AIRBUS 

# ISiA310 SERVICE BU LLE T I N REVIS ION T RA N SM I TTAL S H EE T

CUSTOMER SERVICES DIRECTORATE 

### 1 Rand Point Mauri ce Bellante 31707 BLAGNAC CEDEX FRANCE 

### Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F 

### Fax : (33) 5 61 93 42 51 MANDATORY 

### ATA SYSTEM : 57 MA N DA TORY M A N DATO RY


### TITLE : FUSELAGE· FR40 - INSPECT UPPER CORNER FITTING . MODIFICATION No . : None Th is page tra n sm its Revision N o. 02 of Se rv i ce Bu ll eti n N o . A3 1 0-57- 2064. A D DITIO N A L WORK 

### MANDA TORY

No add it iona l work is requ i red by th is rev ision for aircraft mod ified by any prev io u s issue . REASON Revi sion N o. 02 issued to : Upd ate i nspect ion thres h o lds a n d int e rvals . 

### U pdate Kits 572064A03 and 572084A0 4 . I mprove Noles i n IN S P ECTI O N Paragraph 3 .B. 

### Rev iew of flow charI. C H ANGES SUM M ARY:

- REAS O N/DE SCRIPT I ON/OPERA T I O N AL CONSEQ U EN CE S T

ex t m od ified . EF F ECT IVI TY Operators NGA, RME and T HA de l et ed . Operators updated . MAN POWER 1 6.0 TOT AL MANHO U RS becomes 1 7.0 a n d 1 2.0 E LAP S ED TI M E hours becomes 1 3 . 0 for i nspe ct io n . P LA NNIN G INFORMA T ION : DA T E: A ug 24/95 SERVICE BU LLE T I N N o . : A3 1 0-57-206 4 REVIS ION N o. : 02 - Dec 21 /07 Page:lof3 Prin te d i n Fra no ll Q A I RB US 200 7 A ll ng hts teserved• EFFECT IVITY 

# ($) A310 SERVICE BULLET IN REVISION T RANSMITTAL SHEET



### Para . 1 .A . Aircraft model 310-221 de leted. Operator NGA, aircraft MSN 0285 and 0340 de le ted . Operator RME , aircra ft MSN 0276 deleted. Operator THA , aircraft MSN 0424 de leted. Aircraft MSN 0442 de l eted for operator AFL. Aircraft MSN 0504 de leted for operator AFR . Aircraft MSN 0392 deleted for operator 

### Ale . A ircraft MSN 0311 deleted for operator CNW. Aircraft MSN 0300 and 0352 de l eted for operator GYP. A ircraft MSN 0528 deleted for operator HLF. Aircraft MSN 0426 deleted for operator KQA . Aircraft MSN 0172 deleted for operator KYV. Aircraft MSN 0347 and 0350 deleted for operat or MEA . Aircraft MSN 0409 deleted for operator OAS . Aircraft MSN 

### 0295 and 0306 deleted for opera tor RJA . Aircraft MSN 0432, 0435 and 0440 de leted for opera t or ROY. Aircraft MSN 0363, 0433, 0493 and 0570 deleted for operator SIA . Aircraft MSN 040 4 and 0412 deleted for opera tor SWR. Effectivity updated . REASON Para. 1 . C . Text modified.

- COMPLIANCE Para . 1 . E . Inspect ion thresholds and interva ls updated .

- MANPOWER Para . 1 . G . 16.0 TOT AL MANHOURS becomes 17 . 0 and 12 .0 ELAPSED T IM E hours becomes 13 .0 . 1 .0 hour becomes 2.0 hours for the test. REFERENCES Para. 1 . J . Reference to AMM 28 - 11-23 and IPC 21 -21 -02 deleted. Reference to AMM 12-33-21 and 52-10-00. IPC 21-28-03, ESPM 20-55-00 and SM added . PUB LICATIONS AFFECTED Para. 1 .K. Reference MPD 57- 1 0-25 added . MA T ERIAL INFORMA T ION: MATERIAL - PRICE AND AVAILAB I LITY Para . 2 . A. Address updated. Prices and calendar days added for all kits . LIS T OF COM PONENTS Para. 2 . C. HL75-12 becomes HL75-12AVW in Kit 572064A03 . HL3 75 -12 becomes HL375-12A VW in Kit 572064A04. ACCOMPLISHMEN T INSTRUCTIONS : GENERAL Para . 3.A. CAUTION added . PREPARATION DA T E : Aug 24/95 

### REVISION No. : 02 - Dec 

### 2 1/07 SERVICE BULLETIN No. : A310-57-2064 Page : 2 Printe d i n Fra ncc Cl At RBUS 2007 All rights rClcrvod

# A310 SERV I CE BU L LE T IN REV ISION T RANSMITTAL SHEE T



### Para. 3.A. ( 1) Step de leted . Steps added . INSPEC T ION 

### Para. 3.8. Noles added. Notes modified . Steps added . Steps upda ted. REPAIR Para. 

### 3.e. PN modified i n Kits 572064A03 and 572064A04. 

## TEST Para . 3 . D. Job Set· up modified . Leak l est and rep lenishing of t he fuellan ks deleted. T est of manhole covers and access doors added , Leak les l of air ducts added. CLOSE-UP 

### Para . 3.E . Steps (d) to (i l added . Step de leted I LLUS T RA T I ONS 

### Figures 1, 3, 4 , 5, 6 and 7 mod ified . NOTE: Layout changes due 10 computerization of this revis i on are not iden t ified. 

### F I LING I NS T RUC T IO N S This Servi ce Bu ll eti n has been generated electronically and i s reissued as a complete document. Replace the complet e document. Pu t this Revis ion Transmittal Sheet in front of t h e Servi ce Bu ll etin . HIS TORY OF PREVIOUS REVIS IONS Revi sion No . 0 1 i ssued to add Airworthiness Directive (Cons igne de Nav igabilile) No . 92-106 - 132(B) and a i rcraft post Service Bulletin No. A3 1 0-57-2067 (Mod . No . 1 1352S21172) and post Mod . No . 11353S2 1 173. A l so, this revision is issued 10 upda t e the inspection and repair actions . REVIS ION SEQUENCE ORIGINAL : Aug 

### 24/95 REVISION No. : 01 - Jan 05/0 1 REVISION No . : 02 - Dec 2 1 /07

DATE : Aug 

### 24/ 95 REVISION No . : 02 - Dec 21107 SERV ICE BUL L ETIN No . : A310-S7-2064 Page : 3 Prin ted jn France 0 AI RBUS 2007 AS ri gh l$ rese rvod

### AIRBUS CUSTOMER SERVICES DIRECTORATE 

### 1 Rend Point Maurice Bellante 31707 BLAGNAC CEDEX FRANCE 

### Tel : (33) 5 61 93 33 33 Telex: AIRBU 530526F 

### Fax : (33) 5 61 9342 51

# ~A310 SERVICE BUL L ETIN SUMMARY

This summary i s for i nformati on only and is not approved for mod ification of the aircraft MANDATORY 

### MANDA TORY MANDA TORY ATA SYSTEM : 57 TITLE : FUSELAGE· FR40 • INSPECT UPPER CORNER FiniNG . MODIFICATION No . : None REASON/DESCRIPTION /OPERAT I ONAL CONSEQUENCES 

### MANDATORY

Dur i ng i n spect ions as per Main te nance Review Board (MRS) Structural Significa n t lIem (581) 57.10.25 , two operators have repo rted cracks in itial ing from fastener holes l ocated at th e upper corner ang l e at frame 40 . The cracks were discovered on A310-200 al rcratl at 17,800 and 24 , 000 F l ight Cycles (FC) . 

# I As a result of th e in-serv ice reports, the MRB program ru l es requi re that the inspection now has to be performed on a ll A310 aircratl. This I nspection Servi ce Bu ll etin therefore supersedes MRB SS I 57 . 10 .25 . Cracks, if they rema i n undet ected, could lead to extens ive and time consum i ng repa i rs . Th i s Inspection Service Bu ll etin is rendered mandatory by Airworthi n ess Direct ive (AD) . Before re l ease , t h is Serv i ce Bu ll etin has been va l idated by A I RBUS on aircratl MSN 0427. This I nspection Service Bu ll eti n requires an eddy current inspection of the interna l a n gle fi lling and the verti cal tee at frame 40 on the LH and RH s ides . This inspection will make it possible to detect crack propagati on at an ea rl y stage , thus avoid i ng an expensive repair. 

# I This Inspection Servi ce Bu ll etin has been mod ified in the frame of t he A310 aircraft Extended Service Goa l study.

EVALUATION TABLE COMPLIANCE Mandatory CANCELS INS P ECT I ON SB N o 

## AD Yes AlC OPERAT ION AFFECTED No

DATE : Aug 

### 24/ 95 SERVICE BULLET I N No. : A310-57-2064 REV I S I ON No . : 02 - Dec 21 / 07 Page:1of5

Pri nted i n France Cl AI R BU S 20 07 Al l ri g hts rese rvedEVALUAT I ON TABLE REL I AB I LITY AFFEC TED COST SAVING S T RUCTURAL LIFE EXT N KI T PRICE (USD)
EFFECTIVITY 

## No No No See 58

# A310 SERVICE BULLETIN SUMMARY

PAX COMFORT AFFECTED ETOPS AFFECTED VENDOR 58 INVOLVED



### This Service Bulletin is applicable to these operators : 

## No No No

34W SBX 82Z 99Y All Ale ARG BAF BBC BlM CFC eSA DAH DGA F2r FOX GAF IRA IRM lYE JAB JAV KAe MGl MPD MPJ MWA PIA QSe R 1T RJA ROT RZO S81 SGX SUD T AP THY TSC UAE UZB WHT CONCURREN T REQU I REMEN TS 

## None REFERENCESIREPERCUSSIONS 

## T

FU : 57.10 .00.005 

## aEB : None 

## AaT : None SIL 

### : None LIFE LIMI T 

### : None LINE MAINTENANCE AFFEC T ED : No OTHERS : None NATURE OF THE WORK AIRCRAF T : YES eQUIPMEN T : NO HARD : NO 

### SOFT : NO OBRM: NO 

### DA TE : Aug 24/95 SERVICE BULLETIN No . : A310-S7-206 4 REVISION No . : 02 - Dec 

### 21/07 

### Page: 2 Printed in**Fr~ oca**  CI AI RBUS 200 7 All**rig ts**  res erV\! dMAN POWER 

### Con fi g. 01 Ih ru Co nfig. 03 , for i nspect io n TOTAL MAN HOURS 

# ($; A310 SERV ICE BU LL E T I N SUMMARY

ELAPSED TIME (HOURS) 

### 17 .0 13 .0 Con fig. 01 I h ru Co nfi g . 03 , for repair (Replaceme nt of the in tern al angle tilli ng as speci fied i n Repair Instruction No. 2 1 R57 1 10257 or No. 2 1 R57 1 10259 or No. 2 1 R571 1 0266, on one sid e ) 

### TOTAL MAN HOURS 80.0 ELAPSED TIME (HOURS) 40.0 

### Config . 01 thru Config. 03 . for repa i r ( I nstallation of t he bushes in holes No.2 and 3 as specifie d i n Repair I nst ruct ion No. 2 1R57 11 0260, on on e s ide) TOTAL MAN HOURS 30 . 0 ELAPSED TIME (HOURS) 15.0 

### Confi g . 0 1 thru Config. 03 , fo r re pa i r (Installati on of the fasteners wi th h igh i nterference fi t 

### at r i b 1 as speci f i ed in Repa i r Inst ructi on No. 2 1R57 1 10266) TOTAL MAN HOURS ELAPSED TIME (HOURS) MATER IA L I N FORMA T ION A I RCRAFT DATA Con fi g . 01 t hru Con fi g . 03 , (if repair) K it 572064A01ROO Inte rnal angle f itt i ngs Ki t 57206 4A02ROO In te rn al angle fi tt ings K it 572064A03R02 Bol ts, n uts , co ll ar Ki t 57206 4A04R04 DA T E: Aug 

### 24/95 REVISION No , : 02 - Dec 21107 

### 30 . 0 15 . 0

SERVICE BULLE T IN No . : A310-57-2064 Page: 3 Prirl lod**~** Franco O A I RBUS 2007 Al l righl$ reserve d

### Bolls, n uts, coll a r 

### Kit 572064AOSROO Bo l ls , nuts 

### Kit 572064A06ROO Bolt, nu l APPENDICES Appendix 1 • In spection Report



### DATE : Aug 

### 24/95

# A310 SERVICE BULLETIN SUMMARY

SERV IC E BULLETIN No . : A310-S7-2064 REVISION No .: 02 - Dec 21/07 

### Page: 4 Pri nted I n Fren<: e C A1ReUS 2007 AU**rlg~ls** ,eservea

## A

DATE : Aug 

### 24/95

REVISION No . : 02 - Dec 21107

# A310 SERVICE BULLETIN SUMMARY

SERVICE BULLETIN No . : A310-57 -2064 

### Page: 5 Printed I n Franc;e Cl AIRBUS 2007 All ngh ts rOSONQOAIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rand Point Maurice Bellonte 31707 BLAGNAC CEOEX FRANCE 

### Tel: (33) 5 61 93 33 33 Telex: AIRBU 530526F 

### Fax : (33) 5 61 93 42 51

# ~A310 SERVICE BULLETIN



### MANDATORY MANDATORY MANDATORY AlA SYSTEM: 57 TITLE: FUSELAGE· FR40 • INSPECT UPPER CORNER FITTING. MODIFICATION No. : None 

### MANDATORY

Th is document contains AIRBUS PROPRIETARY INFORMATION and sha ll a\ all limes rema i n the p r o perly of AIRBUS ; no intellectual property right or li cence is gra nted by AIRBUS in con n ectio n with any information contained in 

### i t. It is de l ivered on the express cond ition that said document and the information conta i ned in 

### i t sha ll be treated as confidentia l, sha ll not be used for any purpose other than that fo r which it is hereby de l ivered . It sha ll not be d isclosed i n who le or i n part to th i rd parties and shall not be duplicated in any manner (except fo r the purposes of performing the tasks described hereunder and p rovided that any recipient of such document sha ll comply with the cond itions h erein). without A I RBUS' prior written consent. 

