FORM 1749 A Aircraft~ 25201, 25202 and 25203 Report No. --'7 __ 1.,_/_FAR__,_/ .... 3_0 ___ _ Copy . No. 28 - - - - ------ I ssue 2 !Irr . A. Cr ust Classification cancelled/changed to ••••••• by authority oL .............................. (date) Signature ................. ....... .................... ... Rank. ············- FLIGHT TEST PROGRAM AIRCRAFT 25201, 25202 AND 25203 NRC- CiaTt AERO/ M. E. Approved for Technical Design l;jy : Approved for Flight Test By:=--:----:~~.:;...:;;,:;;;~~;::._.,---- Chief F Engineer S E C R E T L18RARY 89:- 05- 1 2 BIBLIOTHEQUE AERO/ G.M. C NRC - IC I SiiT By(Y.:,---~,.-.,__....,,__ ___ oJec e igner Arrow 1 Issue 1 July 1958 71/FAR/30 CIRCULATION, Copies to Messrs, J. c. Floyd R. N. Lindley J. A. Chamberlin c. v. Lindow (2) w. R. Stephens D. Rogers F. Brame F. P. Mitchell (3) s. E. Harper D. N. Seard (6) J. Ames J. Booth J. Scott J. Lynch c. s. Marshall s. Kwiatkowski A. Thomann J. Lucas J. A. McKillop A. Crust (9) for transmittal to R0 C.A 0 F0 u E trORM 1749 A we:: AVR0 AIRCRAFT LIM/TEO MALTON - ONTARIO REPORT NO. _ _:._7__,l/F'--AR--'-/-=3'--0---------;. i TECHNICAL DEPARTMENT SHEET NO. -----------~ , PREPARED BY DATE AI RCRAFT: 25201J 25202 and 25203 f-------------;f-------: CHECKED BY DATE 1.-__________ L_ __________ _j__ _________ .,___--,r---~ ·. FLIGHT TEST PROGRAMME ARROW 1 lo Introduction 2o Allocation of Aircrafto 3o Stability and Control 3ol Introduction 3o2 Method CONTENTS 3.3 Developnent of control systemo 3o4 Stability and control tests. 3o5 Damper developnent tests 3. 6 Structural integrity tests . 3.7 Demonstration programm~. 4. Systems Testing 4.1 Flying Controls 4.2 Engine handling and structural cooling. 4.3 Air Conditioning 4.4 Telecommunications and antennae. 4.5 Fuel systemo 406 Landing gear, speed brake and hydraulic system. 4.7 Electrical power system. 5. Perfonna:nce 5.1 Introduction 5o2 Objec~of programmeo 5.3 Aircraft configuration. 5o4 Scope of test. 6. Notes on program estimation 7. Tables and Charts of Programo 7.1 Summary charts. 7.2 Systems Testing 7o3 Stability and Control. 7.4 Perfonnance UNCLASSlilED ~ AVRO AIRCRAFT LIM/TEO MALTON - ONTARIO REPORT NO. _7.Ll:./r....cFc..,AR=/'--3,.,.0,L_ _______ l SHEET NO. 1 TECHNICAL DEPARTMENT PREPARED BY AIRCRAFT: CHECKED BY lo INTRODUCTION The following report is a more detailed breakdown of the Flight Test programme t han possible at the time when FAR/Cl05/2 was prepared 0 The objects of this programme is to determine the airworthiness and systems functioning of the aircraftj to obtain a preliminary assess ment of the aircraft performance and handling characteristics, and to establish i n stages a s eries of f light envelope bo undaries for safe operation of the aircrafto It is anticipated this will eventually cover the entire fligh t envelope as far as speed is concernedj and up to 80% of limit structural loadso The performance programme is to be conducted j oi ntly by Avro & C0 EoP0 E0 The Weapon Pack Flight Test programme to be carried out on A/C 25203 will be covered in a separate reporto This pro gramme has been discussed at a joint meeting of Co E0 P0 Eo and Avro and found acceptable to both parties 0 Consistent with the request in RoCo A0 Fo letter refo S36- 38- 105- 15 (APO- l)j this document has been reviewed and agreed to by the resident C 0 E 0 P 0 E 0 representati veo DATE DATE E«' AVR0 AIRCRAFT LIM/TEO MALTON - ONTARIO REPORT NO, _,_7.::cl/'-F_AR___,,/~3'-'0-------~ SHEET NO, 2 TECHNICAL DEPARTMENT PREPARED BY AIRCRAFT: CHECKED BY 20 ALLOCATION OF AIRCRAFT FOR TESTING 2el A/C 25201 = This aircraft will be used primarily for systems testing. 2.2 A/C 25202 - This aircraft will be used for aerodynamic testing, namely stability and control9 flying controlsj and C.E.P.E. handling3 the latter being incorporated in the Avro program. 2.3 A/C 25203 = This aircraft will be used for performance testing prior to starting the weapons system testing. U~ C SS ED S E C R E T DATE DATE AIRCRAFT: ;iijlkg' AVRO AIRCRA FT LIMITED MALTON - ONTARIO TECHNICAL DEPARTMENT REPORT NO. _!.:71::,/:...:F:...:AR=/--"3c::O:..._ ______ ___,_ SHEET NO. 3 PREPARED BY DATE CHECKED BY DATE 3. STABILITY AND CONTROL AND STRUCTURAL INTEGRITY TESTING 3ol Introduction This chapter presents objectives, requirements, method and sequence of flight testing of the Arrow aircrafto 3olol Subjects to be considered 3ololol Developnent of control system o 3ololo2 Stability and Control - including assessment of handling qualitieso 3ololo3 Damper development (excluding AFCS)o I 3ololo4 Structural tntegrity Each of above t opics will be discussed separately and the method in which t hey will combine into one program will be indicatedo 3olo2 The :reasonf!I for combining t he above topics are as fo llows ~ 3olo2 ol Economic execution of the whole program 0 Flight test infonnation is required simultaneously on above subjects in order to proceed with developnent program in a most efficient mannero 3o lo2 o2 To explore certain parts of the fli ght envelope, it is necessary to have damping system not only in working order but 'checked out in a quantitiative 1 manner • • • - 3olo2o3 Structural integrity due to controllability problems l in certa_in areas , must-' be combined with damper and associated limiting devices developmento S E C R E T AI RCR A FT : was:: AVR 0 AIR CRAFT LIM/TEO MAL TON - ONTARIO REPORT NO. -1..71=/F~ A,.::R:..:./L.3.,,0"-----------. SHEET NO. 4 TECHNICAL DEPARTMENT P REPARE D BY DATE CHECK ED BY The overall objective of this flight test pr ogramme is to demonstrate that an acceptable pilot-control s-air craft combi nation has been achievedo 3o l o3 Detailed objectives are as follows: - 3olo3ol To demonstrate that control system is satisfactory from the mechanical point of viewo 3010302 To demonstrate that feel and trim characteristics are acceptable in all control modeso 3olo3o3 To show that damping system hardware gener ally performs satisfactofily eogo is free from oscillations 1 spurious sig,_na_ l _s_et_c....::..."------ 3olo3o4 To demonstrate that all required manoeuvres can be performed safely from control stand pointo 3olo3o5 To demonstrate that damper action results in proper co-ordination and damping during manoeuvres 0 DATE 3olo3.6 To demonstrate performance of limiting devices where practical 0 --3olo3o7 To investigate in flight effects of parti~l failures in control or damper system (e ogo engine failures 1 partial hydraulic and elect rical fai l ures). 3o lo3o8 Demonstrate compliance with MIL Speco on aircraft ~ \ V ./ handlingo ~ 3olo3o9 Investi gation of structural integrity0 UNOtASStflED AIRCRAFT: WK AVR0 AIRCRAFT LIM/TEO MALTON - ONTARIO REPORT NO. _7.:....1""/F'---'AR__,/_3~0~-------·. SHEET NO. 5 TECHNICAL DEPARTMENT PREPARED BY DATE CHECKED BY 3o2 Method of Flight Testing Generally it is planned that flight testing will confinn ground test, simulator and theoretical analysis predictionso Most of the develoµnent has or is to be carried out on the ground in steps requiring fli ght test confinnationo. 3o2ol The following major steps are at present planned in sequences as showno 3o2 olol To demonstrate acceptability of flying control system from mechanical point of viewo This includes feel and trim characteristics in various control modes and flight conditionso 3o 2olo2 Measure stability and cont:i;:g_Lder-i..vatLves-0 the free aircraft in par:tS-0.Lthe_f • ht envelope where t hi s is possibleo 3o2olo3 Test damping system in all modes wi thin this established fli ght envelopeo Evaluate it 1s short com\i.ngs 9 undertake design modifications on the basis of ground test and simulator work in!,Q__wpich_ initial flight test data have been fedo DATE NOTE :- The above desi gn and develoµnent tools will be utilized simultaneously whenever possible within the fli ght envelope initially limited to approxo M,. L 75 9 500 knots EAS . 9 311 g 1s 11 9 120o/seco of roll rate o AIRCRAFT: MK AVR0 AIRCRAFT LIM/TEO MALTON - ONTARIO REPORT NO. _:_71__:/=--F-• A_R....,_/__:3:.._0 _______ __; SHEET NO. 6 TECHNICAL DEPARTMENT PREPARED BY DATE CHECKED BY DATE 3o2olo4 Verify in flights the eff ectiveness of any changes introduced on the basis of data obtained from items 3o2olol to 3o2olo3 until an acceptable but not necessarily optimum performance is obtained eog 0 free from seriously objectionable characteristics. 3o2olo5 Extenp flight envelope into the region where flight without dampers may result in controllability problems o Measure pertinent damper characteristics in this areao It is not possible to predict at this time w~at will be the exact f l ight envelope fort hese testso Approximate expected limits are ~ M • 2.0j 630 k;ts 3o2olo6 Perform s tructural integrity testing to an equival ent of Bo% (or l ess where restricted by other aspects ) of limit loads or to command limits of the damping systems whichever is lesso 3o2olo7 Extend the f l i ght envelope to maxo EAS F by probing technique in steps not larger th~n 50 kts EAS preferably using chase plane of equal capability. 