Handbuch Slingsby T21 - BGA 782
A.P.4309A, VaCI, Par/.r, SUI, A.L,7,,'May Section·. 1 PILOTS.'.... CONTROLS AND' EQUIPMENT LIs"�' 'OF CONTENTS' Po;o, Para Introduction I ,Instrument!l' 5, Flying' controls, i Seats 7 harness Lift spoiler c:o�trol '3 Flying 9 Tow release control 4 Horizntt,'ba;' 10
TLLUsntATlUN Ft, F/ying cont'o/s 'and instruments 1
A'H\ INDICATOR ] SPEEO' 8 OTTFUR. HOOK OUJCX-R�teAsl! T'UR�N:'ANO I�DleATOR" CONTROL '2 'SLIP' eOBn-sLATER; VAR10'ME'l'ER', ,FLYING iiMlTATfONS"DAl'A-'CARD ,3 . ' 9 4 ALn"fl;' T!!R 10' HOR,zoN DAR.s· ;'. BAi",1Uti:�STOWAG1:!. OTTPUR HOOK. RBLBA52 5 - if ...... < ·CONTROL PILOT HeAD ANO URl 6 sPot'CEi.... LeVE�' 12 VENT ASSeMBLY �FOR :,VO:T2R ,7 SWITCH fTl!.\' 2 13 TRAP F1yin'g controls I\�O ';�ments P.S.II .
Seite 1 von 35 Handbuch Slingsby T21 - BGA 782
. r J 't!o'duct1oli ��el? ts.rs b,��,Iij, ip. �.fi g;\ 1f.� -;:T, be;:tu rn�a n d :s} I P t.Jt·'C· ···. .'",., · · �is' . t to · a. :11��JCato�IS ,?pcrated �lectncaUy, tbe' power �l ;J�.:rhiS�s7ct!On i.n end:�d:· .�ser,,:e::.a3 se era location of all cocKpit ;bbLDg 8upphed ....by;dry.;batteries stowed in a : n l gUlde,to,tbe si�� � co'ri (fO\S a":d inst��rp en�l.:.. �
Seite 2 von 35 Handbuch Slingsby T21 - BGA 782
�,P,4309A,. Vol,'i, Parr 1, Sur:-\ :A.L.10, StPl, 70
T.T"T ·OF.:CONTENTS
Para: "6 ?�,��q4fic�!�: :t��.���igAi;��.:9·�� ' -,., posirfori. . . !,D efin{t/r?!!Of'£rr!J�r:f '!J! l!!}v. ilY �W;�g.hl�lWJi�ati�s 'r..' ,:,C.:G: d'!tu'i�i'�{ .c..a!�u'a!;�f!7I.. of.CIG�: PR!lt(012, S , , ," C.G:. li,�i" /" ' ' ·MoiJijic.,ipn( 10 i , . , ,
Introduction' ·tiiomC'Dti of aU' irems",placed, fonvard of the . Thtp�sc of this chaprer is d�cribe C.G·;·"iiatwn:·poin( 8.re··�egative;�·aod .of. those 1 • ... ro' place� aft of the arc positive.' the melhod of··calculating the, 'poSiUC,il of .the C,G:d.1rumPOint ccoue of gravity 9f-tbe gli�er; whe.o'loaded for fligh!.
).b Defini�on of c,cntr� of· g 3:�itY.· p!lsf��� . " � 2. The: positi�n: of Ll�e: C�:Dtrc' ·or. gravi,�:.i�: dcli..oed ,by itS-: distance/"�easured " puallel:',to, . . the fuselage d:arum lioe . fn1:�"a· referc;'nc� po�� rd"errcd [0 as' the'. e.G. ?af4m:poinh(ppr�,·.:A)) s the: po itioo Qf ,\'w'ltich is.;ar�itrarily:seleq:edt,�y. the m3Jlufacrurers. Thc,dislince is'.refcrred�·t'i as. !.he arm oC-.the:;C.G\ it:1'w be:.CaJcu1:it�d from the foUowing' expression:· :Ta�e, and . �elgb.t C.G:: , "," . " . ' � . .' t :. 6.,�;;Yhe, we ,wei�( 'of th� glider is 5981b'J Total'mome.ot. ,. '. , ·its·C.G . is 40·90 Of tbe ,.t."f1. _ ' f C G'· , I . iD:·aft ' C.G. datum and ., J"l.l1l.l 0 " � , i.' " . , ,ils is 24,458 Ib: io. 'positive. .. �; ·Tot.al.wcie:ht " moment ' Weight limitations " . T a..r�'·��·���t ;t-'SUD(�fload mom�DLS ' _ �':� i.: ' T.he:itiiovisiori,of the: C.G. is: beyond mc" a�:'i' iD. afc of.daniicCUt p'ri·ive.r;li.riUt':oC30.5 cait be. i:ori-cc;�d·by. 6ni.og·.thc� 40 Ib: b�UaSl weight. � in,the s{,Oy7'.lge00 the aosc of the aircraft; this �ovcs"�c:.position.of.the C.G.·fo�aid lO e) position 'within the C.G. limits, as shp�.in the ':, . . , ; " .: foUowibg ' ;' ; . . ;: ;. ' .; . Ca1cuJations :� . . ::.> ' . ' . . ' . . . ' • " . . , , , ': I ' , �"":.' ' , : , . . :, • � . : :: � • ,' �::: ;·fi::·:.;:'-��/'::'::<; :�: .:�:;:" : ::;i:.:; ; : �,;'! ' WtJght " .,Ann·· · . � Moment .. Tare weight ' ;�.:. :.:.: ;'� .:-�:.':" : . ' . :. (Ib.)�· :.::." ::: (lo.)·· .. ' (�b. aod moment. 98 ::;;;:;j;j:'9� : · ' . :�.; . in.) , i ; : .: :j ��I458' ��r..�:.'\rl�� . .. ' .... . '.' ,�::,\: Pilot :'180 . ',':::, 1.25 . ,,' , .,225 .' � . :" ' ...,'" .. ," .. �: ...- ' 'Pupil 180 "'::" 1.25 .;; ' 225 AJI-up Seite 4 von 35 Handbuch Slingsby T21 - BGA 782• v l . A.P .tJ09,4, . o . J# p",., J, Sect.S A. L.a, Apr.62 Section 5 AIRF� ,STRU�TYRE LIST OF'CONTENTS' P.", WIn; o1'ac:hm."' oo . . . : "" FUSELAGE· •• . . . ' .. ••• 10 .. , ...... OO . . ' ! ; p FIO. 1:10'- , , ...... ·:!P. Main plan. . . ". . f",1I;.lot;l .. f.l . . ,j. . , ... ·;J ... · .... ·' . I' ...... 3 , . • . ' . . .. ' Toll unit . . . . - . 0 ..(; t cmd/ng ...... wh��/. O1Id did .' �" ,.. :-r, . �.(_! ,; 2...... ... recessed . to t'Hovide wells (or the pilots' General. (fig;)) T. The fuselage Is 01 wooden construcUon. (eet.· The pUots' seats W'e loca ted between . . · Forward ot Ctame 5, the'wing resr attach� � rrame8 2 and 3. ·Pram e 3 (onns the back rest " . a com a. ment !.tbe' construction . ; o serni-' · tor the DUats and c mo es the para .ttame, . 1s: ' t . d t boxes and detachable stressed skin aodconsiate ot bullt--up'f'ramea chute seat.--backs.'· . ' . � . lnteJ'3D8.Ced ·;wlth· longerons and 'stringers. FUSELAGE NECK . � " The whole the st.ru�t�i:i"I�.(X)ver: .' oC t<:>rwe.rd . ed with aid panels Projections' (rames n tllywood Bk1n &..Dd the e " 3. ,4 jod 5 (arm . , . . horn the COCKpit, e ween frames and are .� pri ncip tile, ruselage neck. at b t 2 . 3, the al aUuCblrB 1n double. alt1nDed. Poet Mod.3S',. external : :and these lUe braced by diagonal members · all plywood fa.briC covered... �"at' Ule sides.': The ,. whole; neck' Is Plywciod ...... ". . . . 1s ...... , : :. ·oovered.. ' Dortions or forward ;; . �the thlfneck ' , 01 A " . . , • • " . '".1, • . atowage"ntted ' uie-no'8e'or�the and act trame'5 serving onlY. 8.8 1. A " " , .... ,,'"to , ...... �, : .!rame .4 . at '. J ' . . ; . .:. .I" . ..;. . , ' . .. . ' . cr c e . (a1rin"gs• gs are aJ'l.:.� COrflDll;l�t �:.:.a:� . • .. p� . i:'Pl� wlng. Ilttachme�t. fittin �.O,�l� . �:(.�.a.,st irori� , ballast "81gb\.' )ocate4iat the top o( 'the fUsela.geneck.. COCKPIT.: REAR FUSELAGE " . .. � . , . cockDU'provfdes .ide-by-olde . . ll 2. "'Th.. . " ' "" 'leii' The rear s ge Is' o( braced girder . '. '\ 1'� . ', . ..t.' tu ei ' . . , " seating and Is contllined the portion' or co n co r . ' " . c o and191abrlc v e .