FILE IN VAULT NRC • C IS TI J. H. PARKIN . BRANCH fv/,N 2 9 1995 . r _ ... CP'·l02 fROPOOED FLIGHT TFST PROGRAM (A/C 1, 2 ~nd 3) Classilicalion cancelled/changed to .. H-- DY authority ol----·-·(date} ...................... . $ignature ______ .Rank .... - .. , ...............• Avro Aircraft Ltd., Malton, Ontario. December 1955. • • • FLIGHT TI-ST PROGRAM AND rnsTRUMENTATlON FOR THE FIRST THREE PROTO'I'!!E INTRODUCTION The prilnary role of the first two airplanes will he to check out the stebility and control, however, dur1ng the early flightsof the first airplane, it will be necessary to check quickly that the various mechanical and electrical systems are operating in a satisfactory manner. At this at.age we would not attempt to develop the systems to meet the full requirements of AIR 7•4 or associated apecs. but mPrely sattsfy ourselves that they are safe to continue flying. The development to AIR 7-4 standards will be carried out on the third airplane. It can be assumed, broadly speaking, that when the third airplane gets through its initial shakedown tests tr.at it will do ell mechanical and electrical systems testing and airp]anes one and two will concentrate in aerodynamic testing. All three airpJanea will have. the instrumentation listed in the Appendix so that any one of them cc.uld become in aerodynamic or mechanical development test vehicle as emergency dictates. The flight test program for these airplanea is shown in Fig. I and pages 2 to 6,and instrumentation is listed in the Appendix. The instrumentation list on 'Structural Integrity' only covers preliminary testing, the list for final structural integrity is not included as the method by which this shall be done and the airplane which will be allocated for these tests has not been definitely decided • CF /0..> /"( Iii" )IT n.sr (A/c J, < qi 3) lfAY :r j' A 5 0 1'I .P f .r F M A ,., .r /9.5"? /'?,. l -1 ,5/.l{J.fO/VJ~ f?,'(O/jJAI<; «-S,/1(1.KT. /,Vr£G I ~ {?~Eu;,,. RAl>tO C-0"1 P. ~ P. £) S.UOSONJC l'IAAIJ>L1N'6 J 2 '! ,4E~Ob)'~AMIC ... }>/?DB IA/~ ~ _, VIV~l"tK .S ()l)/,1/c;,. A~.P }1~< MAJV/tcA{. Z>l::YEt..OP~£A/T M :r I • A/C NO. l - AERODYNAMIC Tf.S!S ] . Initial flights for airframe and engine acceptance 2. Subsonic probing and structural integrity A/C stability and control Adjust and assess automatic stabilization Preliminary structural integrity Preliminary position error Preliminary radio compass, Navigation Aids J. Subsonic handling tests Dynamic stability Static longitudinal stability Elevator power and control Effect of air brakes Lateral control, rates of roll Stalls, CL max., buffet boundary Asymmetric power Diving tests ExtPrnal tank 4. Supersonic handling tests (with A/C No. 2) Dynamic stability Static longitudinal stability Elevator power and control lateral control, rates of roll Stalls, CI.,max., buffet boundary Asymmetric power Diving tests Total for A/C No. l and No. 2 (5 months available on A/C No. 1) r, FLIGHTS AmCRAFT MONTHS. 