3o2olo8 Perform preliminary evaluation of damping system limiting devices by adj$ting their limit levels to lie within structural integrity limits established EK A VR O AIRCRAFT LIM/TEO MALTON - ONTARIO REPORT NO. _7_l~/F_ AR-'-/_3_O _______ _ AIRCRAFT: SHEET NO. 7 TECHNICAL DEPARTMENT PREPARED BY CHECKED BY Perform damper optimizat ion tests where requiredo This test will consist mainly of measurements of DATE DATE damper para~eters over the full speed and altitude range in t he configuration as close as possible to 3o 2ololO Perform further structural integrity danonstrations to limits as agreed mutually by RCAF and Company0 This test to be combined with those required for development of damping system limiting devices. 3.2.loll Incorporate all design changes resulting from earlier tests parti cularly items requiring ' long lead t imes in productiono Perform all tests necessary in conjunction with these change so 3.2.1.12 Consider extension of the flight envelope to full speed cabili ties of Arrow 1 aircraft 0. 30 2. 1.13 Demonstrate handling qualities in accordance with MILO Spec:o 3. 2ol.14 Perform fligh t tests in addition to handling or structural i ntegri ty MIL Spee. requirements as required by the Company o S E=G R D AIRCRAFT: w< AVRO AIR CRAFT LIM/TEO MALTON - ONTARIO REPORT NO . _,_7;;::cl ,._/F_AR__,/:....,3::...;0:...._ ______ _ SHEET NO, 8 TECHNICAL DEPARTMENT PREPARED BY DATE CHECKED BY DATE 3 •. 2.2. The above sequence is j ustified as follows:- 3.2.2.1 In development of the damping system it is of particular importance to verify the aerodynamic parameters 'Which were used in it 1 s deaign. Should these· be significantly different in detail j a number of damper parameters would have to be adjusted. If aerodynamic parameters are availabl-e from flight the damper parameters can be apjusted on the ground based on simulator and ground rig workj thus saving a substantial amount of flight .---.. time and eliminating the time consuming tr~a1 and -error method. 3.2 •• 2 , Measurements of stability and control character., 11 istics in the early part of the program will permit accurate safety monitoring and will permit exact evaluation of aerodynamic pheno~ena that are known to have slowed down a number of development programs on other aircraft particularly the various forms of aerodynamic c~osscoupling eff ectis . UNCtffSlflED AIRCRAFT: EK AVHO A/HCHAFT L/M/TED MALTON - ONTARIO REPORT NO. -1.7,,,,11-/ .,,_F""AR:!l--/_,_30"'-------- SHEET NO. 9 TECHNICAL DEPARTMENT PREPARED BY DATE CHECKED BY DATE These measurements will permit also nunerical evaluation of various aerodynamic effect usually required to be demonstrated in flig~t by specifications and may lead to substantial saving in these flight demonstrations ~.g. structural integrity specifications require demonstration of a nunber of manoeuvres which according to predictions result in 'relatively insignificant load levels. These requirem~nt could be precluded by predictions based on flight measurements of aerodynamic parameters. Air loads and structural analysis will greatly be assisted by exact knowledge of aerodynamic parameters permitting e.g. elimination or reduction of arbitrary increments (defined by spec) used in loads evaluation and resulting often in un- necessarily severe' penalties. Initial damper development can9 and should for safety reasons be carried out prior to full structural integrity test. AI RCR A F T : fflK AVRO AIRCRAFT LIM/TEO MALTON - ONTARIO REPORT NO. _ 7_l~/F_ A_R~/_3_0 ______ _ SHEET NO. 10 TECHNICAL DEPARTM ENT PREPARED BY CHECKED BY 30 20 2 0 6 Difficulties arise in trying - to separate ~~ structural integrity testing frOm demonstrations of various limiting devices which al".Y part or the damperQ o These devices were designed to pr?~e~t the airframe a~ai?st ipadvertent applications of large loads by the pilot and also for protection against failureso Full structural integrity DATE DATE testing cannot therefore be-ca=ied.-Ont til these devices are fully assessedo 3o2o2o7 For test safety reasons it is not advisable to extend the flight envelope to maxo EAS prior to developnent of the dMlp~r to a point where f iI'!ll predictions can be made as to its behaviouro Obviously both emergency and normal dampers are required prior to entering of the max. EAS regiono The detailed requirements of test sequences listed under items 3o2olol to 3o2olol4 are given in following sections which for convience have been arranged by subject rather than by sequence of test 9 eogo all tests required for stability and control are 1isted in section 4 irrespectively of their sequence in the overall programo AIRCRAFT: EK AVR0 AIRCRAFT LIM/TEO MALTON - ONTARIO REPORT NO. _ _,_71=,/c...:F:..:AR=/...,_Jc.::O ______ _ SHEET NO. TECHNICAL DEPARTMENT PREPARED BY CHECKED BY In this manner a lo~ of repeti~ion will be avoided since similar manoeuvres are re- quired in each flight testing stage, the difference being in flight. conditions and/ or severity of the manoeuvre. 3.3 Develoµnent of Flying Control Tests 11 Specific flight tests are not necessary. Evaluation of " pertinent control system characteristics can be carried out simultaneously. with stability and control tests descri bed in the next chapter. Some special instrumentation will be necessary to evaluate important parameters. General flying in differ ent flight conditions will supply all the information required. 3, 4 Stability and Control The main obiect of these tests is to evaluate stability --- -- derivatives. ·--..__ This program will present the required number of test · points necessary to establish these parameters over the full fli ght envel ope which could-however be substantially reduced9 if results agree well with predictions. To evaluate stability derivatives a number of specific manoeuvres are required. Generally a similar type of manoeuvre is required at each selected Mach number and altitude. To describe in detai} the whole flight env~lope approx. 17 flight conditions are required. These could be subdivided ------- DATE DATE AIRCRAFT: ) :,tikE'.' AVR0 AIRCRAFT LIM/TEO MALTON - ONTARIO REPORT NO. ___:_7.=lL./c...F_AR_/t....,:_30.:..._ ______ _ SHEET NO . l'3 TECHNICAL DEPARTMENT PREPARED BY CHECKED BY 3.4.2 In dampers off configuration (all speeds) . 3.4.2.1 Rudder deflections to produce dutch rolling oscillations with maximrnn sideslip not exceeding approxo 40% of limit fin load. Static stability in yaw, dir edral effe ct and damping derivatives can be evaluated from these tests o 3. 4.2.2 Repeat the above who l e pulling steady "g ' s" to obtain variation of derivatives wit h angle of attacko 3. 4.2 . 3 Mild rolls to approx.~ 30° of bank angle to evaluate damping in roll and aile~on yaw. 3. 4.2 . 4 Evaluate asymmetr ic power eff ects. 3,4.3 In dampers off configurat ion - low speeds . 3. 4.3 . 1 Steady sideslip investigation o 3.4.3.2 Handli ng in gear down configuration . 3. 4. 3. 3 Eval ua tion of mini.mrnn s afe flying speed and buffeting characteristics. 3,L.L Check handling with one engine shut-offo I n addition to fli ght condi tions listed at the beginning of section 3.4 it may be necessary to probe some areas in small increments and to_ per form additi onal manoeuvres and measurements in th~se areas 0 SECRET DATE DATE ·1 I I r I I ' AIRCRAFT: EK AVR0 AIRCRAFT LIM/TEO MALTON - ONTARIO REPORT NO, _7_l/:._F_AR__,_/,.:c3_0 _______ _ SHEET NO, l TECHNICAL DEPARTMENT PREPARED BY CHECKED BY "3.5 Damper Development Tepts 3o 5ol For the purpose of damper developnent the flight envelope of the Arrow will be represented by 10 fli ght conditions agreed to by AVR0 and Minneapolis Honeywello At these flight conditions the damper performance will be examined in detail and results of these tests will be projected into the remainder of the flight envelopeo The ten fli ght conditions are the following: - Altitude Mach Nwnber 10000 o? Low Altitude 10000 1.15 Low altitude high EAS 20000 o4 Low speed (landing mode) 20000 o7 Initial test point 20000 Lh High EAS supersonic 30000 095 Transonic cruise condition 30000 106 High R~S supersonic 40000 108 Hi ghest available· Mach Nwnber (Arrow 1) 50000 Ll5 Design altitude 50000 106 Design altitude S E C R E' T DATE DATE AIRCRAFT, EK AVR0 AIRCRAFT LIM/TEO MALTON - ONTARIO REPORT NO. _.:_71:c,/Fc._A_R_,_/ .... 