1 r,,I ~ .ill ...... REPORT ON /1.CCIDWIT TO 6.VRO t RRO,J 1 - ?5?01 PAHT 2 June 11, 1 958 71/E'l!G PUB /10 U Nclcr sF'~IVJ-trD '5iiK _______________________ " __ ~_•_r_1t REPORT ON ACCIDENT TO AVRO ARROW' 1 (2.5201) PART 2 Classification cancelled/changed to ... ___ _ -- Lr? oL.~;;/" ":J'·" (date) .. b// _ /~~C~ .. fd~nk .~ ·············- 11 June 19.58 at MALTON Report No. 71/ENG PUB/10 UNCLASSIFIED CONFIDENTIAL EK ______________________ _ NOTE This Report is in two parts. Part 1 contains Qetails of the accident and the investigation into the cause . Part 2 contains details of damage to the air craft resulting from the accident, and details of the necessary repairs. u NCLAS ffEJTL E« ______________ _ INDEX 1. INTRODUCTION 2. SALVAGE METHOD 3. SURVEY OF DAMAGE 4. OUTLINE OF REPAIRS 4.l Examination of Service Equipment. 4.2 Replacement of Major Parts. 4.J Damage and Repair to L.H. and R.H. Inner Wings. 4.4 Damage and Repair at Nose Area. 4.5 Damage and Repair to Air Intake Ramp . • 4.6 Damage and Repair to Rear Fuselage and Engine Bay. 4.7 Damage and Repair to L.H. Outer Wing. 4.8 Damage and Repair to L.H. and R.H. Wheel Bay Roof. 4.9 Damage and Repair to L.H . Aileron. 4.10 Damage and Repair to L.H. Engine Air Intake Duct. APPENDIX 1. Technical Department Report SRA 13 9 Engineering Dispositions Required by Inspection Report S.I.R. #393. 2. Technical Department Report SRA 15 9 Repair Schemes for Assignment X7,J=4l16. 3. Metallurgical Department Report 5158 . 4. ¥etallurgical Department Report 5158, Addendum 1. Figure 1 2 3 4 5 6 7 fl 9 10 10 A 10 B 11 12 13 14 15 16 17 18 19 20 21 22 23 ?4 25 26 27 28 Page. No. CONFIDENTIAL LIST OF ILLUSTRATIONS Title Damage to Underside of L.H . Wing - Looking Inboard. Damage to Underside of L.H. Wing - Looking Outb'oard. Boring Bar for L.H. Landing Gear Bearing . Boring Bar for L.H. Landing Gear Bearing. Boring Bar for L.H. Landing Gear Bearing. Boring Bar for L.H. Landing Gear Bearing. Damage to Nose Wheel Well - L.H. Rear Corner. Damage to Nose Wheel Well - R.H. Side. Damage to Nose Wheel Well - R.H. Rear Corner. Damage to Nose Wheel Well - Aft End. Damage to Nose Wheel Door - Looking Forward. Damage to Nose Wheel Bay Skirt - L.H. Side. Damage to L.H . Air Intake Ramp - Looking Aft. Damage to L.H. Air Intake Ramp - Looking Forward. Damage to L.H. & R.H. Rear Engine Doors and Engine Bays. Damage to L.H. Engine Door & Engine Bay - Looking Forward. Damage to L.H. Engine Door & Engine Bay - Looking Outboard. Damage to L.H. Engine Door and Engine Bay. Damage to L.H. Enrine Bay - Forward Portion . Damage to L:H. Engine Bay- Forward Portion . ' Damage t o Engine Bays, Damage to R.H. Rear Engine Door and Engine Bay. Damage to Rea r Engine Door and Enrine Bay. Damag~ to R.n. Engine Bay. Front View of Aircraft After Accident. Side View of Aircraft After Accident , Under Surface of Aircraft Showing Repaired Areas. Main Landing Gear Fittings in Wing,Showing X-rayed and r Repaired Parts . Left-Hand Main Landing Gear Assembly ARRO,,,l Station and Datum Line s. CONFIDENTIAL s~ ; M Eat' _______________ _ 1. INTRODUCTION Part 1 of this report details the cause of mal function of the L.H. landing gear which caused the accident to aircraft 25201, on landinr at the completion of fli f,ht 11. When the left-hand wheel struck soft ground, it is assumed that the following sequence of events took place and caused extensive dam~ge to the aircraft: (a) The left-hand main landing gear collapsed and was torn from its bearing housings in the wi ng. (See Figure 17 - Part I of Report). (b) The nose l andinf gear twisted out of its attachments below the flight observer's ·bulkhead,and collapsed, causing damage to the nose wheel bay. (c) The right-hand main l a ndi ng gea r broke away at the top of its wheel bogey. (d) Due to its forward momentum, the aircraft pivoted about