NRC-CISTI J. H. PARKIN BRANCH • • Date To From Subject Avro Aircraft Li.,11:.. ted November 27, 1956, Mr. S.E. Harper - Chief Experimental Engineer. John Morris - Assistant Chief Aerodynamicist. CF-105 INSTRUMENTATION - ISSUE NO, 7. Reference: 4028/0ZA/J, Her?wJ. th a copy of Issue No, 7 of "CF-105 Instrumentation", this belng a consolidated list of the instrumentation requirements for CF-105 aircraft numbers 1, 2 & J. This replaces Issue No, 5 which wa; issued in a number of separate parts in Nov,- Dec. 1955. Classili<...,rnon cancelled/c anged to .. • JoLn Morris, DNV/ah Assistant Chief Aerodyna.micist '.'.ess~s: J ,C. Floyd s. Kwiatkowski R.N. Lindley I. Craig J.?.. Chamberlin G. Shaw G. Hake w.s . Sloan F. Brame E. Duret F.P. Mitchell J .c. McKillop A, Crust K. Korsak B. Wood R. Young H. :-lalinowski s. Brown Aero Files s. WM tPley J. Cleminson Central Files (2) A . ii RO E CAN ADA MAL T ON • ONTARIO TECH~ICAL DEPARTMENT (Aircraft) AIR C RAF T CF-105 REPORT No ____________ _ FILE No No O F SHEETS: ___________ _ TITLE CF-105 INSTRUMENI'ATION ISSUE N0,7 P R EPARED BY DATE C H ECKED BY DATE ~UPERVISED BY DATE APPROVED BY 1ss4E NO REVISION No REVISED BY APPROVED BY DATE REMARKS AI RC R A F T : • CF-105 l 2 3 4 5 6 7 • 8 9 . .. /IVRO AIRCRAFT LIM /TEO MA~TON ~ ONTAR I O TECHNICAL DEPARTMENT Instrumentation .nm& Stability and Control Flying Control Hydraulics Engine Installation Fuel System , . ·, Utility Hydraulics Air Conditioning System Eleo.trics Structural Integrity 7 Under carriage i DATE C H ECKED B Y D .ATE ~ l · 8 . . 11 .. 15 21 22 26 28 35 • •• • .'·. . .. ~ AVR0 A I RC R ~ ·";,,- L / Mll'EO MALT O N •• O N T A R I O REPORT·. N o . _ _______ __ _ TECHNICAL DEPARTMENT S HEET NO PRE P ARED BY AI RCR A FT CF-105 C HEC KE D B Y . CF-105 INSTRUMENTATION, ISSUE NO, 7 This issue replaces Issue 5 which was·-issued in a number of separate sections in November and December, 1955, Issue 6 applied only to the "Engine Installation" instrumentation and it also is superseded by this issue. Changes from Issue 5 are indicated by underlining or by ·a vertical line in the margin. The changes are summarised below, Section l Stability and Control Items 1 & 2 7 8 14 Triple range instrumentation introduced, Yaw rate replaces azimuth rate. Yaw acceleration replaces azimuth acceleration. Instrument range increased to •32 to +32 ft/sec2 from -16 to +16 ft/sec2, •• A number of items previously required at 20/sec are nov required on continuous trace. Section 2 Flying Control Hydraulics Items 2 to 12 inoluflive now required at 40/sec in~tead of · at 10/sec. 18 to 32 inclusive added. Section 3 Engine Installation Items 1 & 2 Oil pressure ran~ increased from 0-50 to 0-80 psi._ 21 to 26 inclusive added. 27 & 28 Lower limlt of mass flow range raised to 600 lb/hr. from O lb/hr. • 31 added, this replaces items 25, 26 & 27 of Is sue 5 which are deleted . 32 to'41 inclusive - Instrumentation range changed to have lover limit of 100°F instead of O"F 48 to 56 inclusive added, ' 57 to 60 inclusive - Range -changed to have lower limit of ~5 psi. inst~ad of O psi. D A T E DATE A IRC R AFT ,I ~ Al/R O ; I / RCRAFT L I MITEO r., REPORT No __________ _ MALTON ONTARIO TECHNICAL DEPARTMENT SHEET No. _ _ ________ _ PREPARED BY CF-105 Instrument at ion CHECKED BY JED Section 4 Fuel System Location 3 - Temperature in starboard wing added. 