NAME NOM AVPO AIRCRAFT LT:J --- INTER~DEP AR'l1·~A:, W.HORAmlli.".tl l~te: May 10 1 1956 To: Hr. S.E. f-!arper - Chief Experimental Engineer -om: Mr. J .w. Aioos - Chier Test Engineer {Structural and Mechanical Sub ect: MONTHLY REPOHT - AP!UL 1956 The monthly report for April, 1956 has been especially prepared with respect to the Cl~l5, to cover each t,st job thut w~ have handled on this aircraft. This was dono in order to provide the R.C.A.F. with a sUlllllary of the teirt,ing performed to date as ,,ell as a status rep:>rt on the work in hand. Future reports will revert to the normal te~hnique of recording jobs in work only. Copies of this report have been sent to the reci.pients of this memorandum, 'll'i.ve extra copiec> are delivered herew3:, h for your use, &nd dhlribution to the R.C.AoFo (lassihculio;, c,in,_,'-,1tc .;, ,011ged to ............. - ~~ b ~ uthori ✓ / ~deye) 1° Ames Y' ~~n ......... .......... hief Test Engineer :Si /. ............... ... .. ........ ........ ank.~~ .. - Cfstructural and Mechanical) JWAtec CCc Ro Adey rl.. Lindley P.P. Mitchell H.. Smallrnan-'rew 1-1. Pesando E. Boughton J. Scott Central File File NRG - C \STI J.H. PARKIN BRANCH J U IN JU N 8 1995 ANNEXE J.H. PARKIN C NRC • \GIST ~ 2635 Brake Syste~-E-ralu~tion of Pedal Loads vs .:lraldng Effects. X?-0850 ~ 6.36 Leak Test on Bl~d Air Engine Disconnect X?-0822 ~ 637 Test on Marrnan Jll Type Joint Assembly X7-0822 2638 Resistance Test of Wire i,o Spee. Avrocan 5-715 M-ll<>t> 2639 Alternator Failure Investig:1.tion 5-675 2640 She;.r Pin Tests-Anti-S!:rl.n Parachute 5-008 -\-2641 Stu.tic and Fatigue Strength Tests on Skin~ X7-08&:J Splice at Transpwrt Joint _____, + 2642 Strength of Rib Panels - Ma.in Torque Box X7-086o + 2643 Test of Duct Mounting Rollers, Clamp~ and lnsuh.tion X?-0822 \.--261.4 Static & Dyna."'1.ic Strength Test on Port Side Engine Mount Fittings X?-0862 ~ 2645 Static & Dlnamic Load Test on Starboard Side Engine Mount X?-0862 ~ 646 Strength Test on a Typical Outer Wing Rib X?-08&:J -t-26!+7 Investigation of "Dieseling" Possibilities in H.P. PneUl'l13.tics of l!mergency Landing Gear Lowering Systemo X7-0892 1.2648 Engine Shroud Test X7-0S54 x .2659 <,2660 lr" 266l .2662 ~ 663 -\" 2664 Strengtl-i of Nacelle L«tcn ClOO H,vdraulic S~ • tem Fit ·,., -·~-Leavage Strength of Outer Ta.ilpla.1, Hinge Pracket Asserr.bly Vibration Tests of Hyma.tic Pressure Regulator Production Engine Duct Testa Performance Test of Special Dry Cell Batteries Voltage Brakdown Te~t on Sample Hea.der for Relay cs-R-·131 Pressure test on 6/10 Scale Engine Duct Driving Torque on Tuning Mvchansim of RlOlA/ARN-6 Radio Compass Endurance of Thin-Walled Fuel Pipes with Flexible Couplings En.du.ranee of Thin-walled Steel pipes with flexible couplings Model Test of Worm & Gear Engine Mount Shear Pin Strength Test Temperature Cycli.ng Tests-Windscreen Glass Vibration Test on Air-no-Fuel Valve ~'-; }- PressureTesta of Transit.ion Duct (heat Exchanger-to-Turbine) ? Side Skin Access Door Shear Test 1-06/ 5··008 X7-0!U6 X7-0850 X?-0813 X?-0800 X?-0816 X7-0819 X7-0858 X7c-0854 X?-0852 X7-0816 X?-0854 X?=0856 tl'-' o/ ~ \- 2666 E.valuation of Voltabloc Battery vo-15 X7 0852 Y2 67 Model Te~t of Modified Simmonds lAtch X?-0858 ~ 2hb8 Pressure Sealing Qualities of Ball Bearings X7 016 6 \ 70 Shear Strength of Hon~ comb Adhesive X?-0859 ~ t2671 \" Vibration Testing of Complete Aircr,!ft X7 0800 _. ,-2672 Remote Deflection Indicating System 96600-3131-XXX , 2673 St,1tic & Fatigue Test of .Elevator Bell-crank X7 0882 Lever ~ 2674 Static and Fatigue Test on Rudder Control X7-0884 Lever 2675 Investigation or Elevator Links X7-0815 2676 l-'J:,eliminary Tests Of Ruider Hinge Moment Limiter X?-0815 k 2677 Evaluation of Aileron & Rudder Control Valve X?c-0884 ~ 678 Evaluation of Pilot 8a Transfer Function X?-0815 - -\--2679 30 KVA Alternator Pressure Drop X?-0800 Qualific1.1tion testing for April 1956, ha.a proeressed at a uniform rate. Two more items have been g:i. van Equipnent Approval bringing the total m.m!ber. of approved i tems to !:'tv,;o A nUJrfoer of qualification test reports end qualification test proposal.a nave been ,.eceivedo AS n:uch time as possible has been spent on anazy:dng these "eports a11d propor 1ls, and :informing the nmdor of oui• find}ngso Various vendors have been viai ted by one ,or more mw:Jll.,t;~S of the Quali.f"ication Test Group during the last month. Mr. R.H. Stuart and Mr. Fo Halpin havt. visited Dowty Equipnant of Canada LimH,ed several times to discuas Qualifi~ cation tests. Mr. I<.C. Brown has spent some time a.t P.S.C. Applied Research Limited discussing testi ng wit h them and outside vendors. A consirler:,ble number of meetings h3ve been held at Avro with visiting vendors. R.H. Stuart and KoC. Brown att ended the Second Annual Meeting of the EnvironmGntal Equipnent Institute held in Chicago; Illinois, the 19th and 20th of April 19560 While in Ch:i.cago LC. Bro~m visited Inland Testing Laboratory to see their test facilities and discuss specit cat.ions in generalo i;, • april 17 ~ 1956 the 1.tualificat.ion Test Group movt;d from the Structural and Mechanical Te;:.t Office to a tempora.:ry location at the back of the Stress Office. !!'he move has proven advantageous because of the proximity of the Purchasing and Engineering Officeso At present there is a ba.~k. log of work such as reports, proposals and specifications requiring anal,yzing. It is a.nticipa.ted that the back log Tdll continue to gow and that additional staf,"' will need to be addedo >pr·il 195b lie22rt Including Complete Cl0;'~..!£Q!l~ t o Dato Department 3ll0 ClOO Tests 708 Mark .3 Canopy Strength. Tests a re continuing i.t the National Aeronautic.al Establishment . No further report has been receivedo 2474 Stress Survey of GlOO U/C Leg and Pivotso Tests are continuing at the National Aeronautical Establishment. No furthe report has been received. 2551 Fairey Hydro~Booster ~ Contamination Testing. It is now considered unlikely that a Purolator filter will bet sted in this application, but alt..:rnative supµli'crs are under considerat.::.m by Design Office . 