Puchacz SD50 G-CHEP
Contents
1. ED DT DIT TT ee no M roo wot a m i em caw elf eno cn ow ae DEE mo s M acce on pe bow me en em go Without pillowi 77 1 78 79 1 81 82 83j 85 86 87 39 with pillow B81 82 84 1 85 87 BBI 90 91 I 92 94 Meuse Su au Semen e E TE EE EE ona KOS d b w zka yg Without pillowj 91 92 j 93 94 96 97 99 1 100 1 101 103 with pillow 1 95 1 97 1 98 1 1001 101 1021 104 105 1 107 108 80 without pillow 1041 1061 107 108 1 110 1111 113 114 1 116 117 with pillow 1 110 111 113 114 116 117 119 120 122 123 wa ov on un n KEEN PSM P sae se WA Bx ED RES 900 j 1 90 without pillow 119 120 121 1231 124 I 1261 127 129 1 130 132 ORO un eue uh DU MM AMA DU VW Map HR 000 EE DO ER bai 2 OM ao ms s eon ally me me games ve ae ap sep ap mes Yom tbt wey ED 100 without pillow 133 134 136 1371 138 140 141 142 1 144 145 HP gen I ee NA Med Gordiana wo mod eo Shy ma ap meen to aes ony op ma me an ao ob aa RE 8 110 without pillow 146 i i t i i T3323 OM pp u GM MOS t za dra sa za za zara 21 m2. KU OB qub WEN que vp Den Pe FM qm EED WER VEE HE CUR wek WE M TAA NA W WA uen des MEE OUE Aa TO wn MA Wa WA es Wet TA ipee T Bm LAE EDE www CX ma Du Uum HEL A da CON OP CLR ORO Ha CR OP MACY P UU cst WO QD OR WW EED WE MID C OP EE ved WT NUS MEE DEE SU OV OER qm o WEI H H y H i i H d 2 H R 1 M fi Revision un em 4 HEN W z W OED COD MA OU GR MM HAP th Bu cu RIM Z DE VER amen ne MG ep HE ME UMP PR VER OM HEF Map ORE cm EER TE ODA sue MEE WA Iu POL AE ord CUM que W AA Pet ME OER OE HEM ee ab Ele vp mat 9B EER di mun UA que War db LR Ded MED MAD UL MED OR qu MD ME ME que DE pou PR Rem EE date th ces ud and aub umm Cb que WEE HAS nep eb KA Ge MA WA UT F HE IESER EETL ETE t i Item Page EER JET od nt ze od Pi deed 50 3 FMI ud 2 FEIGHI LIMITATIONS 2 1 Permissible airspeeds IAS VNE max pe
3. 71 Hoeke IEAA AE amana amma ma sr RRR 2 X112 ZI I DI ZI LI N PI MEME MI KJ UL YT DJ DX DJ DI LI HEER S DI SUD 23 N RR Kf ES I SZD 50 3 ese ee a e N MAXIMUM ALL UP MASS IN normal flight 570 kg inverted flight 540 kg MAXIMUM FRONT SEAT LOAD MASS IN normal and inverted one person flight 110 kg i inverted two persons flight 95 E MINIMUM FRONT SEAT MASS 55 kg USE OF BALANCING WEIGHTS i for cockpit load mass up to 70 kg OBLIGATORY for cockpit load mass above 100 kg PROHIBITED UR Aj ed Z PO EE MAP XI MAP OV EED que ME CA ERA NOD EP GE CEP VEE BE HEL VER GO EN eb WE GAP un Que OP HA SU HD qua aub Wem Vo Clo EP An ge mh miu RA pep WE aa PU Ba gue LOAD MASS IN LUGGAGE COMPARTMENT 20 kg aos dig e UP am UMP Um Qup PVP que UD Gnp me qoe MS RAP Ob EED me VO qu eub SOLO FLIGHT ON FRONT SEAT ONLY IF THE FRONT SEAT OCCUPANT MASS EXCEEDS 100 kg IT IS PROHIBITED FOR THE OCCUPANT OF THE REAR SEAT TO USE THE ADDITIONAL BACK PILLOW IF HIS MASS PARACHUTE INCLUDED EXCEEDS 75 kg l sg r PA Z EY KA Gri 2 KI LI LI 22 22 EX LF KE XI KR EA EJ E TM SZ DE XD T3 C1 DI nb TILE 3 DE 33 TD P2 L1 EY D
4. HE Guo uum We ow dai en eer n sa dd m m om m ER Flick roll A 57 59 IDIDIDIIGuimcimimimiiminmrlumuhninnmnuuurcskhuuizunzocazcuzn To perform the above manoeuvres by the rear occupant of two persons crew the installation of rear instrument pansl is obligatory RECOMMENDATIONS FOR MANOEUVRES Entering the inverted flight by means of halferoll At the initial airspeed of 75 5 81 kts the glider should be slightly pulled above the horizon and simultaneousely the rotation initiated using the full aileron deflection Before passing the 90 position the glider should be hold above the horizon by means of deflactio the rudder in direction opposite to bank using the upper 19 Then gradually release the elevator the full deflection if necessary and neutralize the rudder In the 1809 position break the rotation of the glider neutralize the aileron and recover the airspeed to 65 kts retaining the above horizon attitude Correct the eventual bank Entering the inverted flight by means of half loop At the initial airspeed 90 97 kts perform the first half loop In the inverted position prior to the nose drop below the horizon pull the stick resolutely and set the inverted flight airspesd into 65 kts in above horizon position In case the airspeed increases unintended open the airbraks in advance Drux OW PT Bielsko Bia a 0G0 466
5. mem SEE ER Sn Ralease the hook if the cable remained with glider 2 Bring the glider to correct glide 3 Land in place choosen with respect to the wind direction and other landing conditions In case of lack of required number of balancing eights solo light weight pilot interrupt the flight and land on the airfield avoiding the stall 50 3 FM3 50 3 FM3 4 27 b Excess of weights heavy crew 4 64 a interrupt the flight and land on the airfield om d emo m lee MEE SE mm eee o ee e Sm ieee DEE Sm In case the airspeed unintended increases creating the danger of exceeding the allowed valus in normal flight 115 kts or in inverted flight 97 kts the air brake shall be extended in advance and the proper action tor decreasing the airspeed and making the flight steady should be taken In such situations the considerable stick pulling is not allowed parachute Decision to leave the glider Leaving the glider is the obligatory crew rescue when it is impossible to land on the ground in controlled way as 8 9 in case of fire or technical fault making impossible the controlled flight in case of sudden severe nis disposition of pilot during the flight e g injured eyes in case of impossible return to the ground e g the extensive fog region The decision of leaving the glider is ta
6. TWO SEATER SZD 50 3 PUCHACZ GLIDER FLIGHT MANUAL ONE WIO AM du BODAJZE ZSO Issue 3 December 5 This instruction is the part of the D Airworthiness Certificate of the glider of v EE EE oe U Serial No Reg No This is the translation of the original Polish Manual approved by Central Administration of Civil Aviation pages 1 2 to4 i7 Date Translated by wies aw Stafiej D Sc ruk OW PT Bielsko Bia a 2000 466 82 i N b ot i R O O AO aa WO OPR A 50 3 PMS J a CONTENTS LIST OF REVISIONS OPERATION LIMITATIONS Bakes AA PALM 2 4 AD 2 6 rm 2585 2 9 Permissible airspeeds Limit load factors Colour markings of airspeed indicater dial Towing cable safety link Restrictions Masses Permissible range of c g location Table of weighing the glider Graphical checking of c g location 2 10 Placards and inscriptions PERFORMANCES GLIDER OPERATION 4 1 4 2 4 3 4 4 4 5 4 6 4 7 Pre flight inspection Cockpits and their arrangements Service before take off Controlling Aerobatics Danger and emergency conditions Assembling and disassembling Druk OW PT Bielsko Bia a 2000 466 82 DRAWINGS AND DIAGRAMS 1 520 50 3 PUCHACZ glider 2 Instalation of board instruments Glider with two instrument panels 2a Instalbtion of board instruments Glider with
7. 110 i ids 90 H 90 110 1 1 i i front i 0 i 0 i 55 1007 1 0 EET 55 75 X Wee eed wie C ay WO OE EE TRETEN neutral or opposite opposite to rotation t6 rPotation 1 little moderate E tu mo em me um O EO ma no Oe RR O aa ea w a oa me D e Mi EAE am am ouo AE M M am O em A O n A O am ase A Se o smooth or dissppeari without or without oscillation oscilla oscillations smooth Airspeed indications about O kts in range of in range o 0 32 kts 0 43 kts wy E madri ER wa i I i i i t i i H j 3 i an we am oes wa o om tia um 0 om 8 A i i pe waa Pr WER GN UK HUS jme dza EA DIER Nm owa zaa AA BA Ap BIO MR Pom EED ER tt 8 i a 8 i 3 Ko XI LI BE X4 3 ER ER ZX HP FF LI 3 213 39 EE ALPESI LSLE ID FS SEAT GE EE GE WY VEI ee GPS gu Rf D DE FE wh ES Ey EX X3 DD RI Ka n x For the flight with balancing weights a pilot of mass more than 75 kg flying solo b full crew In this table the equivalent mass increment should be observed in the front cockpit taking 10 kg for each balancing weight xx Never exceed real mass of glider