3'-"0 ______ _ SHEET NO. 1 TECHNICAL DEPARTMENT PREPARED B Y CHECKED BY 30$02 The initial damper tests will consist of handling tests in various damper modes to assess the performance and compatibility of damper hardware. Measurements will be made of damper command signals 9 servo motions, sensor outputs etc. The measured quantities in the fonn of oscillograph traces will be examined by AVRO and Minneapolis-Honeywell where necessary analog cc:mputeri and digital computer check programs will be run with data from fli ght te st fed i nto t he computers to establisp proper functioning of the hardware. In this stage optimisation of the damper perfonnance will be limi t ed to whatever is necessary to obtain safe operation. Therefore adjustment of damper gain settings inflight will either be eliminated or limited to a few specific cases. Arry necessary adjustments will be examined on fli ght simulator and introduced into the aircraft damper system on the ground 0 To obtain ai rcraft disturbances necessary to evaluate damper perfo:nnance control column and rudder motions will be utilized and in cases where more exact data are requi red damper step switches provided for this purpose in pilot 1s cockpit will be usedo In the initial t esting stage naviqator 1s damper control panel w~ll not be used in flight but-wilY be necessary for checking r, n'1 r purposes rand a~Ijustments on the ground 0 Since pertinent DATE DATE EK AVR0 AIRCRAFT LIM/TEO MALTON - ONTARIO REPORT NO . .....:...7=,1/'-F_A_R..,_/.,=_3_0 ______ _ AIRCRAFT: SHEET NO. 16 TECHNICAL DEPARTMENT PREPARED BY CHECKED BY testing controls for normal damper mode are located in the navigators cockpit 9 only a preliminary assessment of pitch and roll damper can be obtained. Also it is no~t~ e:~~ e~c~t ~ed~ t=h~a~t~ f~u=l ~l ~dam~. ~p~e=r~ i~n=s~trum~ U~ available for this phase 0 - Flight conditions for these tests will be sel ected from the ten l isted in para0 3o5ol and the usual starting point will be M ~ o7 at 20000 ft. Manoeuvres requi red f or t his evaluation will be t he usual handl ing checks~ e. go commands in roll and pitch generally restrict ed to relativel y small amplitudeso Symmetric and asymmetric power effects will be evaluated and appropriate t ests will be carried out in landing mode at al titude. The general procedure will be that aerodynamic data obtained from f l ight (see section 4) will be fed int o the f l ight si mulator to check damper performance and where necessary appropriate a~justments will be made to the damper parameters. 3.5.3 Second stage of damper testing will begin as soon as the damper and flying control system hardware shows satisfactory performance from mechanicals , hydraulic and electrical point of viewo This will consist of further damper measurements in manoeuvres where higher, ng i s11 and -rates of r oll are used at the flight conditions as DATE DATE d~scribed hriV,.oj.sfll~ P.. . V vl. : 60,000 \.l!S Ri:G\oN I 2. !✓./l'l\ . "y,_W'' :Z ~o,ooo 7.oo,ooo 3 4- l,oc.ooo 2,oo, ooo 5 I 6 l,10~000I\ ~ 0~0001 1 \60,000 12.o, O<>o S"'i'l="P \ t..· O ., ,_ '3· 0 2. · 0 • 3 4 · 0 2·7 2. 0 h 4 4-o '3·4 s 4o 3.4. 'l -7 20 3 ·4 •7-.-, I 2. 0 ~ 6 4-o 3·4 "3·4 3 · 'i.·7 l ·o ll 7 4,0 ~-4 I\ ,g 't· 0 3·4 3· 4- '3·lt 3·4 3:4 [), ·7 1· 0 cl.,·O I ~-• d-.' 0 ~-o &· O ◄ N "' n a ~ ~ n•" -·-r-~0 0 ll• I:' . ~ "'0 ... z•--~· ◄ :a"' _0.., ,.. ... :z ' ◄ ~ ~ tl ,~ ' ' I .. :9 "' ,. Ill ~ n . : -~ " I "' :a .. 0 0 m : II~ -< I I~ I I~ AIRCRAFT: WkK AVRO AIRCRAFT LIMITED MALTON - ONTARIO REPORT NO. --'-7_1,_/F_A_R_,_/~3'--0 ______ _ SHEET NO. __ 2t,__ ______ _ TECHNICAL DEPARTMENT PREPARED BY CHECKED BY 30602 Cont'd coupling effects tends to produce large structural loads in t he majority of f light conditions in damper- off con- figurationo The normal damper mode will be used in these tests and therefore excessively large loads will be avoided. The exact knowledge of damper performance is therefore required for these tests together with firm predictions as to the behaviour of i t 1 s limiting devices and a very cautious approach is mandatory for all tests performed for the first timeo The structural integr i ty demonstration will consist of the following manoeuvres performed at 15 flight conditions representing t he fli ght envelope: 3060 2. l Steady pull-outo 3060202 Checked pullpout. 306.2.3 Steady push- downo 3. 6020 4 Checked push-down. 3060205 Rolling pull~out. 30 60 206 Rudder manoeuvreo The 15 fli gh t conditions will be selected as follows: - 2 low speed conditions 2 subsonic conditions 6 transonic conditions 5 supersonic conditions S E C R E T DATE DATE AIRCRAFT: A VR O A IR CRAFT L I M / TEO MAL TON - ONT ARIO REPORT NO. ~ 7.=1L/F:....::AR:..:./L:3::..:0c,__ ______ _ SHE ET N O. 23 TECHNICAL DEPARTMENT PREPARED BY DA TE CHECKED B Y D ATE 3.6.2 Cont'd The test will be car ried out in steps of approxo 20% in load level peginning at ho% and not exceeding Bo% of desi gn l oads or such lower limit as def ined by the damper system command limits . It is notj.ntended to perfonn all of the manoeuvres listed at each of the flight conditions showno Appropriate selection will be made on the basis of the lmowl edge of mor e critical loadings cases o In the first priority this program will endeavour to demonstrate structural integrityyi£hinr 1 the flight envelope l imited by: - A minimum saf e control speed (to be determined i n fli ght) o Maximum altitude of SOj OOO ft. Yach number ~5 or 6oo kts EAS whichever is lesso 80% of design limi t loads or such lower limit as defined by normal damper protective deviceso It is expected that before this formal program will be started that t he ai rcraft will be cleared to values in excess of 70 by non- instrumented demonstration f l yi ng , see 3.6010 Repetition of the lower loading cases will only be used to collect data for extrapolation and therefor e full coverage is not requiredo Additional manoeuvres may be introduced into the pr ogram i f handling tests show that important loading cases may pe .. re~lised in manoeuvres not ·SECRET AIRCRAFT: tiK AVNO AIRCRAFT LIMITED MALTON - ONTARIO REPORT NO. -C7C.::1CJ.../F_AR_,_/;:;.30 _______ _ SHEET NO. 2 TECHNICAL DEPARTMENT PREPARED BY CHECKED BY ,3.7 Demonstration Program The object of this part of the program is to demonstrate compliance with Speci fication MII,.,F- 8785 "Handling qualities of piloted airplanesn. For these tests the flying control system and the damping system must be fully developed and the program will consist of demonstration flights covering a number of specific manoeuvres. DATE DATE By this time a number of flights required by this specificatio will be completed in the course of the develoµnent. As much as possible of this information will be used to demonstrate the compliance with the specification. Therefore a full coverage will not be necessary and only manoeuvres and flight conditions not tested pr~ttctusly will be included in this program. The aircraft will be tested in normal and emergency control modes. The following in the full list of manoeuvres to be performed at flight conditions as required by the specification. 3.7.1 Au~ented stabi lity1 level flight. 3.7.1.l Abrupt control deflections to produce approx. Am of 1 g1 AP of 30° / sec. and &:F / sec. and side acceleration not exceeding Lo% of limiting side- slip. c AS \f \ED SECRE T AIRCRAFT: MK AVR0 AIRCRAFT LIM/TEO MALTON - ONTARIO REPORT NO . ...-l.7_,,,1,_/ :..FAR=::/..../ ..L3O"'-------- SHEET NO, 2s TECHNICAL DEPARTMENT PREPARED BY CHECKED BY 307.102 To determine trimmability9 trimmers to be operated on all three contr~ls'f to achieve g .:!: lg1 + 30°/ sec. of roll rate 9 .:!: 40% of limiting sideslip • .3 .7.1. 3 Application of step inputs into the dampd.ni , system ~ ( a) step input to rudder d U:ferential servo. (b) step input of roll rate command (c) step input of normal acceleration command. (d) step input of combined roll rate and normal acceleration command. These tests are identical with tests required for damper optimization (section S) and there= fore the majority of them will be available prior to demonstration program 0 Only additional fli ght conditions as required by specification will be tested in this progr~un. 3o 7 .2 AU@llented stability in 2 g turning flight. 3.7.2ol While tri~d into a steady 2 g trim descending if necessary to maintain Mach No. 9 and at as near to constant altitude as power allows 9 pilot to de/termine response of aircraft to gentle control motion9 and repeat i terns 3 . 7. ol.l "' 3. 7.1.3. UNC SSIFIED S ECR E T DATE DATE AIRCRAFT: MK AVRO AIRCRAFT LIMITED MALTON - ONTARIO REPORT NO. _7..c;l=,/Fc........;;ARc.....<./..,.3c;::O _______ _ SHEET NO. 27 TECHNICAL DEPARTMENT PREPARED BY CHECKED BY 3.7.S Control mode transfer demonstration J0 70 S0 l Demonstr ate manual and automatic switching from normal to emergency contra?- mode i .n trinrned level flight and in gentle manoeuvres . 3. 7.6 Demonstrate sideslipping capability at low speeds at altitude. 3o7o7 Demonstrate eff ect of symmetric and asymmetric power in normal and emergency damper mode i including after burner effects . 3.7.8 Low speed tests 3. 7. 8.l Demonstrate minimum safe flying speed in both damper configurations with undercarriage up and down and with different power settings. 3. 7. 8.2 Demonstrate performance of timmers on all three controls . 3. 7. 8.3 Determine stability in pitch at low speed by performing a number of acceler ating ~nd decelerating runs with constant trim setting. 3.7. 