2555 Toreional Strength and Rigidity of Honeycomb Structure. The second of the or :ginal series of test specimens has now been repaired ,,f'ter- the initial tr.st and is ready for retesting. Modifications to the first specimen of the second series of test specimens is now in work in the Experimental Department. The test rig design for t he~,e specimens is complete and will be issued tor nanufacture ahorUy. 2631 Test of Centre Section Structure with Modification 1006 under Landing Gear Loads. l'ianufacture of the test rig is in progres:; in the Experimental Department and modifica.t ions to the Centre Section structu:·e are nearly complete. 2639 Alternator Failure Investigation . A representative fire was finally obtained by running the alternator with one bearing relllOved~ so that t he rotor r,.ibbod on the stator. No test invest i gations - t<:~I' made into possible causes of bearing failure equJ.valent to this conditiono The job :i.s now closed. 2650 ClOO Hydraulic System Fittings=Leakage. Leakage te:;ts on th o; .!!'lrst two of three specimens are complete. The third spec:bne:' is complete with the eseeption of some fittings, the delivery or whic,1 is expected short.ly 2054 • Performance Test of Special Dry-Cell Batteries. The perfor nance ot the batter·ies under loaded conditions and under intermitte short=circuit conditions was dete,dned. This job is now complet .1o Cl05 Strength Tests 2147 Honeyconb Compression Panel Testso Most of forty available specimen panels consisting of aluminum alloy honeycomb bonded between two sheets of fiat alum.i.num alloy WP.re tested in comp es io i.-.t, ~mbient aro elevated temperatures. The general behaviour o" panels w1as d>served and the Ulti!ll8}te strength of each panel o tain~ Th~se tests were discontinued late in 1954~ when it became apparent that the high temperature properties ot the bonding resin wer 3 unsi is factocy- 0 9.JR.i Sl:.renth 'l'ests (Con, nd) 2J02 2.3.31 High Temperature Effects on Laminated Windscreens. Some ear·'l.y tests were conducted during 1954 on the above subject, using ClOO windscreen panels and t emperature:3 up to ❖ 250°Fo It was establii::hed that the vinyl interlayers would evolve vapour bubbles if exposed to local temperatures above about ~ 1700F for significant periods. Attempts were made to investiP,ate them.al shock, but, the app&Patus was inadequate, and work was discontinued in favour of Job #21~8" ll r,<")if'l\" ...... r' D Inner Wing Compresdon Panelso ur~cLf~~ ... : Tests were carried ov..t on firteen panels of rivetted skl.n/stH"fener construction and two yxmels with int~grally machined stiffeners o Proof and Ultimate loads for the various skin/stiffener combinations were obtainedo The tests were completed in October, 1954c, 2341 Development of Methods for Retaining Bearings in Housingso The retention of anti-friction bearings in hou~lngs of restricted width, which precluded the use of the normal flange and spring clip methoci of retention, has been investigated 1mder this job number. Bearings retained by lips formed in the housing material or in an intcrmediat~ sleeve have been tested after installation by the following t.echniqu~a lo Ring Staking 2. Roll SWcl.ging 3. Press Swaging of corrosion resistant steel sleev&s 4 o Double ring staking of 2S Aluminum aleeves. 'l'hese tests have been reported in ATJlUs 2341/1 through 80 Tests are now in progress on the ring staking and spherical point staking of magnesium alloys using Thermal and Resistance He,,t inp n~thodsof retention. 2349 Outer Wing Posted Box. Three structural boxes, typical of the outer wil'1i construction, were tested under combinations of bend.in-:~ shear and torsional loadsc The behaviour of the skins, webs "r.11 stiffener stabilising posts were recorded by means of electr5. ca1. resiotance st.r-,dn gauges and the proof and ult:irrate strength: of the boxes obtained. This job was completed on Febrl.lliry 24, lt55, with completely satisfactory resultso 2351 stati(; Test of Complete Aircraft. Deaign work on this test to date has consisted of: 1. Strain gauge installation dra~ings, of which the Fin drawings have been issued, the Centre Fuselage l e r eady for iasue, the Foruard Fuselage Nacelles are awi:dting Stres:i Office approval, and the Inner and Outer Wing are in w:>rk. Several t.housand gat,ges are to b~· ins1.a .1 1 and extra technicians have been trained for the pu.rp.,,e 2o Test loading attachment drlf'Wings on the aircr:;ft, have qeen is,ued on the forward fuselage , centre fusela ge a::1 l fino g105 Strength Tests (Cont 0d) 2351 St,c:.tic Test of Complete Airc,~aft (Cont 9d) 3. Local reinforcements where the omission of aircraft services would adversely effect the strength of the str1J.cture have been issued en the forward funelap;e, centre fuselage and the fin. .,,, 4. Drawings of wing fuel tank test pres:;urizaiion s;ystems are completeo ;. Drawings of the test rig floor beams and the aircr,-..ft supports have been iasued and the ps.rts rave bel3n built. 60 An aircraft slinging beam for the transport of the test aircraft on overhead cranes has been designed and built and is due for pr·,of testing shortly. 2354 Fin Multi-spc1.r Box Bending and Torsion Tests. These teats were similar in principle to those of Job No. 23lf9• Four structural boxes typical of the Cl05 fin structure were tested. Th{: test programme was o:,mpleted on May 25, 1955, with results t.hat- agreed very closely with calculations. 2355 Fuselage Former Stiffness Test. Tt-10 typical centre furnlage f:rames were test d to obtain stiffnc:;s figures for design purposes . The frames were finally loaded to fi:.ilure. This job waa completed on July 12, 1955, with satisfactory resultso 2356 E"'lgine Intake Duct Pressure Testso Two engine air intake ducts (A/C Station .333-485) built using prelimina.t'Y tooling, wnre subjec·t.