• , in' • � · ' nstru ti e d The , ,t'!.. : . ;' ': "�'" 'I . .' . roBin ' ' .� lhe fuselage Cram the nO se back. . " . components are ,the . . . ' . . . 3•. structural Bide. pMels; , ' . . . to tre.me. . . · ruc runs ;.co ! .f\ box. st ture tDWD the centre ot ,the ..� which n dst o( :top' and bottom:longeroos: cockpIt and tonns'8 division'b etween the '··interspaced· by' 0.' dia.gonal· brac.tDg.�system': box containstbealleron. elevatQ.r. w ' seats; this ' t o side' pa.nels are braced ' . n' ' '::The " •. • ...... together. bY : . . . ' . . ,.. ,.. ...q . rudder and li(t-spoller' control "runs," The t· :llwo" rurther' . ', d1a.goonl.' bracing' Srrstemsl that ," , ... � . . . . � rudderpedal& and · the ' o( the rear . ' . . . , �towingraleaS8 I • . . . a.rep)o·Unt·e� . . ' (ann top and bottom . tusels.ge; , • • . , , . . on e n : Lh � �l:(,�l�.B · ' undersld'-Is"Dl.Ywood· 000000B . The - ' ' ",'v.ted'tO".. . With: . .)! M? . '"�'� . . : . �. tno�ted. ol):·�trame.; .!.CQckpit·: tl9.0r. ,i.�lstand damage. ( 2.;:;Tb� C!Om.. s�De�A:h�,�?�.�, ��:��� stretches between trames jl. s.nd:2;.;th1a .�·;iB :."wheel·on 1aodio£.: RESTRICTED Seite 5 von 35 Handbuch Slingsby T21 - BGA 782 FIN ' ;5.:, The fin is built ictegral -with 'tbe 'fuse� fitted', ccntrally in the underside 'of the J3ge . � · The slern·post or the fuselage acts. fuselage, :,between (rames 4 and 5. The ;8S the fin rear spar, and a second fin spar,' nose skid' is anchored at the front to frame �forward of the stern-poSl, also acts as 9. I ;'·and is flexibly attached to frames 2 aad 'second rear· fuselage frame. by: • • ' 1 cylindrical. rubber buffers, wnich : " . MAIN PLANE General (fig. 1) which are filted with removable stcel. bushes 'in the attacnment holes.' 7. . The "!lain plane is �f w�oden mono.spo r ' construction and bUilt In two sections . which are joined together, and to the fuselage' neck. at the centre line with ,'12.,. � Trc wing rear a(tachment fitti'ogs uc shackle pins. The s(ruchlre is fabricc�vered.: :�mounted on diagonal spars aft of the main , spar.-=·�,.The fitting is a welded steel assembly, ;:and ·i5. bolted to the spar and through an . g MAIN SPAR ,angl e bracket to rib l. The dia onal -spar is curved at the root end, and passes through thc , 8. The main spa rs are straight and aT': rib I to take attachment tilling, the ., positioned at one third of the ,chord aft of outboard end',being attilched .to the maill the leading edge, they ilre of box construe. spar at rib 5. tion with spruce booms and plywood webs. ':-The spar is blocked solid at Ihe ' root and :at tbe strut attachment and' uilcron control FALSE SPAR' ., :.pulley positions,· Diaphragm members are ;fixed inside the spars' at, approximately every 13:�'-:: A raIse "spar is positioned outboard of second .rib position, rib . 14.:19': carry, the . aileron.' ..,This .spar is .buill'JJP.from spruce members nnd is: ply· ,wood covercd.�on its. rcar. face: (carries RIBS ,.\) �ye-bolt.��i��hjch . as ·.five�:rC?J��iry��d : . . ;:8cr· . aileron hinJtes, 9. The twenty-seven .main ribsf in' each ,wing are spaced one foot apart .�and are' constructed with a centre web of plywood,· 'the spruce members forming thc .structure· AILERONS of the rib beins'positioned on'· either side . of (his :'p\ywood web. Intermediate ribs 14.' ':'The�'''ai\�ron : struet ure:·' consists'" '0(;' a. are positioned between the main ribs in 'main "spar, a torsion spar and straight Ilnd diagonal ri main the oose bo.x rorwar� of the ' spar" these ' bs, The spar. is' straight extend from the Icadlng edge to the front' and is constructed from spruce members, which are plywood covered, heir forward face of Ihe main spar. OD t face... ; Five eye·bolts are fitted to the spruce members :to act as hinges, ,The torsion spar WING ATTACHMENTS only extends over the'centre portion of the ailerons;,:;t is 'positioned'four inches aft of. and tparallel'. to, the. main spar.".,';.,The: gap .. 10. ,The ·fronh attachment ·fittings :'3re' ' - ,mounted o� short, stub spars forward of between,these two spar� is plywood covered , .the molin spar, These fiuings form a link to form a �orsion box ..,.The aileron ribs are of similar'.construction to the ,wing ribs and .bet�een the port.and star\>oard �jngs, and. ' do not 'connect to the fuselage: line, up -.rp� position with. the "!U3.in ribs in the' wIOg.:: 'J'he' end bays." of the ail�ron. which :arc' not 'covered by' the' torsion' box, ·11. The' wing :rnain,·attachment'· 'fittings each have-=a'diagonal rib;Flhcse' ribs react are mounted on tnc main spars; ::.They are. torsion: 10'sdS':a,nd also' stiffen the structure , against 'the pull' of the fabric covering. made from heavy.gauge duralumin olates ' ' REST itl <;T.E Seite 6 von 350 Handbuch Slingsby T21 - BGA 782 Generai:.(flr:'.f) hmi��:u.f{t9,�io!l :_:.l?,ox·5�":I�c,aJcd·"'at. . the: reacts,' ' . C t;ul C,�9� e-.r;· ot;'t�e:?:5part:,and;���:: the :,5., 'J1.\"f t �: ,=,..ru C O nslst � : Q � .3 pl��,: · t�e · '. elevator: and � a ;'sine:le� fin(and :'rudder� ,�o.rquf;:loads :in:.the .portip�'.9f.; ele vator. :that:'crosses the :fuselal!e: :TAIL'PLANE �:�).��(�.el��at�r:!>per�t.�Dg 'i::!ever. . , !� '_3,-, 16,�.:,The tau 'plane-is of' tw�spar' construe >r.e1ded:fitt ing made:.p:onystcetplate; It IS . h - .bolte� to the torsIOn 'b x on the centre line -�on.'·'3�rh�� rear'; spar':, �� �: ��raig t ' and j,at o , . :�f�h·�'� sp¥.·: ;i:�iv�{�g�;�: in':�'th�. . angle.!.to:�c luselage: .�:r:hc l{'o'"!tsP¥: fonn of:. ngbt up on is pa.rall�l �o the le!lding edge, which tapers, 'ey�bol.�" ; pi��: �,th,�.:Je�,a1e hinges' the r . :soar' to �roount-�the, ' elc:v alar, Irom !!Ie ccntI�.:linc. o( the.f�selagc'.to.Jh.e ,tall�'plane .tips: FIN · \! is b n -: 17. :'The ' area .between �th · two�sparS�(iS �1� ij:��1:ti4j�\; \ �t'?'J �egr�rwith;: the . � ; e: 1usel · ta en' ·:up�\witl). ·}:,�e,:,ribi� /sevcJ} ••• d".,a .'