9 Demonstr~te long period longitudinal oscillation (phugoid) i n both damper modes . SECRE T DATE DATE AIRCRAFT: EK AVR0 AIRCRAFT LIM/TEO MALTON -ONTARIO REPORT NO, .......:.7=-l/F!....:..:AR=/.:.3:.::0 ______ _ SHEET NO. T!CHMICAL DEPARTMENT PREPARED BY DATE CHECKED BY DATE 307.10 Spins and recovery Sufficient information is not available yet to establish that spins are possible, and that recovery is • satisfactory from established spins. Further tests and evaluations will be necessary to establish the extent of spin demonstrations. J.7.11 Forward critical loading It is assmned that most of the test s described above will be per formed at e.g. positions near or at the aft limit . A number of tests will be done at 'the forward critical l oading conditions bearing in mind air loads limitations, parti cularly the hinge moment limits. Since design forward l imit is not goi ng to be achieved on production aircraft this danonstration could be limited to a mi nimmn accept abl e to the RCAF and SE C RE T AIRCRAFT: EK AVR0 AIRCRAFT LIM/TEO MALTON - ONTARIO REPORT NO. _71...,C/F_AR----".,/ _3_0 ______ ----:I SHEET NO. 29 TECHNICAL DEPARTMENT PREPARED BY CHECKED BY 4oO Systems Testing Considerable amount of systems testing is planned for A/C 25201 in particular, as stated under allocation of aircrafto During < systems testing the aircraft flying t:unecan ,best be utilized by recording data from a number of systems on any given flight rather than investigating a particular system in itsent.irety. All s~tems testing on the Arrow 1 will in general be restricted to that testing necessary to demonstrate safe and satisfactory functioning. The only exceptions to this are ~~ose cases where \ the Arrow 1 and Arrow 2 systems are for all practical purposes identical o This is intended to keep duplication of testing on the Arrow 1 and Arrow 2 to a minimum. The actual systems to be tested and the test procedures are cover ed in section .. 4.1 to 4. 7 0 SE CR E T DATE DATE AIRCRAFT: WUtt:: AVRO AIRCRAFT LIM/TEO MALTON - ONTARIO REPORT NO. _7,Ll:,/c...:Fc...:AR=/~3"'0'-------- SHEET NO. 30 TECHNICAL DEPARTMEN T PREPARED BY CHECKED BY 40 1 Flying Controls The operation of the flying control system wil l be investigated on Aircraft 25202 in conj~ction with the Stabilit y and Control Testing. The reason for t his decision is the impracticability of attempting to divorce the flying control system frcrn the damper. DATE DATE Extensive work has been carri_~d out on the ground rig. This will continue to a~t as a back~up -for t)1e inflight t esting, As outline d in FAR/Cl05/2 the following major points are scheduled for investigation as shown below. (a) Pilots Controls Breakout forces . Emergency mode feel system Normal mode feel system Adequacy of damper schedules and damper modes, Suitability of trimming devices. (b) Control Surfaces Operation of damper an~ command systems hardware, Power controls actuator pe_rformance. The actual test procedures and estimated of flying time are covered in conj unction wi th Stability & Control testing, see section 3o Flying Control centering and trimming test will be carried out on the ground , For details of quantities to be recorded dur ing these SECR E T AIRCRAFT: :WIK AVR0 AIRCRAFT LIM/TEO MALTON - ONTARIO REPORT NO. __;_7_l:..._/_F AR__:_/....:.3:.._0 _______ _ SHEET NO. 31 TECHNICAL DEPARTMENT PRe::PARED BY DATE CHECKED BY h.2 Engine Handli ng and Structural Cooling The engine testing is di;vided into two main .quantities e~gine h:andling and engine and airframe coolingo The actual tests ·are covered in R.FoT. 5037 and 5031 respectively. Examination of the quantities to be measured shows that many of them are common to both tests. L.2. 1 Enr,ine Handling D ATE The engine handling tests are to demonstrate that the installation is satisfactory and to determine the engi ne behaviour and characteristics for various flight conditions 0 Engine relight will be carried out at a series of altitudes in order to establish a relight envelope for the J75 P5 engine installed in the A:rrowo At the same time engine windmilling rotor speeds will be observedo During the engine acceleration and deceleration tests the p_resence of any intake buzz or vibration will be noted 0 Estimates indicate that buzz should not occur below 108 MoNo It is not intended at this time to install any special instrumentation for this investigation. Fixed throttle climb from sea level to altitude will be carr i ed out in order to detect any RIM or JFT creep that may exist. The effect on engine stability of aircraft attitude and yaw will be investigated 3 to gether with the behaviour during descent at idling conditions o AIR CRAFT: ::?tiiif:C' AVR 0 AIRCRAFT LIM/TEO MALTON - ONTARIO REPORT NO. __,_7.=lL../FC....:..:AR_/,_3,0=---------- SHEET NO. 32 TECHNICAL DEPARTMENT PREPARED BY CHECKED BY 4.2 . l Cont'd For more detailed list of quantities to be measured and conditions of test see R.F.T. 5037. !i. 2o2 Engine and Airframe Cooling The objective of th ese tests is to measure and check both structural and systems temperatures associated with the engine ; installati on for safety monitoring, and in order to verify estimates for the Arrow 2o Both stabilized level flight and transient con::l.itions are DATE DATE to be investigatedo The fonner covers the :i:ertinent subsoni c and supersonic cruise an::l. max. speed cases, whilst the latter are descents and decelerationso The recordi ngs obtai ned during these tests will be examined and checked against I estimated valueso The de gree of agreement between predicted and measured values will detennine any re gion that may require fur ther investigat ion 9 For a detailed list of quantities tote measured and actual test conditions see FAR/Cl05/l Issue 79 and Ro f.T. 5031 . The engine handling and structural cooling tests involve the measurement of approximately seventy parameters. i SECRET A I RCR A FT: wast: AVRO AIRCRAFT LIMITED MALTON - ONTARIO REPORT NO. ~71~/~F_A_R~/~3~0 _______ _ SHEET NO. '3'3 TECHNICAL DEPARTMEN T PREPARED BY CHECKED BY 4.3 Air Conditioning The objective of this test is to prove the operation of the Arrow 1 a i r conditioning systan. An extensive ground test programme has been carried out on this syste!l;, which el iminates t he necessity for an exhaustive in- flight program . The key parameters will1be recorded during test, these will establish whether the air conditioning system is working eff iciently or not.. These tests will cover the extreme aircraft operating conditions , namely high alti tude at high speed, ~• high •; altitude at 'lqw speed and low altitude at low speed, together with the pertinent cruise conditions, descent, acceleration and deceleration . This dat.a will then be checked against theoretical calculations, and t he amounts of testing necessary will largely be dictated by the agreenent between estimate and measured values. A detailed list of the quantities to be measured and flight conditions are given in R0 F 0 T0 5045. SECRET DATE DATE AIRCRAFT: MK AVJIO AIRCRAFT LIM/TEO MALTON - ONTARIO REPORT No • ..,1""'1CL./F~J,J1.'-"--h"'"o=--------- SHEET NO. .Jh TECHNICAL DEPARTMENT PREPARED BY CHECKED BY 4o4 Telecommunications and Antennae Testing under the above heading covers calibration , checks for navigation aids 9 range determination on both navigation aids and communications sets and antenna range patterns for a single planeo S E C R E T DATE DATE ' ' · AIRCRAP'T: MK AV.NO AI.NC.NAFT LIMITED MALTON - ONTARIO REPORT NO. "'-'71-<-fr~AR___./--=3;...0 _______ _ IIHEETNO. 35- T!CHHICAL DEPARTMEHT PREPARED BY DATE CHECKED BY DATE /4.4.1 Calibration Checks Air swings will be carried out to check calibration and to compensate the AN/ARN-6 Radio Compass 1 to check calibration of AN/ARA- 25 UHF H 0 mer and J-4 Compass. Station passage characteristics of the AN/ ARN-6 Radio Compass and the AN/ ARA-25 UHF Hqmer will also be determined. The test procedure is as follows . With the AN/ARN- 6 tuned in to a Broadcast station and the AN/ ARA-25 tuned in to a UHF station1 runs will be made from a number of directions over a known checkpoint. The true course of the aircraft being obtained from photographs of the checkpoint and compared with the readings photographed by the recording camera t o check out the navigation aids 0 Station passage characteristics and the complete test procedure are given in Technical Information Bulletin 7- 13-2. SE CR E T »K AVRO AIRCRAFT LIM/TEO MALTON -ONTARIO REPORT NO. __,_7_1/F._A_.~_,_~-i'3'-Q _______ _ SHEET NO. AIRCRAFT: TECHNICAL DEPARTMENT PREPARED BY CHECKED BY ,4.h , 2 Radio Range Checks Flight checks are required to determine the ranges of the AN/ARN- 6 Radio Compassj the AN/ARN- 25 UHF Homerj the AN/ARC- 3h UHF communications set and the AN/APX-6A m · set. Test on the AN/ARC- 3h UHF will be made with both the fin and belly antennae. An auto observer will be used to record the AN/ARN-6 and AN/ARA- 25 displays as in the calibration checks . I t is propos~d that range checks be carried out with the cooperation of the DATE DATE nearest RCAF GCI f acility, which can be used to check the range of the IFF and UHF sets. Strength and readability will be recorded for various ranges. • l " SEC RE T »K AVNO AIRCRAFT LIMITED MALTON - ONTARIO REPORT NO. _7'-'l/F""''--AR__./~·3""0'--------- AIRCRAFT: SHEET NO. '31 TECHNICAL DEPARTMENT PREPARED BY DATE CHECKED BY DATE "4.4.3 Antenna Evaluation Tests The purpose of these tests will be to establish verification of model range patterns for a single plane. It is assumed that if close correlation between flight test and • model range data can be established for one plane 9 then model range patterns for complete 360° coverage will be highly representative of inflight performance of a full scale aircraft. It is proposed to s elect a location about 25 miles from the ground station9 having a suff iciently good land mark that the pilot may fly over it and consistent]y pin point a ' fixed position. The pilot would then perform straight and level nights at a fixed altitude for several headings and fiel d strength measurements would be recorded at the ground station. The flight test resultls would then be compared with the model range data 0 For a more detailed discussion of the antenna evaluav-ion program see Report No 0 71/SYSTEMS- 13/3 0 , Test requirements for tel ecommunications and antenna evaluation are covered in RFT 1s 5028, 5029 and 5044. "".!ii\K AVRO AIRCRAFT LIM/TEO MALTON - ONTARIO 71/FAR/JO REPORT NO. ____________ _ . 