### 1. PLANNING INFORMATION A. EFFECTIVITY ( 1) Models 

# I 310-203 310-203C 310-204 310 -222 310-304 310-308 310-322 310-324 310 -325 (2 ) A i rc raft (a) Effectivlly by MSN Th is Service B u lletin is app li cable to a i rcraft MSN : 01620191 0201 0 2 17 0224 0230 0233 0237 0241 024502480251 025402570260 02640267027302780281028302880291 0293029703030309031303160318 032003260331 0333033503380339 0 342034303450346034903530355 -0357 03590360036203640367 0369 0370 0372 0375 0378 0379 0386 0389 0390 0392 0394 0397 0399 0400 0406 0407 0410 0413 0416 0418 0419 0421 0422 0425 0427-0431 04340436043704390441 0444-04490451-045804670468 0472 0473 0475047604780480 -04920494-0503051905200522 - 0524 0526 0527 0531 0534 05350537 - 053905410542054405450547-0552056205640565 0567 0568 

# I 0571 0573057405760585-05950597-06000620062206240634 0636 0638 0640064206440646 · 06540656065806600661066306650667 0669 0671 0672 0674 0676 0678 0680 0682 0684 0686 0687 0689 0691 06930695 0 697 0698 0700 0702 0704 0706 (b) Effect iv ity by Operato r DATE : Aug 

### 24/ 95 SERV ICE BULLETIN No .: A310·57-2064 REVISION No .: 02 - Dec 

### 21 / 07 Page : 1 of 46

P ri nte d i n FranclI CI AIR BU S 2007 All righ ts reserve d

# I I I I**A310** SERVICE BULLETIN

The Operator/MSN relationship is provided for information only and is correct a\ the lime of issue in accordance with the i nformation available to AIRBUS. Any future changes resulting from transfe r of an aircraft from one operator to another w ill not be reflected in this list unless the Service Bulletin is revised for another reaso n . 

### OPERATOR MSN 34W 0399 

## sax 0431 82Z 

### 05500551 99Y 0489 A1L 0648 AIC ARG 

### 0392 0406 0407 0413 0428 0429 0501 0538 0544 0548 0598 0654 0665 0669 0680 0684 0693 0695 0697 0640 0686 BAF 0367 0372 BBC 

### 0594 0650 0698 0700 BLM 

### 0488 CFC 04250441 0444 0446 0482 GSA 0564 0567 0672 0674 DAH 0291 0293 DGA 

### F21 

## FDX 04180421 0422 

### 0309 0524 01620191 0201 021702240230023302370241 024502480251 02540257026002640267027302780281 028302880297 0303 031303160318032603310333033503390342034303450346 0349 0353 0355 0356 0359 0360 0362 0364 0369 0378 0394 0397 040004390449045204540456045704580467049205000534 0539 0542 0549 0552 0589 0593 0634 0638 GAF 0434 0484 0498 0499 0503 0522 0523 IRA 03380370037503790389039004360671 lRM 0537 0586 lYE 05350568 0702 0704 DATE: Aug 

### 24/95 SERVICE BULLETIN No. : A310 -57-2064

REVISION No . : 02 - Dec 21/07 

### Page: 2 Pr inted in Franoe 10 At RBUS 2007 All ri ghts reserved

# I

I 

# I**~A310** SERVICE BULLETIN

OPERATOR MSN 

### JAB 0320 0419 

### JAV 0357 0481 KAC 064706490663 MGL 0526 MPD 0451 04550842 

### MPJ 0410 MWA 0652 

### PIA 047305850587 0590 0653 0656 0660 0676 0678 0682 0687 0689 0691 

# ase 0620 RH 0591 RJA 

### 04160445049004910531 ROT 0636 0644 RZO 0571 0624 0651 066 1 581 04270430045304680475048604870520 SGX 05 1 90562 

### SUD 0437 TAP 0483049404950541 05650573 THY 0386047604780480049604970502 

### TSC 04470472 0485 0527 0545 0547 0588 0595 0597 0599 0600 0658 UAE 0592 0622 0646 0667 

### UZB 0574 0576 0706 WH T 

### 0448 (el Effectivity by MSN and KiUConfiguralion



### DATE ; Aug 24/95 The Kits and configurat ions applicable to these MSNs are g iven al the end of this l ist 

### 016201910201 021702240230023302370241024502480251025402570260 0264026702730278028 1 028302880291 0293029703030309031303160318 SERV ICE BULLETIN No. : A310-57-2064 REV IS ION No. : 02 - Dec 21/07 Page : 3 Prin ted i n France C'J A I R BUS 20 07 Al t righ ts reso fV<l d

# ~A310 SERVICE BULLETIN



### 032003260331 033303350338-03390342-03430345-0346034903530355
-0357 0359-03600362036403670369-03700372 0375 0378-0379 0386 0389 · 0390 0392 039403970399-04000406-0407041004130416 0418-0419 0421
-0422 0425 0427-0431 0434 0436-0437 0439 0441 0444-04490451·04580467-04680472-0473 0475-047604780480·04920494·05030519-0520 0522
-0524 0526-0527 0531 0534-0535 0537-05390541-0542 0544-0545 0547-0552 0562 0564-0565 0567-0568 05710573
-057405760585-05950597-0600062006220624 0634 0636 0638 0640 064206440646-0654065606580660-0661066306650667 0669 0671-0672 0674 067606780680068206840686-0687068906910693 0695 0697-0698 0702 KIT No. QTY PER 

### NC CONF I GURATION 572064A01ROO 

### 01 02 572064A02ROO 

### 01 02 572064A03R02 

### 2 01 02 572064A04R04 

### 2 01 02 572064A05ROO 

### 2 01 02 572064A06ROO 

### 2 01 02 NOTE (Ol} Kit 572064A01 ROO includes the parts necessary for the replacement of the LH inte rnal angle fitting as specified in Repair Instruction No. 21 R57110257 or No . 21 R57110259 or No. 21R57110266 . NOTE(02) K it 572064A02ROO includes the parts necessary for the replacement of the RH internal ang l e fitting as specified in Repair Instruction No. 21R57110257 or No . 21R57110259 or No. 21R57110266. NOTE(03) Kit 572064A03R02 i ncludes the hardware necessary for the replacement of the LH or the RH internal angle filling (one Kit per side). Th is hardware, which co ncerns Repair Instruction No. 21R57110257 or No . 2 1R57110259 or No. 21 R57110266, is applicab l e to the removed fasteners at the nominal d iameter (hardware identified (a) in the parts lists of the Repair Instructions). NOTE(04) Kit 572064A04R04 includes the hardware necessary for the rep lacement of the LH or the RH i nternal angle filting (one Kit per side) . This hardware, which concerns Repair Instruction No. 21 R57110257 or No . 21R57110259 or No . 21R57110266 , is applicable to the removed fasteners at the first oversize (hardware identified (b) in the parts lists of the Repair Instructions) , DATE : Aug 

### 24f95 SERVICE BULLE T IN No . : A310-57-2064

REVISION No. : 02 - Dec 

### 21f07 Page : 4 Printed in Franoll Cl A tRBUS 2007 All ri9hts r c scr""d

# I$JA310 SERVICE BULLETIN

NQTE(05) Kit 572064A05RQO includes the hardware necessary for the replacement of the LH or the RH inlernal angle filling (one Kit per side). This hardware, which concerns Repair Instruction No. 21 R57110257 

### or No, 21 R57110259 

### or No . 21 R57110266, is applicable to the removed faste ners at the second oversize (hardware identified 

## (el in the parts l ists of the Repair Instructions) . NOTE(06) K it 

### 572064A06ROO i nc ludes the hardwa re necessary for the repair specified in Repair Instruction No. 21 R57110260 (one Kit per side). The Kits and configurations applicable to these MSNs are given at the end of this list 

### 0704 0706 KIT No. 

### QlY PER 

## Ale CONFIGURATION 

### 572064A01 ROO 

### 02 03 572064A02ROO 

### 02 03 572064A03R02 

### 2 02 03 572064A04R04 

### 2 02 03 572064A05ROO 

### 2 02 03 572064A06ROO 

### 2 02 03 NOTE (0 1) Kit 572064A01 ROO includes the parts necessary for the replacement of the LH internal angle fitting as specified in Repair Instruction No. 21 R57110257 or No. 21 R57110259 or No. 21 R57110266 . NOTE(02) Kit 572064A02ROO includes the parts necessary for the replacement of the RH internal angle fitting as specified in Repair Instruction No. 21 R57110257 or No. 21 R57110259 or No . 21R57110266. NOTE(03) Kit 572064A03R02 includes the hardware nece ssary for the replacement of the LH or the RH internal angle fitting (one Kit per side). This hardware, which concerns Repair Instruction No . 21 R57110257 or No. 21R57110259 or No. 21R57110266, is applicable to the removed fasteners al the nominal diameter (hardware identified (a) in the parts lists of the Repair Instructions). NOTE(04) Kit 572064A04R04 includes the hardware necessary for the replacement of the LH or the RH i nternal angle fitting (one Kit per side). Th is hardware, which concerns Repair Instruction No. 21R57110257 or No. 21 R57110259 or No. 21 R57110266, is applicable to t he removed DATE: Aug 24/95 SERVICE BULLETIN No. : A310-57-2064

REVISION No . : 02 - Dec 21/07 Page: 5 Printed I n france C A I RBUS 2001 All**ri ~hls**  reserved

# A310 SERVICE BULLETIN

fasteners at the first oversize (hardware identified (b) in the paris lists of the Repair Instructions). NOTE(05) Kit 

### 572064A05ROO includes the hardware necessary forlhe rep lacement of the LH or the RH internal angle fitling (one Kit per side ). This hardware, which concerns Repair In struction No. 21R57110257 or No. 21R57110259 or No . 21R57110266, is applicable to the removed fasteners at the second oversize (hardware identified (el in the paris lists of the Repair Instructions). NOTE(06) Ki t 

### 572064A06ROO includes the hardware necessary for the repair specified in Repair Instruction No. 21 R57 1 10260 (one Kit pe r side). T he Kits and configurations applicab l e to these MSNs are given at the end of this list 0700 KI T No . QTY PER 

### AlC CONFIGURATION 572064A01 ROO 

### 02 572064A02ROO 

### 02 572064A03R02 

### 2 02 572064A04R04 

### 2 02 572064A05ROO 

### 2 02 572064A06ROO 

### 2 02 NOT E(01) Kit 572064A01ROO inc l udes the parts necessary 

### for the replacemen t of the LH internal angle fitting as specified in Repa ir Instruct ion No . 21R57110257 or No. 21 R57 1 10259 

### or No. 21 R57110266 . NOTE(02) Ki t 572064A02ROO includes t he parts necessary for the replacement of the RH internal angle fitling as specified in Repa ir Instruction No. 21R57 11 0257 

### or No. 21R57110259 

### or No. 21R57110266 . NOTE(03) Kit 572064A03R02 includes the hardware necessary for the replacemen t of the LH 

### or the RH internal ang l e fitt i ng (one Kit per side). T h is hardware, wh i ch concerns Repa ir Instruct ion No , 21R571 1 0257 or No . 2 1R57 1 10259 or No , 2 1R57110266, is applicable to the removed fasteners at the nomina l diamete r (hardware identified (a) in the parts li sts of the Repair I nstructions). NOTE (04) Kit 572064A04R04 includes the hardware necessary for the replacement of t he LH or the RH internal angle f itling (one Kit pe r side) , This hardware, wh ic h concerns Repair In struction No. 2 1 R57110257 or No. 2 1R57110259 or No. 21 R57110266, is app li cab l e to t he removed fasteners at the first oversize (hardware identified (b) i n the parts lists of the Repa i r Instructions) , DATE: Aug 24195 SERV ICE BULLETIN No . : A310-57-2064

REVISION No . : 02 - Dec 2 11 07 Page ; 6 P ri nted i n F ranc e 

# = A I RBUS 2007 All riQhts reserved

# I**~A310** SERV I CE BULLETIN

NQTE(05) Kit 572064A05ROO includes the hardware necessary for the replacement 

### of the LH or the RH internal angle fitt ing (one Kit per side). This hardware, which concerns Repair I nstruct ion No. 21R57110257 or No. 21 R57110259 

### or No. 21 R57110266, is applicable to the removed 

### fasteners at the second oversize (hardware ide ntified (el in the paris l isls of the Repair Instructions). NOTE(06) Kit 

### 572064A06ROO includes the hardware necessary for the repair specified in Repair Instruction No. 21 R57110260 (one Kit per side). 