7 21 7 1 3 1s 8 6 3 5 10 4 6 3 32 8 9 6 14 4 12 4 0.5 39 5.5 6 9.0 85 13.0 5. Performance tests (with A/C No. 2) Calibration· of pitot, static, temperature, sides)ip and angle of attack probes ~vel speed and fuel consumption A/C clean External tank fitted Single engine operation Com~at and ferry missions Climb, descent, ceiling Take-off and landing (normal cases) Take-off - engine failure Acceleration and deceleration Minimum turning radius at altitude Tbtal for A/C No.land Ho. 2 (6 months available ou A/C No. l} Total, Aircraft No. l FLIGHTS AIRCRAFT MONTH§ 8 16 8 7 10 6 0 4 10 8 77 11 27.0 A/C NO, 2 - AER0DYNAM'IC TF..STS 1 F f1 ,4 M FLIGHT AIBCRAFT MONTHS 1. Initial flights for airframe and engine acceptance 4 0.5 2. Aerodynamic Probing and siructural integrity Adjust i assess automatic arlabili~ation 62 Preliminary structural integrity 4 66 9.5 3. Supere~nic handling (with A/C No. 1) (91) (13.0) (8 months available on A/C No. 2) • 4. Perfori;iance tFsts (with A/C No. 1 (70) (10.0) (5 months available on A/C No. 2) Total, Aircraft No. 2 70 23.0 ' AIRCRAFT NO. J - .MECHANICAL TESTS ■CUJ.SJJIID FLIGH'J'S 1. Initial flights - Airframe and engine acceptance 4 2. Mechanical probing and testing {A) .IJ!tl SYS'l'EM {C) HYDRAUJ.,IC - Utility - {D) L.P. PNEUMATIC {D) ELECTRICS Transfer Press.-/ Level regulation Temperatures 20 flights Auxiliary Fuel Tank Baffling Unusual Attitudes etc. Cooling Afterburner Operation Throttle handling, 20 flights response Lubrication Auxiliary Drives etc. operating times Peak Pressures 7 flights Temperatures Emergency system functioning etc. Air conditioning Cockpit Pressurization Canopy Seal 20 flights Anti g suits (Fuel Transfer) Loe.de Regulation Temperatures 6 fJights TOTAL FLIGHTS AlRCRAFT t.!ONTHS 1/2 10 1/2 Months J. -6- Mechanical Development, Structural Integrity and Tbermodyj 2.._D1•J'I' FLIGHTS Structural integrity and thermodynamics Structure Fuel System Engine Cooling Inter Coolers etc. Mechanical dAvelopment time (availa~le) TOTAL 60 flights 17 155 AlRCRAFT MONTHS 8 1/2 monthe 2 1/2 months 22 APffiNDl! INS'J'RUMF'NTATTON TO '8)1; INSTALLED IN A/C 1, 2 and 3 1. StabiJ ity and Control 2. Flying Control Hydraulics J. Engine Installation 4. Fuel System 5. Utility Hydraulics 6. Air Conditioning 7. Electrics 8. Undercarriage 9. Structural Integrity ' Page I ' 7 II 14 /;j 18 2 0 2 1 CF-105 IN3TRUt-ffi:l-n'A.TI0N - I3SUE 5. STABILITY A.ND CONI'ROL D.R. Pattie October /55. I In the following list, the instrument ·ition hss been grouped.ll~\ llllf \El four h8sdings,- ~ ~~~f •-- 1 0 Ambient Conditions. 2. Motion of Aircrsft. J. Control Surface Motion. 4. Control Mechanism. Three sketches are provided to show the locqtion of instrumentation, or to define quantities to be measured. Items marked* - Phase shift at 15 cps must not exceed 3°. Items marked X - Required on continuous trace as well as at specified :., sampling frequency. Provision to be made to telemeter each of these items on continuous trace, but no more than eight of these items will be telemetered at any one time. Required accuracy in continuous trace recording am in tele metry is;!: 'J!,. Changes from issue 4, Ref. 3533/22/J are underlined. 1. AMBIENT CONDITIONS (see Fig. 1) mM ~ ACCURACY Ambient Conditions 1) Aircrsft Static Pressure 150•2160 lb/ft 2 +10 lb ft 2 Limited Range 150-750 lb/ft2 t 4 lb ft 2 ACCURACY SA..\fi'LIN::r % of full range FREQUENCY :to& ~ 1/2 sec X 1/2 seo 2) Differential Pressure (Totsl Head-Aircraft Static)O-J000lb/ft 2 _..:!;. (4 + 0.002P) lb/ft2 1/2 sec I 1/2 sec J) Free Air Total Temperature -65 +J50°F ! 