8 AIRCRAFT: SHEET NO. TECHNICAL DEPARTMENT PREPARED BY CHECKED BY . 4.5 Fuel- System The object of this test i s to prove the satisfactory func t ioning of the Arrow 1 fuel system on a complete aircraft, Fuel contents of all fourteen tanks will be measured together with temperatures and pressures of cert ain critical tanks, Fuel temperature pressure and flow to the engines will also be measured, For detailed list and l ocation of actual quantities see FAR/Cl05/l, Issue 7, DATE DATE Te sting will consist of measuring the above quantities during various flight conditions within the flight envelope, These will include take- off and acceleration at low altitude with and without afterburner, subsonic and supersonic climb with and without after burner , straight and level flight at cruis'e and high altitude , and during dive, This is intended to cover the oper ating speed and altitude range, and variations in aircraft attitude . The actual test conditions are given in detail inR,F,T, 5040pl \ SECRET AIRCRAFT: EK AVRO AIRCRAFT LIM/TEO MALTON -ONTARIO TECHNICAL DEPARTMENT REPORT NO •. --71/FAR/]J SHEET NO. ~; :.39 PREPARED BY CHECKED BY _ .40 6 Landing Gear. Speed Brake and Hydraulic System The object of these tests is to obtain a qualitative assessment of landing gear and speed brake operation and to record hydraulic system pressures and tempe~a tures in order to determine safe and satisfactory operation of the hydraulic system. DATE DATE In addition to this the energy abs"orbed by the landj_ng gear will be investigated. In the design of the landing gear the energy absor bed by wing deflection during landing was ignored~ by measur~ng the actual energy absorbed by the landing gear it is hoped to increase the maximum permissibl e l an:ling weight 0 Landing gear extension and retrac t ion times i utility hydraulics pressures and temperatures will be measured during take=off and l an:ling 0 Similarl y f or the speed brakes p continuous traces of systems pressures and temperatures will be r ecorded for a series of speeds at a selected ' altitude. Speed will then be increased with speed brakes down until they blow back9 the pressure in the ntili ty hydraulic system being recorded 0 S E C RET AIRCRAFT: MK AVR0 AIRCRAFT LIM/TEO MALTON - ONTARIO TECHNICAL DEPARTMENT REPORT NO . ......,_7=1/FL.::...CAR:.:.....J./_,3::_:0:...._ ______ _ SHEET NO. 40 -----'=----------.. PREPARED BY DATE •. 1------------+--------. CHECKED BY DATE L-----------1.. __________ .1__ ________ ____,__ __ ,-____ I Utility hydraulic sys t em temperatures will be recorded during a m.mber of pertinent flight conditions covering critical subsonic and supersonic cruise, together with certain transient conditions. The conditions for these tests are in general tdentical to those for Engine and Airframe Cooling Tests, for details of quantities to be measured and test conditions see R.F.T. 5039. UNClAS~iriclJ SEC RE T AIRCRAFT: MK AVRO AIR C R AFT LIMI TED MALTON - ONTARIO REPORT NO. _7_1~/F_ AR~/~3_0 _______ _ SHE ET NO. 1il TECHNICAL DEPARTMENT PR EPARED BY DA TE CHE CKED BY DATE 4.7 Electrical Power System The in-flight testing on the electrical system for the Arrow 1 is confined to that testing necessary to demonstrate safe operation. Hence temperature measurements are the predominant parameters that will be measured. The main objectives are to check that the cooling air flow through the A.G. generator is adequate for all conditions of el ectrical loading and that the maximum operating temperature of the A.G . generator near bearing is within safe operating limits. To check tenperatures in different zones where electrical equipnent is mounted to ensure oper ating alnbJent s are satisfactory. This will be done for a s eries of flight conditions r anging from low speed at low altitude to hi gh speed at high altitude. For more detailed list of actual conditions and parameters to be measured see R.F.T. 5041 Addo 1 0 ' \ S EC R E T AIRCRAFT, EK AVRO AIRCRAFT LIM/TEO MALTON - ONTARIO REPORT NO. _7e....:l::,/F...::....:.AR:....<./.,:!3..:CO _______ _ SHEET NO. 44 TECHNICAL DEPARTMENT PREPARED BY DATE CHECKED BY 5o4o4 Landing Perfonnance Due to the lack of anti- skid brake system on the aircraft at this stage9 optimum landing perfonnance cannot be detenninedo However 9 landing perfonnance will be measured using the best pilot techniques established at the time of t est will regard to touchdown speeds 9 chute operation and braking effort 0 5o4o) Level Speed Performance A l imited number of l evel speed and fuel consumption tests will be made using the stabilized level technique mainly in the subsonic region for both symmetric and asynmetric powero One check will be made at M ~ 1.5 and 45iooo c and partial climbs from 45 9 000 1 at various supersonic Mach number will be used to establish the ceiling of the aircraft. 50406 Accelerated and Decelerated Levels Data from accelerated levels with and without A/ B and deceler~ted l evels at idling power over an altitude range li000 1 to 45 9000 1 will be used as the main source of level flight drag informationo Effect of air brakes will be assessed from one decelerated level at 40s000 1 with air brakes open 0 SEC RE T DATE :wwmr: AVR0 AIRCRAFT LIM/ TEO MALTON - ONTA RIO REPORT NO. _7_1.:../ _F_A__.:R/:._3:__o _______ _ SHEET NO. L.6 TECHMICAL DEPARTMEMT PREP AR ED BY AIR CRAFT: CHECK ED BY 60 NO TES ON PROGRAM 601 Engine and Airframe T:une Estimates of engine and airframe time presented in the test schedule (compiled to determine occurrence of inspection grounding periods) are bas ed on an assumed average chock to chock per iod of 1 ¼ hrso 602 Flying Ho urs 6.2 0 1 Total Hours The chart of Estimated Total Flying Hours vs Time in Section 7.1 of t he report is based on an assumed average fli ght duration of 55 mins. 6.2. 2 Useful Test Time Of the 55 mins. assumed average fl i ght duration, L.5 mins. is considered to be useful test t ime. Tests/flight have been scheduled in accordance with this and the further considerations detail ed in 6.3 below. 6.3 Flight Tests 6.3.1 System Tests As the instrumentation loads on these flight is high, a lmost 100 parameters per f light, f light and time allocation is based on 66% data gathering efficiency and 2 fli ghts per week. 6.3.2 Telecom and Navigation Aids Tests As the instrumentation pack i s not r eouired for these tests, f light and time allocation is based on 75% data gathering efficiency and 3 fli ght s per week. S E C R E T DA TE D ATE AI RCR A F T: WIK AVR0 AIRCRAFT L I M/TEO MAL TON - ONTARIO REPORT NO. _7~1/~F_A_R~/_3_0 _______ _ SHEET NO. 47 TECHNICAL DEPARTMENT PREPA RED BY CH ECKED B Y 6.3.3 Handling Tests Flight and time allocation is based on 66% data gathering efficiency and 2 flights per week in view of high instrumentation load. 6.3. h Perfonnance Flight and time allocation is based on 66% data gathering efficiency and 1P fli ghts per four weeks. I nstrument 'l. tion is relativel y uncomplicated and of low conten~. 6.4 Aircraft Groundings It will be noted from the bar charts that major groundings have been scheduled to coincide with the periodic engine and air fz,ame inspections . Existing L.F.A. requir ement s against miscellaneous aircraft equipnent would necessitate frequent short grounding periods, however, an investigation is currently underway with a ~ view to incorporation of the majority of these requirements with the periodic engi ne and airframe inspecti ons. L.F 0 A. requirements which cannot be incorporated will be carried out during the flying program. The duration of the gro, nding periods for each aircraft i s based upon the presentlv known work content. ur~ LASSIF ~ SE C R E T DATE DATE ffl< AVR0 AIRCRA F T LIM/TEO 71/FAR/30 REPORT NO. MALTON - ONTARIO : SHEET NO. TECHNICAL DEPARTMENT PREPARED B Y DATE AIRCRAFT: CHECKED BY DATE TABLES & CHARTS OF PROGRAM 7o l Summary Char ts \ ' utt~1f1£1l - - ES IM A -'-' -·- ~- - --- - - 1-- - 1----laG '--- - -- ----- ·- - ~--- I ·-- I Q: ::, ·-- 0 :r W0 -- ~ -- - ~ - - -- / ~ / /. / - - __/ ~- JL y AUG SEP OCT I 9 5 8 Al Rn RI PORT~ 71/ F.A 'i?./ 30 L, S CTIO I 7. I. ·F n trOTA . FI ✓ ING Hrnll ~c; V b T it., IS: SJHEET I OF I . - --- I - ~ - - -- - >\GC REGATI --~ ~ - --, - <-- - - ~ OF >iOURS O N - V 25 01 2 ' 202 V Al ~D 25 0 3 . -- - -~-- - -- ~ - ~ - - / 1---~ - ~ -- / ' ~ - ~ V I --- / v - - - - - - ~ - '-- -~ 202 ~ - l__, i2QT ./ - t:-::"::' V V ~ -_;:;- ~-~ ~ ,v.., ~ v· e.:; v--::: // --- - - C-----1 -~ __....... ---- -= :vii -~ -..C:.:.~ .?"· ~ -- C, ~ ~ _,.. / _£: -,,? ..: ~ -=-.c..c7 - . i - - - (#-.., I ~ NOV DE C JAN FE& MAR A PR MA Y J U N J LY AUG llllf,; I ~- I 9 ~ 9 .__ TEST DEPT PLANN ING t Cl) fi ::0 rn ~ SECRET #. AVRO RE.POR "T 7!/F.A.R/30 rROUND SCHE.OUl..E A/c 2.52.0t-2 & 3. SE.CT ION 7 · I SHE.~T I OF I. i 25 HJ:; e:.