·.st k s�ructure,' �tra.igh.��ribs b�ing 'position�4 :on i,eficfi':�id� of the ::,ce'ltre-linc,.'space5i ' :,ono\foo.t.";ap�; RUDDER. :and" tbree·'diagonal·rib!:: ..w!U,h ::rea,t.i.\�e .lS� rrpe·;-rUd.der, : �s-:,OJ :5Ulgle-sp¥: construe torQ loads on.:the ,tail .n��;:�9:� ��: fi�teq\':1,t�:, c · ue plan�: � �.��radyn� o _ Jlo�.e:.��anc��� , h� '1t.: ���::.th e: ,upper partl n )I plywood Att4chmenu jltt)i�,:·.s£.ar. "1Th�)10s�:p'.a1ance·js " ' ' . ..� . - " ; ': ' . ... r s ,' '' , ' . n . F9�yp �� :,:\��,...:." �as 't,fo,\m�If1 te,m� !:.nb. ,to :,18. ::"Th� :.t�-p]aDe .: : attacl;1m t ....t,? -;: t!:te . e ·mamtain lts. profile. 'fuselage' cOllSLSt9 of �four eye-boHs,dixcd :in blocks glued into thc"corpcrs fo�'ed by, · �';'rudder:-spi.i·i)�: ' from ��� '�T:be u,U l:lP . the and•. the outboard laces ',o!..the l? iS ; spars . -spruce":"members:' and:·. is�'plywood, covered centre ribs. 'T�c,nuts fa,r these �ttacbment ' ��""'''- .....,. ,-. ' , :ori�its�1o'rwaId face : :fittings are on ..top . . the. . ,Ihe. _surface: of ••••-� .. -, .. .. '. ' , . t'. '- ' ,- ,'-1.' ' taiJ .�I�e:.: The e :'19.::: r ar �par is .br�<;ed to th� fusc�g7: :by a strut on elther.slde.,�: The, strut.,attac,h-:; . : meat: fittings': �re<, positioned nt : ' appro,xl� mately. hall the semi-spm o( the . tail plane. ?Jld consist of, two ,"flange'd : plates �:--�h.\�9: t e are bolted o�eth r · thioll.l1b tbe spar,· 20. " The re",. spar o( the tail:plane:.ca.rries. ' ·the el�vator ,binge, 6.tlings:�which :':tons�t of fork-eoded .eye-bolts through the 'centre · ." -- "" " ... 'line of_ thespiu. ' " ' �::' '··rJle_�nic,ide, r .�. �-J)li��ge�:: �p��the: fin .by eye,bolts fixed. t o g .• one ELEVATORS hr u h the.sp.!il', bell1g' PC!�tione� just bel,?��'tb,e:Dost? balance and ' ,co�sis� . ' . )1..: .1he�.r\ey��a�" struc��r,e �o{ :,a: the other near. the bottom'·of:the soar ,. . _nQ.s . : front' spar ,anc;l diagonal .whicQ.. ::ex�.eA4. ,back-to the �railil.lg.�dge ��cnbc{':' ,lJ_\·-,,;T����·�dde�;o�r3..�n·g:;:.1�v�r'· i�: loca�ed f.!e.;;r� (.�ot �o� of!:the��p¥,: a t :the� uoctio� . � . J ·:·!:rhe\:cle�ator (spar,: :straight:::and,. ,Q( �t�e..l'9t tOlli.ri �,\"d.:JW9 t e di go ,21. ' is. I< �of:. l;1 . : a naJ .extends to the (ull. span of!. the tail. plane: .ti�s:;(!W:e le�er i� ma�.e7Iro.m:hi!�h.pl y wood · ' . _ . : '.It is'built up;[Iom spruce :members · and is .and � has .bra.ss bushes ;,lct ·.mtO:.lts ends to o c ;covered witb,'plywood 9iJ).ts fonvard:(ace,' J!-J<�.!.t.l\e� c )llle \io.n. P"-'_s:. Seite 7 von 35 Handbuch Slingsby T21 - BGA 782 . Seite 8 von 35 Handbuch Slingsby T21 - BGA 782 A.'. UO'A... O ... . I: ,,.,., I. SCC' l A.�.7._1' ·It riG. 1'. FUSELAGE RESTRICTED Seite 9 von 35 Handbuch Slingsby T21 - BGA 782 RUBBER NUT ATTACHMENT SKID Z ATTACHME BOLT 'RAIv\E PLATE SKID AHAG:HMENl SKID ENT WOODSCREWS NGS �t-rIf�� SPRI SKI � SKID . � TAIL SHOE) BEARER SKID WHEEL TAIL . ." 6) f'l f'l ",. U> o o A . '" r z , � . · () rn, (fl� --;0 -Gl rn O :::0 � :::O . Seite 10 von 35 Handbuch Slingsby T21 - BGA 782 "/ O.�. M �/N. 1!l!�N� "r sr R IC:rro Seite 11 von 35 Handbuch Slingsby T21 - BGA 782 N N .' . . � � . . ." ':' 1 · - I 0 · I ' ,· SK 11 'IIr \, " I � : ·. 1 L ," .... : 7 I r, ,T,A.! . ... ' . ·�·t . l' : · ' , . \ I BS , . - R S � . : J Sp AR RIB - GUSSETS� R E " " D AGONAL ! Y PLY I S D .�.L � B ; ' RUD TA:CHMEln .' .' ' RI ELEVATOR RUDDER I. PUSH.,.ROD 'i' AT � RUDDER , , I�MjEi - '� . , , , "'.::,." r� I " I .' - J , '!lI.!l.1: '!lI.!l.1: . I!ILPLA� U S:�S _ l '. ONA . - ' - .. T"'JLPL� T"'JLPL� � ELE',IATOR'SPAR I QrAG ..• ..• N r RO TAID:CANE ' , F ; � ' ' ; ; ;; .- , . :;, � :. m m "' � � � � :;� Seite 12 von 35 Handbuch Slingsby T21 - BGA 782 This le3flnued .wM.'A.t."' No.' 5. Oecemberl� 195' ·SeCtIDn�:'G FLYING '.!CONTROLS . . . . ,/. . .LIST ," . ,. OF. .CO ..NT.ENTS - .- " Pora. Para. " . 'I, .�. F.S./I Seite 13 von 35 Handbuch Slingsby T21 - BGA 782 'separate 'cables" tci:oe'taken off,'onc to eacll in'-';ihet,'closed position�, thus: locking 'it in to 'wing;"·, The, cables)n ter the \vings ' through the �winl!'. :rib l� \Vher�'they pass round � p,ulley ;' fr�m; 'here,they pass through the nbs to another,' 6, A)'Jension load on the spoiler cables pulley ',· between ribs 9,and 9B .. ' After opens' ,the spoilers' and the system is rc� passing round these pulleys they ...connect turne\l�tQ the closed position by an clastic to the spoiler ,operating ' levcrs:{. ·�Thesei cord� attached to the wing structure and levers are in tpe form 'of triangula, plates, connected to a lever positiOned alongside mounted vertically, the bottom ,. corners the trianrular oDeratine lever, forming the ' pivots ; the spoiler' 'cables' atta.ch to the rearmost corners and from the QUICK·RELEASE HOOK forward corners push rods take�the control 7, ,The quick-release hook is operated by to the spoiler operating horns" "The system the ' yel1ow�painted knob underneath the is so arranged that the thre� points formed centre of the dashboard, A cable from by the 'joints between the' sP9ilcr 'horn and this knob is'taken to the quick-release hook push rod, the operating lever' and push rod at t,he bottom of frame 1 ; this cable passes and"Jthe pivot of ,the opera�ing.:,le:ver pass through a Cairlead on the dashboard and thr�.':lgh.' dead cent�e w�eJ\,;!the ,spoiler';js round � pu!.lcy on frame 1: Seite 14 von 35 Handbuch Slingsby T21 - BGA 782 A,P,4JO'1,A. YoI. I, ',r< 2 SECTION '( HANDLING LIST OF CHAPTERS 1 'Genera' 2. Ground handlln, Seite 15 von 35 Handbuch Slingsby T21 - BGA 782 , This leo(Juued with ALfNo.�/, ·Se�,em�r. 19�'- A.P.4J(J9A,';Vo',"I. Port 2:.Secc!� 1 Chapter.. " GENERAL LlST� OF� CONTENTS Poro. Gr�und :cqufpment .. I liST OF: ,LLUSTRAT,ONS' , F1 , F12. 