8. clinbed turn with 459 bank with such an attention that when recovered for the returned direction 1809 the airspeed ranged 38 45 kts At the initisl airspsed of 81 97 kts the glider should be centered into the sharp clinbed turn with 45 bank with such an attention that when the direction changed by 180 the turning airspeed was about 43 kts After tha next 45 the glider should be recovered out of the turn the eirspeed of 75 5 81 kts gained once nore and the sare manoeuvre performed into the reversal direction then recovered into the original direction 50 3 FM3 4 19 Cuban eight At the airspeed of 85 97 90 Leaf slides 105 kts the looping should be initiated In the upper inverted attitude when the inverted horizon is seen pull the stick full and deflect the rudder full The glider continues the loop and passes into 3 4 attitude making the quick autorotational vertical turn towards the deflected rudder When the turn reached 180 the stick should be resolutely pushed and the rudder neutralized to brake the further turn and to retain the glider in diving in direction reversal in respect to original one When the airspeed reached 90 kts perform the second looping and recover into the normal flight dallying with stali Enter the stalling on the same way as for the spinning and immedia tely break the turn using the opposite rudder deflection and short pulling the stick Then p
9. u me ta te ao nan mr za za zara ss oes ee N 3 M Mass moment of pilot parachute incl on the rear seat M kgm pu pne MEE ES OE AR AE ES ES MOE OES EN ER TEES Pilot of mass M i a i 1 l 1 1 i i i 0 1 4 5 6 8 9 parach incl kg I 1 y Li m 1 1 i Ed 7 3 d 1 e 1 go Without pillow i 13 13 14j 14 14 Wata pillow 1 0 I 17 17 18 18 18 at 000 RR SOD pm OM QUO VEE W UA MP UA SEP QUO ORA WO W MED l2 i 2 1 L 1 4 w m w ed 60 Without pillow 14 14 14 14 14 15 15 15 15 15 with pillow i 181 SABI SIG 4 181 191 193 191 19i 19 20 jg Without pillow 151 P 15 15 15 151 15 HASE 15 15 with pillow 20 20 20 20 20 20 211 211 21 21 90 X up QUO WM OD CE ex ME Fo p MM Ohm O Qua VO EE NA ESE porem e ek Wa 409 oe D qo w tm UZ we sm Ke Bs without pillow Asi 16 16 i 16i 161 16 16 161 16 16 with pillow 21 21 21 24 221 22 m22 22 22 22 cm D Gen fU vp me gp nm QU WE WE OUO QU UD WE SE sue ER OR i ee do a e pda CHO SER om MA 90 Without pillow 161 16 16 16 161 161 161 161 16 1 16 up vm aus ven OOO ni Om M UOS MO W KW CO MM Gub dat 109 na we a aD om mo wu OF ue EP wo
10. 52 4 22 In respect to a low tollerance of angle in the moment of breaking the loop and the low margin of permissible airspeed in inverted flight this manoeuvre can be learnd when the inverted flight is completely familiar to the pilot Straight inverted flight The glider should be retained in above horizon attitudes with the airspeed of 65 70 kts When correcting the banks pay attention that the stick side movement e g to right results the RIGHT wing to be elevated above the horizon and vice versa In the prolonged inverted flight the trimming if necessary should be set into nose heavy position using even the full range of trimming In the straight flight the stalling at about 59 kts airspeed is possible It requires the full stick movement forwards When the glider drops down the stick should be slighty pulled for a moment then once more pushed to get the above horizon attitude Turns in inverted flight The bank of glider when introduced into the turn is obtained by means of side deflection of the stick in the direction opposite to the intended turn direction It is recommended to control the glider with the small deflections of aileron and rudder The airspeed in turn is 75 5 kts 50 3 FM3 4 23 Recovering from inverted into normal flight by means of half roll Inerease the airspsed in inverted flight up to 75 5 kts Then push the stick to obtain
11. A the left yellow Canopy locking EG the left red lever 1 Canopy emergency ton the righti red jettison handle i i sealed i i with lead Fastening of the floor belt is obligator for flight in which the inverted flying and associated aerobacy manoeuvres controlled roll controlled half rolile half loop controlled half loop half roll are intended In other flights when the floor belt is out of operation it should be piaced below the seat pillo and immobilized by means of the button The cockpit is closed with the integral perspex canopy fixed on two hinges on the R H board with the possibility of emergency jettisoning The opened canopy is hold up with a cabl which when closing the canopy pulls up automatically into the winding set behind the front seat back rest Both seats have the control columns coupled each other the pedals and other control levers are marked with placards Operation of controls is of conventional type The handles are arranged as follows Lruz OWPT Bielsko Biala 2000 466 B2 The cockpit is air conditioned with the side windows in the canopy seperate for the front and rear seat The front seat has adjusted inflation on the perspex front part above the instrument panel operated by the slider in the panel black ball knob Both seat have side packets accessible in the flight Two nests for balancing weights are located before the front seat The weights of mass 6 3 kg each are n
12. MINIMUM SOLO PILOT WEIGHT WITHOUT REMOVABLE BALLAST BARS FITTED 2 PLACARD MINIMUM SOLO PILOT WEIGHT FOR EACH OF 2 REMOVABLE BALLAST BARS WHEN FITTED 3 PLACARD FOR FRONT AND REAR PILOT COMBINATIONS AEROBATIC INVERTED FLIGHT 1 PLACARD MAXIMUM SOLO PILOT WEIGHT 2 PLACARD FOR FRONT AND REAR PILOT COMBINATIONS 10 August 1994 GFA AD 407 ISSUE 1 2 9 PLACARD REQUIREMENTS cont FLICK ROLL 1 PLACARD FOR FRONT AND REAR PILOT COMBINATIONS In this case the AFT CGLIMIT is moved forward making it most unlikely that a rear pilot can be carried WEIGHING THE GLIDER The glider should be weighed to scheme 3 on GFA weighing form W1 and the pilot limits computed on form W2 Both of which should be glued into the back of the log book 2 11 SAMPLE PLACARDS NORMAL CATEGORY VH AHH FRONT REAR kg min max 45 75 110 50 60 110 Minimum Solo 70 kg 55 40 0 Maximum Solo 110 kg 60 25 110 Max fuse load 195 kg 65 10 110 70 0 0 75 0 110 80 0 110 85 0 110 90 0 105 95 0 100 100 0 95 0 0 18 5 90 UU A a NORME cod isst 0007 viY1G ox 1210 Ld ROL MAR RE AN AAAS ut v PCM pt eb NO OE TER Rd LO GE ee uo yi By oI t e s 2 ews 0S 2 8 Tcblo of woighing the glidor Fact No BEOPS ER ERE EI MA LOOO 2 INO It gt lt OAM f s Empty ed mass wit
13. PC EE oF Quick half roll 1 i half loop i 51 8 CA CI TE SD uam HE EY am CUP quam ER LA EI HR HR CO mom ma oe am am cm e 4 aa a Ma WALCA Oe A que Chandelle 1 81 97 Lazy eight 81 i 97 OM Ce 479 Wa M SET Gub Cue en fn 2 CD EI Wc wow pen W WEER Gr OU KA MI cs J eo c ARR OB m a Cuban eight 86 97 i 30 105 mn mc e OP 4UO eme MA Leaf slides stalling speed RECOMMENDATIONS FOR MANOEUVRES 8 i j i 8 l i i 8 8 8 0 q i t t i me ere ut 8 j 8 i i 1 L General In manoeuvres requiring the considersble use of elevator looping quick half rool half loop the increased forces on the Stick are required specially in flight with heavy crew o Looping stall turn spiral Performing ie conventional Lrux O 4 PT Pielsko Biala 2000 466 2 50 3 FM3 Quick half roll half loop At the initial airspeed of 51 54 kts the autorotational half turn is obtained when the stick is resolutely pulled full with simultaneous full deflection of rudder The further rotation is braked by means of neutralization of controls Recovery is performed by means of semi loop downwards Chandelle At the initial air speed of 81 97 kts the glider should be entered into the sharp