(ld to internal pressure and suction testso The ducts were mounted i.11 the test rig by representative fuselage frames and were tested i n tur-tt up to 50 Po6oi.g. and down to -5,5 p.s.Lgo No failura of' t r e dUrJ , S occurredn After these tests, one of the ducts, while under 20 Po 1 log internal pressure, had five 0511 calibre machine gun bullets f ired :l ito i... No explosiV•;:, det:ompression oc -urredo 'fhis series of tests ~,d.'1 concluded in June, 1955e 2.358 • Windscr,(;n Temperature and Pressure Tests. Preliminary tests havJ b(?en ca.rried out on one windscreen with no conclusive results Th,3 test rig for the fi!IH.l tests is now nearly co'llplete. In the ,ina: touts hot (2,00F) and oold ( .35op) fluids will be altenatively pcts.3ed o,rer the outer surface of the windscreen, whi.le the inside is p14 ee,nr faed and maintained at cockPit tomp~rature. Thermal shock effects wi.11 thus be investigated. 2376 Engine Intake Duct (Floating Assembly) Pressu. e Tesr... Jrrlers have been issued for t,he manufacture of the Er.gine Inta'.. r, Due ~, and mnnufacture is in progress. !::onte test rig drawirigs 1ave e .-n issued and the parts are in work. The spe• imen will be euhj ectcc, to approp~iate positive and negative pressu~eso 2377 Fatigue Test-Typical Skin Splice. Static a:·d fat:Lgue t. e its h e been carried out on nearly one hundred tt?~t specimens of typi .al w:.ng skin joints. Test were made n.t. ambient and ,~levd ~e l tern ieraut--eso 23'!' 2,380 2t 01 1ii3 test.s were cornplet.ed lr ')E r3bcc . :,5. '10•,r (ev,,iJ.up;:tent ~ ,w necessar:, :l.n ord ir to < ~cl '3a ti ,fu et.'"' ··~ > .ir l'c rn1cr.ce, 'l.nd the tests brought out t.he t fr i0'4 at ion of .~ 'Jrm. rco c:.t high temperatures, ,, ~- fatigue Test--Doutsch Drive ln E:'..:;n1Hivct, A.~r, . , ® .. 'rast:r'ili:IJ lo.ere ma.de on Bolid se ctfon of l-ing spu· !11/J.tErinl into i.~;d:th t ~ f:eutsch Drive pin blind rb l'.ts had oeen dri rnn. These rivets I a,•e grooved ends wh eh ar pre sed out i.nto the r~.vet hole by a c.r ..1.ven ti.l.per pln., Fat:l.gu • eetf. Gh'l•,~1d the influsign lcl1ds were a I plie C".lrr.p.le•,~13 elevaA,cra in both the neutral ana 30°up position, l'h .. eY .. tors were rno r.ted on a. dtXll!cy' wing \,hose deflecticn was made o f"lllow the est..irr,.i.ted tdrcri-l.~ wing d, xlectionr, Deflections of the elP.vator ,:md wing were recorded, and loads in tht! elevator rc'.lnt ·o:. circuit m·'asuredo Tt· 0 t.ests \ '..me1 is <,o be t,< ,tea later. JI"ObJ.bly at high tern]JC'ratvre 21.,.08 Fusela.p;e Side Sl job was th.n exterded to cover ma E: i I pan.els 1'01 ;ard of A/( i·t:.,1tion 485 'I c prellmin."\ry prum ls ha been 1,e·,'i,rn:! I llr i:x,re m; i r'3siilm P9,nel (: ,,,~ , ~~.11ding typice.l aid jo.:.r.tn) nre to E: tested ,.t roo0n temper &t.ure und two panels \<;ill ':lo tnetf.d ut elto'• ::.ted temper,+ Ul."'eso 2l:09 F~.t,igue ?est ot Pressure "'ipes 1or .!:. ev:i.c.o. Jac1<. I1itially, a stt, of p:.pes haYing i:·hap ., lu.c11 &r,l r,,w ol elate weri:: ~:>und satis~ factory ir f itigue, ir. fur 1, 1 ~ m,t i.$ be i 1g 3nu.l;actur1•c to the c•J.rrent desigr·, but these n~o, he cor· µle c mti l a . , t.isfactory msthod s .f'o•.md for ttac'1 1~ nd f.''..',ti .... gs w .. ldir•g H,' found u:.sa .isfuctory becau. e of 1'l d.i. fflr:uJ t j t r:. •v~ 1tinl r wroi: on ac tha weld, and <::Opf.X:J:· b ,.1.l"1, i.s no :u i11.vestigdfd 1 ,,~ U3e of flare lees tube con .~,:c i.:; .. :.. o t,, b 1 invest ig .1t.ed 2.413 2435 ;:438 2, ~--, ~ 24.51 ;Jre b ~ .1g t f;d l· tor <> "es T n.::il r.'-:IX' ~:it. 'J A .loy '.l'e,.,4.s , c • ccction oi t1e 1i"lrt., E. d ,.1.ect .. ,..,r m- ,H· 1rsment t mperature .:..nc eigh. in Decembt .. , 9~h. 'Iransi,::nt He~t.in0 o t'fpical of tlK •ril', t "'p,-;rat 1 ~ gnit• de of therma. to be ctet~rm:lned C ckpit Plcc~ Beam •· .md is a.I,,pli• Pl E!fiS I ere" ~ re ..,.., ._,.c-- res a. light.• co1strt•c obttai ~ i;J 'o ' • I , SIX' •jJ '1S WI i.ch a wg I ~g. Uul Cl\i:;;.,:..r,r-r 1. , •t. . ln ! •, F'u.l Oc.t lo:1.cft l1t ·cnsm + u at il'C JL'.l hie ~ob was :lose ' model t mk i~ .J cting it .c• hir h h s1J ,c flit ,t, th e d'r,riout, Jn ar t,o co "11ep~e. • arc renJi r, . :if • u u.oc ,.n:l ult Hi1ate , t·ly 11 5~o n, ,;} picc:l of t • ,l I €:l'E; teEt\'. .?cl o c. r ( r ::..muJ.a .:l.n'.~ '- r. re rr 1c ,n i n. •e ~i ~ .(' n ~.11o !CHl.:?d t , e .. o:ic t .ed • U ree r: 11e'li1 to Je te ted !,.l havE r:ic :.1 , .,b ( t'. to ·,pe~'i e :r f tf.fl'.'e JJ.gh fl It. fo~r , .30.~ l\1scla ..,u Tank rr'3ss u"c Test , i'uel t.,n'k, wa::i fati,:,ue test.~ d 1, lo,1ding Tef ,s Wfo e continue1.. t ead 'ller.ibers Oct· ·r d. Te t. t • "h acce·crtablo res'J..1.t.u ,. '~'l-."1{,, tyn·1 cal of tlxi fusel2. ~e ,lJr repeated interral pre'3sur, 1\ 1til failu i'."tl o.f tr• t t;.uik buJ c .,'<:"! c0rr~letr-d in Ncve::abr.:r, 1S'>5 2470 I'atigue 711st of !!.J.e·..rato1· Jc1.'~k j , ,:i.nu.~ Te.:nts arc in abeyance I ending d 1rn~gr. of t e for-ed ,. ng:: l1•? tci , Des:i.gr Oi'f".cs. 2/~.73 ~•trctperature and Pr-es5ure Test .., S.i.e. '.'.<.in 611. Tests were c:o:1ctucted in a S ier1nin 611 lan ~ n . ,e trart9)::£lren1 rlcl.nel. The :in.'1.t:r face was md.ntained ~t 0C ' a'l. pressuri?.fJ:,. "'11 , :; .. s,.c_io 1o·hile ths temper ·tur>? of the oi;..tei.· layer \tar c·J2 .. ~ { £-foJm "'65°F to -r, 250°I•'o '1'his job wa.s c.l.oe: on tpril l!>~ 19!>5 art.~,r the n~i.tcri,u was de:nons .. rated to b"' h:lg l, tmnatJ.sfactory ln this c.pplicutfon~ 2476 'len~ion 'rf;sts of Bo -0--Sea.l ,•rr NA~ 3o1ts with ESNA llin-el ?-..its. 'lh se t~s1,s uere carried out i, A )l":~l ]955, t.o investif;atc tt-o:? rtreng',;,h of .., proposed attach, •· t in tt.e fin etructureo 2478 longeron ,loint at STA,l>85 - Fat.i ,ul3 rert. l'3llu!'acturl" of tt e tc::.t specimens is n0w .in progre.,&o The joint has titn.r iwn pJ.ates 1 :o~ ning 7!iST sin..· s"ctions 2479 ~he_i.r Test of Je~Bolts. She,.1.r 1r:,:,ts re1~e c· rr:i.ed out on v,:1rious ::be Jo •Bolts~ in typical lap o nts. li'ai.1.lng loads e.nd c!efleetions 1e-· e o ·'. J.ned for t , j,u,1t.s. 