12 - Temperature of pressurization air added . 5 Pressure range increased t o 0-35 peia from 0-30 psia. Mase flow - Range of flows to be measured naw defined separately for engine and afterburnet. ; Section 5 Utility Hydr1uilios ./ Items 2 & 3 added. Section 6 Air Conditioning Location 3 - Instrument range and accuracy changed from -,: 0-10 psi. and !0.20 to 0-5 psi. and !0.25 respectively . ., 7 - Instrument range and accuracy changed from 0-10 psi. and !0.20 to 0-1 psi. and !0.05 respectively, 9 - Total head pressure, Pt9, added. In format ion in Inter-Departmental Memo, ref . 9882/16!/J, dated June 18, 1956, should be disregarded , Section 7 Electrics Item 22 added. Section 8 Structural Integrity Requirements for telemeten, of vibration pick-up accelerometers are changed. Section 9 Undercarriage No change. DATE DATE CF-105 INSTRUMENTATION - ISSUE J STABI+,ITY AND CONTROL / October, 1956. In the following list, the instrumentation has been grouped under four headings:- 1. Ambient Conditions. 2. Motion of Aircraft. J. Control Surface Motion. 4. Control Mechanism. IFIED Three sketches are provided to show the location of instrumenta tion, or to define quantities to be measured, Items marked * - Phase shift at 15 cps. must not exceed ; 0 • Items marked X - Paqui rea e.a ee Un-.•~11 i•&H •• wel.1. •• •• •P••'''•d l!lal•;~Jqe~ •• ~glll'!t':f,Noq!ll!!"lliea•s~. Provision to be made to telemeter each of these items . ,\ _,. ae>ft'b1'nUfltta.-+.1'!W, but no more than eight of these items will be telemetered 1. ), at any one time. metry is·.± '3%. Required accuracy in oc: ti:mua it mes •1111 ,Umg and i11 tele- 1 Changes from issue 5, Ref. 48JJ/22/J, (October 20, 1955), are underlined. 1. AMBIENT CONDITIONS (see Fig. 1) .!!fil! RANGE ACCURACY AGCURACY SAMPLING % of full. range FREQUENCY A!!l!21~G!c Conditions ' Aircraft static pressure 0 - 2160 1 . 2 J:. 0.75% 1/2 ± Limited range 0 - 720 1 o. 75% 1/2 sec. Limited range 0 - 283 1 + 0.75'/, 1/2 sec. Differential pressure (Total head - aircraft static) 0 - 2 1/2 sec. Limited range --. ,. 0 - 1 1/2 sec. Limited range 0 - 7 1/2 sec • Free Air Total Temperat ure -65 +J50°F .± 2°F ± 0.5% 1/2 sec. •-· ---------------- • 4. 5. ITEM Angle of Pitch Q * Limited Range * . Q * 6 .• , ~i~uth Angle t _. "Limited range 'i 7. 8. 9. 10. Rate of yaw * Angle of Bank/ Limited range • fl 11. Angle of Attack q • 12. Angle of Sideslip ~ 2. MGrION OF AIRCRAFl' (see Fig • -60 +60° -10 +10° -30 +30°/sec 0-.3600 -10 +10° -.30 +.30°/sec - 50 +50°/ sec2 -85 +85° -25 +25° -300 +300°/sec -10 +40° -15 +15° Accuracy .1 0.5° .1 0.1° .1 0.3°/sec + 0.3°/sec .1 o.5°/sec2 + 0.5° ± 0.25° 13. !4>ng1ivdinal Accelera- • tion X •32 +32 ft/seo2 .1 0.3 rt/sec2 14'. Lateral Accelaration Y •32 +32 ft/sec2 .1 0 • .3 ft/sec2 -100 +.300ft/seo 2 .1 2 ft/sec2 .. 15. Normal Accelerat'ion Z (-3 +8g) Accuracy % of full range .± o. 5% .± o. 5% .± o. 5% ± 0.1% .:t 0.5% .± 0. 5% .± o. 5% ± 0.5% .± 0.5% .± o. 5% .± 0.2% .1 o. 5% ,:t 0.5% .