2°F .,: 2. MCII'ION CF AIRCRAIT_ (see Fig. 2) ~ I mM ~ Accl:!J:~Q:! Accuracy Sampling ~ of. full r1u!t:~ Freguenc;r 4) Angle of Pitch 9 * -60 +60° ! 0.5° + 0.5% 10/sec Limited Range* -10 +10° ! 0.1° I o.5% 10/sec 5) . 9 -30 +30°/sec :t 0.3°/sec :t o. 5% 10/sec X 6) Azimuth Angle 'If* 0-360° ! 0,5° . ;t . 0.]$ 10/sec Limited range* -10 +10° ! 0.1° ! 0.5% 10/sec 7) t -30 +30°/sec ! Oo3°/sec :t c. 5% 10/sec X 8) f -50 +50°/sec2 :t 0.5°/sec2 ! 0.5% 10/sec X 9) Angle of Bank t * -85 +85° :t 0.5° ! Oo5% 10/sec X r Limited range -25 +25° ! 0.25° ::!:. Oo5% 10/sec 10) ~ -300 +)00°/sec + , 2°/sec ! 0.5% 10/sec X 11) Angle of Attack e;(,. -10 +40° ! C. 10 ;t0.',!J, 10/sec X ' 12) Angle of Sideslip,S •15 +15° ! 0.1° j:Oo5% 10/sec X 13) Long~\udinal Accelera- -32 +32 ft/seo2 ! 0,3 tion X ft/sec2 ::!:,0.5% _2/sec 14) Lateral Acceleration ¥-16 +16 ft/sec2 ! 0,15 ft/sec2 ::!:,0.5% 10/sec X 15) Normal Acceleration Z -100 +300ft/sec2 :t 2 ft/sec2 ;to. 5% 10/sec X (-3 +8g) ,: ' J. CONI'ROL SURFACE MarION (see Fig. 1) .tin 16) Port Elevator Angle a<-* Limited Range* 17) Port Elevator Angular * • Acceleration &. ;e 18) Stbd Elevator Angle E,* Limited Range* 19) Port Aileron Angle ~ * Limited Range* 20 ) Port Aileron Angular * • • Acceleration 5, a. 21) St bd Aileron Angle ~ * Limited Range * 22) Angle of Rudder Limited Range* 23) Angular A9~eleration of Rudder* tS..,.., 24) Port Airbrake Angle 25) Stbd Airbrake Angle ~ Accuracy -JO +20° -10 +10 ° -JO +20° -10 +10° -19 +19 ° -10 +10° -200 +200°/ seo2 :;t2°/sec2 -19 +19 ° -10 +10" -JO +JO" -10 +10 ° + 0.3° + 0 1° - . -200 +200°L sec2 + 2° / sec2 0-60° o-60° Accuracy % of Full Range :! 0.5% +' 0.5% !0.5% + 0.5% ! 0.5% :t o. 5% :! 0 .5% ! 0.5% + 0.5% I o.5% Sampling Fr,guency 20/sec X ?!]/sec '?.P/ sec X '?f)/sec X '?!}/sec ?Q/seo X '?:.._0/sec ?Q/seo X 20/sec X ~/sec 20/sec I 20/sec ?Q/sec X 5/seo 5/sec -~ 4. CONTROL MECHANISM (see Fig. 3) llim 1£cation (4l, Fig 3 26) Elevator Stick Force 27) Aileron Stick Force 28) Rudder Pedal Force 29) Stick position Elevator 30) Stick Position Aileron 31) Rudder Pedal Position Location (2) 1 Fig, 3 32) Elevator P~rallel Servo Position 33) Aileron Parallel Servo Position Location (3), Fig, 3 34) Elevator Damper Signal 35) Aileron Damper Signal 36) Rudder Damper Signal ~ -80 +120 lb -30 +30 lb -150 +150 lb 0 - 11" 0 • 10" 0 - 6.65" O - 3" 0 - J" 37) Emergency Rudder Damper Signal 38) Port Elevator Damper Servo Position• -o.6 +o.6" 39) Stbd· Elevator Damper Servo Position * -o.6 +0.611 40) Port Aileron Damper Servo Position * -o.6 +0.611 41) Stbd Aileron Damper Servo Position*· -o.6 + o.6" 42) Rudder Damper Servo* -0.5 + 0.5" Accuracy Accuracy % of Full Range ! 2 lb !: 1% ! 1 lb :t 1% :t 3 lb :t 1% + 0.2 11 :t 7J, + 0.2" :t 7J, :t 0.15" :t 7J, + 0.06" + 0.06" ! 7.1, :t 'Z/, = 'Z/, :t 7J, ! 7.1, ! o.Ol" :t 1% :t 0.01 11 1: 1% :t 0.01" ! 1% SECRET (Continued/ ... S,smpling Freguenci ~/sec X lQ/sec X !Q/sec 10/sec 10/sec 10/sec 10/sec 10/sec 20/sec X 20/sec X 20/sec X '?!}/sec X 20/sec X '?!