2· ''1 Access Fuse/ore trulles �'.::. r • � ' �onels and dra/nore hole; I � ',;., .... ' .... 1 .. ' GROU�D� EQUIPMEr"IT, 'stippQrt the ' fuselage"' d'�ring "rigging opcra-' � 1. ,Th.e ': foUowing';itcms' 01 ground'-e� !lip� tions ; these are simple,in 'construction and ' ment are' provided.for servicing�t1iefghder, should be co'nstructcd locally to the details', In ,addition" trestles',t:will be,ence'ded:tto given in' fig.1 ,2. .. , � .. ' R.f, No, Or" ,�o.: pucrll!,.tlo,!! App!ludoll ;,'." ,'" . B9ard .Mai.n-plan� rib.(No. and :2IB/4/1 inCi�encc ..'I', "A. .:: " 1 14 2lB /4'/2 Board '!tB . Mai'n-planc' rib:No. incidence :' 2S ,',I "'; :2IB'/f/3 Board dihedi'al �-:: C j ! , Mafn�plane 'r' , •• "" ' ' i' D ,; 2IB/f/4 Board incidl!nce ., ' ,Tail-pl.ne' " Seite 16 von 35 Handbuch Slingsby T21 - BGA 782. � r F.S.l1 A. P.4309A. vor. I, POrl 2. S.ct. l " A.L.S, Apr.62 ChaDter 2 ,GROUIID HAIIDLlNG liST OF CONTENTS ,Porc. Para, ... . . InlroJuc'UOl1 to 'l:�.1 ,�IC;:KET1NG. ... • •• _ ••.•. _.� "...... 00' ... .. • • • oo ...... 5 , .PA�KING.j. . GROUNO TOWING .. . ••• ...... •••...... 6 FITTING ANO 'REMOVING BALANCE By ,roetor...... '" ,'2. · By hand ...... oo. ... ••• .to ••• :, i ::.� WE1GHT'_ .'0 ...... 1O. .oo ... ,'" 8 ILLUSTRATION F1v· O"(ur qu''-clc:r.,�;."h �olc ., ... .; ... ':i • ••' �'.I." '" J 1,: Introduction Cltung on. the maln pIano, the third man ThIs ch ter Contains Intormatloll. on should 11ft the tall skid clear ot the ground, 1. . aP handling the gllder on the around. uslng .'j.hs'· UrUng poInt at the rear' ot the ruselage, .lorward ot the taU plo.ne. Care GROUND TOWING ' .' should be taken not to push or pull at the centre ot the maln-plane struts, and when By tractor moving baekwards, ensure that the ground 2. The glIder maybe moved In the rorwa.rd aft ot the tall le clear ot obstructions. whIch dlrection only , by tractor. and tor towing by might damage the �levators or skIds. this means, tile only point ot attachment tor the tow rope ,Is the Q.ltick-reieaae h,?ok in PICKETING the nose ot the tusslage. The tow rope must . . be I!tted" , wlUt . attachment , ri ng ' (f!.if.No. 5, ' Po st Mod. 40, provision 15 made (o r 26EY/4I) which mu et be Ineerted Into' the pIcketing the gllder. it should nonnaU,. be Quick-release hook w1th thelarger at the, two housed In' a hangar eIther complete or with ringe verUcoJ In .the operaUDg the the wings remo ved (Par 2, Sect.2, 'Chap-l). r1ng��ot' � t rele.ee hook (fig:I). During Utetowlrig'oper It, due to excepUonal condiUons, It 15 aUon Uto :gllder should bo held level by a necessa.ry' to'leave the gIlder In the open, lt ' man at tho wing tip. should be picketed by ropes attached.to'the rings on themain-plane struts upper a,ttach 3. The BPeedor the towing vehicle should ment mUngs to concrete blo cks or ground never exceed a fast walking pnce and on no pick-up rings, and the main wheel should be account should sha.rp wrns bo made, it 8 chocked tore and aCt. Additionally. the f.a.U sh8.Jl) turn 18 necessary.. the tow ropo' must skid should be roped down in a simUnr be disconnected and the gllder 'shoUld be manner and, it necessary, a turtherplckeUng man-bandled tnto its new direction {p1ara. 4}, poInt Is avullable at the release hook,", pro- viding the attachment Is either by a looped By hand cabl e on the hook or the correct attachment 4. The glider may be moved by hand In rin g (R ef.No,26EY/41). No oUter attachment either direcUon by three men, two ot whom may be used 'at this point as It may cause /. , ,� ' should push or pull at 'the strut connecUon 'damage to the "rel ease-hook � mech8ntsm ,. Seite 17 von 35 Handbuch Slingsby T21 - BGA 782 Balla.t may be placed the cockpit parklng the gUder on tannac, also In tt. 7. ; \When considered necessary. concrete,�:etc" in mode�te winds, the main wbeOl-. should bs cho cked lore and alt 'and "-' .... '. . PARKING the tall akld should be cho ckedon the down- wind'6Jd,;, to' prevent the g11der moving and .' turningInto . wind. , 6. Tbe gilder may be parked with one wing tip resUng on the KI'Ound. Tbe russiags �ould be across wlnd with the wing on the � 'FITTING·AND REMOVING BALLAST ground pointingInto wind. A sultable'welibt WEIGHT should be,phiced on: \he· wing tlp;';a heavy; . , dul;y motor !.Yre Is the most suitable olllect S; ':Whenthe a1",relt I."to·be now,,' ";10 to use 8s 1tcanbe'straddled acrossthe wing bY a llibt . welibt. pllot, the ballast welibt o wlthoutcaus1ng damage.If B.D.Y othert\YPe le !!tled .by elotting It Into. the container In " , welibt Is used It le lmportnnt th.t the the noseI, 01 the a1rcro!� Tbe welibt I. load Is evenly dlstrlbuted, on suitable pack rotatsd unW the hole in the welibt coincides Ing, over the plywood Up and that It does with theboles In the contalnsr, Tb. pin Dot rest on the tabric turther Inboa.rd. The attached' to the contaiher le pushed through . 11lt epollere should be lelt In the open poel thebol;u,,'1n ." .the'co ntalner and !l.nnly secured. tion when the gUder Is on the ground; they 111 this poalUon with a washer and safety wlll be released by the pllot belore tnke-oU, pin. Hl7 2lJ7 82.1S 37$ 4/62 BPAU:15 RESTRICSeite 18 TEvon' D 35 Handbuch Slingsby T21 - BGA 782 TOW rRQPE:ATTAC-HMENT"R I NG (STORES'lREFi26EV /41)' , - --- \" , \ \, \,��. � .------ , , �=--=___ tf��� _� ___ J-- _ -'� :- ;I-C\::::::- �, '-,-' _ "FIG." I::.;onFUR'QUI CK-RELEASE HOOK' Seite 19 von 35 Handbuch Slingsby T21 - BGA 782 A.P•• 309 A, VOL. I. PAAT �. Sf eT. � ,,1,..1, WAY, $9 FIG .1. MAIN .COMPONENTS RESTRICTED Seite 20 von 35 Handbuch Slingsby T21 - BGA 782 O O T NT NT HME ENT ENT M STRUT STRUT O WING WING T ACH ATTAC T TI WING WING RU �� �� LA G E WIN FUS S S '-Jr '-Jr o o � � a a NT NT 5 5 � � (i:;:o. (i:;:o. HME FRAME FRAME ATTAC AT AT iI= iI= ---- CHMENT CHMENT - - LEROr,j AI ATTA � --- A A @ T T - W - 4 4 EN - � � � FRAME FRAME � � - - ATTACHM AT AT q;;a. q;;a. D AR AR � � � HMEIil �P ATTAC r,jOSI;; r,jOSI;; �� �� '" '" -i -i Z • • m J: J: n :r )- » :j :j m r z .. .. » » » z J: J: '" '" Cl Cl � � 0 m n· -I -I -I ,. VI ,. ,. m Seite 21 von 35 Handbuch Slingsby T21 - BGA 782 A.P.430QA.VQLJ. PART 2. SECT. 2 AL 7. MAY. 5Q fRONT TAILPLANE ATTACHMENT � HINGE ASSEMBLY @ �""O f!j U I@ • � . """ ��J�E PU�L�EVSH�II�TBOP �O �R i:HATTuO�B�N6C&M&HMllilENT TAILPLANETAILPLANEATTACHMENT STRUTIQ f.