### NOTE: Config . 01 is val id for aircraft on which Service Bulletin No . A31Q·57·2067 (Mod . No . 11352821172) is not accomplished. 

### NOTE: Config . 02 is valid for aircraft on which Service Bulletin No. A310-57-2067 (Mod. No. 11352S21172) is accomplished . T his modification is embodied before delivery on aircraft MSN 0700 . NOTE: Config. 03 is valid for aircraft on which Mod . No. 11353S21174 (FUSELAGE - FR40 - IMPROVE INSTALLATION OF UPPER CORNER ANGLE F ITTING (PRODUCTION SOLUTION» is embodied. Th is modification is embodied before delivery on aircraft MSN 0704 and subsequent. (3) 

### Spares None B. CONCURRENT REQUIREMENTS None C. REASON (1) History During inspections as per Maintenance Review Board (MRB) Structural Significant Item (SSI) 57.10.25, two operators have reported cracks initiating from fastener holes located althe upper corner angle at frame 40 . The cracks were discovered on A310-200 aircraft al17,800 and 24,000 Flight Cycles (FC). As a result of the in-service repor ts, the MRB program rules require Ihallhe inspection now has to be performed on all A31 0 aircraft . This Inspection Service Bulletin Iherefore supersedes MRB SSI57 . 10 .25. Cracks, if they remain u ndetected, could lead to extensive and time consuming repairs. Th is Inspectio n Service Bulletin is rendered mandatory by Airworthiness Directive (AD). Before release, this Serv ice Bulletin has been validated by AIRBUS on aircraft MSN 0427 . (2) Objective/Action
DATE: Aug 24/95 SERVICE BULLETIN No. : A310-57-20B4

REVISION No. : 02 - Dec 21107 Page : 7 pnnt ..d In FranC(! C AIRBUS 2007 All ri9htS reserved

# I I (3)

(4)

# A310 SERVICE BULLETIN



### T his Inspection Service Bulletin requires an eddy current inspection of the interna l angle filling and t he vertical tee al frame 40 on the LH and RH sides . 

### Advantages This inspection 

### will make 

### it possible to detect crack p r opagation a\ an ea rly stage. thus 

### avoiding an expensive repair. This Inspection Service Bulleti n has been modified i n the frame of the A310 aircraft 

### Extended Service Goal study. OperalionalfMainlenance Consequences 

## None D. DESCRIPTION To accomplish th is Service Bulletin 

### it is necessary to : 

### ( 1 ) I NSPECT IO N (a) Config. 0 1 thru Config. 03 1 Do an eddy current inspection of the upper corner angle at FR40 on the 

### lH and RH sides. 

### (2) REPAIR (a) Config . 01 thru Config . 03 Do the applicable Repair Instruction(s) . E. COMPLIANCE (1) Classification Mandatory (2) Accomplishment Timescale Accomplishment of th is Service Bulletin has been rendered mandatory by the issue of an Airworthiness Directive (AD) published by the European Av iation Safety Agency (EASA). The AD must be used as the reference document for the mandatory accomplishment timescale. Accomplishment of th is Service Bulletin is mandatory at the th resholds and intervals:

DATE: Aug 

### 24/95 SERVICE BULLETIN No. : A310 · 57·2064

REVISION No . : 02 • Dec 21107 Page: 8**P~n lcd**  in France C AIRBUS 2007 M**ng~tl;** reserve<!

# ($JA310 SERVICE BULLETIN

Tab l e A 

### Thresholds in relation with aircraft configuration Aircraft configuration Th res holds A310-200 

### (see Note (0 1 )) Config. 01 15, 1 00 Fe/3D,30D FH A310-300 (SR) 

### (see Notes (02) and (03)) Config. 0 1 14,700 FC/41 ,300 FH 

### A310-300 (lR) 

### (see Noles (02) and (03)) Config. 01 12,800 Fe/64,OOO FH 

### A310-200 

### (see Note (01)) Config. 02 and 03 

### 21,400 FC/42,800 FH A310-300 (SR) 

### (see Notes (02) and (03» Config. 

### 02 and 20,700 Fe/58,30D FH 03 A310-300 (LR) 

### (see Notes (02) and (03)) Config. 02 and 03 1 8,000 FC190,400 FH 

### Table B Int ervals for subsequen t inspection after no crack finding or after repair Aircraft configuration I nterva ls A310-200 

### (see Note (0 1 )) 

### 8,750 FCf17,550 FH A310 -300 (SR) 

### (see Notes (02) and (03)) 5,800 FCf16,300 FH A310-300 (lR) (see Notes (02) and (03» 4,800 FCf24,050 FH NOT E: This Service Bulletin is required at the given thresho lds and intervals in Flight Cycles (FC) 

### or Flight Hours (FH) wh ichever occurs firsl. NOTE(01) The A31 0-200 aircraft type concerns aircraft models 3 1 0-203, 310-203C, 310-204 and 310-222. NOTE(02) The A310 -300 aircraft type concerns aircraft models 310-304, 310-308, 310-322,310-324 and 3 1 0-325. NOTE(03 ) For Average Flight T ime (AFT) configuration refer to Airworthiness Limitation Item Document Section B . For A310-300 models the limit between Short Range (SR) and Long Range (LR) is optim i zed at AFT=3.23 FHfFC for thresho ld and AFT=3.4 FH/FC for interval. NOTE(04) Grace periods:



# . For A31 0-200 aircraft : For aircraft which have performed 1,500 FC or 3,100 FH below the threshold or have exceeded it by less than 1,500 FC or 3,100 FH, t he first inspection is to be performed within 1,500 

### FC/3,100 FH a ft er receipt of this Inspection Service Bulletin without exceeding the value of the previous revision of this Inspection Service Bulletin . If aircraft have exceeded the threshold by more than 1,500 FC or 3,100 FH , the first inspection is to be performed within 1 ,300 FCf2,700 FH after receipt of this Inspection Service Bulletin. DATE: Aug 

### 24/95 SERVICE BU L LE T IN No. : A310-S7-2064

REVISION No. : 02 - Dec 21/07 Page : 9 Prin ted in Fran<:\! Cl A I RBUS 2007 Al l rights reser""d

# I 

# I F. APPROV AL

# A310 SERVICE BULLETIN



### For A310-300 Short Range (SR) aircraft : For aircraft which have performed 1,200 

# Fe or 3,600 FH below the threshold or have exceeded it by less than 1,200 Fe or 3,600 FH, the first inspection is to be 

### performed within 1,200 FC/3,600 

### FH after receipt of this Inspection Servic e Bu ll et in without exceed i ng the value of the previous revision of this Inspection Service Bu ll etin . If 

### aircraft have exceeded the threshold by more than 1,200 

## Fe or 3,600 FH, the first inspection is to be performed within 600 Fell,BOO FH after receipt of this 

### Inspection Service Bu ll etin. 

### For A310-300 Long Range (lR) ai rcraft: For aircraft which have performed 1,000 

# Fe or 5,300 FH be l ow the thresho ld or have exceeded it by less than 1,000 

## Fe or 5,300 FH, the first inspection is to be periormed within 1,000 FC/5,300 FH after receipt of this I nspect ion Service Bullet i n without exceeding the va l ue of t he previous revision of this Inspection Serv ice Bu ll etin . If aircraft have exceeded the threshold by more than 1,000 FC or 5,300 FH, the first in spection is to be periormed within 500 FC/2,650 FH after rece i pt of this Inspection Service Bullet in . Approved under EASA Design Organ ization Approval No . EASA 21J.03 1 . If an ai rcrafllisted in the effectivity has a mod ificat ion or repair embodied thai is not of A IR BUS origin, and which affects the content of this Service Bulletin , the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorpora t ion of the Service Bulletin. 

### G . MANPOWER The manpower estimates given in this Service Bulletin are based on the d irect labor cost to do the work. T hese estimates assume t hat th e work will be done by experienced personnel. and may need to be revised upwards to suit operator's circumstances . T he estimates do not inc l ude the time to prepare, plan or inspect the work . Manufacture and procurement of parts and lools , drying t imes for paints, sealants, etc, and genera l administ ra t ion work are also not included. Config . 01 thru Config . 03 , for i nspection Gel access 

## 60 Inspect the LH and RH holes No.1 thru 4 

### 4 .0 Test 2 .0 Close-up 

### 5.0 TOTA L MAN HOURS 

### 17 .0 DATE: Aug 24f95 SERV ICE BULLETIN No. : A3 1 0-57-2064

REVIS ION No . : 02 - Dec 21107 Page: 10 Printed in France ICI AI RBUS 2007 AU**ri9~ ts**  ", served

# I 

# ($; A310 SERVICE BULL E T IN

ELAPSED TIME (HOURS) 

### 13.0 Co nfig. 01 thru Config. 03, for repa i r ( Rep lacemen t of the i nterna l a n gle f i lti n g as spec ified i n Repa i r I nstr uct ion N o. 2 1R57 11 0257 o r No. 2 1R57 11 0259 or No. 2 1R57 1 10266 , on o ne side) 

### Re p lacem en t of internal a ngl e fi lli ng 80.0 TOTAL MANHOURS 80 . 0 

### ELAPSED TIME (HOURS ) 40.0 Con fi g . 01 I h r u Config . 03 , for repa ir ( I nsta ll ati on of the b u shes in ho l es N O . 2 a n d 3 as specified 

### i n Repa i r I nst ruc tio n No . 21R57 1 10260, on one s id e) 

### Installat ion of th e bushes 30.0 TOTAL MAN HOURS 30.0 ELAPSED TIME (HOURS) 15 . 0 Co nfig. 01 thru Co nfig , 03 , f or repa i r ( I nsta ll at ion o f t he fasteners wi th h i gh i nterference fi t al r i b 1 as specif i ed i n Repa i r I ns tr u ct ion N o. 2 1 RS7 11 0266) 

### Insl al la l ion of th e fa steners TOTAL MAN HOURS ELAPSED TIME (HOURS) H . WEIGHT AND BALANCE N ot c hanged 

### J. ELECTRICAL LOAD DATA N ot changed 

### J. REFERENCES Ai rcraft M ai ntenance Man u al (AMM)
Co nsumab l e Materia l lis t (CML) Elec . Std . P ractices M anua l (ESPM) I ll ustra ted Pa rts Cata log (I PC) Non destructive Tes ting Manua l (NTM) Standards Ma n ua l (SM) DA T E : Aug 24f95 

### REV IS I ON No . : 02 - Dec 2 1/ 07 

### 30.0 30 . 0 15.0

: 1 2- 1 1-28 1 2-33- 2 1 24 -00-00 24 -41-00

28 -00-00 28-10-0 0 28-11-22 28 -11-29 28 -25 - 0052 - 10 -0052-30- 00

: 20 -55 -00 : 2 1- 28 -0357 -45-1 1 : 5 1 - 1 0-0857- 1 0 - 25

SERV I C E BU LLE T I N N o . : A3 1 0 -57 -2 064 Page : l1 Pr i nted I n F ra nce 10 A I RBU S 2 00 7 All rig hts**re rve<l** 

# I ($!A310 SERVICE BULLETIN



### Structura l Repa i r Manual (SRM) Maintenance Review Board ( MRS) 57 . 1 0 .25 

### Main tenance Review Board (MRS) Sect ion 0 , Para 8 Repair Instruction No. 2 1 R57 1 10257 Repair Instruction No. 21R57 1 1Q259 Repair Ins t ruction No. 21R57 1 10260 