~ G,. ~ AIRFRAME. IOO PARAM TE.R5 IN ,PE C.TICDN DATA-,AP~ & H' D Prf l~K• Ria;.PLACE.MEiNTi 25 CHANNE;.L.!:, ~ P5C . Re:.<;CRO i.;. c &Tfi.-E.M~1RY '. N G . & t J , M E.. I ~PARAME.T Rp I ~E.11E.R5 I DA.TA-TAPE. 2~ I ~ +25 C H ANNE.L.5 o e.c L..SI 06C RE..C.ORte:.p & .D 8, t '.TRY TE.LE.Me;.TR . I I MANCE. \ \ I Z5 HR. E:r!-JGi & A IRF'RAME. IN5Pe:.c,.+10N I , ~ 2M LB ' 1 1 ~ NO V l D~C. i I 50 Hf~. ~NG INE 8 AIRF'RAMk;: IN5~TIPt-J HYO. PIPE R'E.PLACEM-.1.JT I I I. VVEA.f:. 01' 5 PACK. IN'E>TA ... 1.1:r1b..J 2 l)ia. OlbD I I.J~ 1"1pT~ \N NC ~ E.._ 3. 05 11...-011:l,RtiPt- · IN E.LtC:1RIC.5,E.A't' 4, C,.,41 ME RhS 5. Meo IN!t;,T)l L..L A7 ION . JAN FE.B MAR I APR. . L~GE.ND ~AOHOC Oi:VEJ..OPMo.NT FLT. ~ FLIGHT TE.5 TING. =:=:J GROUNDED. ~VA.CATION. WORK ( I) INOICA."TE.'5 P05'5113LE. E.)(1EN~IOl'.J OF AD · HOC DE..VELOPME.NT PROq . TE5T ~EPT PLANNING. Mif AVRO AIRCRAFT l/MITEIJ MALTON - ONTARIO TECHNICAL DEPARTMENT AIRCRAFT:. TABLES & CHARTS OF PROGRAM • 7o2 Systems Testing REPORT NO, ~7_1~/_F_AR~L-39~------- SHEET NO, PREPARED BY DATE CHECKED B Y DATE • • • F I I I I I I V V A_/c GROUNDING. L;~B RE.PAIR &t1NSTALL-A"-r10N OF" Moos. :===::==:==::==::::w◄PR~t-t---+-~ G PRE.PARATION FOR 5Y$TE.M TES,- FLIGHT PREPARATIONo MT AD HOC DE:VEL.0P-TL.YING. TEST CON,-~NT AS F"OUND NECESSARY {PL.U5 NOSE. WHE.E.L .. 5TE.E:.RINC,..) CL. V5 of., INVE.STIG,A.TlON A.Jc GROUNDING SO r-lR. E.NGi, & 25 HR. AIRFRAME. IN$?, HYO. PIPE. RE.PLACE.ME.NT --- - --- -- t-- - -- - t-- - - i.-,[Zj:z-::z::z.:;t:z:,, µ, :jz:z:, ~:z,zj ,z:.t -~ F - - - - - t- - --I-' i.-- - t-- - - r-- - - r - - - - - - i-- - - _ ,.__ FL.IG,~"T' PRi.:.PAAA"T\ONS. FLIGHT T~STING. t----- - - - - ,- - ,1...-1--- -- --- t--- -~- -f--- - -5Y5Ta.MS CHEC),(,.ING. t------ A/c GROUNDING,. • -~ - 75 HR.E.N~ .e '50 1-\R.AIRFRAME. INSPe;.qi- - - - - - - - • - FLl~MT PREPARA"TIONS. FLIGHT TESTING 5Y5'TE.M5 CHE..CKING (co"-J"T'.) A.NTe:..iNA i;;.VAL.LJA'TION A/c G,ROUNDINq. l='Ll~HT PR.~PARA.TiCNS F"l.lGHT T~STING. NAV AIR. Al05 CAL.ISRA'TION. - - ~ - - - - ~ - I::~ <( t-- - - - - - - - -u <( --- -t- - - ---r-- -- T~l.:--~OM FL.T. RANG,E CI-\E.CKS. - - - - -- ~ - - - PROPOSE.O FURiHE:RT~$T5 &De.VI \.ANTI-SK.ID SY&,1:a.M. -- - - ---- -- 2. AIR DATA C.OMPUTOR. 3. AU'T0"'1A"T\C. FLYINGi CONTROL. . -- - - - - - - 1- - - - r- - - 1 -- - - ---,- i -~-- --- --~-- __ _ - - -- - --,---- __ ..,_ __ ~--1-- - 1 f- - - -- -- - ,- ~ - __ .__ :_ .._ __ ._ _ - - - - - - - i- - - - - - - - - - 1,- - - - ~ - --- ---~ --- -1-~--- ->-- -- - --- -~ --r ---- --- --- - --- -- - - r---~----- - I- - I -- - --- -- - - --- --- -- -- -- - -- --- -- ----- --~- - - - -- - -- - - ----- - --- -~- - 4. FINAL SY5TE.M A$$ES5ME.NT, .t--r---+--+-..__-+--+....L..f-+--+--+--1r-+--+--+--+-+--+--+---+-+--+--+--• II I~ ,5 I JULY \ AUG I SE.PT I OCT I NOV I ( IC?)56 I I F _IG-i-· & GR1DUNC ~'l=OGR,L\~1tv E 25 2Ct> I . I /V V /1/; 1 /tl/ l I ? V V V I I I I I I I - - - - j:=:t::=t==+=+' ::::1::=1 I I I > - - · -- - -- -- -- ~ --...._ - - - - - - - -- - 14 , 1 2e b ,~ , ~ "'' : , ,b n , o I> 1:!) , o 21 , ,, , c n , j;) ,~ 44 1 a 16 l2 ~~ , 1i!, 1b o 10 11 ~4 ~ 1 , .JOV I DEC JAN I F" EB I MAR I , APR I MAY I J UNC:. I JUL.Y I I 8 5 ::) I i I 1 1 I A'v RO RE POi T l ~, f.A Rf 30 t I L-c SECT 01' . 2 I~ E , 2 5 ec D \ . s HEE tr I OF I 7 l I/ II V V V J 1/ 1 I I l7 V I I I/ I V V I , , / I I I I I I I I I I \J s~~} i, i 1 rl,~t I I I I I I I 1J .. u o i s a~ 1 qww I I S~e. A+~ACt ,.s,o I ' 1 I TE.ST id•1E o J, 1.. =, . I I = 2 I I I 50 . _l 0 I -t- I _.rt= I 1- I - - ,r < I I -1- · _ .............. .... 5 1-5~ - - - "-- - (J I I I - - --- - 65 6';) <( I I -1---L > ~ol e; - - -f--- - - -- I I ; -,-~,- - "-- - - - - - I - - - - - - - ·.-~R, UN ~ O I I I I =l -- • FL .. C.1-1 . - _, - - - - f... - - -- - - - - '- - - - t-79 I ~ - - ~ - - - - - - - - -J - - ,_ - -- _ _ _ 8::> -81 ~ I I ' ~ -- f- - --- - '- - f-- - f- f-- -- e, I - - - - - -- - - -- -- 7 -i- - - ~ - -- - +- - - - - - - - - f- ~ ➔ ~ '" 1• ; 4 I ~ I 6 ' t) • ~ !D ,2. ,b b \k;) I 17 ~ 4 ' I ,~ l.t ' 8 ' I I IB ; 5 : ·~ It, : ,~ ~ lo 0 I ~ . O • 7 ' APR I MAY I J UNE. l JUL..Y I AUG. SE::.PT OCT I NOV TE.ST DE.PT. F>L..ANNING. '" ARROW 1 AVR O REPORT 71 / FAR/3 0 A/C 25201 TEST SCHEDULE SECTION 7. 2 SHEET 1 EST. EST. FLIGHT ENG. A/C NO. DESCRIPTI ON OF TEST R. F.T . HRS. HRS . REMARKS - Engine & Aircraft Hour~ from previou~ fli ght and Ground Te~t~. 24/17 11½ GROUNDING PERIOD - Repair, In~tallation of Mod ~. and Preparation for Sy ~tem~ Te~t~ PRIOR ' 12 FLIGHT PREPARATIONS - Engine Run~ 3 - AD HOC DEVELOPMENT FLYING 12 Te~t content a~ found nece~~ary, plu~ 24 24 In~trument- ation a~ (1) No~e Wheel Steering a~~e~~ment required . ( 2 ) C L v ex.. inve~tigation. Gear down main u/c door~ clo~ed 30 Total Hour~ 51/44 35½ ' GR OUNDING PERIOD - 50 hour engine and 25 hour airframe in~pection Hydraulic Pipe replacement. UNCtASSIFIED [ARROW 1 IA/c 25201 !FLIGHT jNO , PRIOR 31 31 38 TEST SCHEDULE DErsCRIPTION OF TEST SYSTEMS FLIGHT TESTING FLIGHT PREPARATIONS - Engine Run~ (1) Landing Gear acceleration~ - Record during take-off~ and landing~. No S£ecific Te~t Maneouvre~ R. F . T , 5039 para . 3.5 (2) Engi ne in~tallation temperature~ I 5031 Straight and level ~tabilized condition~ para . and tran~ient ca~e~ a~ detai l ed in 3.2 R. F , T, para , 4 . (3) Utility Hydraulic~ Sy~tem temper ature~ Record during the ~traight and level & tran~ient flight ca~e~ of (2) above. (4) Flying Control Hydraulic~ (i) Record pre~~ure~ detailed in the R. F . T, throughout flight~ . No Specific Te~t Maneouvre~ (ii) Re c ord temperature~ detailed in R. F . T . during maneouvre~ of (2) above . (5) Air-Conditioning Sy~tem.Record para meter~ detailed in R. F . T . throughout flight~. No ~2ecific Te~t Maneouvre~. 5039 para. 3 .J .2 5039 para. 3.4.1 5039 para . 3.4.2 5045 para. 3.1 (6) Wheel Brake~-Record fluid and pad temp~. I 5039 throughout landing~. para . No Specific Te~t Man~ouvre~. 3.3.1 AVRO REPORT SECTION SHEET 71/FAR/30 7.2 2 EST : ··1-EST , ENG. A/C HRS . HRS. 2 10 10 REMARKS , 45" Ej ec t or~ are e~~ent.JA.l for the~e te~t~. In~trumentat .ion require ment~ are defined in t h e relevant RFT~. For the te~t~ of flt~ 31~38,approx 89 parameter~ will be re corded on data tape, 10 of which will be telemetered . :., AVRO REPORT 71/FAR/30 ARROW 1 SECTION 7.2 A/c 25201. TEST SCHEDULE SHEET 3 t: ::;'l' EST FLIGHT ENG A/C NO . DESCRIPTION OF TEST R.F.T . HRS . HRS REMARKS GROUND PERIOD - +n~truroentation Re-Patch, Check-Out and Calibration SYSTEMS FbIGHT TESTING 39 (1) Landing Gear accelerat i on~-Record during 5039 at lea~t fir~t four take-off~ and para. landing~. No Specific Te~t Maneouvre~ 3.5 ( 2 ) Engine Handling and In~tallation Te~t~ 5037 ( 3 ) Landing Gear Te~t~ - Record parameter~ 5 039 ~pecified in para. 3 .1 of RFT during para. exten~i on and retraction of landing 3.1 gear . To be programmed with te~t~ of (~) above . I I ( 4) Speed Brake Te~t~-Record parameter~ 5 039 In~trument- I ~pecified in para .3. 2 of RFT during para . ation requirE • exten~ion and retraction of ~peed 3. ? ment~ are brak e~ . To be Erogrammed with te~t~ defined in th, of ("~). relevant RFT. e For the te~t~ ( 5) Electric~ Sy~tem Te~t~. 5041 of flight~ To be programmed with te~t~ of (2). 39-54,approx 8 3 parameter~ (6) Flying Control Hydraulic~-Record 5039 15 15 will be re- pre~~ure~ detailed in para . 3.4 . 1 cor ded on of RFT throughout flight~. data tape, 7 of No Specific Te~t Mane ouvre~ . whi eh wil 1 bE telemetered. SECRET ~ AVRO REPOR~-71/FAR/30 IARROW 1 SECTION 7.2 [A/c 25201. TEST SCHEDULE. SHEET 4 E0'l' EST WLIGHT ENG A/C NO . DESCRIPTION OF TEST R. F.T. HRS HRS REMARKS ( 7) Air Conditioning Sy~tem Te~t~. 5045 To be programmed with te~t~ of (2) (8) Fuel Sy~tem Te~t~ 5040 To be programmed with te~t~ of (~) (9) Wheel Brake~-Record fluid and pad temp~ 5039 throughout at lea~t the fir~t four para. landing~.No Specific Te~t Maneouvre~. 3 .3.1 50 Total Hour~. 78/71 60½ '. GROUNDING PERIOD - 75 hour Engine and 5 0 hour Airframe In~pection tl?RIOR 51 FLIGHT PREPARATIONS - Engine Run~ 2 - SYSTEMS FLIGHT TESTING 511 A~ for flight~ 39-50 le~~ item~ 1 and 9. 5 5 54 (_~ ARROW 1 A/C 25201 FLIGHT NO . :, AVRO REPORT 71/FAR/30 SECTION 7.2 TEST SCHEDULE SHEET 5 ES ENG . DESCRIPTION OF TEST R. F.T.I HRS I HRS I REMARKS Antenna Evaluation Tel!ltl!I . I I 18.J/4118.:\J Pack In,trumen,.- ation i i!! not Total Hourl!ll04/97 1:34 required for any of the tel communication or navigation aidl!I flight tel!ltl!I , and in 5044 the event of a major inl!ltrume ation l!lnag occurring duri fl tl!I. 31-54, thel!le tel!ltl!I co be l!!Ubl!ltituted at l!lhort notice 1 . An obl!lerver will be required in the rear cock pit during all the telecom munication and navigation aid tel!lt flight. GROUNDING PERIOD-Engine Major Overhaul an d 75 hour Airframe Inl!lpection. PRIOR 70 FLIGHT PREPARATIONS-Engine Runl!I 3 SECRtT 1., !ARROW l l4./C 22201 WLIGHT !No . 7)0 79 eo I 81 82 ' - AVRO REP6RT 71/fi'AR/JO I SECTION 7.2 TEST SCHEDULE SHEET 6 DESCRIPTION OF TEST R.F . T. EST-:-! EST . ENG . A/C HRS . HRS. I REMARKS SYSTEMS FLIGHT TESTING. Navigation Aid ~ AiT Calibration Telecommunication Flight" Range Check~ Total Hou~ . PROPOSED FURTHER TESTS AND DEVELOPMENT (1) Anti Skid Sy~tem ( 2) Air Data Computer. (3) Automatic Flying Control Sy~tem, (4) Final Sy~tem~ A~~e~~ment. .5028 .5029 UNCLASSIFIED SECRET 12½ 2½ 122/11.5 12½ 2_1. 