14. cockpit is designed to use backe type parachutes or pillows of 12 cm thickness when pressed The front saat allows for the pilot above 2 m tall The pedals are adjustable in flight 5 positions adjustment of pedals is made by feet when the knob on the floor painted brown is pulled The pilots havi g short legs or small mass should use tne additional cushion on the back rest The rear seat allows for the pilot above 2 m tall The seat pan is adjusted on the ground vertically and longitudina lly by shifting the backrest cross tube 4 positions When the position is adjusted the cross tube should be secured with the lock In general the higher pilots position in the rear seat the better is the visibility forward including the instrument panel at the front seat Pilots having the short legs should use the additional back rest pillow The standard equipment comprises four belt pilot s harness at both seats The installation of the floor belt additional equipment is possible 50 3 FM3 Ko ec Ga Ga SS IERE Re AUR a Control i Position of i Colour of system 1 handle handle OM sy ED OP Cus MP AD ED nun HI wr KM e ese mn STA ao se cm HE ME EE SE eS He Om ew TU me MR quA WO p Fe Air brake slider jon the left blue Wheel brake knob ton the left I black 1 i D nM tab fon the left 1 green 1 i Towing cable i EA handie
15. flying day or before the every change of loading condition the c g location of the glider in flight shall be checked acc to the following procedure 1 Add the masses of empty glider no see table on page 2 5 pilots with parachutes B mo additional equipment and balancing weights incorporated m see table on page 2 7 The resultant mass of the glider in flight mark on the vertical axis of diagram on page m M m Bo m 2 Add algebraical respecting the sing the mass moments of empty glider Mo see the table on page 2 5 pilots with parachutes M M see tables on pages 2 2 and2 fQ additional qquipment and balancing weights M3 incorporated see table on page 2 7 FM3 5 gt W RE 27 28 2 IRD WOM gt gt DY 8 O ZIP gt ILI I i i Mass Moment i 8 Equipment kg 1 kgm instrument panel of t rear sgat 52 a E i RS 6101 1 transceiver 7 2 2 2 OER wu WA MOCE EP ER OP MP OP HA on EE am M we TA HR ER lm on ex em on wa pu gt TA O3 A Oxygen i t equipment 2943 US a ACh ah M 1 balancing weight 1 6 3 11 2 balancing weights i 12 6 a 22 ra mew cb AU IO CH EP a ER GU OO MP ER ER VR MP OP EO LR CA HY KA RUM
16. oxygen lack low temperature or icing b danger of freezing the body at delayed parachute opening in respect to these circumstances it is recommended to stay in the cockpit of damaged glider if its condition allows for until it descends to the altitude of conditions for safe parachute use If the damaged glider allows for the limited control and the altitud dees not require the immediate cockpit leaving the ship captain can help the pupil in leaving the cockpit a g giving instructions or maintaining the convenient flight condition acc to his decision e g wnen controlling the glider to order the pupil to jettison the canopy and leave the cockpit delay the jettisoning of the canopy or after jettisoning to control the glider again Druk OW PT Bielsko Bia a 2000 466 82 4 30 4 7 Assembling and disassembling Fig 5 and 6 4 7 1 Tools 4 7 2 4 7 5 i assembling lever for fitting the spars screwdriver pliers pin for service of tail plane securing bolt Assembling staff min 4 persons a ee Sm am w m w Emm sop map m m m SEP Clean and grease the working surfaces of disconnected fittings and joints Put the fuselage on the assembly stand Support the front wheel tail skid on the ground Take off the fuselage upper inspection door Retract the air brake in wings set up the brake slider in the cockpit in the front position and the control stick in the plane of glider
17. the above horizon position and move the stick to aileron direction full aileron deflection When passing the 2709 position retain the glider above the horizon by means of smooth deflection of rudder in accord to aileron deflection and neutralize the elevator In normal position neutralize the aileron and rudder and return to the steady flight Recovering from inverted into normal flight by means of half loop In the inverted flight with the airspaad below 59 65 kts gently pull the stick In the diving the airspeed should be controlled and tne glider recovered into the normal flight on the arc path of semi loop In case the airspeed increases considerably the sir brake should be extended in advance Controlled roli In the normal flight at the airspeed of 97 kts the glider should be elevated slightly above the horizon In the same time the rotation should be initiated by means of aileron deflection Before passing the 909 position the glider should be retained above the horizon using the smooth rudder deflection in the direction opposite to bank use of upper leg run O PT Bieleko Biala 2000 456 n2 4 24 50 3 FM3 Then gradually release the stick and neutral ze the rudder When the 180 position passed gradually deflect the rudder in accord to the aileron When passing the 220 position ratain the glider on horizon using the rudder deflection in accord to the aileron In the normal position neutra
18. 5 1 54 65 75 5 86 97 8 AZ Ee w ft min 142 187 262 378 537 738 where V airspeed W sinking speed 50 3 FM3 4 4 1 Pre flight inspection Check for validity of inspection certificate in the glider log book the integrity of structure and covering locking of fittings and control system joints control system operation towingehook operation locking and opening of canopy and the condition of canopy in open position securing cable condition of undercarriage wheel roliability air pressure in tires by eye locking of seat and back rest at rear seat pilot s safety belts ports of total and static pressure operation of airspeed indicator fit enous operate when blowing on ports Operation 9t slip and turn indicator x In the rear instrument panel also if installed Drux OWPT Bielsko Bia a 2000 466 82 50 3 FM3 4 2 Cockpits and their arrangements The standard equipment comprises one instrument panel at front seat only The instruments are located in such a way that they are satisfactorily visible from the rear seat also During the flight the upper panel edge allows for controlling the glider in respect to horizon or in respect to towing aeroplane Additionaly the glider can be equipped with the second instrument panel mounted on the canopy The