### Repair Instruction No. 2 1R571 1 0266 Service Bulietin No . A310-57-2067 Appendix 1 

### K. PUBLICATIONS AFFECTED Ma i ntenance P la n n i ng Document ( MPD) 

### S tructural Repair Man ual (SRM) 

### L. INTER C HANGEABILlTYfMIXABIUTY 

### Nol app l icab le 

### : 51-43-0051
-76 · 20

: 57-10-25 

### : 57
- 10
-24

DATE : Aug 

### 24f95 SERVICE BU L L ET I N No . : A3 1 0-S7-2064

REVISION No. : 02 - Dec 2110 7 

### Page : 12 Prin ted in F rarn;e CI AI R BU S 2 007 All lig ht ! r no rvod

# I I**~A310** SERVICE BULLET IN



### 2. MATERIAL INFORMATION 

### A. MATERIAL - PRICE AND AVAILABILITY (1) Material 

### Customers with aircraft shown in the effectivity of th is Service Bulletin should send a purchase order to AIRBUS . Quote the number of this Service Bulletin. The address is : 

### AIRBUS SPARES SUPPORT AND SERVICES Weg bein Jaeger 150 

### 0-22335 HAMBURG GERMANY 

### For ordering by 

### internet: hllp:flspares.airbus.com For ordering by 

### fax: +494050 76 25 90 (2) Price and Availability Kit 572064A01ROO Cost : 2,040.00 US dollars Availability: 90 calendar days from receipt of order The Kit availability given above is the standard lead time from the dale of your purchase order. If you require the Kit(s) before this lime , please include a retrofit planning schedule with your order so that we can try to comply wit h your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 572064A02ROO Cost" : 2,040.00 US dol l ars Availability: 90 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. I f you require the Kit(s) before th is time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (cos ts and ava ilabili ty ) a re estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 572064A03R02 Cost : 6,400 . 00 US dollars Availability: 90 calendar days from receipt of order
DATE: Aug 

### 24/95 SERVICE BULLETIN No . : A310-S7-2064

REVISION No. : 02 - Dec 21/07 Page : 13 PriMed I " Franco**~** AIRBUS 2007 AU rignls**r(!s~rved**

# I I !$!A310 SERVICE BULLETIN

The K it ava il ab ility g iven above is the standard lead t i me from the dale of your purchase order. If you requ ire the Kit (s) before th is l i me , p lease i ncl ude a retrofit plan n i ng sch edu l e 

### w ith 

### your orde r so thai 

## we can try to comply wi th your requ i remen ts . The sales 

### terms (costs and ava il ab ili ty) are estim ated in rel ation to economic condit ions 

### at the issue date of the Service Bull eti n . Kit 572064A04RQ4 Cost : 8,710.00 US dollars 

### Availability: 90 cale ndar days from receipt of order The Kit availability given above is the standard lead lime from the date of your purchase 

### order. If you require the Kil(s) before this time, ple ase include a re trofit planning schedule with 

### your order so that we can try to comply with your requ i rements . The sates terms (costs and availab il ity) are estimated in relation to economic conditions at the issue date of the Service Bulleti n . Kit 572064A05ROO Cost : 5 ,660.00 US doll a rs Availabil ity: gO ca l endar days from re ce i p t of order T he Kit availabi l ity given above is th e standard l ead time from the date of your purchase o r

der. If you require the Kit(s) before this ti me , p lease incl u de a retrofit planning schedu l e w ith your order so that we can try to comp !y with your requirements . The sa l es terms (costs and availabi l ity) are esti mated in re lation to economic conditions at the issue date of the Service Bullet i n . Kit 572064A06ROO Cost : 207.00 US dollars Availability : gO calendar days from receipt of order The Kit availability given above is the s tanda rd lead t ime from the date of your purchase order. If you require the Kit(s) befo re this time , pl ease incl ude a retrofit pl ann i ng schedule with your order so that we can try to comp ly with your requirements. Th e sa l es terms (cos ts and avai labi l ity) a re est i mated i n rela ti on to economic condit ions at the issue date of th e Serv ice Bu lleti n . B . INDUSTRY SUPPORT INFORMATION A I RBUS will not p rovi de indus try s u pport 

### fo r accomp l ishmen t of th is Service B ull etin . C . LIST OF COMPONENTS Kit 572064A01 ROO DATE : Aug 

### 24/95

REVISION No . : 02 - Dec 21/07 SERVICE BULLET I N No .: A310-57-2064 Page : 14 Printed in F ranco CI A tRBUS 2007 All fig htS reurV$ d

### ITEM

ITEM

ITEM NEW PART No. A5711206120602 A5711242720096 Kil 572064A02ROO NEW PART No. A5711206120502 A5711242720196 Kil 572064A03R02 NEW PART No. ASNA2027T7·28 ASNA2027T8-20 ASNA2027T8-23 ASNA2027T8-28 ASNA2027V6-15 ASNA2027V6-19 ASNA2027V6-20 ASNA2027V6-27 ASNA2531-6 ASNA2531 - 7 ASNA2531-8 ASNA2532-6 ASNA2532-8 Hl112VBJ12-10 HL 112VBJ12·14 HL 112VBJ12-16 HL 112VBJ12-17 HL 112VBJ12-19 HL 112VBJ12-20 HL112VBJI2-27 HL112VFI4-19 HL112VF14-20 HL 112VF14-23 HL 112VF 16-20 H l 112VF16-23 HL112VF16-28 Hl75-12AVW Hl87-12 HL87-14 HL87-16

# A310 SERVICE BULLETIN

QTY UM KEYWORD IT EM OLD PART No. Fitting 1 Shim
QTY UM KEYWORD ITEM OLD PART No.

QTY 

## UM

2 2 7 

### 1 2 2 4 

### 2 12 2 4 

### 3 4 

### 1 2 

### 3 1 2 1 

### 5 1 4 

### 1 

### 3 11



### 8 6 Fitting Shim
KEYWORD Bolt Boll Bolt Bolt Boll Boll Boll Boll 

### N,I N,I N,I N,I N,I Bolt Boll Boll Boll Boll Boll Boll Boll Boll Bolt Bo ll Bolt Boll Collar Collar Collar Collar ITEM OLD PART No. INT I NST DISP

INT INST D I SP

INT INST DISP

NOTE: Refer 10 Ihe AIRBUS Siandards Manual (SM) if you find pari numbers of hardware components in the related kil(S) which you cannot idenlify in Ihe LIST OF COMPONENTS of Ihis Service Bullelin. T he SM will give you the correct pari number to part number relat!onship. Kit 572064A04R04 DATE : Aug 

### 24/95 SERVICE BULLETIN No . : A310-57-2064

REVISION No .: 02 - Dec 21/07 Page : 15 P rul tcd In Fta nce Cl AlRBUS 2007 Al l ri ghts reserved

# I ITE M NEW PART No . Hl375-12AVW 

### H

l 4 1 2V8J 1 2
- 10 Hl412V8J 1 2-14 HL4 1 2V8J 1 2-16

# A310 SERVICE BULLE TI N



### QTY UM KEYWORD ITEM OLD PART No .



### 3 4 

### 3 3 Collar Bolt Bolt Bolt 

### Hl 412V8J 1 2-17 1 Bo lt 

### Hl412V8J12-19 2 Bolt Hl412VBJ 1 2-20 3 Bolt HL412V8J12-27 1 Bolt HL412VF 14- 1 9 2 Bolt HL412VF14-20 1 Bolt 

### HL4 1 2VF14-23 5 Bolt HL412VF16-20 1 Bolt 

### HL412VF16-23 4 Boll HL4 1 2VF16-28 1 Boll 

### H L93 - 12 1 1 Collar H L93-14 8 Collar HL93 - 16 6 Co ll ar 

### NAS l 726-6E 4 Nul NAS 1 726-8E 8 Nul 

### NAS 1 727-6E 2 Nul NSA5479BV6 -1 5X 2 Bolt 

### NSA5479BV6·19X 2 Bolt NSA5479BV6-20X Bolt 

### NSA5479BV6-27X 1 Bo lt 

### NSA5479BV8 -20X 1 Screw NSA5479BV8-23X 6 Bolt I NT I NST O ISP



### NOTE : Refer to t he A I RBUS Standards Man u al (8M) if you find pari numbers of hardware components i n t he re lated kit (s ) w h ich you cannot identify in the LIST OF COMPONEN T S of this Service Bul l eti n . The SM wi ll g ive you the correct pa rt number to part number relat ionsh i p. Kit 572064 A05ROO ITEM NEW PART No. ASNA2027T8-19 ASNA2027T8 -20 ASNA2027T8-23 ASNA2027V7-10 ASNA2027V7-14 ASNA2027V7- 16 ASNA2 027V7- 17 ASNA2027V7-19 ASNA2027V7-20 ASNA2027V7-27 ASNA2531-7 ASNA2531 - 8 ASNA2532-7 NASl726-6E NAS l 726-8E DATE : A u g 

### 24f95 QTY UM KEYWORD ITEM OLD PAR T No . INT INST DISP 

### 2 2 

### 5 4 

### 3 3 1 

### 2 4 

### 11



### 8 

### 3 4 

### 8 Bo l l Bo lt Bolt Bolt Bolt Bolt Boll Bo lt Bo lt Bolt N, I N,I N,I N,I N,I SERV I CE BULLETIN No. : A310-57-2064 REVIS ION No . : 02 - Dec 

### 21 / 07 Page : 16

Pri nted I n France Cl AIR BU S 2001 Al l**ri~h s**  reservedIT EM 

# ($;A310 SERVICE BULLETIN

NE W P ART N o . 

### a TY 

## UM KEYWOR D ITE M O L D PART No . tNT INST D I SP NAS1727-6E 

### 2 

### Nul NASl727-7E 3 

### Nul NSA54798VG-15Y 

### 2 Bolt NSA5479BV6-19Y 

### 2 Bolt NSA5479BV6-20Y Bolt NSA5479BV6-27Y 

### I Bo lt NSA54798V8-20Y 

### I Bolt NSA5479BV8-23Y 

### 6 Bolt 

### NOTE : Refer to the AIRBUS Standards Manual (SM) 

### if you find part numbers of hardware components in the related 

### kitts) which you cannot identify in the LIST OF COMPO N EN TS of this Service Bulletin . The SM will give you the correct part number to part number relationship . 

### Kit 572064A06ROO ITEM NEW PAR T No. QTY UM KEYWORD ITEM OLD PART No . IN T INST D I SP A$NAZ027T7· 28 ASNA2S3 1 -7 

### 2 

### 2 Bo l l 

### Nu l NOTE : Refer to t he A I RBUS S tandards Ma n ua l (SM) 

### i f you find part numbers of h ardware 

### components i n Ih e re lated kil(S) wh ich you can not iden tify in the US T O F COMPONENTS of this Service Bul leti n . Th e SM wi ll give you the correct part number to part number relationship . D. LIST OF MATERIALS· OPERATOR SUPPLIED ( 1) Consumable Materials DESCRIPTION Solven t General Purpose REFERENCE TO CM L MA T No. Mat. No. 11 ·026 QTY PER AlC INS TIDISP As requ i red NOTE : To accomp lish this Service Bu ll etin, it is necessary to use the expe ndable parts listed in the SRM 51·76-20 , AMM 28- 11 -22, AMM 28-11 -29 and in Repair I nstructions No. 21 R571 1 0257, No . 21 R57110259 , No. 21 R57110260 and No. 21R57 11 0266 . (2) Componen ts None E . PARTS TO BE RE-tDENTlFIED BY THE OPERATOR None

DATE : Aug 24{95 SERV I CE BULLETIN No . : A310-57 -2 064

REVISIO N No. : 02 - Dec 2 1 /07 Page: 17**Pti~l d**  in France O AIRBUS 2007 A ll "," hll tOliOtvod

# (tJA310 SERVICE BUL L E T I N



### F. TOOLING· PRICE AND AVAILABILITY T

o accomp li sh th is Service Bu ll et i n 

### it is necessary to use t he I DOls li sted in NT M 57 · 1 0· 25 , Page b l ock 60 1 and N TM 5 1-1 0 -08 , Page b l ock 601. 