2 99 L \ l ) ti@C \ AVR 0 AIR C R AFT L IM/TE O 71/F Afl./30 REPORT NO. MALTON - ONTARIO SHEET N O. TECHNICAL DEPARTMENT PREPARED B Y DATE AIRCRAFT: CHECKED BY DATE TABLES & CHARTS OF PROORAM 7o 3 Stability and Cont r ol ' n ,.... ) SE CR E T ' 1-, • r VI I/ I/ I I AIRCRAFT GROU N DING J / MOD. ll>l~TALLA"TION _ _____ ::=~ P A E,P. FOS'l ' HAMOLlr,1 6 TE.&;.TS FLIGHT PRE.PARA"TI ON~- - - - - - ! FLI GH1 51MULATION .- - - -; -- _l:l I . FLT. TESTING.- HA~DUNG.{~T<>tJ FL'S.ME.N'"f 3A"'51¼Ml'fl A IRCRA~T SROUNDING{VAC. P~ } AC.TI\/A T ION OF FUR,HE,R ~'1'. C.HNLS ,.._ >- - '-- - - - - -.... . '- I rU GoH"T PP..11!'..PARA'T IO"'!:> FLi. TES"Tl~·HANDI..ING (~iGE. I.) I F"LYIN~ CONTROi. OEVE.1.0PMU,IT & I INITI Ai. A~SESS..,E:NT 3 A11S DAMPE.R I ' I F"R.EE. A/c O~RIVl-r'IV_E.~ - - - - - . - - - - - e- - - 5 • re, ·I· E;('T&;N&ION OF 1"1.IGiH'T e. IJVf.1.0Pli.. ·~ AIRCRA~T GROU._,Dll'JG. 2 I I I I f 0 i 25 r4 R . E.NC,i. §) AIRFRAM&. IN~Pi:(:TION - I- - - ... - - ...:- ..... - - - - - - ""1 - '- MOQ . IN ~ T ..... 1.LAT I Ot,J . t- I PRE.?ARA."TION5°.- - - - - - - -~ - - ~ - - - - -- ,... - -- - - c::: rL.,: - - - -- I F"L.I . TC~Tlt-JGi-H~h!OLIN§ (~Tri~ ~ u I OA.MPE':.R 5Y~'T~"'1. -'.~Se'..S!;;M~ PJT. - - I- - - - - - - - - - I- - - ._ 1 l':l ...__ _ - - I- ~ -..... SiRUC'TUR.A.'.,. INTE:.GiRliY INVE.':,il(:,AT\O~ -. > ' C0NTIIJUE.D E.')(TE.NS10N OF I THE. FL\G,HT ENVE.1..OPl;;.. I , AIRCRAFT GR0UIJOING . - -~- - '- - - r- - - l- - - - - -- - L... - - - - - SO HR. EI-J~.l, AIRFRAIVE IN::iPE.CTION ... - -r-- - - - RE.P LA.C E.ME.NT 01= MYO. PIPES I ~- FI-IGHT P R E.PARATION5 - - - - - - - - - ~ - - -- --- - - - ._ - - I- - - -'- - - -- - 1-- - (L-I i E. Si lNSi-HMIDLING, L5TGE. 2) I DAMPER A~$E&SM~NT !, _ - - - ~ - - - '-- - '- - - -r- _l_ - - - - ~ - - - ~ - -- - - STRUCTURAL IN,E.C.RITY INVE;.GTl~ATl()t, F"L.. T . T ~5t1NG-HA"'-'OL-1"1G (ST.G,E,?,') - L- -_j _ IOA....,,PC..R OP"TIMIZ.A"TION . - - - - - ~ - - - - - - - - - - ..... - - - - - - - '- - -• 27 t 11 15 ll!i f Ip 16 : 12 : 4 I !; I e, I Cl Ip It : f4 ; , " I~ • I : I', 'b "i IEI ~b l.l U L.Y I AU~ I &E. PT I OCT l NOV I C I 9 5 8 SECREl A ~VF 0 F EP t:>R #, l=.A R./ 3_0 £\ v11 ~1- J ~ ., :;) £ 5, ~( ) ~ . ~-'-' ◄ .... SEC TI< N 7 . SH ~E I 01 2 I V II 1 I/// I J I I RE ~ E~ TO ~HE E T 2 . i. I I . I I I I I I I I I I I I I I I I I I 2 I I '1\ '' I 0 I ,~ ,r ' ll~ ' - I r I I <{ I I 0 I - 4'. > I coc E '. _ ~ ~lou NC E.CI> . 4 8 - F'~ u:3' ~,. I I / I/ / I/ / 1-- - RI FEI ~ T b s HFE IT IP I 17 ;;14 I I 15 , 2 ~b IC I~ ~lb ;) I~ I 17 2 14 J R I~ 'I ~ b APR, I MA..Y v UN E. I 0 ULYI AUG, I SE.PT \ OCT I NOV. 195 9 I I; Vi '/1 / VJ II V/ Vi I/, v; V; I I/; '/ AIRCRAFT GROUt-JOiNG. N 75 HR.:E:NG. ~ AIRFRAME. INSPECT-_ - -- -- - - - FLIGi~T PREPARA.TION5 r-- -- - - - - - - - - - - -n.lGiHi TE$Tl>JG-HANDL.ING(STGE.3 OAMPE.R 0PTll'-'11Z.ATION . I/ , , , II I I II I I ' -- - -- -- -- - - - -- 75 FL GH fT 5 15 AIRCRAF"f GROUNDING. N 100 HR. E.N{iilNE. & AIRFRAME. IN$PE.CT -- - -- - - - - - - - - -- - - - - ·- - - - ,-- - >- - - Fl-1Gil-4T PRE:PARAilONS. -- -- -- -- -- - - -- -- -- -- -- -- - - - ,- - ,__ ,__ ,__ 1-- - - - rl.lGHT TE'.STl~G-HANDING{5iGE. 3), 5"TABILl"TY &, CON'TROl.. . I- t-- - -- --- -- i-- - - - - -- - - - - - - - - ,_ - AIRCRAFT GROU t\lOING 12.5 M HR . EN~INE. 8,, AIRFRAME. IN!>Pic.CT,-.. - -- - - - - ,_ - -- -- -- - -- - - ,- - - ._ - - - - FI.IGH, PRE.PA.RA.1IOtJ5_ t- - ,- - - t- - - ,- - - ,- - - r- - - ,__ - -- - -- - -- - - - l-lGHi iE.STING-HA.~DLING.f 5,Gf.. ~) 5TABll...l'TY Iv C0l'-lTROI.. ~ - - - - - - - -- - - - - - - - -- ,- - - - - _._ - - I- ~1-IGI-IT TE.SJINQ-HANOL:1Nq, (STGf..._) DE.MON5iRA.ilON 'TO Mll..-1="- 8785. ~ - - - -- - - - - - - - - - - - - - - ,-- - - -- I- - - - - AIRC.RA.F'T GROUI\IDl~G. 150 HR. E_NG,INE.. 8t AIRFRAME. IN~Pf.C,. !::! ,-. - -- -- r-- - ,- - - t- - - -- -- - ,.... - - - - - - - - - - - F'..IGtt-1,- PRE;;;.PA.RA'TION~. .... -- - -- - - - - ,.... - - r- - - -- - - - ,- - - ,_ - - - - - -- F'I-IGHI iE:.STfNC-.-HANOL.IN6'(5TGE.+) DE:.MON~"1'RAilCN 'TO MIL.. -F'-8785. -- - - - - -- - - - - - ~ - - - - - ,- - -- - - - ,_ _ - -- - - ~}RCR~FT G.R0UNOING, 175 HR. &..NG,INE& AIRFRAM~ INSP~CT'~ _ - -- -- - r- - - - --- - t- - - r- -- - - - -- - - - FL..\G l-4-r PRE.PA.RA"TION5 -- - - - -- - - >-- - - FL.IGHT TE.$TING-HANDL.IN!;a (~TgE4 -- - ,-- - - - - - - - - c- - - .. ~MONSTRATION TO Mu..· F. 8785 - - - t- - - - r-- - - -- --- - ..- - - -- - - -- - -- I 8 15 22 2~ 5 12 1'3 2& 3 10 17 24 31 7 14 21 26 4 11 18 25 MAY JUNE JULY AUG SEPT 195:) FLI GI n 2, G RC )U ~(~ Dj ~c G R, ~~ ~~ ~E ~ A 'c •::> r:: t>c .C 2. ... - - j ~--- ;'/ V; I / 1 1 ; I/ V; JI I /1 v; I I / I I I I I I I !/, I/ I/ VI 1/ / . I I I z:gs -- ...- --- t-- - - - - ---- I I - - - - - - II / / I I I I I I I - F .. IG Hi To ~5 - - - - - t-- - I- - - - -- - -- - - - I ~ - -- - - - - -- - ..... - - - - - - ,.. __ -- -- - -- - - ~ I I I ~ -- - - - -- - - - ... - - - - - I- - -- - - - - - - - - '2) ' I= IG H"T I D& I I I - - - - - - - - -- - - --- - I- ,.. - - - -- - - - - - t- - F -IG, H, 107 117 I - - -- - - - t- - - - - - - ---+-- - - - - - t- - - ,- - - - - - -- - r---, - - - - -- - - t- - - - - - - - - -- - - - - t-· - - - - - - - - f- ... - - - - - - - - _ .___. I I -- ... - - -- - -- - - - - - -- -- - - - - - - - - - - - - t- - I I I I - - - - - - FLI ,_.H 118 - - - - - - - - - - - - - - - - - - - - - - - - I- ... - - - - - - - - - - - - - -- -- t- - - - - - - '- - - - ~- - ~ - - - - - - f- - - - - I- ... - - - - - - - - - t- - - - - - ...... - -1- t-- - - - - - - - - - - -- - - - - - - - I- -- - - --'- - ,.. - - - t- - - ..... - - - - - - - - - - - - -- -- - - - - - -- • 4 11 18 25 ~ 5 16 23 30 lo I~ 20 27 4- 11 IB '2.S I 8 IS 2'2. 2':> 5 IZ I') 2.b S 12 \'.) 2b 2. ~ 16 23 30 7 14 21 28 4 SEPT OCT' NOV DEC JAN FE.B MAR APR MA.Y 1.) 1 1960 I Al RO R PC' IRT :tc7 1 F~ R 30 ~ ~c ,b i: t>c .C 2. SE CT I ON' 7 ,3 __, ' i .... - St EE 2 OF 2, v; 1; !I I I I I/ V, I/ / I /, I V ; / I V1 / I V, I I I / I I I I/, / . I LE.< 11E. Ne . ::::z I 6F OL PNC DE b l b& ', , , S:-L IC3 ~-n . I I I G H "T 10~ 117 ~ ~ ~ I ~ - I- - - - I- ~ --- ~ - - ~ I- - - - - - - - - _ ,__ ~ ' I I - +- I I I I I I ' I / - - .... - - - - - FL.1 l:iH 118 13 - - - - I- I- - - - - - - - - - - - - - - - - -- - 1-- 1-- - - .__ - - .... - - 1-- - - - - - - - - - - - - c- - - - - - 1--.--1- ~ - - - ~ ---- V I I / / / V / / / I/ , - - - - - - - - - -- - - - ~ -~ -- - -- - - - - - - - - - • I" L.IG 1-(1 l3~ l5i 2h 5 12 I'.) 2'=, 2 ~ 16 23 30 7 14 2 1 '28 4 I I 18 2 5 2. :) lb 2 3 30 6 I~ zo 27 ~ 10 Ii 2 4 I B 15 2.2 2.5 I MA R I A PR MA.Y I.J UNE. JLJI..Y AUG, I 5E.PT oc.., 1960 ow 1 /c 25202 FLIGHT PRIOR l i PRIOR l l l I 4 s I I 1, TE9T SCHEDULE DESCRIPTION OF TEST R0 F0 T. ENGINE HOURS FRO~ PREVI0US GROUND TESTS EST. ENG . HRS. 3 E,ST. A/C HRS , AIRCRAFT GROUNDING - Mod. Installation and Preparat,ions .for Handling Flight Tests FLIG!-!T PREPAR4.TIONS = Engine runs FLTGHT Sil'ILTLATION TESTS HANDLING FLIGHT TESTING (S_T0i\.GE __ l_} (1) Flying Controls developnent and initial assessment of 3 axis damper. 2 s s AVRO REPORT #71/FAR/30 Section 7.3 Sheet 1 REMARKS Choice of test par meters as required for developnent. 12 telemetry channels will be available. AIRCRAFT GROUNDING (VACATION PERIOD) - Activation of further instrumentation channels. Flight preparations PANDLING FLIGHT TESTING {STAGE (1) Flying controls developnent and initial assessment of 3 axis damper. (2) Determination of f r ee aircraft derivatives wi thin Fli ght limits ~ M~l .75 9 EAS Soo kts 9 3g, tl (3) Extension of flight envelcpe TOTAL HOURS 5051 17½ 271. 2 71. 2 221. .a Instrumentation requirements are defined in l-' emo No. 1354/02A/J. However, it should be noted that fina choice of para= meters will be dependant on ARROW l A/C 25202 FLIGHT NO 18 HUOR 19 19 22 23 2'8 TEST SCHEDULE DESCRIPTION OF TEST R. F. T. EST. ENG . HRS . AIRCRA FT GRO UNDING = 25 Hour engine and air frame inspection. Mod. installation. FLIGHT PREPARATIONS = Engine Runs HANDLING FLIGHT TESTING (STAG~__l)_ (1) Damper system assessment. ( 2) Structural Integr i t y I nve stigation . Step 1. Subsonic and transonic manoeuvr es at 40% limit l oad (3 ) Ext ension of f l ight envelope (1) Damper system asses sment. ( 2) St r uc tural Int egri ty I nvestigation. Step 2 (a) Subsoni c and transoni c manoeuvres at 60% l imit load ( b) Supersonic at 40% limit load ( 3) Ext ens i on of fli gh t envel ope. 71/FAR/ 23 5034 71/FAR/23 5034 UNCLASSIFIED 3 5 7 1. 2 AVRO REPORT #71/FAR/30 SECTION 7. 3 EST. A/C HRS. 5 7 1. 2 SHEET 2 REMARKS devel opment r equlr= ements . Instr ument at i on will be act= ivated pr ogress= i vel y as permi tted by devel opment flyingj t owards the ul timat e tar= get of 100 channels . I nstr umentation r equi rements are defined in the r elevant R.F. T. 1s and in Avro r eport 71/FAR/ l Issue 7. I t is expected that appr ox. 100 cliannels will be avai labl e on data t ape and osci ll ograph with pr o= vision for tel~= metry. ARROW 1 A/ C 25202 FLIGHT NO 29 36 3.7 38 PRIOR 39 3.9 41 • TEST SCHEDULE DESCRIPTION OF TEST (1) Damper System Assessment ( 2) Structural Integri ty Investigation. St ep 3. (a) Subsonic and transonic at Bo% limit l oad. (b) Tr ansonic and supersoni c at 6o% l imit l oad (c) Supersonic at 40% limit load. ( 3) Extensions of fli ght envelope. (1) Damper system Assessment (2) Structural Integr i ty I nvestigation. Step 4 Transonic and Supersonic at Bo% limit load (3) E~ension of flight en~elope TOTAL HOURS R0 F..,T. 71/FAR/23 5034 71/FAR/23 So3L, EST. ENG. HRS. 10 2 ],_ 2 55 ½ EST. A/C HRS . 