± o. 5% .:t 0,5% Sampling Frequency 10/sec 10/sec Cont. 10/sec 10/sec Cont 10/sec X 10/sec X 10/sec 10/sec X Cont 5/sec Cont X. X X X X UNC J. CONTROL SURFACE MOTION ( see Fig. 1) - Accur acy Sampling ITEM Rang:e AccuraC:£ 'I, of full range Frequency 16. Port Elevator Angle Oe * -JO + 20° .± o.Jo .± o. 5% Cont. X Limited Range*' -10 + 100 .± 0.1° .1 0.5'1, 20/sec 17. Port Elevator Angular Acceleration * o·e -200 + 200°L .± 2°/sec4 sec2 .± o. 5% Cont. X 18. Stbd Elevat or Angle 6e * -JO + 20° i 0.30 .± 0.5% Cont. X Limited Range* -10 + 100 .± 0.1° .± 0.5% 20/aec 19. Port Aileron An1le 6a * -19 + 19° .± 0 2° .± 0.5% _Q_g_ni, X -10 + 10° • 0 .± o. 5% 20/sec Limited Range .± 0 .. 1 20. Port Aileron Angular Acceleration* Oa -200 + 200°1 "' '- sec2 .± 2°/ sec2 .± 0.5% Cont X 21. Stbd Ail eron Angle Oa ~ -19 + 19° + 0.2° .± o. 5% Cont X Limited Range • -10 + 100 ; 0.1° .1 0,5% 20/sec 22. Angle of Rud,1er 6r i. -JO + J0° .± 0.3° ± 0.5% Cont X LimiteJ Range i. ., -10 + 10° .± 0.1° .± o. 5% 20/sec - 2J. Angular Acceleration of Rudj er 1 Br -200 +200°{ .± 2°/aec2 sec .± 0.5% Cont X 24. Port Airbrake Angle 0-60° .± 20 .± 'ft 5/sec 25. Stbd Airbrake Angle 0-60° .± 20 .± 'ft 5/scc ~ ... (1ocAr10N OF TOTAL. HeAo AND '1t>TAL TEl"IP~~A"TUR.£ PJC.ot!.eS Nor YET J)eC1!)0:,) ' t ,j .r i ·i l, ·1 lj I t t 1 l I .ED .STLJD. WING i .SK'e-Tr/-1 511°"'1'/NG l.DCATION oF /NSTRUl1£.NTA.TON ;=-ak AH.B1E1Vr COHIUrJOJ,JI { rllJJAAI< ANG££ -PoRT'9-JTIJI>. \ I 9- CoNTROL .SUR. ""'er /1,fO.,.JON F'iG.1 pESCRI PT ION OF SKETCH 1 Jl Let OX, OY and OZ be three mutually perpendicular axis with origin O, such that:- and OX is parallel to the longitudinal datum of the aircraft, OY is parallel to the lateral or spanwise datu~, DZ is perpenJ icular to the plane XOY. Let O be projected into a horizontal plane in 0 1 , also project OX into 0 1 X', OY into 0' Y',. Let 0 1C' be a refe rence direction in the horizontal plane, and let OC be the reference di rection in the plane of the aircraft. Let the horizontal plane thr ough O intersect xx•· in X'', and YY' in Y", then, ANGLE OF PITCH Q = LXOX•~ the angle between the loneitu 1inal datum of the aircraft and the horizontal plane. ANGLE OF BANK_1 • /JOY", the anele between the l~teral datum of the aircraft and the horizontal plane. AZIMl.n'H ANGLE t m Lc•o•x•, the angle between the reference direction anJ the projection of the longitudinal datum of the aircraft in the horizontal plane. YAW AN GLE :( • /cox, the angle between the reference direction and the longitudinal datum o1 the aircraft, in the plane of the aircraft, XOY. Further, l et OR lie parallel to the direction of the r elative wind, and let OR8 and ORp be projections of OR in planes XOY and XOZ respectively, then, ANGLE OF ATTAC~ g. LXORp, the component of the relative wind in the plane xoz . ANGLE 01'' '.