}/sec X ~/sec X ECf. ,c;G. 1 DESCRIPTION OF SKETCH Let OX, OY '3.Dd OZ be three mutually perpendicular axi s with origin O, such th9t:- OX is parallel to the longitudinal datum of the aircraft, OY is parallel to the lateral or spanwise datum , and OZ is perpendicular to the plane XOY. Let O be projected into a horizontal plane in 01 , also project OX into 01 X', 0Y into O'Y', and let 0 1G be a reference direction in the horizontal plane. Let the horizontBl plane through 0 intersect XX' in X",and YY 1 in Y", then , 10CzLE CF PITCH 9 = LXOX", the arw,le between the longitudinal datum of the aircraft and the horizontal plane. ANGLE CF BANK t = LYOY", the angle between the lateral datum of the aircraft and t e horizontal plane, AZl'lliTH ANGLE ~ = Le&. 1 , the angle between the reference direction and the projecion of t he longitudinal datum of the aircraft in the horizontal plane. Further, let OR lie pRrallel to the direction of the relative wind, and let ORS and ORp be projections of OR in planes -XOY and XOZ respectiv ely, then, A.NGU: CF ATT ACK q( = ,LXOR,e, the component of the relative wind in the plane X0Z 0 ANGIE CF SIDESLIP = LxoR.s, the component of the relative wind in the plane XOYo ITEM OUANTITIES TO BE MEASURED Angle of Pitch 9 ~ Angle of Bank ~ ~ Azimuth Angle f , f Angle of Attack ol, Angle of Sideslip .i Longitudinal Acceleration X .. Lateral Acceleration Y .. Normal Acceler~tion Z .ANGLE" OF S1.DE'6UP /!, y" ){' d AllMUTH AN6Lt f t' NOl'E ON FLYln'., CONTROL MECHANISM The sketch opposite, shows the elevator control system in its essentials, for the purpose of describing the instrumentation. While the aileron system is practically identical to the elevator system, the rudder system h3s no parallel servo. In the elevator and aileron systems the feel unit and trim adjust ment are employed only in Emergency Manual !lode of operation, when the parallel servo is by-passed and the damper servo locked in the central position by automatic means. The rudder damper servo is not provided with a centralizing and locking arrangement, but has duplicate electrical and hydraulic systems. In Manual Mode of operation, the pilot 1 s effort on the stick strains the mechanism from the stick grip to the rear quadrant against the parallel servo, which operates in response to an "error" signal. The strain is picked-up by a force transducer, the signal being balanced against the signal from the "feel" network which may consist of - etick position, q, stick force/g, etc., components. The resulting "error" signal, suitably amplified, is fed to the parallel servo, which moves in such a direction as to reduce the error signal to zero. ® PAK.AL I. E: l .5£Rvo V'-E:CT~D -WY .bJu.LJu c.) {ci.ECTRO 'HYDRAUL1cJ @ TXIM AD.TUSTl"f £ NT' ACTuAroR. 5 £:1(. '(0 \ \ \ TO COIVT/(OL .SuKrAcc SKETCH OP Fl...YJNt; ccuvrROL MECHAN IS M Key: 1. Stick Force - Elevator, Aileron, and Rudder Pedal Force. Stick Position - Elevator, Aileron, and Rudder Pedal Position. 2. Position of Parallel Servos - Elevator and Aileron. 3. Damper servo signal - Elevator, Aileron, Rudder and Emergency Rudder. Damper servo position - Elevator Port & Stb 1d, Aileron Port & Stb'd, and Rudder. 4. Trimmer position - Elevator, Aileron, and Ruddero s FIG. 3 • ' . ,, ,. ,... ,. J ... ""\l ,-.l '1F~' ""\ "'! ..... .. .,.. ,. . . ,... ... ~~ ,.. ~ .. r ;.._,,., ___ ------·"::::_ -·- ., T , ~ .., rL: l' :t .,_\_. t : r - ·' - 'I \ . ., .. ' , r, t 1-- t "'I, t ..c. ♦ .. ,11=.~-~- ~ ~-r t >· J 1 • ~ t~; ".: r r - '"'·~ .. "' ~ J ~r,, ◄• 1 • . ' C Cl ..,_ ... ') .... , . 