the right-hand l anding gear stub causing it to drop upon t he left-hand air intake ramp and the rear fuselage . The left wing tilted downward, so that the wing tip and aileron struck the ground . The position of contact with the ground is shown in Figures ?J and 2/i. CONFIDENTIAL 2. SALVAGE METHOD In order to conduct· salvage operations 9 the ai rcraft had to be lifted so that a low float could be positioned under the fui=;elage. The hoisting sling (part no. 7- 2700-6) id designed to atta ch to four pickup points in the airframe. The two forward points are tapped receptacles, located on top of each air intake duct (26.25 inches each sid e of aircraft t) and at stati on 256.125 just aft of the intake opening. The sling is desi r ned to screw int o these receptacles . The two aft pickup points are t he cross -shafts in the upper part of each of the main landin? gear ler;s. Two metal s traps from the 8ling are i9serted through two emerrency holes in t he t op of the wing 9 and are looped around each landing rear cross . ( 8tation 5R9.97). However 9 since tha left-hand landi nr gear had been sheared off, the approved sling could not be used, Consequently it was decided to use three cranes to hoi st the aircraft . Two holei=; were cut in the-:fing skin . One crane was attached to the right-hand landing gear cros R•shaft to lift the ·right-hand wi ng. A second crane 9 using ~mergency tackle and air bags 9 was requ i red to lift the left-hand wing. The third crane was attached to the two forward pickup points. The aircraft was lifted and transported to the hangar where the instrument pack , batteries and liquid oxygen were removed. The residual fuel was made inactive • with dry ice before the damage survey was started . CONFIDENTIAL ..,r"' '""" ~ r, ~ .,- .. ~-.. >ffi§C ________________ _ 3. SURVEY OF DAMAGE 3.1 The initial survey r evealed the following damage: (see Figure 25) . (a) (b) (c) (d) (e) ( f) (g) (h) (k) (1) (m) (n) (p) Left-hand main landing gear torn out of its housing. Right -hand main l anding gear broken at top of wheel bogey. Nose landing gear torn out of attachment fittings . Rear fuselage buckled and tor'.'-mostly on left-hand side . Left-hand air intake r amp bucKled a t bottom edge . Left-hand air intake scoop buckled inside . V-struts broken at station 742.0 . Vertical strut buckled at station 717.36. Left-hand main l anding gear door buckled. Left-hand outer wing l eading edge dented. Engine bay bottom fo rmers and skin buckled from station 697.0 to station 742.0. Inner wing skins over main l anding gear pivot housings damaged due • to salvage operation. Left,.,hand ail~ron damaged due t.o ·wing striking the ground . CONFIDENTIAL '}Mg{ _______________ _ 4. OUTLINE 01" REPAIRS 4.1 Examination of Service Equipment The electrical harnesR from the lef t-hand gear was reinstalled1 and circuit checks conducted to investigate possible cause of the accident. (Ref. Part 1, para . J.J) Damaged areas of the aircraft were then dismantled to assess further damage. Flying control , radio and hydraulic equipment was removed f or s tructural and functional examination in accordance with ''B" aircr aft crash proce - dure. . CONFIDENTIAL 'J ,.. >a«: ________________ _ 4.2 Replacement. of Major Parts I The survey indicated that replacement of the following major parts was necessary: (a) Left-hand and right-hand main l anding gears. (b) Left-hand and right-hand main landing gear doors . (c) Nose landing gear. (d) Nose wheel door. (e) Left-hand and right-ha~d rear enr,ine access doors. (f) "Heavy former 11 at station 697 .o. (g) "Heavy former" at station 742.0. (h) V-strut assembly at station 7/i2.0. (j) Front inboard lower boom cap at inner/outer wing joint. (k) Bushing for left-hand l andinr gear front pivot bearing housing. CONFIDENTIAL E~ ________ u_N_C•_A_s,_tl_f~_·_ 4.3 