~ l ; ~SLI P = LXOR8 , the component of the relative wind in the plane XOY. ITEM QUANTITIES TO BE ME ASQRED Angle of Pi ·,eh Q Q - Angle or' Bank fJ ~ Azimuth Angle • Angle of Attack a: Angle of SiJeslip ~ .. LongituJinal Acceleration X .. l-ateral Acceleration y .. Normal Accelerat ion z .. Yaw angle )' y NOfE ON FLYING CON TROL MECHANISM The sketch opposite, shows the elevator control system in its essenti a ls, for the purpose of describing the instrumentation. While the a i le ron system is practically identical to the elevator system, the r udJer system has no parallel servo • • In the elevator and ai l eron, Sy items th e feel unit, and trim adju s tment are ~mpl oyctl onl y in Emergency Manual mode of operation, when the parallel s ; rvo is by-passed and the Jr.unper servo is centrali " ed by a central i s ing device. The rud ,er darnper servo is also provi-led wi th a central i sing arrani:::ement, anJ has duplicate electrica~ and hydraulic systems. In ~1ar.ual MoJe of operation, the pilot 1s effort on the stick strains the mechanism from the stick i:; rip to t he rear quaJrant against the _mrallel se rvo, which operates in response to an "error" signal. The strain is picked-up by a force transducer, the signal being balanced against the sii:::nal from the "feel" network which may consist of - stick position, q, stick force/g, etc., components. The resulting 0 error" signal, su i tably a mplifieJ, i s fe d to t he parallel s ervo, whi ch moves in such a direction as to reduce the error signa l to zero. 1. 2. J. ® PAKA LI. E: l .5£R.v (n.£crRo -.WY.bR.~.w.,c) I .-,:-cc L I UNrr I @ /;)4/1 P£ fl.. .5 f"~ VO {ELECTRO HYDR.Au L 1cJ Acru1,,ro1t 5/(F'TCl·I OP Fl...YINC. CCJ/f,ITROL MECHANlS.1'1 Stick Force - Elevator, Aileron, and Rudder Pedal Force. Stick Position - Elevator, Aileron, and Rudder Pedal Position. Position of Pprallel Servos - El$vator and Aileron. Damper servo signal - EleTator, iileron, Rudder and Emergency Rudder. Damper servo position - Elevator Port & Stb'd, Aileron Port & Stb'd, and Rudder. Trimmer position - Elevator, Ailtron, and Rudder. FiG. 3 • 1. 2. J. 4. 5. 6. CF-105 - INSTRUMENT AT ION - ISS f»iJ •7 FLYHG CONTROL HYJ:1AULICS November, 1956. In the following list, changes from Issue 5, Ref. 4861/22/J, dated October 21, 1955, are underlined, or i ndicateJ by a vertical line in. the margin. The sketch, on the f oll.owing paee, in ..1i cates the location of instrument ation in the Flying Control Hyuraulic System. Item System Range Accuracy A,; curacy % of full range Location ~1i see sketch Port engine pump inlet temp. B •65 +J00°F .± 5°F .± 2% Port engine pump inlet press. ~ 0 -200 psi .± 5 psi .± 'Jf, Port engine pump outlet press. 12 0 •5000 psi .± 100 psi .± 2% Locat ion {2L seo sketch Port elevator valve inlet press. A 0 -5000 psi .1100 psi .t 2$, Port elevator valve inlet press. i 0 -5000 psi .t 100 psi .± 2% Port r eturn 0 -2000 elevator jack press. 12 psi .± 40 psi ± 2% 7~Port aileron valve inlet press. A 0 -5000 psi .t 100 psi .± 2% 8. Port ail eron valve inlet pre ss. 12 0 -5000 psi .± 100 psi .± 2% 9. Por t aileron jack return press. 12 0 -2000 psi .t 40 psi .± 2% 10. RudJer valve inlet pressure. A 0 -5000 psi .± 100 psi .± 2% 11. RudJer valve inlet pressure. 12 0 -500 '.) psi ± 100 psi ± 2'!, 12. RuJder jack return pressure. 12 0 -2000 psi .t 40 psi .± 2% Location { 2l see sketch lJ. No. 1 Heat Ex. inlet temperature B -65 +JOO~F 0 + 2% .t 50 F 14. No. 1 Heat Ex. outlet temperature B -65 +JOO F .t 5 F ± 2% 15. No. 2 Heat Ex. outlet temperature .§ -65 +J00°F .± 5°F .± 2% Location- ~sJ see sketch 16. Accumulator piston position 11 0 .;. 9.6" ± O.l" .