0- ~ - ' . r ps£ ' J ,.,. r ,~ ,, 1' y ,-- ·,-- "" .... I ,,.,_.., NOfE ON FLYHU CONI'ROL HYDRAULIC (See Sketch Opposite). The flying controls are operated by two independent but practically identical hydraulic systems, A & B,each system having in parallel a pump driven by the Port engine and a pump driven by the starboard engine, ~Thereas each system contains a number of actuators and servo units in parallel, as detailed in the following table, only one actuator has been drawn in the sketch:- System "A" Port Elevator Jacko Stbd Elevator Jack. Port Aileron Jack, Stbd Aileron Jack, F.uddPr Jack. Rudder Emergency Damper Servo. S:yatem "B" Port Elevator Jack. Port Elevator Damper Servo. Stbd Elevator Jack. Stbd Elevator Damper Servo, Port Aileron Jack, Port Aileron Damper Servo, Stbd Aileron Jack, Stbd Aileron Damper Servo. Rudder Jack. Rudder Damper Servo, Elevator Parallel Servo. Aileron Parallel Servo, The control surface actuator jacks are each composed of two units in tandem as indicated in the sketch, one unit being supplied by System "A", the other unit by System "B". M.Y.l --i;ocgtion In Sketch 1, 3. 4. 5. • ' Qu~ntities to b9 Measured Port engine pump - System "B" Pump inlet temp, am pressure: pump outlet pressure. Port elevator, port aileron, and rudder jscks. System "A" valve inlet pressure: System "B" V'llve inlet and outlet pressures, Heat exchangers System "B". Inlet temperature to H. Ex. No,l: outlet temp. H. Ex. No. 1: outlet temp, H,F.x. No. 2. Accumulator piston position, System "B" Compensation piston position, System "B". • 1. 2. J. • ., . 6. CF-105 - INSTRUMENTATION - ISSUE 5 J-75 E~INE INSTALLATION D.R. Pattie - Dec . Items which have been added or changed since Issue 4, Ref: 3533/22/J, are underlined in the following list. The instrumentation required on the engine installation has been grouped under five headings as follows:- 1. LUBRICATION (No Sketch) Item Range Accuracy Accuracy Sampling ~ of full range Freguencz Port engine oil pressure 0-50 psig :!: 2 psi :!: lJ, 5/min Stbd engine oil pressure 0-50 psig :!: 2 psi :!: 4% 5/min Oil temp at Port engine inlet 0-500~ :!: 10°F j:ZI, 2/min Oil temp at Stbd engine inlet 0-500°F + 10°F + ZI, 2/min Port engine gearbox oil heat exchanger inlet temperature -65 +500°F + 10°F + 'l1, 2/min Stbd engine gearbox oil heat exchanger inlet temperature -65 +5oo°F :!: 10°F :!: 'l1, 2/min 2. ENGINE CONDITIONS (No Sketch) • :;, Item 7. Port engine power lever position t 8. Stbd engine power level posit.ion t 9. Port engine L.P. compressor R.P.M. 10. Stbd engine L.P. compressor R.P.M. llo Port engine H.P. compressor R.P.M.* 12. Stbd engine H.P. compressor R.P.M. * 13. Port engine intake static pressure 14. Stbd engine intake static pressure 15. Port engine intake total head pressure. 16 .Stbd engine intake total head pressure. 17. H.P. compressor discharge press. Port. 18. H.P. compressor discharge press. Stbd. 19. H. P. compressor diseh~rge temp. Port 20. H.P. compressor discharge temp. Stbd 3 • FUEL FLCW • • Mass flow to Port engine. !. Mass flow to Stbd engineo 23. Fuel temp at inlet to Port engine burner. 24. Fuel temp at inlet to Stbd engine burner, Range Accuracy Accur cy Sampling % of full range Frequency ! ]$ 2/min ! J$ 2/min ! 0.5% 12/min :!: o. 5% 12/min ! 0.5% 12/min !. o. 5% 12/min 0-30 psie. !. 0.3psi ! ]$ 6/min &Cont 0-30 psia ! 