### G. SPECIAL TOOLS 

## None

DATE: Aug 

### 24/ 95 SERV ICE BULLE TIN No . : A3 1 0-57 - 2064 REVIS ION No . : 02 - Dec 21107 

### Page : 1 8 P ri nted i n France (l AI RBUS 2 00 7 All ri ghts rese rve d

# I**A310** SERVICE BULLETIN

3. ACCOM PLI S HMENT INST R U CTIO NS 

### A. GE N ERA L WARNING: MA KE SURE T HAT YOU OBEY AL L THE WARNINGS AND ALL THE CAUTIONS INC LUDE D IN T HE REFERENCED PROCEDURES . WARNING: BEFORE YOU DO WORK I N A FUEL TANK, MAKE SURE THAT YOU OBEY A LL T HE SAFE TY PROCEDURES. T HIS WILL PREVEN T INJURY TO PERSONS AND/OR DAMAGE TO THE AIRCRAFT. CAUTION: A L WAYS OBEY THE PRECAUTIONS THAT FOL LOW TO KEEP E L ECTRICAL WIRING IN A SA T ISFACTORY CONDITION (E L ECTRICALLY AND MECHANICALLY 

### SERVICEABLE) . WHEN YOU DO MA I NT ENANCE WORK, REPAIRS OR MODIFICAT I ONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE, TO DO TH IS: PUT PROT ECTION, SUCH AS PLASTIC SHEE T ING , CLOT HS, E TC; AS NECESSARY ON WIRING AND COMPONENTS. REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CON T AMINATION. T HESE PRECAU T IONS WILL DECREASE T HE RISK OF CON T AMINATION AND DAMAGE TO T HE ELECTR ICAL WIRING INSTALLA T ION. IF THERE IS CONTAMINATION REFER TO ESPM 20-55-00. (1) Preparat ion

PANEL 131VU 1 3 1 VU 13 1 VU (a) Config. 01 thru Config . 03 1 Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page block 301) . 2 Pu t the access plaiform(s) in position.**~** Open the passenger/crew door (Refer to AMM 52-10-00) .**~** Open, safety and lag these circuit breakers: DESIGNATION FIN LOCATION VENT IL ATION/AVIONICS BLOWER/LO 65HQ 

### 060 

## SPD VENTILATION/AVIONICS B LOWER/HI 48HQ 

### 064 

## SPD VENTILATION/AVIONICS BLOWER 49HQ 

### 062 CONTROL**~** Open, safety and tag the circuit breakers lis ted in AMM 28 - 1 1 -22, Page block 401 , AMM 28-11-29, Page block 40 1 and AMM 28-25-00, Page block 301.
DATE : Aug 

### 24/95 SERVICE BU L LE T I N No .: A310-57-2064

REVISION No .: 02 - Dec 

### 21107 Page : 19 Printed In France 10 AtRBUS 2007 All rig hts reserved

# I I$;A310 SERVICE BULLETIN



### §. Defuellhe center fuellanks and the LH and RH inner wing tanks (Refer to AMM 28-25-00, Page block 301). 

### 7 Degas and ventilate the fuel tanks (Refer to AMM 28-00-00, Page block 301 and AMM 28-10-00, Page block 301). 

## !! Open the access doors 540AB and 640AB on the lower surfaces of the wing to get access to the inner tanks (Refer to AMM 28-11-22, Page block 401). 

### 9 Remove the manhole covers 147AZ and 148AZ (Refer to AMM 28-11-29, Page block 401). 

### 10 Remove on the LH side the air distribution dueling from FR4Q, as shown on the I Pe 21-28-03 . 11 Open the forward cargo compartment door 811 (Refer to AMM 52-30-00, Pag e block 001) . 

## .1.f. Open the Krueger panels (RH and 

### lH sides) PN A5784395200000 and PN 

### A578439520Q1QO on the lower surfaces of the wing to get access to FR40, as shown on the IPC 57·45·11. (2) Standard Practices (a) For the specification of the material numbers (M at. No .), refer to the CML. (b) Torque the standard threaded fasteners (Refer to SRM 51.43·00) . (c) Clean the surfaces to seal with Solvent General Purpose (Mat. No. 11·026). (d) Repair the sealing of the fuel tank (Refer to SRM 51·76·20) . (3) Work Breakdown The purpose of the flow chart (Refer to figure 1 ) is to show the various Inspection/Repair phases described in this Service Bulletin. 

### 8. INSPECTION (1) Config . 01 and Config. 03 NOTE: Installation of the fasteners with high interference fit as specified in Repair Instruction No. 21 R57110266 or Repair Instruction No . 21R57110257 is app li cable one time only. From repair embodiment, aircraft is considered as Config. 02 in the inspection process, so refer to Config. 02. NOTE(01) When the work is completed, you must report the i nspection results to AIRBUS, on the recording forms attached (Refer to Appendix 1).

DATE: Aug 24/95 In case of findings, refer to the Service Bulletin instructions to do this report, that is : Imm ediately (maximum within 48 hours) in case of damage which is more than the permitted or rework l imits for further action(s) before the next flight. SERVICE BULLETIN No. : A310·57·2064 REVISION No. : 02· Dec 21/07 Page: 20 Printed in France C A I RBUS 2007 All ri ghls rese"'ed

# I 

# I$iA310 SERVICE BULLETIN

After completion of the corrective action when damage is either in the permitted or rework li m its , 

### or repaired as specified w ith the Service Bullet i n i nstructions, In case of no fi ndings , you must send the inspection report as soon as the ma i ntenance check or i nspection report is completed . To prepare these documents, refer to this Service Bulletin. 

### (a) For the i nspection area, refer to figure 2. 

### (b) Do an eddy current inspection of the upper corner angle at FR40 on the LH and RH sides.

DATE: Aug 

### 24/95 Refer to NTM 57·10·25 , Page block 601 Refer to figure 1 , sheets 1 thru 2 

## 1 Remove the fasteners from the holes No.1 , 2, 3 and 4 to inspect. Refer to figure 2 

### NOlE(Ol) For the subsequent inspections, remove the fasteners only from the ho l es to inspect. NOTE(02) If repair bushes are installed in the ho les No.2 and 3, remove them when inspection is necessary in these holes . If you don't know when the existing bushes were inst alled or when the repair as specified i n Repair Ins truction No. 21 R57110260 or Repair Instruction No. 21 R57110266 was done, contact AIRBUS. 

## £ If necessary, on FR40, push back some fasteners for access.



### 2 Refer to figure 8**~** Remove: Not 

## 12 Push back (do not remove) : Screw Screw Jlem (22)

Item (20) Item (21) Retain**~** If no crack i s found:**~** Install the new nominal fasteners in relation to the removed fasteners. 

### Q Do the subsequent inspecti on of the holes No.1, 2, 3 and 4, i n relation to the aircraft configuration at the interval given in PLANN I NG I NFORMAT IO N paragraph E.(2) Tab le B. 

### f. Or accomplish Servi ce Bulletin No . A310-57-2067. The aircraft becomes in Config. 02 (refer to Config. 02 ) :

SERVICE BULLETIN No. : A310-57-2064 REVISION No. : 02 - Dec 21107 Page : 21 Printe d in FIance**AIRBUS** 20 07 All rig hts reserved

# A310 SERVICE BULLETIN

Do the subsequent inspection of the holes No . 1 , 2, 3 and 4 at the th reshold 

### and interva l given in PLANNING INFORMATION paragraph E , (2) Tab les 

### A and B. 

## .1. If crack is found: 

### !! Crack only in the ho le No.1 , in the internal ang le filling, no crack in the ho l es No . 2 and 3 and no bushes i nstalled in these ho le s Refer to ACCOMPLISHMEN T INS T RUCT IONS , paragraph B.( 1)(b)S . 

### Q. Crack i n the hole No . 1 , in the internal angle, and crack or bushes in the hole 

### No . 2 and/or 3, in the vertical tee Refer to ACCOMP L ISHMEN T INSTRUCTIONS, paragraph B .( 1)(b)6 . 

### f. Crack or bushes in the ho le No.2 and/or 3, in the verlicallee Refer to ACCOMPLISHMEN T I NSTRUCT I ONS, paragraph B.(1 )(b)7. 

### Q. Crack i n the hole No.4, in the vertical tee Contact AIRBUS. 

### !! Or crack in other(s) part(s) Contact AIRBUS . 5 Crack only in the ho le No .1. in the internal angle fitting. no crack in the hol es No.2 and 3 and no bushes installed in these holes: Replace the i nternal ang le filling and install in the app l icable ho les the fasteners with high i nterfere nce fit as specified in Repair Instruction No. 21R57110257 (Refer to ACCOMPLISHMENT INSTRUCTIONS paragraph C.(1 )(a) (Refer to Note ». The aircraft becomes i n Config. 02 (refer to Config . 02 ) : Do the subsequent i nspection of the holes No.1 , 2. 3 and 4. at the thresho ld and interval given in PLANNING IN FORMATION paragraph E.(2) T ables A and B. NOTE : Replacement of the i nterna l ang l e filling as specified in Repair Instruction No . 2 1R57110257 inc l udes the i nsta ll ation with h igh i nte rference fit of some fasteners at FR40 and rib 1 . 

### §. Crack in t he ho le No . 1. in the i nternal ang le fitting, and crack in the hol es No . 2 and 3 or bushes insta ll ed in these holes :**~** 

### Replace the internal angle filling and i nstall the fasteners with h i gh interference fit at rib 1 as specified in Repair I nstruction No. 21 R57110266 procedure A (Refer to ACCOMPLISHMEN T INST RUC T IONS paragraph C.(1)(a» and do the i nstructions fo r the holes No .2 and No.3 as spec ified i n ACCOMPLISHMENT INSTRUCTIONS, paragraph B . (l )(a)7 . DATE : Aug 24/ 95 

### SERV I CE BU L LETIN No .: A310 · 57 · 2064 REV I SION No . : 02· Dec 21/07 

### Page : 22 Pnnlcd In France IC AIRBUS 2007 Al l nghlS rese rve d

# I

DATE: Aug 

### 24/95

# ~A310 SERVICE BULLETIN



### 12. Do the subsequent inspection of the hole No . 1 at the applicable threshold specified in Tab le 2 (Refer to fjgure 4) . 

### .£ Do the inspection of the hole No . 4 , i n relation to the aircraft configuration at the interval given in PLANN I NG INFORMAT ION paragraph E . (2) Table B. 

## g Do the subsequent inspection of the holes NO .2 and NO.3 as specified in ACCOMPLISHMENT INS TRUCTIONS, paragraph B.(1 )(a)7 . 

### 7 Crack or bushes in the holes No . 2 and 3, in the vertical tee:**~** 

### If there is a lso a crack in the hole No.1, at first refer to ACCOMPLISHMENT INS TRUCTIONS, paragraph B.(1 )(b)6. 

### Q Find the crack length in the ho les No . 2 and 3 (Refer to NTM 51-10-08, Page block 601) and calculate A Refer to figure 2**~** 

### I f A is less t han or equal to 9.15 mm (0.360 in.) : Remove the crack(s) and install the bushes in the hol es No.2 and 3 as specified in Repair Instructio n No . 21R57110260 (Refer to ACCOMPLISHMENT INSTRUCTIONS paragraph C.(l )(a». Instal l the fasteners w ith h igh i nterference 

### fit at rib 1 as specified in Repa i r Instruction No. 21 R57110266 (Refer to ACCOMPLISHMENT INSTRUCTIONS paragraph C.(l)(a». Do the subsequent i nspection of the holes No.2 and 3 at the applicable threshold specified i n Tab le 3 (Refer to figure 5) . Do the inspection of the hole No.4, in relation to the aircraft configuration at the interval given in PLANNING INFORMATION paragraph E. (2) Table B . 

### 00 the subsequent inspect ion of the hole No . 1: if the interna l ang le is replaced, refer to ACCOMP LI SHMENT INSTRUCTIONS paragraph B .( l )(b)6 , if the i nternal angle is not replaced, at the applicable interva l specified in Table 5 (Refer to figu re 7) . 

### Q I f A is more than 9 . 15 mm (0 . 360 in . ) : If A is more than 9.15 mm (0.360 i n.) only for a crack which propagates upward (crack at 12 o'c lock) from the hole No.2. Install the bushes in the ho les No . 2 and 3 as specified i n Repair Instruction No. 21R57110260 (Refe r to ACCOMPLISHMENT I NSTRUCTIONS paragraph C.{l )(a)) . SERVICE BULLET I N No. : A310-S7-2064 REVISION No. : 02 - Dec 21/07 

### Page: 23 Prin ted In France ICI A I RBUS 2007 All rig hts re served

# ($) A310 SERVICE BULLETIN



### Inslalilhe fasteners with high interference fit 

### al rib 1 as specified in Refer to Repair Instruction No . 21R57110266 (Refer to ACCOMPLISHMENT INSTRUCT IONS paragraph C.(l)(a». Do the subsequent inspection of the holes No.2 and 3 at the applicable interval specified in Tabl e 4 (Refer to figure 6). 

### Do the inspection of the hole No.4, in relation to the aircraft configuration at the in t erval given in PLANNING INFORMATION paragraph E.(2) Table B. 