19. EAR SEAT THE REAR INSTRUMENT PANEL IS OBLIGATORY 50 3 2 3a 1385 FM3 Masses kg Max permissible empty glider mass with standard equipment 370 where the mass of fuselage and 2 tail unit without the moveable 19 balancing welghts is re ese cette gt Max permissible load mass see page f Max permissible load mass in the luggage compartment see page Max peraissible load mass on front ssatin normal flight eessccsesceseses 110 inverted flaght two persons Crew esssesessees 95 Max permissible alleup mass in normal flight Selina 0 inverted flight ooo 540 Tr OM KD ED Wee Mee US OD Hu Em FW OP ER CM Se Uu OER CEY HR OD OR Z A TW x The standard equipment consits of 1 Instrument panel at front seat only with airspeed indicator altimeter variometer with compensator slip and turn indicator compass Two towing books of SZGeIII or TOST 2 type 3 Two sets of four belts pilot s harness 4 Two sets of seat pillows 5 Assembling wrench 6 First aid kit xx Inverted flight the aerobatic manoeuvres listed in item 4 5 2 included Druk OWPT Bielsko Biala 2000 466 u2 LOAD IN LUGGAGE COMPARTMENT am SO ow we ZA MO HE EG MW we Due Mas SEP MED OD WE OD UU GC ON CD Max load in luggage campartment is 20 kg The above load comprises the fixed equipment battery transce
20. MO Ge CO BU Gum i c m EP que HR LAM OF EL Wa Snow ski installed 1 on glider 11 5 EE Ds Luggage stved in the luggage compartment Euri 10 3 wo e dii e OM M ane ma Coh Aum ey mn gt 2 5 MO SO gt gt 3 gt gt IR 8 RE gt gt ERS The resultant value of glider mass moment M s Mo M Mo M mark on the 1 horizontal axis of diagram on page Druk OWPT Bielsko Bia a 2000 466 B2 50 35 FM3 3 From the points marked on the diagram axes on page 16 draw the perpendicular lines to the axes and find the point of intersection If this point is located in the dashed field of the diagram c g is in the correct position If this point is located out of the dashed field the c g location shell be corrected with the balancing weights and c g location checked once more 28 99 0002 t 1G OXE13 G 1d MORA SW gOS aaa Mass moment of pilot parachute incl on the front seat in respect to the leading edge of wing root chord M4 kgm i EE WIRE WMG 7 t RU DS TY ERA n M SG Tp TO BT DA MR KI SEE OQ EIZI 93 RS LI gm rz ZZ RR Pilot of mass M a I a 1 1 tO 7 2 i 3 4 t 5 i 6 1 7 1 8 1 9 50 without pillow i 1 1 701 71 I 72 74 1 75 with pillow i i 741 75 76 78 79 we ee am ua cmo O
21. NDED INVERTED FLIGHT ROLL AND ASSOCIATED AEROBATIC MANOEUVRES allowed in smooth air only and with floor bslt fastened FLICK RODL only with two occupants PERFORMING OF THESE MANOEUVRES BY THE REAR OCCUPANT allowed only when the rear instru ment panel is installed e que pun gb PA uS M CED HED QU R quas quas CS ME WED HE TEE qa Hut GEE qua AA Qf ere VEE UP F9 amb QUI Geb VE OD oup qub WER Placards 3 of EBM 7 Trimming tab slider i placard on the L H board at front ane rear seat Air brake Siider E placard on the L H board at front and rear seat _ Druk OW PT Bielsko Bia a 2000 466 s2 FM3 Canopy emergency jettisoning lock placard on the canopy frame at front and rear seat Air conditioning tab slider placard on the instrument panel at front seat Pedal adjustment placard at front seat floor before the control column 50 3 c 2 17 35 Wheel brake placard on rear seat m OER Towing cable release placard on the L H board at front and rear seat Urea OX PT Bielsko Bia a 2000 4bo E2 3 1 50 3 FM3 3 PERFORMANCES Fig 4 Calculated speed polar plotted on Fig 4 has the following main points nin sinking speed 8 ft min at about 40 kts sax lift drag ratio 30 1 at about 46 kts Other points of the polar e EE a j 3 kts 4
22. SI ET RJ ES ZO TZ ET DR ES D2 D BST EE R AR AR 3 SI EW 05 2 f29sur PUB SpJBESETJ paJe5eryd usrd Burpeo st eg SUOTI AE DIEP a HE AS AR AAHS AA HARARE ARE DE MAN HE AE DU ES 520 50 3 c om un NORMAL FLIGHT IN smooth air VNE n 116 i gust conditions Ve 86 INVERTED FLIGHT IN smooth air 97 i gust air not allowed i 1 MANOEUVRING AIRSPEED airspeed for abrupt i deflection of controls Va F 81 i i AEROTOWING 81 i WINCH LAUNCHING Vy 59 d i AIRBRAKE EXTENDING and flight with air i brako extended 116 i l Ln KA Gt WA UT DU DZ IN EC 5 UD PR TI DI DOES EJ ZU BN NA NU 82 SA DYMY FG C2 Y3 DI MM KI KIEJ EY X3 I3 CP E KI DL PG IA MD CJ CE C FF E KIER KU Es Spsadsute eiqrssryu4ged jo pueosig vlI C e e 708 50 3 FM3 2 15 Placard of restrictions ue KR me FO QNO KA as GAZU W MA CHR R OP WW OM Cu DE PER ME HER MEER RW OD TE Om GU cm sub ME EA HE wu Z ane RA RESTRICTIONS an om KD D gam REWA WA FID M HE OR OP WES czy GUP ice EP COD EI HR MP HE OP sum Ca ER Aun XD Z SUD MEE WA Az COND uS Ow TER Que um A a ea Um 1 GLIDER NOT APPROVED FOR NIGHT FLYING WINCH TAKE OFFS ALLOWED WHEN USED THE BOTTOM HOOK ONLY FLYING UNDER ICING CONDITIONS NOT RECOMME
23. The table of spinning characteri stics is not the loading plan The table concerns glider with all the additional equipment variants acc to the loading plan on page 2 13 The aileron deflection towards the spin favours the appearance or augmentation of longitudinal oscillations especially in the solo spinning with light weight pilot and therefore it is not recommended The not full deflection of elevator specially with heavy crew leads to the airspeed increasing up to 54 kts or more and even the automatic break of the spinning The recommended recovery technique consists of full rudder deflection opposite to the rotation a considerable leq force is required waiting for about 1 sec pushing the stick forward more than to its neutral position The maksimum delay when this technique is used is lower then i turn In case of other technique or not resolute action the delay can be more than 1 turn 50 3 FM3 Recommended aileron deflection 9 fo EE EE O I 0 VOED 1 w WL mA PM b mo Longitudinal 1 i i inclination high TEG OX51218 0002 78 99 Longitudinal pom ue OUS QUE QUO R Pub A UNA MED VER OR UU OU ano Tn UI ZO t W CHARACTERISTICS OF GLIDER IN SPINNING Crew masa 55 75 175 807 55 75 7 190 110 Roe E a aS ss Crew mass 55 75 175 90 SO
24. achu tes and luggage equal to the subtrac tion of 570 kg total mass of empty gliderwith standard equipment and additional equipment installed Max pilot 8 mass parachute included on fornt seat defined as the subtrac tion of max load mas pilot s nass parachute included on rear seat If the value so calculated exesd 110 kg the value of 110 kg should be inscribed If the inscribed value for two persoas flight exceeds 95kg the sign X should be added Date seal and signature of Techn Check Dept NOTE To define the total mass of tha crew and luggage the NOTE of page 2 4a should be taken into account Dreck a 6 3 Individual loading plan placard copy of glider placard for Flight Manual SZD 50 3 PUCHACZ Fact No 4 INDIVIDUAL LOADING PLAN Mass of empty glider with standard equipment and the following additional equipment N 3 320 Maximum all up mass in normal fight 570 kg inverted flight 540 kg 478 75 Maximum summarized load mass i e crew and luggage Mass of pilot and parachute kg Balancing Front seat weighis Signature pieces Seal of man a jo ma aa spec 79 10 tne Inspection dii d 72 E OOOOOOOIO x for inverted flight ON PT Bielsko Bia a 2000 466 52 6 4 e Individual loading plan placard Spar placard for the glider in case of revision make the inscriptions acc to new page 6 3 cut off and place in th
25. cording to the take off method and crew mass Check the operation of turn indicator Close the canopy Insert the esble into the hook and check the locking pulling it firmly Post flight procedures Switch off the turn indicator If necessary remove the used batteries If necessary drain the instrument installation according to 4 3 5 Inspect the glider as before take off and remove the eventuel failures 4 4 Controlling ee SEE m EED AE SE Xu MEER ee w me HEER SEE The SZD 50 3 PUCHACZ glider allows for correct and easy controlling as do it most of the modern performance sailplanes Characteristics short and wsll shock absorbad ground run good lateral and diractional controllability safe low speed behaviours with out the excessive ine lination to POR 4 8 50 3 FM3 Om o pe m SEE w ED _ ae OER ye m front hook Pay attention to have the towing cable straight tensioned before take off According to the crew mass adjust the balancing tab solo flight nose heavy heavy crew neutral The ground run begins on two wheels At the airspeed of about 16 22 kts the front wheel should be lifted by pulling slightly the stick when avoiding to hit the ground with the tail skid According to the all up mass the glider airborns at speed of 35 to 41 kts When the flight becomes stable correct the setting of trimming tab Recommended towi