± 1% Location {5l see sketch 17. Compensation pi ston pos ition 12 0-10.75" ± 0.2" .± 2% ' Sampling Frequency 2/min 40!._sec 40/_sec 40bec 40 sec 40 sec 40/__sec 40 sec 40 sec 2/min 2/min 2/min 10/sec " 10/min lED Item Range Accuracy Accuracy Sampling % of full range Frequency Location {2 i Se tJ sketch Port Elevator Jack 18. Pres sure in chamber (a) 0-5000 psi .:!: 100 psi .± 2'!, 40/sec 19. Pres Pure in chamber ( b) 0-5000 psi .:!: 100 psi .± 2% 40/sec 20. Pressure in chamber (c) 0-5000 psi .!. 100 psi .± 2% 40/sec 21. Pressure in chamber ( d) 0-5000 psi .± 100 psi .± 2% 40/sec Port . Aileron .Tack 22. Pressure in chamber (a) 0-5000 psi .± 100 psi .± 2% 40/sec 23. PrtJ ssure in chamber ( b) 0-5000 psi .:!: 100 psi ..± 2% 40/sec 24. Pressure in chamber (c) 0-5000 psi ..± 100 psi .t 2% 40/sec 25. Pres sure in chamber (d) 0-5000 psi .t 100 psi .t 2% 40/sec - R.udJer J ack 26. Pressure in chamber (a) 0-5000 psi .:!: 100 psi .t 2% 40/sec 27. Pressure in chamber ( b) 0-5000 psi .± 100 psi ± 2% 40/sec 28. Pressure in chamber (c) 0-5000 psi ± 100 psi .1 2% 40/sec 29. Pres sure in chamber (d) 0-5000 psi ..± 100 psi ± 2'!, 40/sec Valve Pos ition 30. Port elevator valve 0 - 0.25 in. .± 0,002 .t 1% 40/sec 31. Port aileron valve 0 - 0.14 in. .t 0.002 .t 1% 40/sec 32. Rudder valve 0 - 0.10 in. .± 0.,002 .t 2% 40/sec (Friction of the valve position indicator potentiometers should not exceed 0,02 lb.) NOfE ON FLYIN:i CONI'ROL HYDRAULIC (See Skatch Opposite)o The flying controlJ are operated by two independent but practically identical hydraulic systems, A & B,each system having in parallel a pump driven by the Pol't engine and a pump driven by the starboard engine. Whereas 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:- sutem "A" Port Elevator Jacko Stbd Elevator Jacko Port Aileron Jack. Stbd Aileron Jack. Rudder Jacko Rudder Emergency Damper Servo. - sntem "B" Port Elevator Jack. Port Elevator Damper Servo. ·stbd Elevator Jack. Stbd Elevator Damper Servo. Port Aileron Jacko Port Aileron Damper Servo. Stbd Aileron Jack. Stbd Aileron De.mper Servo. Rudder J aek. Rudder Damper Servo. Elevator Parallel Servo. Aileron Parallel Servo. The control surface actuator jacks are each composed of two units in tandem as indioeted in the sketch, one unit being supplied by System 11 A", the other unit by System "B 11 .; Ku, . --rocation In Sketch 1. 3o 5. •Quantities to be Measured Port engine pump - System "B" Pump inlet temp. and pressure: pump outlet pressure, •• Port elevator, port aileron, and rudder jacks. Syatem "A" valve inlet pressure: System "B" valve inlet and outlet pressures. Jack internal pressures. Valve positions. Heat exchangers System "B" 0 Inlet temperature to H. Ex. No.l: outlet temp. H. Ex. No. 1: outlet temp, H.Ex. No. 2. Accumulator piston position, System "B" Compensation piston pcsition, System "B". sure . ve p I SY.ST~,.. tB•/ IIAfl,AB1.• D,$PL.N:£1'1ENT PUMP - FbR r- EW& ,WF (P,sn,w ,..,,,,,.,.,..,-,) :ZER.O ~Tll.O~ C Ar Aooo J,$..i, >fAK . .L'TROIC.lr AT -39.!>-0 /).j.i . p F,T p 0 p Ft1.TE~ GRDU1'D SEIN>C1Nr. PUrtP TE./WfPC/f!ATUlt..£ l••~.JUW'r.AJW£b A"r 2"2S •F P~u/11.E 90/JUJ. • • • INTER- DEPA Rl'MF',NI'.'