-.J)--SPRINGS � ® TA IL SKIP HORN /-- RUPPERAT TACHMENT Seite 22 von 35 Handbuch Slingsby T21 - BGA 782 1 @ 1 I i @ . ® t;)@ I @ ® • �O ' �BUSH tcm.6�� SHIM (IF .EOo) CONE � SHIM (IF REO D.) .. CONTROL COLUMN CROSS TUBE fRAME 2�(- • Cl) " f.AME I "lD o RUDDER PEDAL S SPOILER LEVER WHEEL FIG. 4 COCKPIT CONTROLS AND LANDING WHEEL DETAILS RESTRICTED Seite 23 von 35 Handbuch Slingsby T21 - BGA 782 . Seite 24 von 35 Handbuch Slingsby T21 - BGA 782 I, rh!! leaf issued with A.L. No. September, 1949 A.P.4309A, Vol. I. Part 1. Sect. 3 Chapter 1 RIGGING AND FLYING CONTROLS LIST OF CONTENTS Para. Para. General I Spoilers 17 T"stllng ... . 3 Levelling ... . � FLYING CONTROLS Aileron control .. .. RIGGING 18 Rudder control .... 19 Diagonals .... 7 Eleyator control.. . . 20 Main-plane incidence ... . 8 Sp oiler control ...... 21 Maln·plane dihedral .... 9 Control cable ,tensions 22 roil-plane Incidence ... . 10 ..vleran (on(ro/ 23 Ta ll·plane level.... " Elevator control H Control surface movements Rudder control .... 25 General 12 Static friction loads 2. Ailerons ,. Aileron (onlrol 27 Rudder 15 E.levotor (antral 28 £lc't'Qwr .... 16 Rudder control 29 LIST OF ILLUSTRATIONS Flg. Fir· Rlnlng diagram I Lubrication diorram 3 Flyinr conlro/s 2 General tured locally, are illustrated in Part 2, 1. This chapter describes the method of Sect. I, Chap. !. rigging the glider, using a spirit level and a parallel straightedgc, at least 6 ft. 3 in. LEVELLING long, in conj unction with incidence boards, 4. To check the lateJ;at level, lay a straight Part No. 2IB/4/1, 2IB/4/2 and 2IB/4/4, edge on the levelling blocks fixed to the and dihedral board, Part No. 21B /4/3. front face of frame 3 (the rear bulkhead in lhe cockpit) and, using a spirit level, adjust 2. The packing referred to in the rigging the trestles under the wings until the operations (para. S to 11) can, for con straightedge is horizontal. venient adjustment, take the form of a long wedgc of approximntcly' 2 dcg. included S. To check the fore-nnd-aft level. hold a angle and i in. wide. Alternatively, an straightedge so that its top edge lines up adjustable level can be used and direct with the straight portion of the top longeron angular readings taken on the top edge of of the fuselage aft of the cockpit. Apply the incidence board, dihedral board or a spirit level and adjust the trestle forward straightedge, as appropriate. of the tail skid either with packing or by moving it, until the straightcdge is level. TRESTLlNG 6. An alternative method of checking the 3. : For all rigging checks the glider must fore-and-aft level is to set up a straightedge, be rigidly supported so that the rigging on any convenient support, at a distance datum lines are horizontal ; trestles should of approximately 15 ft. from the side of be pLaced under the fuselage a.t frame 2 ·the fuselage, approximately parallel to the 'and forward of the tail skid, and under the longitudinal centre line of the glider, and main spar of each main plane, adjacent to at the same height as the top longeron. the main strut attachment fittings. Suitable Level the straightedge and sight across the fuselage trestles, which can be manufac- top edge la the top longeron. F,S./I Seite 25 von 35 Handbuch Slingsby T21 - BGA 782 RIGGING DIAGONALS used under the straighledges on the port 7. Check the diagonal measurements with and starboard sides (at similar positions a tape measure, observing the following along the main plane) are bo�A at tile points :- sanu: ePld of the incidence board the difference between the two must not (I) Always select exacUy oppo,ite points exceed :- when taking port and starboard measuremen ts. Inboard position Rib No. I-it in. (2) Pull the tape to the same degree of Mid-wing position Rib No. 14-n in. tautness Cor opposite measurements. Outboard positiot� Rib No. 25-1. in. (3) Note that the limits given on fig. I are If the!aCkillgs are at opposite ends the not exceeded. sum 0 the two 111ust not exceed : MAIN·PLANE INCIDENCE Inboard posilio1L-u in. Mid w;"g positi01L-U it�. 8. To check the incidence of the main Ol,tboard positio"�1r in. plane, procecd as Collows :- (I) Hold the incidence board, Part No. MAIN·PLANE DIHEDRAL 21B /4 11. so that it rests on its two pointcd lc�s on the top surface oC one 9. To check the dihedral of the main plane, of the malO plancs, at rib No. 1 (the proceed as follows :- root rib), with the long rectangular (I) Place a dihedral board, Part No. leg in contact with the leading' edge. 21B/4/3, on one of the main planes Place a straightedge on top of the so that the longer leg rests on the incidence board and a spirit level on nose ply at rib No. 2 and .the shorter top of the straightedge. The in leg at rib No. 8 (the inboard end of cidence is correct if the straightcdge is the spoiler) : it must be parallel to, level. If it is not level. raise the lower and approximately 16 in. aft or, the end of the straightedge by inserting leading edge. Place a straightedge on packing between its bottom edge and top of the dihedral board and check the extreme end of the incidence witli a spirit level. The dihedral is board, until the straightedge is level. correct if thr. straightcdge is level. If (2) Measure the amount of packing in it is not level, raise the lower end of serted ; the