26. e cockpit SZD 50 3 PUCHACZ Fact No INDIVIDUAL LOADING PLAN Mass of empty glider with standard equipment and the equipment following additional normal flight 570 kg inverted flight 540 kg load mass i e crew and luggage Date Signature Seal of Factory Inspection Maximum all up mass in Maximum summarized Mass of pilot and parachute kg Balancing Front seat weights Rear seat ____Front seat weigh minimum maximum pieces maa LE 110 ON OOOOOOO SONO x for inverted flight 95 kg
27. er Altimeter Turn indicator Compass Turn indicator battery socket Turn indicator switch Nuts fixing the rear instrument panel to canopy Arrows mark the drainage unit end which should be disconnected when draining the installation K 1 tube K 1 tube duct Fig 2 Druk OW PT Bielsko Bia a 2000 466 82 Fig O O NO DN gt 10 11 L2 13 14 15 5 6 50 3 2a installation of board instruments Glider wit one instrument panel Total pressure port Static pressure port Drainage unit Bottle Compensator Airspeed indicator Variometer Altimeter Turn indicator Compass Turn iddicator battery socket Turn indicator swith Arrows mark the drainage units ends 6 which should be disconnected when draining the installation 16 K 1 tube duct Lruk OW PT Bielsko Bia a 2000 166 82 5 8 a 50 3 FM3 Fig 3 Wiring diagram of electric turn indicator 1 Turn indicator 2 Switch 3 Batteries the poles arrangement shown on drawing 50 3 FM3 Druk OW PT Bielsko Bia a 2000 466 32 5 10 50 3 FM3 Flight measured Fig 4 Speed polar Fi u amp WN b 0 10 r g FM3 Wingsefuselage assembling a R H wing fitted to fuselage L H wing prepared for fitting b Locking the spars by means of assembling lever attached on thrust pivots Full arrow rigging Broken arrow derriging Spar root pivots Fuselage pivots Self aligning nosts in wi
28. g it by 90 red mark on the pin should be visible Take off at first the LH and then the R H half of the tailplane pull outside applying the oscillating motions to loosen the connection If necessary beat the carrying tube end using the hammer and the wooden block Retract the air brake and take off the safety pin which secures the main pin Support the wing ends and take out the pin Drux OWPT Bielsko Biala 2000 166 82 4 32 50 3 FM3 4 Support the wing ends put on the assembling lever on the spar feet and loosen the connection of spars with motion of a lever Next support the fuselage and take off at first the L H and next the R H wing Install the main pin into the fuselage fitting and secure with safety pin Lo ES EE EE EE SIE Druk OW PT Bielsko Bia a 2000 466 82 Eig 4 820 50 3 PUCHACZ glider we tw an 50 3 35 2 5 4 wi 50 3 FMS Fig 2 Installation of board instruments 0 17 18 85 88 1 Glider with two instrument panels Instrument panel of front seat Instrument panel of rear seat location of panels ports and ducts in fuselage Total pressure port Static pressure port Total pressure duct end in fuselage botton Static pressure duct end in fuselage upper Rubber ducts Total pressure duct end of rear instrument panel Static pressure duct end of front instrument panel Drainage unit Bottle Compensator Airspeed indicator Variomet
29. h standard i equipment 370 8 i Location of c g tor empty glideri with standard equipment in f 23 respect to root chord loading Q 653 edge A 1 EE I Static momant of mass of empty f glider with standard equipment 234 in respect to root chord 44 i leading edge 1 6 tf eee O i Max perpiesible loading mass I J68 05 200 MEN i Mox parmiosible loading mas8 i in nvortod flight 468 t bo eo sw w CD ar Date _signature and Beal of 1 inspection representant LED Er URO UR en DD dub PRZ QUA Pet 9 Ge up He UB Qon VA hd FO mes VI RM and Qg mass of both wings Qa mass of empty glider 733 Q92 2Qe vkgy 7 N e EEN 1 1 I ele EI C quotum ue ed wc Q3 we pe ub Ene Map CON ha aw a QR mv HR WW AE CO exo Oe de DE TR HER KP a ha w PO mat FD wu RD ER Cw po OP Du Cu 1 H 1 i I 3 me i j 0 8 j l 1 1 1 1 1 i 1 i I 1 1 t i 8 i I l o Do e e AT TE TE pub Rae n me w Of 2 6 50 3 FM3 2 9 Graphical checking of c g location see diagram on page 2 11 Before the
30. he autorotation the airspeed decrsases considerably Therefore to avoid the stalling and unpleasant dropping of the glider at the end of the manoeuvres it is recommended to initiate the flick roll with the position pitched clearly below the horizon In the steep diving accelerate the glider to 57 59 kts not more 7 then simultaneousely pull the stick ful and deflect full the rudder The glider performs the autorotation in respect to longitudinal axis with the tendency to climbing Before gainin the 360 position neutralize the controls to break the rotation If necessary finish the rotation with the aileron and return to the normal flight DruA OW PT DBieisko Diala 2000 4uv DZ w SEE EE ma In respect to the fact that the steady inverted spinning is not possible to be performed in the greater part of c g location range this manoeuvre is not allowed In the case of unintended developing of inverted spinning as a consequence of inverted stalling the stick should be pulled immediately and the other controls neutralized The glider breaks the rotation nearly immediately and passes into diving It should be recovered slovily controlling the airspeed If necessary extend the airbrakes in advance The recovering from inverted spinning into the inverted flignt is prohibited 4 6 Danger and energency conditions procedures p me SR STE SEE SEER o BEE BEE ma SR am
31. ht fiight sucn a recovery is a little slower than the previous one 4 4 9 Air _brake The air brake is very efficient and can be if necessary extended in full range of permissible airspeeds The effectivness of brakes allows to avoid the use of sideslips during norma approach to landing 4 4 10 Landing Generally the landing should be perfor Bed against the wind If necessary the landing with the side wind up to 10 kts or the back wind up to 6 kts is allowed when paying special attention The recommended approzch speeds in smooth air 49 54 kts depending on all up mass in turbulent air 54 60 kts depending on all up mass The flying path inclination should ba adjusted by the air brake According to all up mass and air brake travel the touch down with the main wheel follows at airspeed of about 35 to 41 kts it is recommended to touch down with the partly extended air brake After touch down the glider rolls at first on the main shock absorbed wheel Then smoothly drops the front wheel this effect can be delayed to dianish the shock during rolling with gradual pulling of stick Drux OWPT Dielsko Diala 2000 4buv 52 4 16 50 3 FM3 The lenght of landing run in windless condition is Without use of wheel brake about 90 110 m depending on all up mass with use of wheel brake about 60 80 m depending on all up mass 4 5 Aerobatics Before take off for aerobatics it s neces