0.3psi ! ]$ 6/min &Cont o 0-30 psia ! o. 3psi + J$ 12/min 0-30 psia + 0.3psi ! J$ 12/min 0-400 psia ! 4 psi + J$ 12/min 0-400 psia :!: 4 psi ! J$ 12/min 0-lOOO°F ! 10 F 0 ! ]$ 12/min 0-lOOO°F + 10 F 0 ! ]$ 12/min (No Sketch) 0-25,000lb;br :!;125 lb/br ! 0.5% 12/min 0-25,000lb;br:!;125 lb/br ! 0.5% 12/min -65 +3oo°F ! .5Fo + Z1, 2/min -65 +300°F + 5Fo ! Z1, 2/min To be measured on the airframe end of the flexible drive to engine. * A visual indication of both Port and Starboard H.P. compressor speeds is required in the Pilot's oockpito 4. COOL!!£ - Port engine only (See Fig • • Item 25. Top of No.l wing spar beside engine mount 26. Bottom of No.l wing spar beside engine mount. 27. Neck of engine mount. 28. Structure below turbine* 29. Top inboard shroud aft of Stn. 742 t 30. Top inboard shroud aft of Stn. 742 t 31. Top inboard shroud aft of Stno 803 t 32. Outer segment of shroud aft of Stb 803t 33. Lower segment of shroud aft of Stn 803t 34; Bottom shroud Steel-Al. junction at Stn. 803 t Range 0-300°F 0-300°F 0-750°F 0-400°F 0-400°F 0-400°F o-4oo°F o-4oo°F 0-400°F o-4oo°F 35. On the inner surface of sting on enginef_ 0-lOOO°F 360 Air temp top rear compressor Zone 1 37. Air temp under turbine Zone 2. 38. Air temp above turbine Zone 2. • • Air temp at Stn. 803 top Zone 2. 1. Air temp at Stn. 803 Bottom Zone 2. 41. Ambient air temp fwd.of parachute bay (Not'' shown in Fig). 0-500°F 0-300°F 0-300°F 0-400°F 0-400°F 0-300°F * On the inner face of the inner flange of the frame. t On the outer surface of the shroud. Accuracy Accuracy Sampling .! zyo + zyo + zyo + zyo + zyo ! zyo ! zyo :!: JFO % of full range Frequency :!: 1% + 1% ! 1% :t 1% + 1% :;: 1% :;: 1% :;: 1% ! 1% :!: 1% + 1% + 1% + 1% + 1% :;: 1% :t-1% :!: 1% 1/min 1/min 1/m.in 1/min 1/min 1/min 1/min 1/min 1/min 1/min 5/min 1/min 1/min 1/min 1/min 1/min 1/min • 5. STATIC PRESSURES - Port engine only (See Fig.l) Item Range Accuracy Accuracy Sampling • ~ of full range Freguencr 42 . Zone 1, top centre compressor 0-20 psig * :!:: 0.2psi + 1% 6/min & Cont. 43. Zone 2, top rear compressor 0-20 psig * + 0.2psi ! 1% 6/min & Cont. 44. Zone 2, bottom mid-section tailpipe 0-20 psig * + 0.2psi :!: 1% 6/min & Cont . 45. Ambient bet'ween engines f'w~ of para- chute bay 0-5 psig * :!:: 0.2psi :!:: 1% 6/min & Conto With reference to aircraft static • • / ,.., sECRt.' i ---- -- ---- ~ X _ri __ • - ✓----- ......... ' / " / " I \ I \ £/Vtr1-1f'Kr Sy-s T01ncAL fbR7' SYfT~/1 p o-3o ~ ,L_-...;.... rVJEL,.,-.~ Tlllll( "'Vl. -'rlfQ J .ST/jJ). 4 L Jo ICATNl. 7'1HIC L - At.il FLOV /...1M1r1:<1t PR{~ 'P/(ESflllU KEl>IIOl>lLlln,-J ,41.'- AJA. /{Ever VALVk- Or'~DO. NEC.. 0 G Sr&P. 6 SECRET V ··~ ') p o-30 zJ. 10L_--.;... P 0 -30 .z). . V)ILY( ,;_;.... _ JTC>D 8 .fr8.D 7 l l 1----- Oi'.lfl). • 1. 2. .3. • Pump inlet Pump inlet Item pressure CF-105 - INSTRUM8Nl'A.TION - ISSUE 5 UTILITY HYDRAULICS Range Accuracy (one pump) 0-200 peia :t lOpsi temperature (one pump) -65 +J00°F + 5Fo 1 Brake cylinder return temperature (one off) -65 +500°F + 10F 0 Accuracy Sampling :& Qf full range Fregutuic:i: :!:. 5% 10/sec :!:. 1% 2/min ! z,, 1/sec ,. CF-105 - INSTRUMENI'AT I ON - ISSUE 5 AIR CONDIT IOI/ING SYSTEM D,R. Pattie November , 1955. 