incidence is within per the straightedge by inserting packing missible limits if it does not exceed at the extreme cnd oC the dihedral board until the straightedge is level. U in. A corresponding adjustable level reading, taken direct from the (2) Measure the amount oC packing In top edge of the incidence board, is serted, the dihedral is within per o deg. ± i deg. missible limits if it does not exceed (3) Using incidence board, Part No. n in. A corresponding adjustable 21B /4/1,. on the same .main plane level reading taken direct from the at nb No. 14, repeat the procedure top edge of the dihedral board, is 0 given at sub-para. (I) and (2), deg. ± t deg. (4) Using incidence board, Part No. (3) Cheek the dihedral of the other main 21B 14/2, on the same main plane at plane in a simiLar manner. rib No. 25, repeat the procedure given at sub-p.ra. (I) and (2). At this Note ... position the thickness of the packing The dihedral auglc of the port m.ain must not exceed It in. (adjustable plane flU�st Mt diffe r fro m the starboard level reading 0 deg. ± ! deg.). mai" plane by 1II0re than 1 deg. ,' there (5) Check the other main plane at similar Jo re, if the, packing used 1mder lite positions. straigMedges on the port and starboard sides afe both at the same end (;J the Note , .. dihedral board (both olttboard or both The angle of incidmce of the port inboard) lh, difference oelluem the two main plane must 1LOl diff er fro m that must 1�Oe excet:d u in. If the packings of llse starboard main plane by more are at opposite ends the sum. of tlae two . than i deg .. thtr Seite 26 von 35 Handbuch Slingsby T21 - BGA 782 A.P.4309A, Vat. I. PQJ'I 2, Sect. 3, Chap. 1 (A.L. 6) TAlL-PLANE INCIDENCE plane). Move the control through its full travel and check the movement of the 10. Place the tail-plane incidence board, ailerons; the correct movement is in. Part No. 21B /4/4, on the top surface of 5·4 in. upwards, and 3·6 in. in. down the tail plane, on either side of the fin, ± t ± t ward. Adj ustment is effected at the fibre parallel to- the longitudinal centre line of ' stock blocks on frame 4, either by filing the fuselage. The top edge of the board or renewal. will be level if the incidence is correct, jf otherwise, place a straightedge on top of the incidenCe board and level it with Rudder packing inserted at the extreme end of the incidence board; the packing must not 15. The neutral position of the rudder exceed n in. in thickness. A corresponding can be established by sighting from aft adjustable-level reading, taken direct from down the centre line of the fuselage; the the top edge of the incidence board, is 0 balance .portion of the rudder should also deg. ± t deg. be in line with the top of the fin. The foot bars of the rudder pedals should now be all in line with the frame to which the TAlL-PLANE LEVEL rudder pedals are attached. Move the rudder through its full travel and check 11. Remove the fin fairing and place a that the movement to each side of straightedge on the top surface of the tail the plane, parallel to the spar and just clear of neutral point is 14 in. in. Adjust at the elevator operating rod, so that the ends +5' the stops clamped to the cables aft of rcst on the gussets on the fo urth rib from frame 4 the centre. Check with a spirit level and, . jf required, raise the lower end of the straightedge by inserting packing on the Elevator gusset until it is level; the thickness of the packing must not exceed fr in. A 16. To establish the neutral pOSition of corresponding adj us table-level reading, taken the elevators, place a straightedge obliquely direct from the top edge of the straightedge, on top of the tail plane so that it passes must not exceed 0 deg. ± t deg. over the centre line of the fu selage at the leading edge, in front of the fin and over the inboard trailing edge of the elevator. CONTROL SURFACE MOVEMENTS The neutral position is 1 tt in. below the bottom edge of the straightedge. The General control column should now be vertical 12. The range of movement of each fo re-aDd-aft. Move the control column control surface is expressed as a direct through its full travel and check the move measurement from the neutral position of ment of the elevators ; the correct move the trailing edge to its position when moved ment is 7·6 in. ± t in. in both directions. to the stops in both directions. Adj ustment is effected at the stops on the front face of frame 4. �3. The neutral position of the ailerons IS reprcsen .ted by the adjacent trailing edge Spoilers of the mam plane. The neutral positions 17. The movement of the spoilers is Qf the rudder and elevators must be tem measured from the rear edge of the spoiler porarily located on a trestle will which recess, at the surface of the main plane. r�main in place dul'iog the checking opera- to the top. rear, edge of the spoiler. The tion.). . correct movement is 7-, in. ± I in. and variation in movement between port and Ailerons starboard spoilers must not exceed ! in. Adj ustment of both spoilers is effected at 14. With the control columns vertical, the turnbuckle in the control cable in Jat��ally, there should be no droop (the the cockpit. and of each spoiler individuallYl traIlIng edges of the ailerons should be in at the turnbuckles in the main plane, aft line with the trailing edge of the main of the spoilers. , F.S./2 (A. L. 6, Oct. S8) RESTRICTED Seite 27 von 35 Handbuch Slingsby T21 - BGA 782 FLYING CONTROLS AILERON CONTROL (5) Check the static friction load (para. 29). 