32. iize the aileron and rudder and return to the steady flight NOTE Having some experience the rolls can be performed with the initial airspeed of 85 kts z Controlled half roll half loop Perform the first half of controlled roll with initial airspeed of 75 5 81 kts In the inverted position decrease the airspeed up to 59 kts Then pull the stick passing into the half ioop Pay attention that the sirspeed must not exceed 116 kts if necessary extend the air brake in advance Recover the glider from diving into the normal flight Half loop half roll At the initial airspeed of 108 kts perform the first half of looping in such a way that the airspeed in the inverted position would not drop below 59 kts In the inverted position push the stick forwards resolutely and then perform the second half of controlled roil deflect the airleron retain the glider above the horizon by Beans of rudder deflections in accord to the aileron 50 3 FM3 4 25 When antaring the normal position neutralize the aileron and rudder and return to the steady flight Flick roll In respect to the troubles in correct controlling of the flick roil at the rear location of glider c g this manoeuvre should be limited to two persons crew only Performing of flick roll depends on the extorting of autorotation by means of simultaneous full stick pulling and full rudder deflection towards the intended rotatior direction During t
33. in flight is 570 kg E zn OSL 50 3 FM3 4 4 8 Sideslip can be performed in 2 ways a With simultaneous gradual deflec tion of ailerons and rudder at the airspeed of about 38 45 kis the directiongl sideslip with bank of to 10 15 is obtained Indications of airspeed indicator drop below 27 kts Keeping up the rudder deflection requires the applying of resolute force on pedal releasing of this force causes the automatic neutrali zing of rudder and the glider passes into a turn towards the bgnk With the bank of above 15 the glider also turns towards the bank b With deflection of controls in an order at first the ailerons then rudder when the bank of 15 is obtained the glider allows to enter into directional sideslip with bank of up to about 309 During deflectio of rudder the force on pedal disap pears simultaneously it appears the impulse to raise the glider nose above the horizon It is necessary in this moment to stabilize the glider by pulling back the stick Indications of the airspeed indicator in this condition drop down to about O When recovering with aileron and rudder deflections simultaneously it is necessary the resolute deflection of rudder towards the bank the glider passes into the turn When recovering with aileron at first as the bank diminishes the rudder is neutralized automatically and the glider passes gradually to FM3 the straig
34. iver block etc and a hand luggage The mass of luggage uniformly distributed in the compartment does not contribute to the c g location of glider in flight The hand luggage shaild be immobilized by means of cord or belt using the six removable lugs on compartment floor 2 7 Allowed range of c g location in respect to wing root leading edge empty glider without the balancing weights 9 610 to 0 635 m glider in normal flight 0 092 to 0 533 m what corresponds to the range of 23 5 to 44 0 per cent of M S C glider in inverted flight 0 133 to 0 333 m what corresponds to the range of 27 0 to 44 0 per cent of M S C for performing the flick roll 0 133 to 0 204 m what corresponds to the range of 27 0 to 33 0 per cent of M S C NOTE To define the Maximum permissible loading mass use the formulas given in item 2 8 Example The empty glider with standard equipment 2 without balancing weights mass is Qc 7 370kg Both ME mass is Qq7172 kg According to the formula 763 Qs 2Qc item 2 8 maximum loading mass gt 7634 172 740 5 195 kg 50 3 FMS S0 3 PMS 2 8 ALLOWABLE WEIGHTS AND PILOT ARMS FRONT SEAT MAXIMUM PILOT 110 kg PILOT ARM 1339 mm REAR SEAT MAXIMUM PILOT 110 kg PILOT ARM 247 mm NOTE Pilot arms assume a 70 mm thick cushion or parachute MAXIMUM WEIGHT OF NON FLYING PARTS 398 kg MAXIMUM BAGGAGE ALLOWANCE 20 kg 2 9 PLACARD REQUIREMENTS NORMAL CATEGORY 1 PLACARD
35. ken by the ship captain Ore a PI Lielsko Biala 2660 46 s b c 4 28 Sequence of leaving the glider The crew member being not the ship captain leaves the glider first The ship captain leaves the glider in second sequence after using all the possibilities to enable the second crew member to leave the glider Sequence of procedures 1 Release the control stick 2 Hold firmly and push forwards simultaneously canopy lock handle with left hand canopy emergency jettisoning lever with right hand 3 When holding the handles push the canopy and jettison out 4 Release the safety belts 5 Fold the legs and jump out of the cockpit If the glider gets the quick rotational movement jump towards the centre of rotation 6 Wait at least 3 sec to get a distance in respect to glider and open the parachute d Procedures in special cases If the canopy does not allow to be jettisoned destroy the perspex starting from the windows If necessary use the action of legs If the cockpit leaving occurs on the altitude below 200 m open the parachute immediately paying 50 3 FM3 50 3 4 29 E FM3 z gn attention to avoid a collision of the parachute and glider structure or another crew member If the cockpit leaving follows on the high altitude take into consideration a danger of further climbing on parachute in the strong climbing currents in a cloud and danger af on
36. main wheel valve is located on the R H side and is accessible after shield deflection Pressure 3 0 at The front wheel valve is located on the L H side Pressure i 2 at Druk OW PT Bielsko Bia a 2000 466 s2 4 6 50 3 FM3 Remove the pressure ducts of the rear seat instrument panel 3a and plug them on the port Detach the drainage units from the ducts of the front seat instrument panel in points marked with arrows in Fig 2 and blow through the drainage units together with port ducts screw out the drainage unit bowls take out and dry the inserts Install the dried elements and bowls tighten firaly connect the drainage units free ducts to the rear seat instrument panel check the operation of sirspeed indicator it should operate when blowing on ports Put the weight into proper nest and screw on full the clamping screw Balance the glider with balancing weights according to the crew mass and if necessary put on the back cushion small or light weight pilot Adjust the rear seat correctly Before the solo flight clemp the free belts and protect or remove the contents of side pockets in the rear cockpit 50 3 FM3 1 ame TES RE EE ie ras Druk OW PT Bielsko Bia a 2000 46b 2 4 7 m Take place in the cockpit adjust the pedals and fasten the balts Check full movements of controls air brake and trimming tab Retract the air brake Set the trimming tab slider ac