### Do the subsequent inspection of the hole NO . 1:

. if 

### t he internal angle is replaced, refer to ACCOMPLISHMENT INSTRUCTIONS paragraph 8 .(1 )(b)6,

. if the in l erna l angle is not replaced, at the applicable inte rval specified in Tab le 5 (Refer to figure 

### 7). If A is more than 9.15 mm (0 .360 in.) for a crack not at 12 o'clock in the hole No.2, contact AIRBUS. 

### §. After t he inspection and the repair, install the fasteners that you pushed back at removal (if necessary). Refer to figu re 

### 8**~** 

### Pu t i n position: Screw Screw 

### Q Install : 

### 2 N"I NOTE : Item (22) was retained at removal. Item (20) Item (21)
Item (22) (c) For the Inspect ion Report, refer to Appendix 1 . (2) Config. 02 NOTE : When the work is completed, you must report the inspection results to A I RBUS, on the recording forms attached (Refer to Appendix 1).

DATE : Aug 

### 24/95 In case of findings, refer to the Service Bulletin instructions to do this report, that is : Immed iate ly (maximum within 

### 48 hours) in case of damage wh ich is more than the permitted or rework limi ts for fur ther action(s) before the next flight. After completion of the corrective action when damage is either in the permitted or rework limits, or repaired as specified with the Service Bullet in instructions .
SERVICE BULLETIN No. : A310-57 -2064 REVISION No.: 02 - Dec 21/07 

### Page: 24 P rin ted i n F ranoe C AI RBUS 2007 All ri ghts reserved

# ~A310 SERVICE BULLETIN



### In case of no findings, you must send the inspection report as soon as the ma i ntenance check or i nspection report is completed. To prepare these documents, 

### refer to th is Service Bu ll et i n. 

### (a) For the inspection area , refer to figure 2 . (b) Do an eddy current inspection of the upper corner ang le al FR40 on the LH and RH sides. Refer to NTM 57-10-25, Page block 601 Refer to fi gure 1, sheets 1 thru 2 

### 1 Remove the fasteners from the ho les No.1 , 2, 3 and 4. Refer to fi gure 2 NOTE(01) Fo r the subsequent inspections. remove the fasteners only from 

### the holes to inspect. NOTE(02) If repa i r bushes are insta ll ed in the ho l es NO . 2 and 3, remove them when i nspection is necessary in these holes . If you don'l know when 

### the existing bushes were installed or when the repa i r as specified in Repa i r Instruction No . 21 R57110260 or Repair I nstruction No. 21 R57110266 was done, contact AIRBUS. 2 If necessary, on FR40, push back some fastene rs for access .



### 2 Refer to figure 8**~** 

### Remove : 

### N,I 

### Q. Push back (do not remove) : Screw Sc rew Item (22)
Item (20) Item (21) Retain



### ;i If no crack is found :**~** 

### I nsta li the new nom i na l fasteners in re latio n to the removed fasteners. b Do the subsequent inspection of the ho les No . 1, 2, 3 and 4 , in relation to the aircraft configu ration at the interval g iven in PLANNING INFORMATION paragraph E.(2) Table B.**~** 

### I f crack is fo u nd:**~** 

### Crack only in the ho le No.1 , in the interna l ang le filting, no crack in the ho l es No. 2 and 3 and no bushes insta ll ed in these ho les Re fer to ACCOMPLISHMENT I NSTRUCTIONS , paragraph B . (2)(b)5. b Crack in the ho le No . 1 , i n th e i nternal ang le, and crack or bushes i n the ho le No . 2 a nd/o r 3, i n the vert ical tee DATE: Aug 24/95 SERV ICE BULLETIN No. : A310-57-2064

RE VI SION No . : 02 - Dec 21 /07 Page : 25 Prinled In France (l AI R BU S 2007 Al l ri ghts reserve d

# I**A310** SERVICE BULLET I N

Refer 1 0 ACCOMPLISHMENT INSTRUCTIONS , paragraph B .( 2) ( b)6 . 

### f. Crack or bushes i n the ho l e No . 2 and l or 3 , in t he vertica l tee Refer to ACCOMPLISHMENT I NSTRUCT IONS . paragraph B. (2)(b)7 . 

### Q. Crack in the ho le No.4, in the ver lica l lee Contact A IR BUS .**~** Or crack in other(s) part(s) Contact A IRBU S.**~** 

### Crack only in the hole No.1, in the internal ang le fitting, no crack in the holes No . 2 and 3 and no bushes in these holes :**~** Replace the inlernal ang l e fitting as specified in Repair I nstruction No . 21 R57110259 (Refer to ACCOMPLISHMEN T I NSTRUCTIONS paragraph C . (2)(a)). 

## !! 00 the subseq ue nt inspection of the hole No . 1 a lth e appl icab le th reshold specified in T able 1 ( Refer to figure 3) . 

### f 00 the subsequent i nspection of the ho l es No . 

### 2 a nd 

### 3 at the app licable thresho ld specified in Table 3 ( Refe r to figure 5) . 

### Q. Do the i nspection of the hole No . 4, i n re l at ion to the aircraft configuration at the interva l given i n PLANNING INFORMATION paragraph E. (2) Table B. 

### §. Crack in the hole No . 1 , in the interna l angle fitting , and crack i n the holes No. 2 and 3 or bushes installed In t hese holes**~** Replace the internal angle fitting as specified in Repair I nstruction No . 21R57110259 (Refer to ACCOMPLIS HMENT INS T RUCT i ONS paragraph C.(2)(a)) . 

## 2. Do the subsequent inspection of the hole No. 1 at the applicable thresho ld specified in Table 1 (Refer to figu re 3) . 

### .£ Do the inspection of the ho l e No . 4 , in relation to the ai rcraft configuration at the interva l given in PLANNING INFORMATION paragraph E.(2) Ta b le B . 

### Q. Do the subsequen t inspect ion and instruct ions o f the holes No . 2 and No . 3 as speci fi ed i n ACCOMPLISHMENT I NS T RUCT I ONS , parag raph B . (2) (a)7 . 

## I Crack or bushes i n the ho l es No . 2 and 3, i n the ver tical tee**~** If th ere is a lso a crack in the hole No . 1 , at firs t refer to ACCOMPLISHMEN T INSTRUCTIONS, paragraph B . (2) (b )6. b Find the crack l ength in the holes No . 2 and 3 (Refer to NT M 51-10-08, Page block 601) and ca lcu l ate A. DATE : Aug 

### 24/95 SERVICE BULLETIN No . : A310-57 -2064

REVISION No . : 02 - Dec 2 1/07 Page: 26 PriMed In France Cl AIRBUS 2007 An rign l s rlllOMld

# I

DATE: Aug 

### 24/95

# A310 SERVICE BULLETIN



### Refer to fig ure 2 

### £ If A is less t han or equal to 9 . 15 mm (0.360 i n.) : 

### Remove the crack(s) and install the bushes i n the holes No.2 and 3 

## as specified in Repair I nstructio n No. 21 R57110260 (Refer to ACCOMPLISHMENT INSTRUCTIONS paragraph C.(2)(a)) . 

### Do the subsequent inspect ion of the holes No.2 and 3 althe applicable threshold specified in Tab le 3 (Refer to figure 5), 

### Do the subsequent inspection of the ho le No.1 althe applicable threshold specified i n Tab le 1 (Refer to figure 3) . 

### Do the inspectio n of the hole No.4, in relat ion to t he aircraft configuration althe interval g ive n in PLANNING INFORMATION paragraph E .{2) Table B. 

### Q If A is more 

### than 9. 1 5 m m (0.360 i n.) : If A is more than 9.15 mm (0.360 in.) only for a crack which propagates upward (c rack at 12 o ' c lock) from the hole No.2. Insta ll the bushes i n t he holes No.2 and 3 as specified in Repair Instruction No. 21R57110260 (Refer to ACCOMPLISHMENT INS T RUCT IONS paragraph C . (2)(a». Do the subsequent inspection of the holes No.2 and 3 at the applicable interva l specified in Tab le 4 (Refer to figure 6). Do the inspect ion of the hole No . 4, in rela t ion to the aircraft configuration at the interva l given i n PLANN I NG INFORMA TION paragraph E.(2) Table B . Do the subsequent i nspection of the hole No. 1 at the applicable threshold specified in Table 1 (Refer to figure 3). If A is more than 9 . 15 mm (0.360 in.) for a crack not at 1 2 o'clock i n the hole No.2, contact AIRBUS. 8 After the inspection and the repair, install the fasteners that you pushed back at removal (if necessary). Refer to figure 8 

# • Put in position : Screw Screw**~** 

### Install : 

### 2 N" 

### Item (20) Item (2 1 )
Item (22) SERVICE BULLETIN No. : A310-57-2064 REVISION No. : 02 - Dec 21/07 

### Page: 27 Printed In France = A I RBUS 2007 AD rignls resorved

# I**A310** SERVICE BULLET I N



### NOTE: Item (22) was reta i ned al remova l. 

### (e) For the Inspection Report , refer to Appendix 1 . C. REPA IR 

### (1) Config . 0 1 and Config . 03 (a) Do the applicab le Repa i r I nstruction(s).

DATE : Aug 

### 24f95 Refer to ACCOMPLISHMEN T INSTRUCTIONS paragraph B. ( 1)



### 3 B 11



### 6 1 2 4 

### 2 12 4 

### 3 4 

### 1 2 

### 3 2 2 1 1 1 2 2 

### 7 5 To replace the internal ang l e filling as specified i n Repair Instructi on No .

2 1 R571 1 0257 or Repair Instruction No. 21R57110266, use the necessary 

### parts be l ow: 

### 9. K it 572064A01 ROO, for t he LH side: S h im F itting 

### A5711242720096 A571 1206 120602 b Kit 572064A02ROO, for the RH s i de : Sh i m Fitting 

### A57 1 1242720196 A5711206120S02 

### £ Kit 572064A03R02 , 

### for one s ide (LH o r RH) : Coliar H L7S-12AVW Co ll ar H L87- 1 4 

### Co li ar HL87- 12 

### Co ll ar HL87- 1 6 

### N,t A8NA2532-8 

### N,t ASNA2532-S 

### N,t A8NA2S31-6 

### N,t ASNA2531 - 7 

### N,t ASNA253 1 -8 Bolt Hl112VBJ12 - 1 0 Bolt Hl112VBJ12-14 Bolt HL112VBJ 1 2 - 16 Bolt Hl112VB J1 2 - 17 Bolt Hl112VBJ12-19 Bolt HL1 1 2VBJ12 -20 Boll HL1 1 2VF 1 4-19 Boll ASNA2027T8 -20 Bo l l HL112VF14-20 Bo l l ASNA2027T8-28 Bo l l ASNA2027V6 -27 Bolt ASNA2027V6-20 Bo l l ASNA2027V6-15 Bolt ASNA2027V6-19 Boll ASNA2027T8-23 Bo lt HL112VF14 - 23 Boll HL112VF16-28 SERV ICE BU L LETIN No. : A310-57-2064 REV I S I ON No . : 0 2 - Dec 21/07 Page : 28 Prin ted In F rance IO AIR BU S 2007 Al l ri ghts rese rve d

# A310 SERVIC E B ULL ET I N



### 2 Bo lt 

### ASNA2027T7 ·28 1 Bo [t 

### Hl112VBJ12·27 1 Boll HL112VF16-20 

### 4 Bolt HL112VF16-23

### ~ Kit 572064A04R04, 

### for one side ( LH or R H ) : 

# I 3 Collar HL375·12AVW 

### 4 

### N"I 

### NAS1726·6E B N"I 

### NASl726·8E 2 N"I 

### NAS1727·6E B Collar 

### Hl93·14 11 Co ll ar 

### HL93· 1 2 

### 6 Co llar 

### Hl93-16 4 Bolt 

### H l4 1 2V8J 12
- 10 

### 3 Bolt HL412VBJ12-14 

### 3 Bolt 

### Hl412V8J12-16 1 Bolt 

### Hl41 2V8J12
- 17 

### 3 Bolt 

### Hl4 12VBJ12-20 2 Bolt 

### Hl4 12VBJ12-1 9 2 Boll H L412VF14-19 

### 1 Bol l H L412VF14-20 

### 1 

### Boll NSA54 798V6-27X 1 

### Boll NSA5479BV6·20X 

### 1 

### Screw NSA5479BV6·20X 

### 2 Bo lt 

### NSA54 79BV6-15X 

### 2 Bolt 

### NSA54 798V6-19X 

### 6 Bo l l NSA54 798V8 -23X 

### 5 Bo lt HL41 2VF14·23 

### 1 Bolt H L41 2VF 1 6-28 

### Bolt HL412 V8J12·27 Boll HL412V F16 ·20 

### 4 Boll 

### HL 412VF16 · 23 

# • Kit 572064AOSROO, for o n e s id e (LH or RH) : 

### 3 N"I 

### AS NA2 S32-7 

### 3 N"I 

### NASl727-7E 4 

### N"I 

### NASl726-6E B N"I 

### NASl726
-8E 2 N"I 

### NAS l 727-SE 11 N"I ASNA253 1-7 

### B N " I ASNA2531·8 

### 4 Bo lt ASNA2027V7 ·1 0 

### 3 Bolt ASNA2027V7 ·14 

### 3 Bo lt ASNA2027V7 · 16 

### 1 Bolt ASNA2 0 27V7 ·17 

### 4 Boll ASNA2027V7 ·20 

### 2 Bo lt ASNA2027V7 · 19 

### 2 Boll ASNA2027T8·19 

### 2 Bolt ASNA2027T8·20 Bolt NSA5479BV6·27Y Boll NSA5479BV6·20Y DATE : AU9 24/95 SERV I CE BULLETIN No. : A310·57·2064

RE VISIO N No . : 02 · Dec 21/07 Page: 29**rir1 tc~**  In Franc a CI A I RBUS 2007 AI1 right,**e,erY\! ~** 