18. The aileron control is rigged and ad· justed in the following manner:- ELEVATOR CONTROL (1) Set the control column vertical and 20. The elevator control is rigged and temporarily secure it in that position. adjusted in tite following manncr:- control Check that a line drawn through the (1) Set the column vertical fore (2) and-aft, and temporarily push-rod attachment bolt holes in the secure it in that double lever at the aft end of the aileron position. torque tube (aft of frame 4) is horizontal. (2J Adjust the connecting tube between the Connect the lower ends of the push control column cross-shaft and the control (3) lever on the rods to the aileron torque tube lever and front face of fr ame 4 until tile the upper ends to the levers on the main centre of the top hole of the contro!" lever is plane root ribs. and adjust the length of the 11 in. fr om the front face of the frame. push-rods until the levers on the main (3) Connect the control cables at the turn. plane root ribs are parallel to the root ribs. buckles on the control levcr and at the lever Connect the inboard cnds of the aileron in the rear fu selage (the cable with the (4) shackled end is attached at the upper position contl'ol cables to the control levers on the root ribs (the longer link-plate is attached on both levers) and adjust them until a line to the lower arm of the lever) and· their drawn from the pivot point of the lever in outboard ends to the aileron levers (the the rear fuselage to the top cabJe�attachment hole is inclined forward at an angle of71 deg. cable with the shackled end is attached to the lower lever). to the fuselage datum (the top surface of the deck under the tail plane). The tail (5) Adj ust 'he cables at the ,urnbuckles, plane must be removed for the purpose of accessible through the panel on the under this adjustment. side of the main planes between ribs 5 and 6, Connect the elevator push�pllll rod from until the trailing edge of the aileron is in (4) the lever in the rear fuselage to the control line with the adjacent main plane: trailing lever on the elevator, and �djust it until the edge. elevator is in its neutral position. (6) Check and adjust the aileron movements (5) Check and adj ust the elevator movcment as instructed in para. 14. as instructed in para. 16. the cables to the limits given (7) Tension (6) Check the tension of the cables and in para. and lock all adjustments and 23 adjust to the limits given in para. 24; lock connections. all adjustments and connections. Check the static friction load (8) (para. 27). (7) Check the static friction load (para. 28). RUDDER CONTROL SPOILER CONTROL The rudder control is rigged and 19. 21. The spoiler control is rigged and adjusted in the following manner :- adjusted in the following manner:- Set the rudder pedals so that thc foot (I) (I) Connect the cable at the turnbuckle in bars arc in line with the frame to which the cockpit, at the shackles at the port and the pedals are attached. starboard wing roofs and an of the operating (2) Connect the cablcs at the turnbuckJes levers in the main planes, and adjust the on the inboard rudder pedals and ut the tension of lite cables until they are rensonably control levers on the rudder (the cable with tigitt when the control lever is fu1Jy fo rward the shackled end is attached to the port against its stop. the rudder and the starboard in lever on (2) Move the control lever in the co�kpit to board rudder pedaL) its full extent aft and check and adjust the (3) Adjust the cables at the turn buckles spoiler movement as instructed in para. 17. until the rudder is in line with the centre . (3) Release the control lever and check that line of the fuselage. - the spoilers are flush with the upper surf�ce (4)�heek and adjust the rudder movements of the main plane and that. the operatl.ng as . instructed in para. IS and lock the levers in the main planes are In contact With tumbuckJes and connections. their stops. RESTRICTED Seite 28 von 35 Handbuch Slingsby T21 - BGA 782 I A.P.4309A, YoJ. I, ParI 2, S�cl. 3, Chap. (A.L. 6) CONTROL CABLE TENSIONS STATIC FRICTION LOADS 22. The tension of the control cables 26. The static friction loads of the controls should be checked wi th a S.M.E. Mk. 3 should be checked with a spring balance tensiometer (Ref. No. IC/6134) at the applied at the positions given in the fo llow positions given in tbe fo llowing paragraphs. ing paragraphs. When checking the load, They should be adjusted to the tensions move the controls thtough their full travel stated. in both directions and take the average reading. Aileron control Aileron control 23. AppJy the tensiometer 10 the cables, 27. Apply the spring balance at the top accessible through the access holes in the of the control column; the average load underside of the main planes, between ribs must not exceed 4 lb. 5 and 6. The tension should be between 40 and 50 lb. Elevator control 28. Apply the spring balance at the top Elevator control of the control column, Since the weight 24. Apply the tensiometer to the cables, of the elevators affects the spring balance accessible through the triangular door on reading in both directions, the nverage load the port side of the fuselage, aft of the will be half the difference between the cockpit. The tension should be between readings obtained during fo rward and aft 35 and 40 lb. movement of the control column; this must not exceed 2i lb. Rudder control 2S. The rudder control is automaticaUy Rudder control loaded by the rubber compensator cord in 29. Apply the spring balance at the fo ot the nose of the fuselage. Its tension need bar of the rudder pedals; the average load not be checked. must not exceed 71 lb. F.S./3 (A.L. 6, Del. 58) '.11 )423'0 11151 316 O.B,48,LkL Op.:rI6 RESTRICTED Seite 29 von 35 Handbuch Slingsby T21 - BGA 782 A.P. 4J09A. Vo l.!. Pari 2. S'CI.J. Chop.!