'l'he ,iob waf c.los€1 in , .. ~, 1955, 2481 2484 2466 Fat,i gus 'fP-sts o.f Bonded ZF: 41 l< test and three futir;ue te !;.s h The res1.i.l.t of th tests on th th~ Krouafl Tc:ti~~ ~~bora "Y 1as:.u:r. AL. y Shueto Gne st,ttic bs?on carr ~d out during Apr.i.l. ... ' .1, .,., uim 1 is expect.ed sh,r ,ly 1 Hatic Strength c.rd F i,1g load of t.he spJcimms e"e O~t:>ber 1955 "' • 1-,ion 'I e-ts .. Shea.r mct 0 !Tari et: er Camloc :md E lo 1.d~. ar!fl .,oint de!lectio:i i~ ?iove Er" 19550 1;Ei , ... ach'll rt at, Rib l. Str ,np • t J.:nr,a t:r ~d.ca:!. of tt e rll!:t.in •TJ' r Le dj,. ,ftection curve:i ar; 1, a: t d, 'lne job wa.s c) ">sed 2497 2502 2,0,. 2.505 2509 2510 2515 2519 f'1ev.r Tos.. or Court,:. t • sunk nd D • m;:iled I i•-Slll:l.tr Fl~. ve 1:1 11° ,law ''5 s ·r6 Sheet Th first 1 ()< t O, o:ir :iled anJ 1,)t'O.t'L",Uilk r~.- t h. tig Te~,i: t ~ ere s ... tisfa torily '.Y.lnple'l:;. d :! ,.or tber • , 55. on Jeng' h3 oi' r mi;e tyuical Clf th subject ol.n~;, J \ tht~-i d~signcCJ.. s,_1bst pent < ,sign !:l'W,n"'"'S I;) fa ~Hi tat' r 'l:.d <.,t,iur imp oved the fc •. ~ue ~-ocictitio,1t1s md no r,i-t.ect nf, .t e '!''3ilX,f Phis jo h . .1s t ,r closed. flJ i n ~ he~r Test. of NAS Bolts wlth S - - i.nP Jl'OO'Ies. Test t :0rli c, cu_, on val'ious size tl./1.S. 1:-cJ.t in hI joint.a Ore p ~ 1 bf .,till :oint was grooved in a manner t:i, ;xi,..~.l of th<> wl..ng tenk , e.-d .. ir ~ t .,.,e r r';s r w in work in the :FJ.::peri n r:t r,mp • nt F ·t.igue 'rest, on Hoa·,';!, Formet· t'1e terw •pec:;,,l"ll'-?ns h·ive be"r a d th "'lc.rts ane in ·.~-ork. Joiti,, j ~ i t.it .. a ·..,o t,~ t: 'I s p~. ~n• 1 r.g£>l"(J r • ra:i1ir ~,erim~ t; J Dot· r. , be t1;;f, ,e:1 in t._ ,t rig i'or .::e-b No 25v9 S\ ti bJ.y ~dif·1 (. 'Te~par, ture "'..ln .. s r-,,_, .imrcin w ,re te ,t.rd. ~ p. esutirzeo t irr r face ,:l.ch ,.-a.• !11i:.irt ~'1 ! ~t, ir, w r- dove- outer s1.,rface r ;J.SUl"Cl!c€!) ♦ ((: ar11" th,.. fciJ r pres,;ure ,btai mrl apeo.imo.r ri AS \; •i r jn:te:-n1l pressure wn:l le at 'I) •. t T'On Rt: 1,s e-+ f fac•,ci:::-_r ar: d th jo;;.i w s C lc-f ,d .,, 19.5b Eir,ht Frar . .e dt.a b:Hiz ,ng 'I'~ .3. t pical cf t .e :..-car Je;la.ge l f of the eb arrl ,~1anu• n1c.mb r ~0 1955, 1<.it.h rHtl3fact~ry r~. c1 t, 'e,t,., '-'"rt' ca..rric,d c1 :i 1 , f'·• ml:' "> n e..,t,,:_~ f' }lP :cb wd c. 1p .. etct j ·, Ne,• 2530 l'a.tigu., Test. of llig.i.ne Bleed Imct.ing S'.f'A.485., The test rig l!a.S been const;-u.cted and th,1 t.'• . .:.; are now .n1dc:::- wa.y. \ section l f thiEJ a:Lr-co11dit.ioning srt m d-1ct, with f}.e:xibl end , ls being testeC" under circlic bc!r.din •, ilr its ··ntcr"l .l presoure :..s ~o p.soio~o and .i.ts tempero.t.ur• ',)OOJ?o 2534 I udder Stiffness ;;m' Limit 1 o ... ".l Test. The 1•udder sti rn~so a.n1 :J.mit lo·c1d test will. be c.:i.rthd o,1t on the rudder i\mct.:.oilal test, l'ig which if: now being defi.rnna 1ne test ls nchec;ulcd for the J.ate fall of 1956. 2.537 Shectr Test en 11Kingr Fa·,tener Cl 7'Yl. Tests were carr:.:.cd o,1t, to c etcrmln'J the load car:ryin cap.: c:i. ty o: the King 1 fantener . Proof c 1d. ultiro."!.te loads wer e obt~ ine< , l'he job was closed in Sc pt emb,:r, 39550 2540 lain Frame Stabilizing. A rortion ot' a typfoal t;F_;gf\.\J,.1,y _ r chined rear fuselhge fame w, teotec to ~mrestigute t},.e staoili1 c,f the flanees One speciniE n •• J t.e!:.ted a."ld the mode of failure o. 1:he flanges and the failing loo.c1 o! t'l specimen was r~co:rdec, The . it was completed in No cr-irer 9 5: w-... th r~sults tho.t J.F,t"ecc, t 'osely w:1.th calcula;,ionn. 25ll9 1.:ileron Stiffnesu d.nd Limit l oe.c •rest" rn, Aileron stiffrer s an" limit lon,1 test will be ca.r-·ied o.rt. eh thP. 1. loron func ... ionaJ .,es 1•. g, which is now bo.;.ng reanuf, ct.t.tred in the Experimental Dcp~ rtm1:n , ';be test, is s heduled for the 1. t.e fall of q56. 25'.lO f" n Ri Shear a."'l.d Be'iding ,:,tre,' ,h Tests, 'l"«> s.i!:ri.l: • rib tipeci. ".:.th differen~ web 'tl.cime .... t ~ J.:\.g'.-it.Lnine; hol0 spacins were tc~ ( u1d,;r bendirg and s ?ar lcac s rhe bchav i0ur or the 1 b \'.•i th th flanged l:Lghteninl1' ' oles 'ltaf:' ob _ rved rnd UJ.t,ir:;ate load a:.'ld J "'ld c C.ectio,'1 c:i;;: ve3 ob~.ained o Tt ese tests 'If re complet "l in I b, i956, with oatisfactory resl'lt ( 8ting~:.il(ron Fivo+, Sui:,port C tavc been completed. The jo C 200~ • 'fonts on th. J closed o ·1 ·1rch 9, cast L"~ 5o 2562 (a.sting Lev r Aileron Pb,ot C.::i,C 2000, Th',) r:.: sting ii·i ne;w ., .. c>, 1occi.v d a.nd in beini machined ·n the .llopso test r:., drciw:' l e b~en issued and thf.t"e to .. - Ln ~urk 2563 C'a200 Tests on the casting lu:ve been completed. The job was closed on March 2~ 19560 2572 Cc\sting CSC 2017 Bruck,t-st~p, Elevator. b<3en tested under different loading caseso on April J.O, 19560 Two The 2574 Casting CSC 2036 Pulley Bracket St,n. 183-.45LHo Dsdgn of th~ tnsL rig is oomplete arrl is in work in the shopso The castinr, h. s not yet been received from the foundero 2576 Casting CS('; 2.044, Elevator Quadr nto Man facture of tte te t r .. g has been completedo We are now a.waiting delivery of the cnsting from the founder. 2577 Casting CSC 2045 Bob Weight Lcvero Test rig design is in pi-ogres:;, but no casting has yet been r'!cei ed from the foW1d ro 2578 Casting CSC 2042 Sup;:ort Bracket ~Elevator Q rant. rests oi s closed on &r }, 26 this casting have been complot d The job 1956, 2579 C.r sting CS~ 204J Sup-port Eraoket •ElEVator Ql.! dranto Testa on this Cal>ting have been complotedo The job .zus cloeed on March ). 1956 2580 Casting CSC 2061 Housing - ThrotJle Qua.drad,o iu c~mplete t.rxl has been issued r~r rranufactur not yet been received from the frunfer. Des_gn of tes n The Castin ha 2581 Casting CSC 2062 L-Over-Throttle Quadrant Mcunving .&~gin~ Controls Tosts on this c~sting have been -::ompletcd. l'he job was clos March l, 19 ► • 2582 Costing C.:iC 2060 "'uadrant Throt.t e ~}uadrant '•lounting-foµne C ,. 'f·~sts on this casting have been compl,tedo l'he jo w ... s clos F~bruary 15, 19560 2583 C 1sting CSC 20)0 Hud er Pedal. 