10 2 ]._ 2 47½ AVRO REFDRT #71/FAR/30 SECTION 7.3 SHEET J_ RENARKS AIRCRAFT GROUNDING - So Hour Engine and Airf rame Gr ounding. Replacement of hydraulic pipes. FLIGHT PREP \RATIONS · HANDLING FLIGHT TESTING (STAGE 2) CONT'D (1) Damper system assessment (2) Structural Integrity Investigation , Step 4 cont ' d Supersonic at 6o% limit load ,....,,......._. ,_.., ____ ....., 2 71/FAR/23 I 3 3/4 5034 3 3/4 ARROW 1 A/C 25202 FLIGHT NO 42 45 I 49 58 ~ • (1) TEST SCHEDULE DESCRI PTION OF TEST Damper System Assessment (2) Structural I ntegrity Investigation. Step 5 Supersonic at 80o/ limit load. (1) Stabi lity and Control - Extens i on of Flight envelope to maximum EAS i n stages (2) Flutter checks. HANDLING FLIGHT TESTING (STAGE 3) Damper system opt imization and final assessment of limit devices, Checks at following test points with normal gain + 50% :- 10 9 070 (i.e. 10 9000 1 M~0.70) Io_.115 9 20 9 040, 20 .. 070_. 40_.140_. 30~095, ~ 30_.16o 9 40_.180_. 50_. 115_. and 50 9 160, TOTAL HOURS S EC R E T R. F.To EST. ENG. HRS. 71/FAR/23 5034 5 71/FAR/23 3 3/4 71/FAR/23 12 ½ I tl2i EST. A/C HRS. 5 .\ AVRO REPORT #71/FAR/30 SECTION 7,3 SHEET 4 REMARKS 3 3/4 An observer will 12 ½ be required in the rear cockpit for the tests of flts. 49-75. 72½ ARROW 1 A/C 25202 FLTGHT NO PRTOR 59 r 75 ,_. t_ TEST SCHEDULE DESCRIPTION OF TEST AIRCRAFT GROUNDING - 75 Hour Engine and airframe inspection FLIGHT PREPARATIONS HANDLING FLIGHT TESTING (STA~E 3) CONT'D Damper optimization - Continuation of program of fli ghts 49,-5'8 TO TAL HOURS ESTo Rofo To ENG" HRS" 2 71/FAR/23 1 21-,, lOS 111, : ESTo A/C HRS" - 21¼ AVRO REPORT #71/FAR/30 SECTION 7 o3 SHEET 5 REMARKS en 111, AIRCRAFT GROUNDING - 100 Hour Engine and Airframe Inspectiono - PRIOR 76 FLIGHT PREPARATIONSo ,-..;:. 2 00 76 HANDLING FLIGHT TESTING (STAGE 3) CONT'D Stabili ty & Control Tests (1) Fr ee Aircraft Derivatives 71/ FAR/23 (2) Rolls (3) Cross wind landings 25 25 (4) Fr ~e Stabil i t y, 2g fl ight (5) Low speed stability (6) Asymmetric power 95 TOTAL HOURS 132 3/4 lltl 3/4 - ·---·-- - - - -· --- - --- -- -~- - I --· ··· ·----- ----·-- - - -- - ------ I ARROW 1 A/C 25202 FLIGHT NO PRIOR 96 96 106 107 I 117 I I ,:. TEST SCHEDULE DESCRifl'ION OF TEST - - AIRCRAFT GROUNDING - 125 Hour Engine and Airfr ame Inspection FLIGHT PREPARATIONS HANDLING FLIGHT TESTING (STAGE 3) CON T'D ( 7) Free stability power effect (8) Control system failure (9) Free stability, 3g fli ght (10) Free stability, 4g flight HANDLING FLIGHT TESTING ( STAGE 4) c.- The followin? tests are to meet t he requirement of MIL=F-8785 as qualified by Avro Repor t 71/FAR/23 . The t ests completel y cover the requi rements of Report 71/FAR/23 9 within the limitations of the Mk. 1 aircrafto It should be noted 9 however 9 that it is unl i ke l y that all of the conditions listed will have to be checked as the tests of the earlier stages of. the handling program should satisfy some of the r equirements . To what extent the earlier tests might r educe the program is difficul t to pr edict, consequently, the stage 4 section of the Handling Program has been scheduled i n its entirety. Augmented Stability (1 ) Level f light. TOTAL HOURS ~--- I EST o RoFo To ENGo HRS . 2 71/ FAR/23 13 3/4 13 1/4 1621 AVRO REPORT #71/FAR/30 SECTION 7.3 SHEE'T 6 ESTo A/C REMARKS HRS o - 13 3/4 13 1/4 146¼ ARROW 1 A/C 25202 FLIGHT NO PRIOR 118 I PRIOR :p8 138 156 - TEST SCHEDULE DESCRIPTION OF TEST R.F. T. AIRCRAFT GROUNDING = 150 Hour Engine and Airframe Inspection FLIGHT PREPARATIONS HANDLING FLIGHT TESTING (STAGE 4) CONT'D Augmented Stability (Cont'd) (2) Level Flight 71/FAR/23 (3) 2g Flight (4) Flight envelope demonstration TOTAL HOURS AIRCRAFT GROUNDING= 175 Hour Engine and Airframe Inspection I- ( ' FLIGHT PREPARATIONS HANDLING FLIGHT TESTING {STAGE 4) CONT 1D Augmented Stability Cont ' d 71/FAR/23 (5~ Rolling pull-outs (6) Limiter checks ( 7) Clirnbs and dives (8) Damper switching (9) Cross-wing landings {10) Symmetric power (11) Asymmetric power (12) Low Speed (13) Phugoid investigation (14) Hingemoment investigation (15) Forward critical loading investigation e.g. • 28% MAC TOTAL HOURS -- - - ---- EST. ENG . HRS. 2 25 Ltl9 1- 2 23 3/4 215 - EST, A/C HRS. - 25 1711 - AVRO REPORT #71/FAR/30 SECTION 7,3 SHEET 7 REMARKS 23 3/4 __ l 195 -- - 1 _,,,, AIRCRAFT: Miff' AVRO A IR CRAFT L IM/ TEO MAL TON - ONTARIO TECHNICAL DEPARTMENT REP O R T NO. _ _..l7C...::l::L/F-=-::A:..:cR:.t../...<3cc::0 ______ _ SHEET NO. PREPARED B Y DATE CHECKED B Y DATE TABLES & CHARTS OF PROGRAMME 7 o 4 Per fonna nce " S EClR E T Fl.lG H T 81 ~ROUND TE:.'5- II I/// I /1 I PRE· FIRST FLIGHT I I INSTALLA,IONS. • JPROOUCTIOt.J 5YS'TE.M F"UNC"TION TE.5 I MOD. 11\J~TALLATION } I PRE.PARA"'TION OF A/ c. FOR ::, PtRfORMANC.E PROO.RAM I PRe::'.PARAi1O1'lS.- - - - - - c:: l=J I FL..IGH-r - - - - - - - t- - - - I r1R5T FL.\G,HT. _f -- - - - --- -- - - - - -- -- t- - - - - - - I I A/c, GROUNDING. IN~"'TA.1.. L-A..,.ION OF I A I CA.L.IBRATED ENCii1"1E$ i:-R0M 7{; 2.5202. , _ - - -- - -- - - - t- - .--=□ '-NG. CA.LIBRA'TION RUN$. _____ _ - - - - ... - - - - - - - - - -- =o I ' V - - ~ AO. HOC. OE:.YE.\..OPME.NT Fl..YING . - - I IX Y y - -- - - - - - - - - - ... - ,- - - 2. 71 ' F'L..fGI-IT 'TE.Si"ING·F'E.RFORMANCE. - - f-- - - - - - • I- ~c GROUNDING. - I- - -- / / t- - - ~ 25 ~R. E."-1~. &, AIRFRAME IN'i:>PE.~'TION -1- I - - - - - - - - - - - - - - - - - .___ - - ,_--, . FLIGH'T PRe:.PARA"Tl0N5 - - - - - - - - - t- - - - - - - - - - - - ... - - - - .... - - ~ F"l..(G.1-CT TE~'Tl"'-1~-PE.RFO~MAl',JC:.~ - - - - - - -- - - - - - - - - - - - - - - - . AIRC.RAl=''T GR0UNOING } ► 50 I-IR .E.NG. &, AIRFRAME. IN$PECTION ~- - - f- - - t- - - t- - .... - - - - ~ - -- - - - - . PRE.PARA.-rlON FOR ARMA ME.N"T PROG.RA.M- ' ' I ~ I I • 2b 2 IJ ' I ·~ ,15 I , 115 2 2. : ' I I I~ ~b 1b , ,. ~ JUNE. u UL.Y I AUG $E.PT OCT I AVRO REPO;; #;I/FAR /'30 . i &, GROUND TE:..'5T PROGRAM - ARROW I 25203. SECTION 7. 4 . SHE.ET I OF 1,.., ''} - •----\' -~ I I///// I I Vl / / / l /1 ,1\.~~~-, ~ .. -- I / \1~\\t I I I ~ I I . I I F( R: DE .~ ILf D B REI l(C Q',/ VN 4 !:,I _E T E.$ ~,et HEI ::>U c--.E . - ::::::J . - .J ~ I I A. D . HC DC DE VE. -°' PMI Nl FI YII JG M GH T co t-lC-. =-1v ~B ~Y E)(. tT E. '10 - _ ;:::a I Ml JC.I- f UR TH E':R TI- A.t-. Tt ~E =□ I I -- - - ' I PE Ri(pD INI DIC ~,. ~D 'TI ~E.F 115. 6'( vv "-,; - =- - oc - -- '- - I ll( v e--- Rto we N( - HE FA tAl 2 TIMI LO E.O - - - ~ - -- / / / I/ F"< R PE: !:.>Fe bRI 11A~ ~CE T its CIR e ;,;o s D .. u ~YI NGt THE. ~ rrA.I ~T OF Tl1E. - +- - - +- - - t- c-- - - - ~~ - A~M ~"' El !-IT Pf l>Q( ~R~ M - - - +- ~ - - - f- - - +- - _ __ _c= , / , , / / / - - - - - - - - - - -- - --- -- 21 412 > - - - - ~ ~-~ 1- - - -- -- - - -- -- - -- ~ - - -- - +-- - I - I * =-R )U" Of D . I , n ·_ F"L IG~ ~T I 2. ' ' I 1• IE) ~b 1b 117 , 4 'I 7 I~ 21 ,s II!, I b l k:, , { '"' 2 ~ ~p P I b ' t> c 7 IP lb ' ~ 217 p I::) I f7 24 ~E.PT OCT ' NOV OE.C. J AN FEB MJ,>..R APR TEST DEPT PLANNING. • ARROW 1 A!__C 25203. FLIGHT NO . PRIOR 21 21 1 22 23 24 1 29 I 31 t2 34 re • TEST SCHEDULE DESCRIPTION OF TEST FLIGHT PREPARATIONS - Engine Run~ FLIGHT TESTING - PERFORMANCE . Level ~peed performance, 30,000 1, with one engine, at M= . 80 , .85, . 90 and max . ~peed Level Speed performance at 45,000i M ~ 1 . 5 Level flight acceleration~ (with & without afterburner~ ) and deceleration~ at 10,ooo v, 20,000 1 and 30,000 1 Level flight acceleration~ (with afterburner) and deceleration~ at 35,000 Y, 40,000 ' and 45,000 1 • Level flight deceleration~ at 40,000 with air brake~ out. Climb~ from 45,000 1 to ceiling at M=l.3,1.5 and 1. 7 Demon~tration Climb~. Minimum time to height . \ • AVRO REPORT7I7FAR7JO SECTION 7-4 SHEET 3. EST . I EST ENG , A/C R, F . T.I HRS HRS I REMARKS, 2 5059 2½ 2½ 1.1. 4 l ¼ I The in~trument- ation require- ment~ are de- 6¼1 6¼ I fined in the RFT . A total of 38 para- meter~ will be recorded during 3.3/4 the performance 13.3/4 I te~t~, 31 on ar: auto-ob~erver and 7 on an o~cillograph . 3. 3/4 13. 3/4 5 I 5 - ! 'ARROW 1 ALC 25203. !FLIGHT jNO . y 41 42 • AVRO REPoRrTl/FAR/30 SECTION 7,4 TEST SCHEDULE SHEET 4 DESCRIPTION OF TEST EST I EST ENG , A/C R. F. T I HRS . HRS . I REMARKS . Maneouvre~ - Power Boundarie~ 45,000 1 , M= 1.5 Three check~ . 40,000 1 , M= 1. 5 One che ck Maneouvre~ - De celerated turn to buffet boundary or limitation . Total Hour~ . The following additional te~t~ are incidental ! to the te~t~ detailed above and will be fitted in a~ convenient. 1 . Take - off performance - normal take-off we ~gh t. 2 . De~cent 3 . Landing. 4, Ac ce lerati on check , 180 k t~ . to limit ~peed at 1,0001 • SEC RET 3.3/4 13.3/4 1 .1. I 1 .1. 4 4 68.3/4 l5o.3/4 •

Flight test program: aircraft 25201, 25202 and 25203

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