(A.L.6) CHECK INCIDENCE C.HEREI�. � �� \. � x \ = = :2 CHECK INCIDENCE HERE CHECK DIHEDRAL HERE RIGGING DATA HORIZONTAL DATUM LINE IS THE TOP lONGERON AFT OF FRAME 4 MAIN PLANE OIHEDRAL li- 1 i· INCIDENCE 2- t: i AT THE ROOT MAINTAINED TO RIB 14 11 BOTH WINGS TO BE WITHIN 1 t· TO EACH OTHER I' TAILPLANE . " INCIDENCE 2- 1';° WITH DATUM LEVEL " DIAGONALS A. r. - A, 2. !: 2� r--==".,;SPOILER� � 6.1. - 6.2. 'I: C.i.-C.2. 'f WITH WINGS LEVEL WITHIN TOLERANCES TA ILPLANE LEVEL MEASURED· ON TAILPLANE SPAR TO BE WITHIN 1 iO SPOILERS TO BE WITHIN i" OF EACH OTHER WHEN FULLY OPEN AtLER(JN ' ' RUDDER MEASURED " " M'tASURED AT ·x· VATQR MEASURED AT y AT I Fig .1 Rigging diagram (A.L.6, Ocl.se) RESTRICTED Seite 30 von 35 Handbuch Slingsby T21 - BGA 782 \ \ /. •/ ./ / Fig.2 Flying controls Seite 31 von 35 Handbuch Slingsby T21 - BGA 782 I. A.P. 4300"" VOL. P... RT 2. S"tCT;'; AI...7. MA, �D- PIILlL" � • AlL � ATTACHMENT PINS • [ • OIL ANTI- F'RHl.(\ / OM-I$O REF. No.J"B.I'100550 {j) r.REAS( LOw TEM!3RATURE XG· 27� REF. No.,)"B/OOO�''2 or 34 BfPOO513 FIG.3. LUBRICATION DIAGRAM RESTRICTED Seite 32 von 35 Handbuch Slingsby T21 - BGA 782 Thl. J&(J( Is$ued with A.L. No. S, Oeumber. " 950 A.I.4J09A.',VoJ. "I" Part 2 Section '2 ASSEMBLY. DISMANTLING AND REMOVAL LIST OF CONT�NTS. Para. Para. General . , Elevator control...... : : � ...... :"1 " .... ';' ' .... 7 , '\" ... ASSEMBLY t9!rinvs ,�.... • ...... -, .. 8 �. .REMOVAL Moln plones 3 · .Ta ll plone Ailerons ...... , '�"" 10 4 ' � Alferon control ...... 5 Rudder .... ,,.,.� .... "'- ..... : , o!.... ."" .. .. . 11 . " Spoiler control .. E/�'v�to, . , .. . . • .. 6 ;,; ...... 12 LIST OF' ILLUSTRATIONS Flf· .. I • Ma;n components ..... , ,,' .... Tall'runlc and toll IIdd oUachments ... . . ; Main·plane auachmenu ' 1 CockPlc comrals and lond'n, wheel detail)' Gt!lnt!lral will'� bel'receiyed;.broken I.down.; into the 1. ::The purpose of this '.chapter .ds � to [P1l9�ving.:coqlponents': �} describe. the method of .· assembling t,the. 'F4s�lag'et ,�bipple ��v(th! nil';and I rudder glider from its main components ·a.ndnthe � ':utd �.t all: removaL of individual . items of the '.main 'P.lap<;:.s.tru t�; ·ana. components. Neither the p,ismantling"o f .PQ,rt :Siarbo�d' ,Wi.iigsj iq�mpl Tail. plane-to-fm. fairings:, 'f 2: 'The: glider is so designed that it can , . . .. . '� easily be assembled and dismantled without A�tachment" and locking',pins' (these are the use of special tools ilnd equipment 'nonnallyt! packed ' in "a' .canvas bag other than fusela£e trestles, It nOnTIallv stowed in -the cockpit). ASSEMBLY· •• • '. .. � MAIN PLANES rI. . . .. , . . . With .one man;at... the wing tip. one - - . . '(3\ ' . . 3.'\.:. ,.;The . method . of assembling' the '.main under ,th_e ma;n spar at. the ...wing . root planes to the fuselage is as follows :'-:" ', '1 and'.'one· man'lsteadying the 'wing at I ; '. , .' I' j' (I) Support the fuselage in tbe rigging the ''roaPI trailing,ledge, lift . the ' star position (Pari 2, 5,,1. 3, Cllap.• 1), board wing and align the "wing root either by one man holding it at the attachment jiltings with .tbe .attach· side oC the cockpit or in fuselage ments 'pn the 'fuselage neck. I trestles (Pori 2, Sect. I/� Chap: 1):".\" l1 i riisert the m';';n;''spar--attac!tiPent pin ; (2) ! Attach the' two main-plane struts to t!Iis: ·�hould,;'b�;'-.c;to�e. . frami the port the · fuselage �with; half-inch','diameter Side oC the fuselage by the:..man .who shackle 'pins,' inserting them' from the was steadying Ihc.. frailing �!Ige. Lock front. p Lock the attachment pins with �qe :at��AAqi�.�t: pif},;� th �·.�afety. pin. ,;mCety, pins and rest the outboarc;l. ends (?) AHach;;.the. • \�ng"�trut Ip, tbe main of the struts on the �round. · plane with a half-inch diameter shackle F.S·II RESTRICTEDSeite 33 von 35 Handbuch Slingsby T21 - BGA 782 �. !H:�Sep�. oeki pg :i:pins · � i�)·!a·; Sir'nil�) m.�Mc;r��o )h�;,tail. plane.�a ttachmen t.: pn.l�t.er·glide.r.s.. the.struts are attached; Y6Sh�shackle .spins:� whic!t;.tsh�uld 'i, bc'� pu�hed.. home and JQcked. with a'safety 1 I!� (6) 'AILERON CONTROL 5�� ConnecHthe "aileron control lJy�lining' (7) Ass,emble;"th,e �p�rt;::winv:"l'lnt1C.!l;tnlt;" in �P.�t!>�)'"'!. of: ,tbe pusb-rod ,in, tbe fuselage a slffiiladinanner� !le£��ynthA.tJ).e '·lcve..t.�t . t,hc ..w !ng ..,oot :,anq, 8 ��er.t!ng.$.a�shac��;.pln :�tlockyJhe �sback.lc: ( ) D1n�W1th'arsafetv OlD. 'SPOILER 'CONTROL 6. Connect�Jhe' shacklest-'at ':the� cnds"'o! the,'cables:which' pi'otrude' fromlthe fuselage: neck;ait�of rframc'5'5."i�o ', the !cO'l)t�ol'i cables: protrudiniH trom" the, lmainMpiane� .root -' ribs' aftlof 'ftlie1"diaEonal spar;"' ELEVATOR�CONTROL' 7i' Coimect·the elevator control,"'by.joining: lll e1pu'sh�iod; from1 UieJ elevator�lever :to·. thc� con trol'l.leve{· ini; the l' rear� fuselage �' With ·tii� §l{ackle'f:prn�';j'i{ r;�ck ': the :shacklel;pin ::wi th'· a� fafetYJ'pirl :ig.The "ele�ator.icontiol ('push:rod: iiormaUy�re�ainsIattached ' to �:the, '�levatorl contrololev er1 when! th'e -'!lider,is'dismantled� --... Note ..•.. T.he·�1>ins.W miJsJ· Jliari1rfiiii!l�Wh1z1lt1.{ �,'iiuri)fonlv":"lI MVrl1i',i:rffi1li'lilh'Tiiffillil1 in"Jwilh.f"a�hiirm)1i� '(3) AttachWtIii\=!lll,y,lan�ffiit: REMOVAL Seite 34 von 35 Handbuch Slingsby T21 - BGA 782 Gl\ Jlte" ailerO�"'''I,tVf.l'J)d(al'l.'tn.e: ELEVA"[.O K �upporte pmg " }�m:;;.. of . the l"lS '9\1t:, Pip.�es mUS nbe�TemQy£4.:from; M'��ered.. 'J.� .��e. ·J�P: en4:-"1>��Y�. f2: 'trncwtiij..plane a �ne ' tevcrse..J.Il�nner t9�that r.-\!..u,}b er:, :�a; ,p.qs� l1on'lv..f Jhese �wa'sher� U:ie fHsclflp'C; in'''a sh be.. ould .... noted. pllcnlfor its.;a."sembly..tm.para �'" belore the, RUDDER e.uNator can be rcmo¥oe.d:.. The,.cleyator�is·. . e o then' remov.ca ";,n a. '�iin!1;!X malUu::r;. �.o�··tne 11 J.r B� 't�d.q r�-LS.�cn: y�� a, 10 'a' siin!lar t m an n cr.�to .. thc.jrulerons � (Pa:r.!i.11.1 0). aileronsA(pai:a.! 1.0)' f.S./1 :01610- WJO'Ill 'U/U ·,60 ;O.D . •U.t.Ld ,.... OIl.lG Seite 35 von 35