'lhe te">t r::.g ',e.s been •namua u a·1d we are now aW1•iting the deli ery of the c. :-iting fror tho c 2584 Casting CSC 2Q58 Rud er Pedal UcJ.crru11 Leve1 • The te~t rirr minufact,ured and we ere now w iting the de: ivery of th£' ea •t t'1e founder. ' ,,..,,, -~ . lJ C,1sting CSC 2029 Rud.•;er Pedal Quadrc1.r,t LevE-1 Pivoto The C0.,,t>~f ~ • have been machined and the test rig completed. Testing 5.s due t.o s-;art shortl;/o 2586 C·1sting CSC 2057 Foot Brake :i..ever. The fint of three c;:.stin_:is h:1s b•aen tested. 'l'he other two urc now b:dng machined, in view of t, he fact that Class lB loadf:' wero not wi t.hst.ood.. Cla:, i; lC rat in~ w.i.a passed by the firt.-t SIY.!dmeno 2587 ~1sting CSC 2056 Rudfer Pedal su~poTt Fitting. Tnc test rig hr.:3 b,3en manufac'·,cJl'ed. and we are awaiting d1:11ive.ry of the carJting from t'1e foundero 2589 C1sting CSC 2059 Rudder Pedestal BeE,ring Hou:singo 'foe test. rig }nn b-sen nti.nufactured and i,r,ro All dr .wings of the ·":.est spE:cimen he.Ve been issucdo 'Ihe te:-it will be perforn;('d on the test rip: for •. ~b No. 2509, suit b:Y nudifiedo 2641 Stc;tic and Fatigue S r ength Tests on Slu.n Splice at 'l'ranuport. Joint. Dr .... ings of the specimens have been issued and the l!Unu fc1cture of the specL ,ens is nearly o:implete 2642 S:;rength of Rib Panels-Main Torque Box. Four typical rib panels a-e t,o ~ testedo Drawinrs of t.hc fimJ.l specimen with its test rig have been issued and are in work in the shops. Drawings of the test x-ig for the remaining three specimens are now ready for issueo The tests will subject the u, the work involved will be added to Job 2.358. These tests were completed in March 1956. 2664 Pressure Testa of Transition Duct. (Heut Exchanger to Turbine) o Orders have been issued for manufacture of the duct. D~sign o ~ the test rig will conu,;ence in duE. course o 2665 Side Skin Access Door Shear Test. Drawingi~ of the test specimen have bean completed and are now 1·eady for issuing to the Experi~ msntal Department for manui'actureo 2670 Shear Strength of Honeycomb Adhesive. Ttrl., job was rec~ived at the end of April, and no action has yet bee, taken. 267?. Sl:.atic and Fatigue Test of Elevator Bell-Ci·ank Levero This job wa.s received at the end of April, and no ac· ion has yet been taken. 2674 Static and Fatigue TPst on Rudder Control Levero Th:i.s job was received at the end ,r Apr·1l., anc. no action has yet b,1len taken. 2675 Investigation et Elevator Ll.nkso F .. -xperience to date on the flyi.ng controls tes~ rig (reference job 2268) has established t.,e de: irability of fui·ther investig;,.tions of the propc"'i,i, s of b:alarings in the elevator output circuito 'l'est rig parts are being rll:Ade up, represent1itive of t.J-1e actual installation , to facilitate these ir-vestigationa. ClO~ Mec~.1.anical and Hydraulic Functional_l.t~ 2190 C"ntrol System-Bearh,g Selection The life of anti-frfoti{m hearings subject to oscillation 'Wtile undel' load have be :m investiga.tedo A variety of bea7 ings used on the Cl05 have b er• tzsted. These tests have rece1t]y been reviewed by the desir,n o.t'fice, and new testH have been -£.quested or beerings d ·:.h ,rl.,;h i::iterference fits ;.tiich ropresentf t,he incn·ase in intEr;'er}rl 'i, of the bearin.gs when the { rcr1d in August 1S'54o Cl05 Me.:ha.nical and ijzgrauli~ctiotB._l ~~ (Con:~ ) ' ... 2344 Complete U/C System Function Tests. The nos~ and main under• carriages will be momteq in separate test ri,1s ~ each of t,,rl.cll w.Ul provide for t he a.pplicat:ton oi' air and inertia loads ;:,:, the gear and doors ~ Design of the nose gear rig ic appro:d. mately 70% complete and manufa.cturs ic pi-oceedingo The ruin gear rig is still in the layout stage. Test~ ng is scheduled for the end of 19560 2359 End Pu\y for Various Thrust Loe.ds on Fafnir Bearings. The subject properties of several Fafnir bearings were investiBatcd by test in July 1954. 2402 Preliminary Elevator and Contr ol System Response Tests. This was an interim test on t he elevator system which waa perfo:-.•med between t he a ctuator and valve test (,Job 2271) and the complete syst.e:n test (Job 2268) o A single elevator, with represeni~utive output linkage and jack was mounted on a te~t rig, with no at~e:npt d• to repre sent control box stiffness. A ,:,rogran~e of no load frequency response and impedance te ·ts was cor:;pleted and ti1e job was closed in April 1956. 2425 Ground Tests of Fully Powered E.levator Contro] on A/C 18lO"o A fully powered elevator control system waa ins~ alled in ClOO A/C 18107 in order t o gain experienco for the Cl05. A series of gro.md tests was necessary to demon~trate that the A/C 'fms air~ worthyo These were successfully completed and the job was closed in Jul,y 19550 2432 ~draulic Line Connections for 4,0..'"'0 posoio An extensive series of tests on tlareless tube fittings for 4,000 psi hydraulic Lnes tu.s been carried out under contract at the National Acronautbal Est:1blish,itent to prove the suit .. ,bility of these fittings for ;ha Cl05 aircraft. The test µ-ogi-anme h0.w recen J.y been "eviowe-J and further aeries or t est specimens t,e.ve been mar:ufactt1red and s:tl.pped to t.he &,tional Aeronautical Establishment for- testingo 2442 Ail13ron Power Cont rol Unit-Frequen-:y Response Testsn Er,r.,.y att~mpts to conduct this test were aborti vo due to difficulties experienced with the Sarge-:it Cont,..ol valve and with the strength of the actuator itself. Aft.or modification3 to the valve wecc oo:-.1plete,i, no load i"requency response runs we.re performed and further te'lts with a bad representing aiJeron inertia will be cc.nducted shortly, •- .ex Pipe and Boss Coup.lil'lgs for LoP. Hydraulic:s c In t,ial tPsts sho.-.ed that :irepeatcd fiexil.g of the coupUng re ulted i:n f . ..i.ttet ing of the h l.ded :.nd of the tube and in da.rnag~ to tte tube caused by sharp c:orrr:;!rs of the coupling 1 et,ainers. Further este 1~·3re perfor·med with modified couy.,ling re+ ainers and tubes witt reinforc::Jd beadso Additional specimens are new bel·ig made with a ne-,r type of bead reinforcing and some specimens will aJ.do be l sted with no reinforcingo 2472 Canopy Functioru.rtg 'l'estso Assel!'