Damage and Repair to the L.H. and R.H. Inner Wings Damage to the L. H. inneir wing did not warr;ent removal of the outer wings. Radiographs were taken of the main leg pivot fitting, the surrounding structure at the front spar, the drag strut fitting and aft pivot fitting at main spar, (Ref. Appendix 1, Metnllurgical Report No . M 5158). The acc i dent caused elongation of the sleeve insert which carries the main leg pivot forward fitting. The sleeve was removed using heat lamps and dry ice. Examina tion showed that .:the bore of the pivot fitting had elongated with the sleeve. The fitting was rebored in situ using a special boring bar. (Ref. Figures 3,4,5 and 6). A·modified sleeve was made to fit the rebore, ·and the internal bore of the sleeve was honed out to suit the pivot shaft. Radiography and measurement checks indicated that no damage had occured to the right wing . Firure 26 shows the examination conducted on main landing rear leg attachments. The R.H. ref uelling door surrounding frame s tructure was replaced. CONFIDENTIAL E~------~llt~tC_lA_SS_lf_lE_D_ 4.4 Damage and Repair at Nose Area Ma:Jor damage to the nose , area was at the attachment of the nor.e leg pivot mountings to the flight observers bulkhead. In addition, the nose wheel bay skirt and nose wheel door were also damaged. (Ref. Figures 7,8,9 and 10) . Repair oft he ma:J or damage to the nose area was effected by installing a new f lieht observer' s bulkhead and cross beam assembly , below the cockpit floor. A utility j i g was fabricated t o positi on the nose leg pivot fittings. Stuctural repairs were made to nose wheel bay skirt, and nose wheel door. 4.5 Damage and Repair to L. H. Air Intake Ramp The left-hand air intake ramp was buckled and cracked at the outboard web, and buckled at the inboard web. (Ref. Fi gures 11 and 12). Damage'-to the intake ramp perforated bleed skin was determined by radiography and was repaired in situ by means of a machined patch, Additional repairs in the ramp lower area were as follows: (a) De - icer boot replaced . (b) Bottom skin complete with attachment angle beams for the bleed skin _and inner skin repl aced , (c) Ejector scoop froot guide vane replaced. CONFIDENTIAL ;ffi1$'( ________________________ _ 4.6 Damage and Repair to Rear Fusel age and Engine Baz Damage was mainly confined to the left-hand side of the rear fuselage and engine bay-. ( see Figures 13 to 19 inclusive). The L.H. and R.H. rear engi ne doors suffered damage (Ref. Figure 13) _and were r eplaced. Figure 14 shows damage to L.H. engine access door and engine bay, just fo r war rl. oft he door . The L. H. enp.-ine acce '>S door was repaired and L.H. engine bay skin r epl aced . Figur es 15 and 16 show damage to L.H. engine bay lower ~surface . Figures 17 , 18 and 19 show damage at forward postions of L.H . engine bay . Figures 20, 21 and ?2 show damage to R.H. enr,ine bay. The skin in these areas was r epl aced. The fuselage and engine bay were repaired by replacing formers 697 . 0 and 742.0 right acros s the fuselage. 4.6.1 The lower portions of formers at following l ocations were replacepg Former Sta. 702 .JO Former Sta. 722.38 Former Sta. 727.40 Former Sta. 732.42 Former Sta. 737.44 (L.H.) (L. H.) (L.H.) (L. H.) (L .H.) 4.6.2 4.6.3 CONFIDENTIAL The lower portions of formers at following locatio~s were repaired by splicing in new portions: Former Sta. {:fJ7 .65 Former Sta. 712.34 Former Sta. 717.36 (L.H.) (R.H.) (L.H.) The former at station 697.0 was replaced and a new portion of centre skin was spliceci in t'o facilitate this replac._ement. Repairs were also made to the L.H. enrine shroud stiffeners in the station 742.0 area. Rear Fuselage The centre portion of the former at station 753.0 was repaired by installing a reinforcinr cioubler, after a distortion was pressed out. f . .. CONFIDE_":!TIAL "n'1&.N~~irf • ')WA! ________________ _ 4.7 Damage and Re~air to L.H. Outer Wing Pa,rt of tli.e outer wing leading edge and lower surface were damaged by contact with the L.H . landing gear wheels. (see Figures 1 and 2) Repairs to this area were as follows~ (a) Nose ribs 6,7,9, 10 and 11 were replaced. (b) New portions or ·stringers ~ ,and 3i-Tere_spliced in: (c) Nose skin between ribs 6 and 14 was replaced. (d) New portion of nose skin spliced in between ribs 3 and 6. (e) Navigation light fairing and cover replaced. 