1. LIST OF INSTRUMENT AT ION Number indicates location in system, see sketch. T PS pt 6,P Location See Sketch 1 2 3 4 5 6 7 8 9 10 11 T T T T T T T instrument to measure temperature. instrument to measure static pressure o instrument to measure total head pressure . Instruments Reffi!ired Descri12tion PS as close to Port engine bleed as possible. PS immediately after reducing valve on Port engine line, Ps ,'.j p macs flow for fuel pressurization system, Pt turbine inlet conditions. PS turbine outlet conditions. RPM bearing temreratures and shaft R.P. M. PS ll P mass flow to cabin (at temperature se?sor). ps cabin conditions, Tempernture to be measured at six points. T at inlet to fan, ,,. ....L Pt mass flow of exhaust from fan (exit conditions) ,* rake Pt rake m~ss flow at ram air exit,* * Items under-lined are added or changed from Issue, (Continued/ •.• /6 2. SUMMARY • 2.1 Temperature • Instrument Ran;,;e Accuracy A.ccuracy Recording ( °F l (F 0 ) (~ of R,mge) F;:eguencr Tl -t-100 +1000 ;!:10 1% 1/sec TJ -20 +400 !5 1% 5/min T4 -20 +250 :!:5 Z!, 5/min T5 -1.30 +100 :!;4 Zfo 5/min T6 Instrument to be bu:l.lt into turbine unit. 2/min T7 -20 +130 ,!5 '51, 5/min T8 - 6 off 0 +-200* !2 1! T9 0 -t-500 :!;10 21, 5/min llQ_ 0 T600 :!:10 Z!:. 5/min lll.. 0 +500 !:10 ~ ~ • 2.2 St atic Pres~ure Instrument Range A.ccuraoy A.ccuracy Recording (pstal (pail (~ of R~!:!,cre) Freguencz P81 0-360 ;!:10 Zf, 1/sec P5 2 0-100 :!:l 1% 1/sec Ps '.3 0-100 ;!:l l% 5/nin Pl'!5 0-20 !0• 2 1% 5/min Pa? 0-20 :!;0.2 ]$ 5/min P6 8 0-20 !C'.1 o. 5% 1/sec P 8 10 0-20 ;!:0.2 1% 5/min P8 11 0-20 ,!v.2 1% 5/min • Items under-lined are added or changed from Issue 4., Ref. ,. • ,. (Continued/ .• o rt 2o3 Total Head Pressure I nstrument Range ~ Accuracy Accuracy Recording ' ~[!si l {~ of Range} Freguenci ~p 3 0- l0 psi ,t0.2 2% 5/min Pt4 0- l00psia ::!.l 1% 5/min Ll P 7 C- l0psi 2;0. 2 2,t 5/min Pt10 .rake 0- 30psia :!;:0 . 3 1% 5/rnin Ptll rake 0-J0 psia .:;;.0.3 1% 5/min 2. 4 Miscellaneous I n addition, it is required to measure turbine R.P . M. , sea location 6 in sketch . As in the case of bearing temperature, transducers will be built i nto the unit, PY AIR.search . The sampling rate required :for turbine R. P.M. is 5/sec . ,e T +-JOO + 1000• F QV'•~#•- L. ,. (i~OV/11# TUlll1W( I/. ,I. i------'/ <:, - •• .J'r&p J,i:N(;l/11& Co "T ~ ""lSOlt 0 -JOO f.s1.<1 J )', J ~ttr ~ - ~ - Co#CPrs. llP CM..!P!. H.P.@(OUVP Cofi'{'l!C.r>DH A.WE ~A.JJ,t.t Ml5"•"'" lt-'EL 8ATrtilfY ~t---- • 1. 2. 3. 4. • 5. 6. 7. 8. 9. 10. ll. 12. 13. 14. 15. 16. 17. • • 18. CF-105 - INSTRl.11£NTAT!0N - ISSUE 5 EI.ECTRICS Item Range Accuracy ! Temp of aft bearing - port alter- nator. -70 +45o°F ;!:10F 0 Voltage A ,6 port alternator. 0-13CNAC ! o. 75V Voltage B f6 port alternator. 0-130VAC ! 0.75V Voltage C ,6 port alternator. 0-l:3CNAC i o. 75V Voltage A f6 stbd alternator. 0-130VAC ! o. 7':N Voltage B f6 stbd alternator. 0-130VAC ! o. 75V Voltage C t1 etbd alternator. 0-130VAC :!: o. 75V Current A f6 port alternator. o-8oA :!: 0.4A Current B f6 port alternator. 0-80A !, 0.4A Current C ~ port alternator. 0-80A :,:!: 0.4A Current A f6 stbd alternator. 0-80A :!: 0,4A Current. B f6 sthd alternator 0 0-80A :!: 0.4A· Current C ,6 stbd alternatoro 0-80A !. 