.bly of t,he specimen in the rig is ,,cing C->.:ipleted, a.nd the first tests will caumence shortly. In these tests, du..:iicy- cancpies are to Le actuated by the Mart.in-Bak"'::- cartridge system, under representative external loads. In a second phase of testings similar tE.:sts will be conducted with actual canopies mounted on the static test aircraft structure. 2475 bpedance Te.Bt ot Elevator Jack &'ystern. Performed )n the interim 2482 2492 2493 2496 2498 2499 alevator test rig (eee Job 2402) this t est was successfully completed and the job was clo~,ed in April, 19560 Cold Temperature Pressure Drop of Elevator Servo Valve. Me~surerents ot pressur drop versus now were ma.de for three different valve ope:n ings uBinf fluid temp,3:ratures ot zero degrees 1''ahrenheit. The job was closed in Februa:cy 1956, but further low temperature tests ot the elevator ~alve are included in Job 2544. Fu."lctionn.1 Tests of Rudder Powered F4ri.rig Control System. This job i3 similar in principle to the elevator system test 'Job 2268)< D3sign of the rudder mounting beam and maey test rig details are complete. Design of the rig tr,r...me and beam mounting structure is procaading. Testing is scheduled for the late fall of 1956a Preliminary Selecticn Tests of Hydraulic Pressure Reducing Valveo Sample valves supplied by- two different manufacturer'3 were tes·i;ed and both were found unsatisfactory. Since this particular valve h-1.s beon cancelled from the aircraft 11i7stem, the job was closed in No ember 1955. Load-Compr'eesion Test for C.S.E. Rubber Seals. These are rubber seals of ipv section for which Design Of'.i'ice needed information on compressibility. The necessary tests were made in March, 1955. Frequency Response 'l.'est of Rudder Power Jack and Valve. This job io silllilar in principle to the elevator ,1ack test (job 2271). The test will be perforJJ1::d when a rudder val.Ye and servo are avail.able. A preliminary stiffness check ot the actuator itself has been completed, Flaroless Tube Fittings-tighteni ng Torque Vs Displacement. •re~-ts were carried out to determine the opti lilUlll tightening to1•que f'ol." a wide variety of Flareless Tube fittings. The tests were ~ompleted on March 2, 195C Cl05 ?,:l{rcr~l and Ilydraulic Functiom..l~~~ (Contvd) /" P. ~,... 2503 'fests of Steel Tubing and Fitt'i.n~s for Hydrau.lic Systemso ..,, 1•h'2:.t-e ,.. ~. tests on steel tubi~g and fittings for the 4000 psi hydr~ulic systems are being carried out at tho Na-t,ional Aeronautica.l Est.abli~~llt m3nt for testingo 2506 Speed Brakes Functional and Endurance Testso abeyance. This job ie in 2511 Assembly of Sea.l a t Duct Joint (Stn.485). A test was conductEd in June 1955 to detennine the manuHl effort requ1.red to assemble this joint, and to investigate the possibility of leakagn. The design was found satisfactory in both respects. 2521 Endurance Flexing Test of Rear Spa.r F/C Hydraulic Line. 'l'he hydraulic lines will be installed in the aileron control system test rig, but their behaviour will ho reported under thin job numbero The test is to examin{l tho fatigue characteristics o:f the installation, and the possibility of mechanical fouling under deflected conditions of thawing. 2527 Fin Inspection Doors (Plugs)., Tests were ma.da on a Fin Inspact,ion Door plug which proved the PI'()poser JX,Wt to be eatisf'actoryo The job was closed on September 22, 19550 2529 Determination of Efficiency or Compensator within Flying Control H,ydraulic Syste.mo This test was to determine the change in compenautor pressure wr1ich occurred with changes of system volumeo T'ne job was successfully completed ..nd closed in November, 19550 2535 Rudder Pedal Adjustment. Tha test wa.s successfully completed and closed in January 1956. In it, the load resisting prop«rt,y of the pedal adjustment scheme was investigated. 25.39 Evaluation of 0o0 Ring Ma.terialso Some enviromnental tests on different 0-ring compounds have been carried out by the Metallurgical Department. It was i.nitially intended to carr.y out a progra.um:e of operat1 onal tests, but it is now dfic:i.ded to gather o-ring data by observation of the components in thfi vti.rious hydraulic and control system test rigs. 2544. 1','\rcduation of the Elevator Control Valveso Tests to deternd.ne flow versus valve spool displacement, at l.36 Fuel Pick~up Tests Fuel-no-Air Valve. Tests to check functioning of Fuel no Air Valves in typical flight attitudes. Valves were fitted to a. steel fuel tank mounted so as to be capable of being poeitioned in al\Y attitudeo Valifes tested were not sati sfactory. The test rig was also used for fuel sloshing investigt1.tions, in which the rate of travel of the fuel C.G. wa.B measured, foll owing a tank attitude change. Tests completed October, 1955. 2237 Fuel System Testso A test rig hao been designed and bu·'l.t:. tchic:h contains a tu.11. size replica of th ~ port side fuel aystein" Wld is capable at simulating aey flight altitude- -r-,e pur::>::iee i:s to check the £ule syst6Sl ror all flight attitude:3, fuel temperatures a.,d attitudes. f'uel C .G. checks c- n a.lso be ,1adeo T•~st'.r:g c n thie rig will conmence during May 19560 2239 Fuc~ System-Pressure Drop Across Tees. loe.ees - test complet..ed April 19540 To obtain data on pipe 2)00 Sealing Test on Huck Loclc Bolts. •rests to d11termine sealing qualities of Huck bolts under high and lcw temperature conditiom,. Test Results satist'a.et,0ey" Test completed May, 1954c 2321 Effectiveness of Rivet· Sealing in Panels Uepresenting Fuselage Integral Tanks, Tests was not completed due to change in !uselage tank design. Test cancelled J uly, 1954" 2336 •rests on Integral. Tank Models of th~ Wing Structure. Tank models were made i ncorporc1ting features of tank sealing to be used on the aircr aft. Test tanks subjected to bending and torsional loading under high and l ow temperature conditions. Considerable progresi.i in sealing hae been ma.de as a result of these te:;ta, although e.t present the aealing is not entirely sat:. sfactory, a.nd develop,-nent continues. 