shown on Figure Observe the kind and direction of the glass cloth and replace accordingly FIG 56 For ...

Page 59: ...contour or remove the wet fiberglass With small curvaceous surfaces one may use modeling clay or typewriter cleaner or even Plaster of Paris to form a mould but do not use silicones Remember that some of these molding materials may contain grease which ruins the epoxy bond So after removing the molding material clean the rebuilt area well with hot soapy water and roughen it well after drying if yo...

Page 60: ...lass cloth around the tube and another layer lapping over to the skin and let harden in position B Greater strength is achieved by wrapping the part with soaked strands of rovings Spread the end out over the shell and secure it with an additional layer of cloth C You can also build a removable attach point 1 First cover the shell with foil and then proceed as described above After hardening remove...

Page 61: ...berglass or wood or metal Vinyl PVC plastic electrical tape clear cellophane tape old newspapers Plastic sheeting polyethylene Parting agents for epoxies In emergency try paste wax or clear shoe polish also a candle However never use waxes containing silicones because one can never remove traces of them from the work and silicones will prevent adhesion of resin or lacquer Solvents Acetone or MEK m...

Page 62: ...i ip pt ti io on n O Op pe er ra at ti in ng g M Ma ai in nt te en na an nc ce e a an nd d R Re ep pa ai ir r M Ma an nu ua al l Document No 304S MM Date of Issue 08 14 7 0 H P H Ltd 7 7 I IN NS SE ER RT TE ED D S SU UP PP PL LE EM ME EN NT TS S ...

Page 63: ...l l D De es sc cr ri ip pt ti io on n O Op pe er ra at ti in ng g M Ma ai in nt te en na an nc ce e a an nd d R Re ep pa ai ir r M Ma an nu ua al l Document No 304S MM Date of Issue 08 14 7 1 H P H Ltd INTENTIONALY LEFT BLANK ...

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