0~4A D.C. voltage of trans rect unit port. 0-321/DC :!: .16V D.C. voltage of trans rect unit stbd. 0-32VDC ! .16V D.C. current of trans rect unit port. 0-135A :!: • 75A . D.C. current of trans rect unit stbd. 0-135A + .76A Exhaust temp of T.R.U.S. 0-300°:F :E 6F Accuracy Sampling of full r~D&l:!l Fre~Jd~!lQI ;!:Z/, 2/min ! 0.5% 1/min ! 0.5% 1/min :!: o. 5% 1/min ! 0.5% 1/min ! 0.5% 1/min :!: 0.5% 1/min !. o. 5% 1/min :!: 0.5% 1/min :!: 0.5% 1/min !. o. 5% 1/min :!: o. 5% 1/min ! 0o5% 1/min !. 0o5% 1/min !. o. 5% 1/min :!: 0.5% "ss,~" ~~ 1/min _ 1/min SECRET • • (Continued/ .•• Item Range 19. Temp of N.W. well, above circuit breaker 0-200°F 20. Temp of N.W. well, above master warning box 0-200°F SECRET ·!i.ccuracy A.ccuracy % of full range ·Sampling Freguency 21. Temp of electrical bay. -70 +275°F : 7F0 1/m1n 1/min r , • 1. I 4. 5. 6. • CF-105 - INSTRUMENTATION - ISSUE 5 UNDERCARRIAGE Item Range A.ccuracy ~ Temp of brake plates o-2ooo°F :t 40Fo Temp of brake plates o-2ooo°F :t 40Fo U/C leg acceleration fore & aft port. -75 +75g ! 6g U/C leg acceleration fore & aft starboard. -75 +75g :t 6g sECREi Accuracy Sampling Q1: full r1ang:e F;cegu12ncz :t ZI, 1/sec) )4 off :t ZI, 1/sec) :t 4:1, 50/sec :t 4:1, 50/sec • • • CF-105 INSTRUMENTATION - ISSUE 5 STROCTOR{\L INTF..GR!TY November 1955. D. R. Pattie . Structural Strnin Gauges, (Ref, letter 3770/22/J) Figs. l to 4 show the approximate positions of 52 channels of strain gauges to be installed in aircraft l, 2 and Ji- Fig. l - r ; Fig . 2 - Fig. 3 - Fig. 4 " - One channel on each strut at stations 485, 591, 644 and 697. 10 Channels on frame at Station 697 6 Channels on lower longeron 12 Channels on inner wing 4 Channels on aft box 12 Channels on fin 18 6 16 .. Total number of Channels 52 The frequency of sampling in each channel is provisionally 5/sec. Strain gauges are not to be placed close to joints, doublers, rivet holes or bolts. Final position of all strain gauges to be approved by F.P. Mitchell, Chief Stress Engineer. Vibration Pick-Up Accelerometers. (To be installed in aircraft 1 and 2 only) Fig . 5 shows the approximate loc~tions of 57 vibration pick-up accelero meters, exact locations to be confirmed with J .McKillop ·or Aerodynamics Dept. The required range is -10 to +l(l, , accuracy ' - :!: 0.2%, recording up to 60cps. Airborne continuous trace recording of all accelerometers is required, and provi, ion should be made to telemeter each accelerometer, only , ten u accelerometers being telemetered at any one time, these being selected at tb~ ground station. Flight Test Dept should report any complication in the instrumentatJ n ·Jising from the LJ cJ l I "!'f"" requirements of ground selection of chan 1 "°"' ~ ne s. _::C::;,./2.::::.'5__;_Fi_:R~A--'-M--'-'t="------=4-.::.._~.5"--''T,c....,if'-'--""'U--'--T----=S=-----'-,4_._1-'-----=S::;__r'-A....:..T--'--'--I O_N_-"6"----1 ..... cu1ifll ...Si:CTION B ·/3 r / NUl'-fBcR. OF Cfl/\N Nici...!; ON FRAN.£ - 10 ·• UNetfsfif:,ro FIG. l • A A • SrA Of 5fl!l 6'i] lOWE{ LUNG£R0II/ - ONE SW£: ONL.( ~-- • u NOMB1---- -f': Sli.ErcH SMow,Nc- LocA,,ofV OF j_q 47 441 .. -+ 4S 6 S' + 5"0 ~ '+- s-, -.rr .r.s ~2 + 16 ♦ - ---------- -- --- -- - -- - - - - - - -- - - - '------I IJ -t:'------ " ______ ,.__ ------ == ----------~- - - - -- ------ ---- - - - --- -- - - - -~----\

CF-105 Proposed flight test program (A/C 1, 2 and 3)

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