2390 Stresi; Sealing Eff ect iveness for Various Fastenerso Test apscimens were made incorporat i ng different fasteners which were nubject,ed to shear and internal pressure. Final results r1ere satisfact,oryo Test complehd November, 1955. 2410 Pump Priming Test -Thompson Preducts Pump. T~e pump was installed in the rig used for Job 2236 to check its performance in various fiight attitudes. The pump perfo1·rna.nce was found to btJ below that required. Test completed March 1955. 2418 Naeh Booster Pump Test. The pump waB installed in the rig uaed tor Job 2236 to check i ts peit'form.ance in v,.rious llgjrt. attitudes, The tests were extended to cover the puop perform nee with various inlet arrangements. The pump was consic:ered unsatisfactory dull: to bad priming characteri sti cs. Test completed Feb'."'Uary 1956. 2430 Fuel Flo-"° Proportioner Test. 'f'ne test is to check the per.formance of the proportioner unit under all flight conditions. The test is being made by the manufacture, Eclipse Pionee •, at 'l'eterborough, N .J. U.S.R.. The results so f1:.r achieved have not been entirely Sdtis fa.ctory. Testing isd'.111 in progrces. 2501 Fuel Line Presi:;ure Dr'Jp Test. Test to comi:a-r-e the actual pr3sm1re drop in the transfer pipes with estimated -..aluea. Test reau.lt~1 were satisfactory~ Test completed Q{.-tuber, 1955. 2652 Vibration Tests of Hymatic Pressure Regulator. Test to deterrni11e the resonant frequencies on the valve operatir1g mechanism and to subject it t o the vibration test procedure as laid down in Avrocan Specification E.266 . The reaonant !requenciei;.: of the ve.lvo mechanism were determi:ned in April, 1956 but i.h,, endurance vioration testing haa been deferred until ,h re:m~ance re~;'.,lts are mor~ fully evaluated. Cl05 Fuel ~yste::i FW1ctional Tests (Contvd) 2663 Vibration Test on Air-no-Fultl Valve. Test similar tot the Hymatic Pressure Hegul~tor - Job 2652. ~ lt w-ait.ing ret or specimen va1ve from manufacturers t'ollowirlfl repairo Cl05 Air Conditioning System Tests 2363 Air Conditioning System Tests. Trf' rig is a full size replica of the air conditioning system containing aircrd't ducting and equ. pmento The purpose is to check the performence and functioning of thr i n a wind tunnel model. 2227 Bea.ring Strength of Aluminum Casting. This test was oonducted in January 1954 to determine material propertie:s for the design of the free f. .light models. 2249 Control Surface Actuator Tests-Model. Tests to develop a method of operating t he control surfaces on the free flight models. A suitable system has been developed provided that a fiuid can be found which will r~t deteriorate synthetic materials in the syGtem. Testing is still in progress. 2270 Static •rests of Free Flight }'.odelo Manufacture of the te,;L rig is complete. We are now awaiting the deliver:; of the Free Flight Model for testing~ 2.312 Actuv.tor Test-Fr.ee Flight Model. An available elt,ctric actuator was investigat ed in April 1954 for possible use in t he free flight models, but was found unsatisfactory, and was rot uoed, 2313 Limit lead on Preli1ilinary Booster Wing- Fr•,e Flight Hodel Boostero Development tests were carried out O"l wings fO!" the bc:,oster rocket used in launching tree flight models. Wol'k w2s concJ.uded in o;une~ 1954 without:. actually testing the final deriign. j 2332 Tests on Plastic Model fro.- Strength Investiga::.ion. A Be:i:les of' tests werP. carried out on a strain gauged plastic r.,:,del J% thick fin. Strain dis';.ribution and efl.ections o"' tl'"!e fin were recorded under varioun leading co11Clitionae .. complete model of the Cl05 with ·a 4% thick !in has been rnanufac· . ..,rcdo Tcst,s o:i this model have been placed in abeyance, 2:362 Tensile Capacity or 11 Nylock11 threaded inserts ·in Magnesium Ca3tingc Tests were conducted in August 1954 to determine the loads required to pull out Nylock inserts from castings, in >rder to provide design information for the free fiight models" 2392 Investigation of Rate of Evaporation o'l Solveit from Cemented joints Made in ;~ylonite at Room Tem:;:erature and at l6QOF. Te:;ts W3re carried out, on coupons of Zylonite bonded together with ac3t,0.1e, to obtain the necessm-y curing time for this typ o! joint, for pl.2.stic model design purposeso The job was clo!ed J) Nc-"ember 15., 195'~0 2)98 Front. Fuselage Plastic Model Strength Test'J were ca't"ried out en a plastic model of the C105 fuoelage fol"\'fard t stc1tion 485. The fuselage was cantilevered a'tj :-rt..!.,85, and repr .sentative inert .a loads applied to the structure. Deflection and strtdn gauge recordings wero im,,ie. Tests were a.loo carried out on a c.;,...-; sectional model or the fuselage at frruue 371 ; nd )SO. The jl'>,} W-d.D closed on September 2:1, 1955s after valua le information or. load distribution had been obtained. 2407 Shock Absorber Strength Teat-lfod~l Lau.~cher~ Str£ngth tests i>~ automobilo shock absorbers intended for use in the f're~ !1:lgi'1.'.; rcdel launching device were !\":Onducted, and i.f' er some ioodificat,ions .''Jad been nnde to the end attacrurents, 1.he;y UP.re r, und to be aatisfactory" Work was concluded in Nov~'llber 1955. 2419 ::itiffness of Model/Booster Connection. The ~tiftness of t..1-ie jo:Lnt of the free night ioodel to the booster rocke wao measured aY1d found to be satisfactory, Work was carried out in ,November, 1954, 24,Jl Functional Tests of Free Flight Hodi::l Launche~~. Funct,ional 'fegta were carried out on the Fre0 !-'light Model La.m1chero Some mi:1or DX>difications were made after the first tests, tollowing llhicn the functioning of the launcher W't!.S satisfactory,, The job wc.1.s i::losed on December 2, 1954. 2461 6/10 Scale Model Air Intake Testa Tests were run in i:.re summer of 1955 using a wooden model o! the Cl05 air intake in conjunction vrl.th a.n Orenda engine, to examine the intake chara.