.I.L :llEMCRANDUM Ref 9777 /02A/J Late July 2J, 1957 To S. E. H<1rper - Chief of Experimenta l Engineer From J. D, Hodge, - 'l'echn1 cal Flight Test Coordinator Subject ARROW 1 INS'I'RUMENT\TION F'\R/Cl05/l - P~ Rl' 3, ISSUE 9 CBL/bb C, C, !.lessrs Herewith I 2sue 9 of Part 3 of F.rJ-:/Cl05/l, "CF-105 Instrumentation - J75 Enoi ne Inst r.ill&tion", superseding ti ll previous i ssue s of Part j. The Y.ajor changes from Issue Pare as follows:- 1 , Item~ 17 to 20 incl. have been deleted. 2. Items 5P..a and 6J have been added. ), The ranges of Items J, 4, 9 - 12, 25, 26, have been amended, and all temperature ranges have been made to conform where possible with the r s nges proposed in Flight Test Dept. '.temo Hef: 6360/22/J dated 25 March 1957, . '. - Al l changes from I ssue 8 are shown underlined in this issue. J . .'\. Chamber] in w. D. Raymond F. P. !Jitchell G. Hake E. Duret s. Whiteley F. Brame R. Young (2) D. ".card ( 5) J. A.mes J. Morr1s 'J. Booth A. Buley Central Files • \{.~ I. J, \i, ~odg~r Te~fnical Fli ght Test Co-ordina tor lE • • • CF105 Instrumentation (~/C Nos, 1, 2 & 3) Part 'J : J75 Engine Inst 'll lation I ssue No. 9 July 23rd 1957 FAR/Cl05/l Part J, Issue 9 Note: 1, All chanees introduced since Issue No, 8 are shown underlined. 2. Items 17 to 20 incl. have been deleted. J. Items 58a 'lnd 6J have been added. 4, The majority of temperature ranges h,ve been amended to reduce the number of different ins trument range s in the interest of s impli city snd ease of calibration between fli eht s . ED ~ .Pi.ASS If IED • Item 1. Port engine oil press ure 2 . Stbd .eng i ne oil pressur e J . Oil Temp at port e ng ine inlet 4. Oil t err-p at S~bd .engine i nl et 5. Por t eng ine gearbox a ir / oil heat exchanger i nl et temperat ur e 6. St bd . e ngi ne gearbox a ir/o il heat exchanger inl e t temperature • 7. Port engine power l ever position+ 8. ·~bd.engine power lever position~ 9 . 10. ll. 12. lJ. 14. 15. 16. Port engine Stbd .engj ne Port eng i ne Stbd.engine L.P . L.P. H.P. H.P. compre ssor compres s or compre :; sor compressor ~ R.P. M .. R ,P.M.::i: R.P. U. k R.P. !.'.. t Port engi ne intake St l d.engine intake Port e ngine intake Stbd.engine intake static pressure (Ps2 ) st atic pressure (Ps2 i total head pressure (Pt 2 ) totnl head pres sur e (Pt 2 ) • 1. LUBRICATICN (No Sketch) Range Accuracy 0 to 80 psi t 2 psi Oto 80 psi :!: 2 ps i -75 to +250° F !6. 5°F -75 to +2500] :t6.50F -75 to +-500°F· -t10°F -75 to t500°F !"10°F 2. ENGINE CONDITIONS (No Sketch) o to 100 deg. Oto 100 deg . o to no% O to 110 ~ 0 to 110 O· to uoi O to 3C psia Oto JO psia O to _30 psia 0 to 30 psia ! 1 deg. t 1 rl eg . to.3 psi ±0.3 ps i to. J psi to. J psi +To be measured at the engine end of the fl exible drive to the engine. Accuracy % of full range !4% !4% "!