### 2 2 1 

### 6 

### 5 Boll Bolt Bolt Boll Boll 

### Boll 

# r$)A310 SERVICE BULLETIN

NSA5479BV6-15Y NSA5479BV6-19Y NSA5479BV8 · 20Y NSA5479BVS-23Y ASNA2027TS-23 ASNA2027V7-27 2 Replace the i nternal angle and install fasteners with high interference fit al some specified holes . Refer to Repair Instruction No. 21R57110257 

### NOTE: Th i s repair is only app l icab l e when there are no cracks and no repa i r bushes i n Ihe holes No . 2 and 3 .**~** Instalilhe shim and the fasteners with h i gh interference fit al some specified holes al rib 1 only. Refer to Repa i r Instruction No. 21 R57110266 NOTE(01) This repair can include the replacement of the internal ang l e fitt i ng when crack is found at the ho l e NO.1. NOTE(02) For th is repair. use the necessary parts of Kit 572064A01ROO 

### for the LH side, of Kit 572064A02ROO for the RH side and of Kit 572064A03R02 thru Kit 572064A06ROO as specified in the Repair Instruction. 4 I nsta ll the repair bushes in the holes No.2 and No . 3 .



### 2 2 Refer to Repai r I nstruction No . 21 R57110260**~** Make the bushes and the washers as specified in the Repair Instruction No. 21 R57110260 . 

### Q Kit 572064A06ROO, for one side (LH or RH) Install the bushes and the washe rs w ith : Boll Not ASNA2027T7·28 ASNA2531·7 (2) Config . 02 (a) Do the applicab l e Repair Instruction(s) .

DATE : Aug 

### 24/95 Refer to ACCOMPLISHMENT I NSTRUCTIONS , paragraph 8 . (2) To rep lace the interna l angle fitling as specified i n Repair Instruction No . 21 R57110259 , use the n ecessary parts be l ow:**~** Kit 572064A01 ROO, for the LH side: Shim F itting A5711242720096 A5711206120602 SERV I CE BULLETIN No . : A310·57·2064 REVISION No . : 02· Dec 

### 21/07 Page : 30 Pr;n ted I n Fra nte C A I RB U S 20 07 Al l ri g hts reserved

# ($)A310 SERV ICE BULLETIN



## !> Kit 572064A02ROO , for the RH s ide : Shim 

### A5711242720196 Fi

tting 

### A5711206120502 £ Kit 572064A03R02, for o n e 

### side (lH or RH ) : 

# I 3 Collar HL75·12AVW 

### 8 Collar HL87 · 14 

### 11 Collar HLB7-12



### 6 Collar HL87-16 

### 1 Nut ASNA2532-B 

### 2 N ut ASNA2532-6 

### 4 N ut ASNA2531-6 

### 2 Nut ASNA2531-7 

### 12 Nut ASNA2531-B 

### 4 Bolt HL 112V8J 1 2-10 

### 3 Bolt HL112V8J12-14 

### 4 Boll HL112VBJ12-16 

### 1 Boll HL112V8J12-17 

### 3 Boll HL112V8J12-19 

### 3 Boll 

### Hl112V8J12-20 2 Boll HL112VF14-19 

### 2 Boll ASNA2027T8-20 

### 1 Boll HL 112VF14-20 

### 1 Bo l l ASNA2027T8-28 

### 1 Bolt ASNA2027V6-27 

### 1 Bo l l ASNA2027V6-20 

### 2 Bo l l ASNA2027V6-15 

### 2 Bo l l ASNA2027V6-19 

### 7 

### Boll ASNA2027TB-23 

### 5 

### Boll Hl112VF14-23 1 Bo l l 

### Hl112VF16-28 2 Bo l l ASNA2027T7·28 

### 1 Bo l l Hl112VBJ12-27 

### 1 Boll 

### Hl112VF16-20 4 Boll 

### Hl112VF16-23



### Q Kit 572064A04R04, 

### fo r one si de (LH or RH) : 

# I Coll ar HL375-12AVW 

### 4 Nut NAS1726-6E 

### 8 Nut NAS1726-8E 

### 2 Nut NAS1727-6E 

### 8 Co ll ar HL93-14 11 Co ll ar HL93-12



### 6 Co ll ar HL93-16 

### 4 Bo lt HL412VBJ12- 10 

### 3 Bo lt HL412VBJ12-14 

### 3 Bo lt HL412VBJ12-16 

### 1 Bolt HL412VBJ12-17 

### 3 Bolt HL412VBJ 12-20 

### 2 Bolt HL4 1 2VBJ12-19 DATE: A u g 

### 24/ 95 SERVICE BULLET I N No. : A310-57-2064 REVISION No. : 02 - De c 2 1107 Pag e: 31 Prin ted in f rance O A I R BU S 2()()7 Al l ri gh l s reserved

### 2 1 1 

### 2 2 6 

### 5

4


### 3 3 4 

### 8 2 11



### 8 4 

### 3 3 4 

### 2 2 2 1 1 

### 2 2 1 

### 6 

### 5 

## ? 

# "-

DATE: Aug 

### 24/95

# A310 SERVICE BULLETIN

Boll HL412VF14 · 19 Boll HL412VF14·20 Bolt NSA5479BV6·27X Bolt NSA5479BV6·20X Screw NSA5479BV8 · 20X Boll . NSA5479BV6·15X Boll NSA5479BV6·19X Bolt NSA5479BV8·23X Bolt HL412VF14·23 Boll HL412VF16·28 Boll HL412VBJ12·27 Bo l l HL412VF16·20 Bolt HL412VF16·23**~** 

### Kit 572064A05ROO, for one side (LH or RH) : 

### N, I ASNA2532·7 

### N,I NAS1727·7E 

### N , I NAS1726·6E 

### N,I NAS1726·8E 

### N,I NAS1727·6E 

### N,I ASNA2531·7 

### N,I ASNA253 1 · 8 Boll ASNA2027V7·10 Bo l l ASNA2027V7·14 Boll ASNA2027V7 ·16 Boll ASNA2027V7 ·17 Bo lt ASNA2027V7·20 Boll ASNA2027V7 ·1 9 Bolt ASNA2027T8·19 Bolt ASNA2027T8·20 Boll NSA5479BV6·27Y Boll NSA5479BV6·20Y Boll NSA5479BV6·15Y Boll NSA5479BV6·19Y Bolt NSA5479BV8-20Y Bolt NSA5479BV8-23Y Boll ASNA2027T8-23 Bolt ASNA2027V7-27 Rep lace th e inlerna l ang le fitting and i nsla ll the bushes in Ihe holes No. 2 and 3. Refer to Repair I nstruction No . 21 R57110259 I nstalilhe repa i r bushes in Ihe holes No.2 and No . 

### 3 . Refer to Repair Instruction No. 21R57110260**~** 

### Make Ihe bushes and Ihe washers as specified i n the Repa i r I nstru ction No. 21 R57110260 . 12. 

### Kit 572064A06ROO , for one s ide (LH or RH) Insta ll the bushes and the washers with: SERV I CE BULLETIN No. : A310 - 57 -2064 REVISION No. : 02 - Dec 21f07 

### Page : 32 P ri nte d in Fran ce**BU S**  2007 Al t**rig~ s**  reserved

# I D. TEST 

### 2 2 Boll 

### No.

# ~A310 SERVICE BULLETIN

ASNA2027T7·28 ASNA2531-7 

### ( 1) Config. 01 thru Config. 03 (a) Job Sel-up 

## 1 Install on the lH side the air distribution dueling on FR40, as shown on the IPC 21-28-03. 

### (b) Test

E. CLOSE UP 

## 1 Do the test after the removal/installation of the access doors 540AB and 640AB 

### (Refer to AMM 28-11-22, Page block 401) . 

## .f. Do the test after removal/installation of the manhole covers 147AZ and 148AZ ( Refe r to AMM 28 - 11 -29, Page block 401).**~** 

### Do a leak check of the air conditioning distribution ducls : 

### 2. Do the pre-cond ition ing through the Low Pressure (LP) ground connect ion (Refer to AMM 12-33-21). 

### Q. Do a check for leaks at the duct co n nections. 

### NOTE: Leaks are nol allowed. 

### f. Stop the pre-conditioning through the lP ground connection (Refer to AMM 12·33·21). 

### Q. Do the fuel system leak test (Refer to AMM 28·25·00, Page block 501). (1) Config. 01 thru Config . 03 (a) Make sure that the work areas are clean and clear of too ls and other items of equipme nt. (b) Close the Krueger panels (RH and LH sides) PN A5784395200000 and PN A5784395200100 on the lower surfaces of the wing as shown on the IPC 57·45·11 . (c) Close the forward cargo compartment door 811, (Refer to AMM 52·30·00, Page block 1) . (d) Install the manhole covers 147AZ and 148AZ, (Refer to AMM 28·11·29, Page block 401 

## J. (e) C lose the access doors 540AB and 640AB on the lower surfaces of the wi ng, (Refer to AMM 28·11·23, Page block 401) . DATE: Aug 

### 24/95 SERVICE BULLETIN No. : A310·57-2064

REVISION No . : 02 • Dec 21/07 

### Page: 33 Prin ted i n France C AtRBUS 2001 All rights reservedPANEL 13 1 VU 131VU 131VU

# A310 SERVICE BULLE TI N

(fl Refuel the fue l tanks (Refer to AMM 12-11-28, Page block 301). 

### (9) Remove the safely clips and lags and close these circuit breakers: DESIGNAT I ON FIN LOCATION VENTllATIONfAVIONICS BLOWER/LO 65HQ 

### 060 

## SPD VEN T I LAT I ON/AVIONICS BLOWER/HI 48HQ 

### 06. 

## SPD VEN T ILA T I ON/AVIONICS BLOWER 49HQ 

### 062 CONTROL 

### (h) Remove the safety clips and tags and close the circuit breakers listed in AMM 28-1 1 -22, Page block 401, AMM 28-11-29, Page block 401 and AMM 28-25-00, Page block 30 1 . 

### {il Close the passenger/crew door (Refer to AMM 52-10-00) . (j) Disconnect t he ai rcraft electrica l ground connection, {Refer to AMM 24-00 -00, Page block 301 

## J. (k) Restore systems and aircraft in norma l operating cond ition. (I) Remove the access platforms. 

### F. DO C U M E NT A

T I O N Write in the applicable aircraft records that you have done all the work given in the Service Bulletin.