37. ng airspeeds at climb 51 to 65 kts at cross country flight 65 to 81 kts Before take off the glider should be positioned in line with towing cable The slight directional deviation is allowed to the left of e cable but the deviation to the right should be avoided in respect to the possibi ity of front wheel to the cable contact during the ground run the possible touching or even the rolling of the front wheel through the tensioned cable does not create however any danger nor disturbs tne ground run 50 3 FM3 4 9 The adjusting of the trimming tab according to the pilot s mass on the front seat solo light weight pilot nose heavy mean pilot nose heavy heavy crew neutral The adjustment of the tab should not be corrected during take off The glider ground run initially on two wheels next on the main is correct and the run length depends on the crew mass and taka off conditions After sirborning fly correctly near ground avoiding ths tail skid to ground contact and pass into steep climbing With glider correctly balanced the Stick forces are not large and with incorrect balance the forces are not excessive The launching speed should be 49 54 kts not less than 43 kts in the final climb phase slightly pull the stick Before relessing the cable put the stick forwards to discharge the cable During intended self releasin the stick should be pulled forward after
38. ngs Control system joints in wings Air brake control system joints in fuselage Aileron control system joints in wings Aileron control system joints in fuselage Main bolt with tommy bar Safety pin Spar thrust pivots Assembling lever R H wing LH wing Fuselage 50 3 FM3 Fig 5 Urzx OWPT Bielsko Biala 2000 466 52 Fig 10 5 14 50 3 FM3 6 Assembling of horizontal tailplane R H half tailplane with carrying tube fitted with fin L H half of tailplane with trimming tab Carrying tube Carrying tube nests in L H half Pivot fixing fin half Securing pin in dissecured position protruded forward secured position small hole in wertical position Red caution sign visible in this position disappears when the pin is pressed in Trinning tab control joint on L H half of control surface Trimming tab control joint on vertical stabilizer Control joint on elevator Elevator control joint on vertical stabilizer 50 3 FM3 Urur OWPT Bielsko Bia a 2000 466 u2 5 16 50 3 FM3 Fig 7 Colour markings of airspeed indicator dial PETER ZAS uc A 50 3 FM3 5 17 gt PR 4005 o zn t Ebo Drux OWPT Bielsko Biala 2000 466 52 50 3 FM3 Rewer 6 1 z APPENDIKX z ww TED Qu W WZM W During the daily operation of the glider the simplified method of checking the loading mass and defining the balencing
39. on all up mass In all the cases of stalling the glider allows for recovering the normal flight reliably by the resolute elevator 50 3 FM3 4 31 deflection and if necessary by the other control deflection for balancing the bank Cireling_ When circling in thermals the glider has very good lateral controllability The circling speed is of 38 to 49 kts depending on all up mass bank and flight conditions Spinning Before the intended spinning in one person flight the pilot of mass below 165 lbs should check the proper glider balancing with weights When entering the spinning in the straight flight it is recommended for making it easy to have a little bank towaids the intended spinning direction It is also possible to enter the spinning in the turn In both the cases it is recommended to decrease the airspeed by slow pulling the stick and in the moment of stall initiation to pull the stick full Deflect the rudder towards the intended spinning The recommended aileron Geflections are listed in table on page lt f f3 To obtain the stable spinning especially in the case of heavy crew the precise full deflection of elevator is necessary with the comparatively high force depending on the crew mass When the above directions are observed the glider performs the steady spinning with the characteristics described in the table on page 4 13 Urux OW FT Bielsko Bisia 2050 466 52 4 12 NOTE
40. one instrument panel 3 Wiring diagram of electric turn indicator 4 Speed polar 5 Wings toefuselage assembling 6 Assembling of horizontal tailplane 7 Colour markings of airspeed indicator dial APPENDIX Individual loading plan PMS 1 LIST OF REVISIONS qe me mA pam wa We Ow de que OS Qua Om m um I mos NOTES The place in which the text has been revised is marked with vertical line on left side of text and with the number of revision Item i Pago i RB 0 Date Signature 5 i On page pes the 4987 i 5 6 Ltems 17 and 18 i f i and on page 5 6 07131 t the item 1 1 i have been added i The drawings 1 i Figs 2 and 2a hd have been revised N 2 5 Replaced with i 2 4 2 3a 1385 2 48 14 03 1 A 2 5 2 5a and 6 2a 1992 T am 6 2 1 I we we Cua We Qu ee adi SE Ma MAL DE ved HE ab EE Te vr mr ED Wwa we me DR Dos WB WM D wa w wap W u Gub mA aa may pap WM ate fone ess HER dep qu 9 det WEE MEE DEE VM Shu How MP Pup HE p wp aw cb AG We Sed AR Deb wa 4j gem HO Val ap KA an ow Druk OW PT Bielsko Biala 2000 466 82 50 353 FMI m 44 joe old iDate Signature FO alto PEER mon rm w WER cun WEE HEM que
41. ot interchangeable They are fixed on bolts with tommy bars without using of tools In the cockpit and the luggage compart ment the fittings for the oxygen equipment and transceiver are installed 4 3 Service before take off During the transportation of the glider the cockpit should be locked and the windows opened The air brakes can be extended or retracted The glider with or without the occupants can be towed by the front hook or by the tail lug having the posibility of free turns The ground towing cable length should be at least 4m The glider can be also rolled on wheels forward or backward At turns the tail should be pressed or the nose lifted 50 3 e Jem Um FM3 mma w DEE SEED w w w The rear seat can be adjusted in an unloaded condition as follows 1 Open the canopy and the securing tab on the L H fuselage surface under tha wing accessible from inside Shift the supporting tube to the left up to releass the seat pan Set the seat in the required position put on the supporting tube and close the securing tab 4 3 3 Locking of hooks In the gliders having TOST hooks they are operated from cockpit by pulling the releasing knob when the knob is free the hooks close automatically In the gliders having SZD III hooks each one hook opens independently when the near hook positioned tension cable is pulled pa w pet m w w mm w It is necessary to use the extending end The
42. rmissible airspeed in smooth air 416 e pax permissible airspeed in gust conditions 89 manoeuvring airspeed speed of full control surface deflection 81 e max permissible aerotowing airspeed 84 max permissible winch launching airspeed 59 e Rax permissible airspeed for extending and flight with airbrake extended 115 gt max permissible airspeed for inverted flight fin ssooth air only 97 2 2 Limit load factors positive C E E AE ao La 5 35 9 negative ooo od VR SAK T 2 65 9 Droxi UAN PT Bielsko Biala 2000 460 82 2 2 50 3 2 3 Colour markings of sirspeed indicator FMS dial Mie kts Ysa stalling speed radial green line at 38 Yo47 Va Morral operation S1 B range green Brc at from 38 to 86 Va Ype higher attention range yellow arc from 86 to 116 VNE radial red line at 116 i 2 4 Towing cable safety link The safety link of ultimate strength of 1520 lbfs 10 should be installed on tne towing cable 2 5 Restrictions SOLO FLIGHT ALLOWED ON THE FRONT SEAT ONLY GLIDER NOT APPROVED FOR NIGHT FLYING e FLYING UNDER ICING CONDITIONS NOT RECOMMENDED WINCH LAUNCHING WITH C G HOOK ONLY INVERTED FLIGHT ROLL AND ASSOCIATED AEROBATICS ACC TO ITEM 4 5 2 ALLOWED IN THE SMOOTH AIR ONLY AND WITH THE FLOOR BELT OF PILOT S HARNESS FASTENED FLICK ROLL ALLOWED FOR TWO PERSDNS CREW ONLY WHEN PERFORMED BY OCCUPANT OF R