~ !2% !2% !21, !"1% t1% ±0.5% !0.5% !0.5% !0.5% '!1% 't1% !i% !'1% ~Visual i nd ication of both L. P . compressor speeds i s required in pilot's cockpit if possible • c:: t 'vi sual indicat i on of both H.P. compressor speeds is a definite r equirement s in the pilot's cockpit. Sampl i ng Frequency 5/ mi n 5/ min 2/min 2/mi n 2/min 2/ min 2/min 2/min 12/ min 12/ min 12/min 12/ min 20/sec 20 / sec 12/min 12/Mi n - • 2. ENGINE CONDITIONS (cont'd) Item Range Accuracy } DELEI'ED Turbine discharge press. {Pt7 ) Fort 0 t o 45 psia !0.45 psi Turbine discharge press . {Pt 7 ) Stbd. 0 to 45 psia !0.45 psi Turbine di s charge temp. (Tt 7 ) Port. 0 to 14000 F 't14F° Turbine discharge temp . {Tt Stbd. 0 to 1400° F !14FO L. P. compressor inlet temp. 7±t 2 ) Port -75 to+-350°F '!4FO L.P. compressor inlet temp. (1't 2 ) Stbd . -75 to+ 350°F !4FO Bleed valve shut indic'lti on + + .. ++ Wiring provi s ion onl y, to auto observer. For ground te s t only . J. _Ji l pressure r~e mav be - J to +18 psi. ~ 8amplin~ Frequency 1 / min 1/min 1/mi n 1/min Cont, Cont. 5/min 6/min 6/min 6/min 6/min 6/m1n • • CF-105 INSTRUMENTATION - ISSUE 1 FUEL SYSTEM October, 1956. FE Changes from issue no. 5 are indicated either by being underlined or by a vertical line in the margin, , 1. LIST OF INSTRUMENTAT ION Numbers refer to location in system, see Figs. 1, 2 and 3, which show Layout of Fuel Tanks, Fuel Transfer System, and Fuel Tank Pressuriza tion System, respectivel y, Locations l to 8 correspond to fuel tanks l to 8. T instrument to measure temperature. P inetrument to measure pressure. Q instrument to measure fuel contents of tank. M instrument to measure mass flow of fuel • Locat i on Instruments Description See Sketches Reguired l 2 p 3 T 4 5 T p 6 7 p 8 9 T 10 p 11 T p 12 T Q Q Q Q Q Q Q Q M M forward fuselage tank. rear fuselage tank, temperature in stbd. wing onlz 1 contents in part and stbd. tanks. port and stbd, wing tanks. temperature and pressure in stbd. tank only. Contents in port and stbd. t anks. port and stbd, wing tanks. pressure in stbd: tank only, Contents port and stbd-. port ani stbd. tanks. fuel entering H.E., stbd. 1 n • fuel to port engine/AB combination. fuel to stbd, engine/AB c~mbination, pressurization air ent ,,ring tank, (Continued/ .•. ' 2. SUMMARY • ,!C 2.1 Temperature Instrument Range Accuracy Accuracy Recording ( OF) (FO) (% of Range) Frequency T5 -65 +160 .t5 2% 2/min T9 -65 +200 .t5 ;t2t 2/min Tll -65 +250 ;±5 2% 1/min TJ -65 +185 _.12_ ~ 1/min Tl2 -65 +350 ;±5 2% 1/min 2.2 Pressure I nstrument Range Accuracy Accuracy Recording • (psia.) (psi) (% of Range) Frequency P2 0-30 ;t0.5 2'/, 1/min P5 0-35 .t0.5 2% 10/min P7 0-30 ;t0.5 2% 1/min Pl0 0-75 .t2 2% 2/min Pll 0-75 .t2 2% 2/min (Continued/ ... •· • (Continued/ ..• ,~. re U.Jt1 2.3 Fuel Contents (This information has been a:.ided since I ssue 4) Instrument Range Accuracy Accuracy Recording (Gals.) (Gals.) (% of Range) Frequency Ql 0-277 .:t 6 ±21, 1/Min. Q2 0-281 .1 6 .:t 2% 1/Min. Q3 Port 0-151 .± 3 .± 2% 1/,un. Stbd. 0-151 .:t 3 ± 2% 1/Min. Q4 Port 0-90 ± 2 .± 2% 1/Min, Stbd. 0-90 .± 2 .t 2% 1/Min • Q5 Port 0-146 .t 3 ± 2% 6/Min. Stbd. 0-146 ± 3 .:t 2% 6/tilin. Q6 Port 0-154 ± 3 ± 2'/, 1/Min. Stbu. 0-154 .± 3 .:t 2% 1/Min. Q7 Port 0-279 .± 6 .± 2% 1/Min • Stbd. 0-279 ± 6 .:t 2G .:Jxrrc:H O F NOJE___ IVHEE/.... WElJ.. Pl".5 I r 10 N • • CF-105 INSTRUMENTATION - ISSUE 7 STRUCTURAL INTEGRITY October, 1956. Changes from Issue 5 are indicated by a vertical line in the margin. Structural Strain Gaugea, (Ref, Letter 3:rzo/22/J) Figs. 1 to 4 show the approximate positions of 52 channels of strain gauges to be instal~ed in aircraft 1, 2 and J:- Fig. 1 - One channel on each strut at stations 485, 591, 644 and 697 10 Channels on frame at Station 697 Fig . 