4.8 Damage and .Repair to L.H. and R.H. Main Wheel Bay Roof Skin repairs were incorporated in each wheel bay roof where holes were cut in each inner wing top skin to facilitate salvage operations (ref . para. 2). 4.9 Damage and Repair to L.H . Aileron The L.H. aileron outboard end was damaged when it struck the ground , and was repaired by splicing in a new skin portion. 4.10 Damage and Repair to Engine Air Intake Duct 4.10.1 The left-hand engine air intake bottom skin was buckled between StA. 244.0 and Sta. 255.0 . The damaged skin portion was cut out and replaced. R.H. LA~Ol~G GeAe e,oc;ey F='Ll 1..1. E O AWAY F"R~M LEG ARROW 1 25201 LA~( A ,ece,AFT POSITlc;,~ • NOSE L..,ii PUL.LED c ATTAC!HM 0~ ~A\/1~ bUL.KH EA WOSE W't- 5201 LA~DltJG ACC IDE~T >0 5 1TI~~ • FQOtJT VIEW AIFcC:RAFr FELL 0~ A l~ !~TAKE ~AMP, DAMA~E'D E,L ADE & e:>LJC:KL.EO l~SIOE oF o we,-; LEF'r H At-JO LAfJDlfJG GEAR c::>OGEY ~ OSE L A~DH.JG GEAR P ULLED oL.JT o,= ATTAc=H M et.JTS 0~ ~AVl ~ATOR~ bUt..KH EAD &.. OAM Ac;eo WO~E WH EEL. WEU. DAMAGED uuoERSIDE OE OUTetc w1~G FIGURE '23 /// INBOARD J L 7//77 > ~ ll1BOAR0j /L 7 7 / / / / 7777 /// 777 A OUTEk BY MA A ARROW ! .._ 2520t LANDIN~ ACCIDENT. AIRCRAFT POSITION - • SIDE VIEW. OUTER WIN~ DA MA~ED BY MAIN LANDIN ~EAR AIR INTAKE RAMP. Sll§HT DAMA~ E TO AlltRON & WIN TIP. I EN \NE. BAY rnRME.RS LOWER SURFACE BUCKLED. I • / / :\DENT. .W . • OAMA~E TO N & WIN TIP _ INBOARD , / /////T/Tr, /7,7 ST~ TIC .L ._ ~- ~NO~RM~A~\.. _______ _ _ -1-----=--:---1-- EN INE BAY rnRMERS LOWER SURFACE BUCKLED. I , ... Fl~URE. 24 ,! [JJ ·- ARROW 1 - 25201 L .. e 9 f 0 0 0 LE GE ~D REPAIR BY REPLACE ME NT ~ COMPONENT REPAIR. ~ NUMBER INDEX TO PH OTOGRAPHS LETTER INDEX TO REPORT I a CJ ot IT ' [ VIEW OF - 25201 LANDING ACCIDENT. - - - -- - - - - CD C) oB CD P HS VIEW OF UNDER SURFP\CE. FIGURE 25 I , D AMA6E -·--::;::::::o-- / I OVALi TY DAivlAG c DI A /v1 . S L E. [VE. AN D Pi VO T FT u . L~ H. S I DE. 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SI DC5 -- - - - -- ;-) r-- C ,.L, K"' tc I C O OU T C.; N FI TT I N G S F!GURE. 2.wer Segment "Flower Pot" General Shots Film Idents. 4, 10, 15, 16, 17, 18, 19, 20, 21, 22, 23 31, 32, 33, 34, 38, 39 11, 12 5, 6, 24, 25, 26, 27, 28, 29, JO, 40, 41, 42, 43, 44, 45, 46, 47, 48, 49, 50, 51 57, 58, 59 1, 2, 3, 7, 8, 9, 13, 14, 35, 36, 37 CONFIDENTIAL ~ ~ ~ ; ~ ; ~ ~ ~ ~ ~ ~ ! ~ ! ~ ~ ~ ~ ~ ~ ~ ~ ~ i ~ ~ ~ ~ ~ ~ ~ : ~ ~ ~ ! ~ ~ ~ ~ ~ ! ~ ~ ~ ~ ~ ~- _ _ _ -·- __ 'i.....Q.uil.- - -- -·- NTRE FU S ELA G E "ING OA I U M S(All (INCHES) WIN O OAT UM SCA LI !IN CH ,S 1 / .--<:::;,,-;;,r----:r--,-----·--· Ol~~~r:-~:-·c_· _ DIVE BRAKE ..... ., ... ..,,._o .,..,_ .. ..,.,,,.,_,.,._ ";;::!ti ::;::-:;;:::_;:;:;: ;::;::;::;:-;;::;::;::;: -:; ~,.,,.,;!:..,~ .... ; "':" • 9~N$ ~"' ~~: .... --.... ,:s "'i"' ..,,~:H .Cl.",::<>:<> "''" • 8 INS ., : "''"So, IN$ ~ " : AILERON IN(>HS 10 ./C ___ , ... ,., .... ,, _ STll'IGU fO.MUS lt,I ,.o,,n ONLf i;_ lNGIN l STING!• fO•MU$ ONLY"'" Of 10) SH OIIAIL fO• f0lMU !, Of CON! DUCT BAY 00 ENGINE BAY REAR FUSELAGE ~ ~I ~ ~ ~ ~ gl :: ~ ~ ~I~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ! ~I ~ ~ ~ I ~ ~ ~, ~ ~ ~ ~I ~ ~ : ~I ~I ~ ~ ~ ~ ~I ~I ~I~ ~ 2 ; .ROW STATION AND DATUM LINES

Report on accident to AVRO Arrow I 25201 on 11 June 1958 at Malton. Part 2

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