~teris-.1:,icso :,cm'! develc!r' ment. was shown to be necessary, and prepar;,ticns for r-.i hHr te:1ts a.r,: in progress in the Aerodynamics Departmento This jc•b was closed in July 1955, but w.a.y be re-opanedo 2500 Resonance Test of Free Flight Model=Boost,er fu: sa,"tblyo Fesom.ncc tests ver-e condvcted on tw. first fr~, -fHgh'1;, ,node] ani l ocst •• roe,,;:et. assembly to detect ary- object.ionehJ.,s feat.ur1? n TheN , ere '1.0 1e. This wo:rl< was done in May~ 1955 ~ .. 2517 Yaw l'ulse Mechanism Tests undur 1Gv Condition,. Following th,1 apparent .fa.ilu:ro to operate of the yau pulse iring mecharo sm of one of the frea !light models, an 5nvostigati n was rcade on. a centrifuge, without cliscovetlng rf fault. No conclu.s.tons -we ·e drawn concerning the flight incident, and the job was clo1:nd on June 2, 19550 2523 Pressure Test on Duct. Three !ibrc-~lal!ls model ducts wern subjected to intemal air pressure while at a. temperature of J00°F a.nd also at room t emperature. The third trial was found to hs satisfactory. The job was cleared in August 25~ 19550 2551+ Pressure Testing of Free Flight Node! Ductso Pressure a leak rate tests were made on the intake ducts of t wo free fiig , rodcls, with results that were u,.t.iltfactory after eo.mt~ rework had oo,n don-a. The job was closed February 14, 1956. 2656 Pressure Test on 6/10 Scale »tgine Duct. To determine le'aka~e rates of duct sections and to check their strength. ·rert in pi.'Ogress, approximate~ 70% completed. B.eam:. nder will be carried out when modification in the shops haa been f.inished. Instrument.at ion 2060 Strain Gauge I nstrumentation. About one and one-half' years uo k has been done t,o date against this j ob, to de ennine the best procedures and techniques fo1• using strain ga gee on tests of .air craft structures, particularly wit respect to adhesii/ee arrl 16ter prcnfing methods. Observation will continue indefinLeh on ,;:oupon samples intended to predict the behaviour of .1.nstalle.tiori on the Cl05 static test aircraft, over the extended ceriod of l.cs ,inJ anticipated~ 2672 Remote Deflection Indicating System. This job covers the de'3ign and construction with transducers now on order. The 3ystJm is to be used for deflection r eadj_ngs t inaccessible points, e.~" under water. in interiors, or in high temµirature locations. :!ork has been confined t o preliminary scheming to date J!._l.anning and Reporting Advance Test Results Closing .1obs issued during Apr 1 1 1956 ATR 2359/2 End Play for Various thrust l oads on F fnir 13earil"g3o ATR 2381/2 Casting Strength Test for Receiving In' pection CSC-1296. ATR 23'irJ/3 Check of the Efficiency 01 the new Ca 1 on 1'.::lectric Pre_.;sur:l.sed Comector. ATR 239'J/2 Heat Resisting ( haracteri t:lcs of Term. ntl St ipe. AT~ 2406/2 Ga. ting Test fo~ Receivint spection (,SC-138'9, 1390-o Advance Teat R,2ulto Closing Jobs (Contud) ATR 241.3/5 Strength of Light Weight Windscreen Panels ATR 2419/2 Stiffnem; of Mode.l/Bocster Connection ATR 2447 13 f!ylok Eolte-S8lf Loc'oicm trnck upo A ,r,ound test at.and "'U' manufactured. The erJ.st.ing n:oc.<,.up package is to be modified for pn limine.ry b .ndling trials !o~ t he sparrow missile installation ruid f ur!"..her Sparrow pa.ckage handling trial n w:Ul be ,;er formed t'l'.d'!r , his job number. Missile Actuat,ing Mechani8m On a CFlOO~ The insta l b.tion in the aircraft W-ns app::roxima.tely 90% complete wr ~ this proi r,ill.Ulle was cancelled in Uo'romber, 1955 all inst ·tm1enta .J.on w;is rE m:>vcd from the airer-a.rt, tho speciiran removed md stor ed and t he aircraft returned to the .lt.C.J\ F o Armament Test-Complete Installation. Praliminary Design 1-,ork was completed on this project to ground 1'unction and .t"in th0 Falcon and Spu-row missile test µ:i.ckages as 011.r;i naJ l ,7 C')r.ceived,, Tno work on this test is no,, in abeyance aft er t he PaJ.co.1 cancellati on and this job nunh er closed pending fur" l ~- .nformation on the s p; rrcns in::;tallation 1.enting will cont inue t d :ir Jo J llo< 10066. Latch-Mi ssile Package Fr<>nt At tachn:ento Tests were compl e ;ed and a report:. is sued on the original specimen which f ailed. . Thfl job is now cl osed on Design Ofrice requeAt . Semi-Submerged Falcon Instillat.i.ono Thi t est was completed and a report written , it will be issued .hort.-1¥ under No ., AE 100510 Sparrow Missile Installation cm Cl05 Aircr aft . Tt'-.ie joo a 111 abeya nce pending further ~ f'ormat ion '.'ro": tht> Der :.,gn Of hice reference the grc· md te "in~ f the f',J.ll. S rrot- pac-k;.J.ge. Cam PJate r pc1!:,ed load t est , This _lob • as comrlet.d and ru~ rt AE l ()()C:l9 i t,suod,, JU"ffl&lllent ( Cont, u d) 10,115 Siarrow Missile Look Angle ClO!i Auerafto Variouc • have been performed .o dete ll'.ine the optin.U?tt look a 13,'L the sparrow missile .rhen ext.ended from the package n th'3 aircra:t'to All tests to date are reported in A.AoR 1 10,105/1 ,nd 2o Thie j ob is being kept openo Spirrw Package Door Tests. PreliJri.ina.ry Spacimen drawings received from the Desi f11 Of'fice and i55ued to the ar.perimcntal shops for nnnufactureo Deta5.ls of the doors and door op£rating mechanism are still awaited. An existing rig can bi[) uaed for the testso Spu-row Missile .Eictension Mechanism Testso Manufact~re of the specimm is appro:rlmately 70% complete, the chief hold u.p being on the jack mnufacture. Rig design is in work, 'l'hc test is estimated to start. approximately June 15, 1956. A,:mament Data Sheets Issued during Apz:il. 1956 10052/22 52 x 211 rocket pod developnent 10116/2 Modified '1 Tube training launcher tr.sta 10118/1 and 2 2.,75 11 Blast Operated latch, Ament Advanced Reoorts Issued during April, 1956 10052/44-46 IncL 52 x 2 11 Ro~ket pod developlllento 10104/10 & 11 Pennarnent. type rocket pod testso 10108/;3 & 4 Measurement or look angle on ClOO Aircraft 10109/1 V "G. Py1on Jettison Tests 10ll7/l to 7 IncL Rocket Retainer Tests 10ll8/l to J lncl, 2e75" Blast Operated Latch.

Monthly Report - April 1956

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