2 - 6 Channels on lower longeron Fig, 3 - 12 Channels on inner wing 4 Channels on aft box Fig, 4 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 & 2 only) Figure 5 shows the approximate location of 57 vibration pick-up accelerometers; the precise location is to be obtained from J. McKillop of the Aerodynamics Department. The required range is -10 to +10 g with an accuracy of~ 0,25 g, and the instruments should be capable of recording. frequencies up to 60 cycles/sec, ,. • Airborne continuous trace recording of all required and telemetering of each should be possible (but not simultaneously). During normal flight testing, telemetering of only two accelerometers will be required, and then only if control surface characteristics are being telemetered for the stability programme; if this is not being done then the telemetering of two accelerometers only will provide no useful information ,and may be dispensed .with. During a specific flutter programme, the requirement fO'f telemetry of accelerometers may be greater, the number required being dependent on the availability of telemetry channels. I c/5 FRAME 4 sr&ur.s ,1-r srArroN • __!;i:CTION B ·C3 NUl'-fBt:-R, OF Cl/AN Ni[l.!i ON FRAME - 10 • ( - .0-A- 742. .5rJ-\.48F NLJMBtJUM8£K. or Cf/ANNJ::J..S - 16 S1;c.r,01v I I I I I I l LDw£& SuRFl;C~ CWt..y 5~CTIOW /Hj I f;:U)'.ATet.l ,- .J>OO"'-. I I 7'yPl(AL Sii<:7tON £J..Jj_ [I G-. 4 1. i. CF•l05 - I NSTRUMEilTATION - ISSUE , 70 "'~" UNDERCARRIAGE No changes have been made i n t his instrumentation list since no, 5, ref, 6J55/22/J, dated January 5, 1956. Item Range Accuracy Accuracy issue Sampling % of full range Frequency U/C leg acceleration fore and aft (port undercarriage) t -75 +75g .:t Jg .± 4% 50/sec u/c leg acceleration fore andt aft ( starboard nn-1ercarriage) -75 +75g .± Jg .± 4% 50/sec * Accel erometer should be mounted on the lower end of the undercarri-age leg, close to the wheels, . r Da~e Decomber 21, 1956, To Mr, S,E. Harp c,r From J chn Morris Avro Aircraft Lirnited• U NCLASS'-fJf INTER-DEPARTMENTAL MEl10RANDUH Reference:4510/02B/J S\lbject CF105. I~TRUMEN'l'ATION a IS$UE ~l 01 7 cc In section l 11Stability and Control" of cFl05 Instrumentation • Issue No, 7, an X mar k, i n~icating tha t provision should be made for telemetery, was omitted from the foll owing i terns, Item numbers: l ( complete range), 2 ( complete r 'lnge), 5 , '/, 11, 12, 14, 15, 16 (complete r 'l.Dge), 17, 18 (coillplcte range), 19 (complete range), 20, 21 (complete r ange), 22 (coDple ',e ran;e), 23, 34 to 42 i nclusive. The definition of t he symbol X given on sheet no, l of the instrumentation schedule is to be ammended to read as follows: "I terns markeJ X - Provision is to be maJe t o telemeter each of these i terns, but teleme tery of no more t han eight will be required nt any one tlme, The r eq .1 ireJ. accuracy in t elemete ry is 3%, D:iv/rs MeS!ff8: .J .c. Floyd R, N, Lin,.1l ey J,A, Chamber lin G, Hake f. Brame F,?. l,li tchell K. i

CF-105 instrumentation. Issue no. 7

Archive

AVRO Museum

Name/Title

Entry/Object ID

Category

Web Links and URLs

General Notes

Note