43. sary to check the correct glider balance with balancing weights concerns solo flight remove the free elements out of the cockpit check the locking of back rest tube at the rear seat check the full deflections of controls having the belts fastened before the solo flight remove the needlass pillows and fasten the pilot s harness at the rear seat In the flight just before performing the manoeuvres it s necessary to fasten the back belts balance the glider with trieming tab on the airspeed of 60 65 kts i e similar as for towed flight e check the locking of canopy and air brake shut the window and airecondittoning tab 50 3 FM3 4 17 The schooling in aerobatics can be performed in the good horizon visibility conditions only w SE de wn n BEER m SE t BEE Se Pe BEd EE BEE SE Sm ee floor belt MANOEUVRE EE OT KEN kts 1 71 crew fone person t two persons a ce EP Wa OU of WA EE um de GOM M Oe Gp me QUU Cue e se EE DIR re ev 29 po ce en M Se ed Kw Looping stall turn l GO s9 3 90 105 ma cw ote mc OE HE D gt WA lt A Cm auam um HU MT ee COD Cw EER seg pe an ame HO VO wa SD CD OU WA WOW ce Spiral i 65 i 70 m ae Um e ow om OP FR RE
44. symmetry Insert the R H wing to the fuselage acc to Fig 5 aileron to the neutral position air brake retracted Insert the L H wing to the fuselage keeping the ailerons in the neutral position Obtain the connection of pivots and nests as well as elements coupling the control system After having wings in position lock the spars finally by the lever instal led on spar feet acc to Fig 5b insert the main pin insert the tommy bar into the hole in glass fibre member 50 3 FM3 50 3 FM3 6 8 4 31 and secure with the safety pin Assemble the R H half of a tailplane with the vertical stabilizer acc to Fig 6 insert the tubular spar end and the front fixing pivot into proper nests Connect the control system joint set up the elevator and trimming tab properly Slide on the LH half of a tailplane on the tubular spar protruding from the L H side of a vertical stabilizer Pull forward the protruding end of securing pin and lock it turning by go Connect the control system joints set up properly the elevaror and trimming tab After connecting the L H half of a tailplane turn the securing pin by 90 and press it back red mark must disappear Check all the connections and operation of controls Close the fuselegs upper inspection door m w exe ies aan een Se w wa w m 1 Pull forward the protruding pin securing 2 3 the L H half of tailplane and lock turnin
45. the releasing After releasing the cable pull the releasing handle once more snd pass into the normal glide Depending on the glider all up mass and the winch power with a cable 550m long in smooth air the gained height reaches 200 250 m Dr x O W PT Bielako Biala 26087466072 4 10 50 3 35 4 4 4 longitudinal tris in free flight The trimming tab allows for glider trim for solo light weight pilot within the airspeed range of 32 to 81 kts for heavy crew within the airspeed range of about 42 to about 116 kts Stalling airspeeds IAS Depending on the glider alleup mass the stalling speed in the straight Flight is of about 34 kts for solo lightweight pilot to about 38 8 kts heavy crew and all up mass of about STO kg The stall warning is in from of per ceptible vibrations of fuselage oscillations of sirspesd and over horizon attitude When stalled the glider drops down symmetrically in general and at further pulling the stick with tendency to drop the wing The stall in turn is preceded by distinct inclination to decrease the turn radius With further pulling the stick glider drops with tendency to increase the bank If however the tendency to decrease the turn radius is prevented with proper aileron counter action the stalled and strongly vibrating glider turns without dropping With air brakes extended the stalling speed in straight flight is of abour 35 to about 41 kts depending
46. ull the stick once more and deflect therudder tiil to the stalling into the opposite direction etc Orek OW PT Bielsko llia a 2000 466 52 4 20 4 5 2 The following manoeuvres can be performed only when the correct location and fastening of all 5 belts of pilot s harness is observed mar ma w MIS x on ME Crew rone person 1 two persons DN TR Tr ae a T Res EE EE EE ER Nt EL EE IE Entering the inverted i flight by means of 75 5 81 half roll 1 i m as w Om KE e su us OD m EE Pe C8 an a UMP TER A N e re e Entering the inverted i flight by means of i 90 i 37 288 25 28 0 iese SEE PRZECENA i i Straight inverted 1 i e n AO oe AN NIE dc I i Turns in inverted 1 pit luces MAINE ESI N Recovering from inverted into normal i flight by means of BR i me half roll 1 oom aM ue aue HIE wee pub GU EF ME on Qua GD mA ME e moe a CT CP OU C quor MED HO m we E My qe D Recovering from I inverted into normal S 59 65 flight by means of i i 5027757706 MEE MEE 99 us Controiled roll i 90 i 38 mw map dup Uu WA WU WWR WE Use WE VEE WA an TD ar W Houk add E E De po I3 tus OF A m EMR A HER i Controlled half roll i al Half loop half roll 108 113 uA dU qup me OD em or A WR SE
47. weights amount can be applied on base of the table of individual loading plan page 86 7 Rules for use the individual loading plan i 2 Ja 4 The balancing weights are required only in solo flight if the pilot s mass is lower than 70 kg The total load mass defined as the sum of real crew mass parachute included and eventual luggage cannot exceed to maximum value listed in the table Mass of single crew member parachute included cannot exceed 110 kg The mass of front seat occupant in the inverted two persons flight must not exceed 95 kg Rules for inscriptions to the table of individual loading plan 1 The inscriptions are made by Techn Check Dept of producer or work shop which performed the repair or replacement of additional equipment Lrux OV PT Bielsko Biala 2000 466 82 6 2a 50 3 3 Every time two tables are fulfilled ons remains in this Manual the second one is to be stored in the pocket provided in the cockpit In case the revision is made the page 6 3 of Flight Manual should be replaced with the new one with actual data On the same way prepare the new table on page 6 4 cut it off and place in the cockpit It should be inscribed Fact No of glider Actual additional equipment traneceiver oxygen equipment rear instrument panel Empty glider mass with standard equipment and additional squipment installed Max total load mass crew with par
48. wr c 9c oD s 930 Och A gt WR Wo Oh aD m ap ge Wo e WO CH 0 KM wia o Ma M mo CV qb 100 without pillows 151 151 15 i 15 151 15 15 15 15 15 110 without pillow 151 i i 1 1 d i BI XE INIA OF ER PR 23 DA US KE gu ER Ee TR 24 ux EETTETETTITETETTTECTTECTECETETESETETEFTTEELECEPE es ea ZWI 0S OT c 78 99v 0002 PLEA oss121g Id None GRAPHICAL CHECKING OF IN FLIGHT C G LOCATION Diagram valid for gliders of maximum allowable empty glider mass with standard equipment of 370 kg m ko i P example 136 re S8cr g ON 2024 WOJ sJepr 6 404 pTTeEA aBed 2 12 50 3 FM3 EXAMPLE Individual data of empty glider from table of weighing the glider on page 2 D c g m 372 kg M 235 kgm Crew Front seat pilot with pillow my 60 kg My z G1 kgm Rsar seat pilot without pillow m 296 kg M z 16 kgm Additional equipment Instrument panel of rear seat 5 2 kg 4 kgm transceixer 2 kg 2 kgm AT N e m 12 4 kg M 2 kgm Glider in fliaht mass tarta Z z N EE VEE EE ES iene rge m 372 60 96 12 4 540 4 kg Moment of glider in flight mass M s 235 81 16 2 136 kgm The perpendicular lines from points m 540 4 kg and M 136 kg on diagram of page 2 11 cross in point A which is in the dashed field The glider in flight c g location is correct
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