DATE: Aug 

### 24f95 SERV ICE BULLETIN No . : A310·57 ·2064

REVISION No . : 02 • Dec 21107 Page : 34 PriOled In France O AIRBUS 2007 Al l rig h l$ reserved

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# A310 SERVICE BULLE T I N

SECTION



## A-A (EXAMPLE OF CRACK fiND I NG)

R

HOLE No . 1 

### o
R

[ VERT ICAL TEE REAR finiNG OF FR 40 FORWARD FITTING OF FA40

• HOLE RADIUS : R

CRACK DEPTH : 0 • CRACI< LENGTH : L

(YOU CAN NOT MEASURE L) USUAlJ.V : L - O A - O+A 

## Hom TO INSPECT



### Figure 2 , Sheet 1 LH SI DE SHOWN HOLE NO .2



### Config. 01 thru 03 : Inspection Areas And Definition Of A 

# t:)B

INTE RNAl ANGLE FlmNG



### DA T E : Aug 24f95 

### SERVICE BUL L ETIN No . : A31O-57-2064 REVISION No. : 02 - Dec 2 1 /07 

### Page: 39

Pnnlcd I n Franco C AIRBUS 2007 All ngnls resc 'vod

# ($JA310 SERVICE BUL LE T IN

TABLE \
DIAMETER OF HOLES No.2 AND No.3 THRESHOLD 

### THRESHOLD I N VERTICAL TEE A31Q-2QO A3 1Q-300(SR) 

### mm in, 

### FC F H FC FH 11.1**~** 0 

### < 12.7 0.437 , 0 

### < 0 ,5 15,100 30,300 14,700 41,300 12.7(0<13 0 .5 , 0 ( 0.512 13,900 27,800 13,500 37,600

13(0< 13.5 0.512 , 0 ( 0 .531 13,600 27,300 13,200 37,200 13.5 (0 <14 0.531 , 0 

### < O .SSI 13,200 26 ,500 12,800 36,100 14 ( 0<14.5 0 .551 , 0 

### < 0 .571 12.800 25,700 12,500 35,000 14.5(0<15 0 .571 , 0 ( 0 .591 12,500 25,000 12,100 34,000

15,0<15.5 0 .591,0 ( 0.610 12,100 24 ,200 11,700 33,000 15 . 5(0<15 0.6 10 , 0 

### < 0 .630 11,700 23 , 500 11,400 32 ,000

16(0<16 .5 0 .630 , 0 

### < 0 .650 11,400 22 ,600 11,000 31,000 16.S( 0< 17 0 .650 , 0 

### < 0 .669 11,000 22.000 10,700 JO,OOO

17,0<17.5 0.669 , D < 0.689 10 ,600 21,300 10.300 29,000 17. 5 , D < 17.8 0.689, D < 0.701 10 ,300 20,600 10 ,000 28 ,000 11.8 , D , 18.2 0.701 , D , 0.717 9 ,900 19,800 9,600 27,000 18.2 < D , 18.5 0.717 < D , 0.728 9.600 19.200 9,300 26.100 18.5<D,19 0.728 < D, 0. 748 9.200 18 ,500 8,900 25,200

19<D,19.5 0 .748 < 0 , 0. 768 6,900 17,800 8,600 24,200 19 ,5<0,20 0.768 < 0 , 0.787 6500 17,100 8 ,300 23,300

NOTE . DO THE SELECTION OF THE AP PLICABLE THRESHOLD ABOVE WHEN YOU REPLACE THE I NTER NAL ANGLE FiniNG. BUT IF YOU MODIFY THE DIAMETER OF THE HOLES NO.2 and NO .3 BETWEEN 2 INSPECTI ONS OF THE H OLE No.1. CONTACT AI RBUS TO ADJUST T H IS THRESHO LD.

Figure 3, Sheet 1 THRESHOLD A311)-300(LA) 

### FC FH 12,800 ",000 11.700 56,700 11.500 57 ,700 11,200 55,000 10,800 54.300 10 ,500 52 .700 10,200 51 , 100 9,900 49 ,600 9,500 46,100 9,300 46,500 9,000 45,000 8,600 43 ,400 8,300 4 1 ,900 8.100 40,500 7,800 39,000 7. 500 37.600 7.200 36.200

Config. 02 : I nspect ion T hres h olds For Hole NO. 1 After Repair As Specified i n 21 R571 1 0259
DATE: Aug 

### 24/95 SERVICE BULLETIN No . : A310-57-2064

REVIS I O N No , : 02 - Dec 21/07 Page: 40 Pri ntnd in Franco C AI RBUS 2007 AU rights reserved

# !$!A310 SERVICE BULLETIN

TABLE 2 DIAMETER OF HO L ES No.2 AND NO .3 THRESHOLD THRESHOLD I N VERTICAL TEE A31O ·200 A310 - S00{SR) 

### mm in. 

### Fe FH Fe FH 11 . 1,0< 12.7 0 .437 " 0 

### < 0. 5 21,400 42,800 20,700 58,300 12.7(0<13 0.5 " 0 

### < 0. 512 19,600 39 ,200 19,000 53,400

13 ( 0<13.5 0.512 , 0 ( 0.531 19.300 38 ,600 18,700 52 ,500 13.5(0<14 0.531 , 0 

### < 0.551 18,700 37 ,400 18,100 50,900

14(0<14 .5 0 .551 " 0 

### < 0.571 18,100 36 ,300 17,600 49.400 14.5 ( 0<15 O.sn " 0 

### < 0.591 17.600 35 ,200 17,100 47,900

15(0<15.5 0.591 , 0 

### < 0.610 17,100 34.200 16 ,600 46,500 15 . 5(0<16 0. 610 , 0 

### < 0 .630 16,600 33.200 16,100 45 , 100

16(0<16.5 0 ,630 " 0 ( 0 ,650 16,000 32,100 15,600 43,700 16.5(0<17 0.650 " 0 

### < 0.669 15,500 31,100 15,100 42 ,300

17,0<17 .5 0.669 , 0 < 0 .669 15,000 30.100 14,600 40.900 17 . 5 , 0 < 17.8 0 .669 , 0 < 0 .701 14,500 29,000 14.100 39,500 17 .8 ' 0 , 18.2 0 .701 , 0,0 .717 14.000 28 ,000 13.600 38.100 18 .2 < 0 , 18.5 0.717 < 0,0.728 13,500 27,100 13.100 36,800 18.5<0 ' 19 0.726 < 0,0 .746 13,000 26,100 12.600 35.500

19<0,19.5 0.746 < 0,0 .768 12.500 25.100 12. 200 34,200 19.5<0 , 20 0 .768 < 0,0 .767 12,100 24,200 11.700 32,900

NOTE : DO THE SELECT ION OF THE APPLICABLE THRESHOLD ABOVE WHEN YOU REPLACE TI-lE INTERNAL ANGLE FITTING . BUT IF YOU MODIFY THE D IAMETEA OF THE HOLES NO.2 and NO.3 BETWEEN 2 INSPECT IONS OF THE HOLE No . 1 , CONTACT AIRBUS TO ADJUST THIS TI-lAESHOLD.



### Figure 4, Sheet 1 THRESHOLD A310 - 300(t.R) 

### Fe FH 18 ,000 90,400 16 , 500 82.BOO 16,200 81,400 15,800 79,000 15,300 76,700 14. 800 74,400 14 ,400 72,200 14,000 70,000 1 3,500 67,800 13 . 100 65,700 12,700 63,500 12. 200 61,300 11,800 59,200**11,~OO** 57,100 11.000 55,100 10,600 53, 1 00 10.200 51 , 100



### Config . 01 and 03 : Inspection Thresholds For Hole No.1 After Repair As Specified in 21R571 1 0266 (Config . 01 and Config. 03) DA T E: Aug 

### 24195 SERVICE BULLET I N No. : A310-57-2064 REVISION No. : 02 - Dec 21/07 Page: 41 Pr i nled I n Fran ce Cl A 1RBUS 2007 All M gh lS res erved

# ($;A310 SERVICE BULLETIN

TABLE 3 DIAMETER OF HOLES No.2 AND NO.3 THRESHOLD THRESHOLD I N VERTICAL TEE A31o-2DO A31o-300{SR) 

### mm i n. 

### FC FH FC FH 11 . 1,0 ( 12.7 0.437 .. 0 

### < 0.5 15,100 30 ,300 14,700 41,300 12.7 .. 0 

### < 13 O .S .. 0 ( 0.512 19.500 39 , 100 18,900 53 ,200 13 (0<13.5 0.512 .. 0 

### < 0.531 2!J,300 40,700 19,700 55,500 13 .5(0<14 0.53 1 , 0 ( O.SSI 21.100 43 .500 21.100 59,200

14 , 0<14 . 5 0 . 551 .. 0 ( 0 .571 23.100 46 ,200 22,400 62,900 14,5(0<15 0 . 571 .. 0 ( 0 .591 24 ,200 48 ,500 23,500 66,000

15,0<15.5 0.591 .. 0 

### < 0.610 25 ,000 SO,l00 24,300 68.100 15 .5(0<16 0.610 , 0 ( 0 .630 25 ,800 51 ,600 25 ,000 70,300

16(0<16. 5 0.630 , 0 ( 0 .650 26 .500 53 .000 25,700 72,200 16. 5(0<17 0 .650 " 0 ( 0.669 26.BOO 53 ,700 26 .000 73 , 100

17, 0 <17.5 0 .669 , 0 ( 0.689 27,100 

# " . 300 26 .300 13,900 17 . 5,0< 17.8 0 .689,0< 0 .701 27,500 55 ,000 26 .700 74 ,800 17 .8,0, 18.2 0.701, 0 ,0.717 27 .800 55.600 27,000 75.700 18.2 < 0 , 18.5 0.7 17 < 0 ,0.728 26.900 53.900 26.100 73.400 18.5< 0 '1 9 0 ,728 < 0 , 0 ,748 26, 1 00 52 .200 25 ,300 71.000 19<0,19 .5 0 .74B < 0,0.768 25,200 SO .5OO 24,SOO 68,7 00 1 9.5<0(20 0.768 < 0,0.787 24,300 48 ,700 23 . 600 66.300

NOTE : THE THRESHO L D SPECtFtED tN TH IS TABLE ARE G IVEN FROM THE CRACK REPAJR IN THE HO LES NO . 2 AND No . 3 ,



### Figu re 5, Sheet 1 

### THRESHOLD A31Q.300(LR) 

### FC FH 12 ,800 

# ".000 16,500 62,500 17,200 66,000 18,300 9 1 .800 19,500 97,600 20.400 102,400 21 , 100 105 ,700 21 , 800 109,000 ,,>00 111 ,900 22.600 113.300 22,900 114,700 23,200 116,000 23.400 11 7,400 22,700 11 3,800 22.000 110,100 21,300 106,500 20,500 102.900



### Config , 01 thru 03 : Inspection Thresho lds For Holes No .2 And No . 3 After Repair As Specified in 21 R57110259 

### andlor 21 R57110260 DATE : Aug 

### 24195 SERVICE BULLETIN No .: A3 1 0 · 57 · 2064

REVISION N o. : 02 - Dec 21107 Page: 42 Printed i n France C A I RBUS 2001 All rlghll rCSO 'V1td

# ($) A310 SERVICE BULLETIN

TABLE 4 DIAMETER OF HOLES No.2 AND No.3 INTERVAL INTERVAL IN VERTICAL TEE A3H}200 A31o-300(SR) 

### mm in. 

### FC FH FC FH 11 .1 

### <: D 

### < 12.7 0.437 

### <: 0 ( 0 . 5 3,700 7,400 2.050 5,650 12 .7 

### <: 0 (13 0 .5 <: 0 

### < 0 . 512 3 ,600 7 ,200 2,000 5,650

13 (0<13 .5 0 .512 

### <: 0 

### <0 .531 3,400 6,850 ',900 5,400 13 . 5(0<14 0.531 

### <: 0 

### < 0.551 3,300 6,600 ',850 5,200

14(0<14.5 0 .551 

### <: 0 ( 0.571 3,150 6,300 1,750 4,950 14.5(0<15 0 .57 1 

### <: 0 

### < 0 .591 

### 3.000 6,000 1,700 4,750

15 ,0<15.5 0.591 

### <: 0 

### < 0 .610 2,900 5,800 

## '.600 4,550 15 . 5,0<16 0.610 

### <: 0 ( 0 .630 2 ,750 5.550 

# '."" 4,400

16(0<16.5 0.630 

### <: 0 ( 0 .650 2,650 5.350 ',500 4,200 16. 5(0<17 0.650 , 0 

### < 0 .669 2,"" 5,100 

### ,,,00 4.050

17(0<17.5 0.669 " 0 ( 0.689 2,450 ',900 ',350 3 .850 17.5" 0 

### < 17.8 0.689 , 0 ( 0.701 2,400 4 ,800 1,350 3,750 17.8 , D , 18.2 0.701' D ( 0.717 2,350 4,700 ',300 3,700 18.2 

### < D , 18.5 0.717 

### < D, 0.728 2 ,250 

## '.500 1,250 3.550 18.5 <D ( 19 0.728 

### < D, 0.748 2,150 4 ,300 ',200 3,400

19<D ( 19.5 0.748 

### < D, 0.768 2,050 4,150 1,150 3,250 19.5<D(20 0.768 

### < 0,0.787 2.000 ',000 1.100 3.150

NOTE: THE INTERVALS SPECIFIED IN TH IS TAS LE ARE APPLICASLE WHEN THE CRACK I N TH E HOLE No .2 (CRACK AT 12 O·CLOCK) IS NOT REMOVED .



### Figure 6, Sheet 1 INTERVAL A31Q-300(LfI) 

### FC FH 1,700 B.650 1,650 B,350 ',600 B,OOO ',500 7,650 1,450 7,350 1,400 7,000 '.350 6,750 1,300 6,500 1,200 6,200 1,150 5,950 1,100 5,700 1,100 5,550 1,100 5,500 1,050 5,250 ',000 5,000 950 4,850 900 4.650



### Config. 01 thru 03 : Inspection Intervals For Holes No . 2 And No.3 After Permitted Damage In The Ho le No.2
DATE : Aug 

### 24/95 SERVICE BULLETIN No. : A310 -57-2064

REVISION No .: 02 - Dec 21/07 

### Page: 43 Pr inted I n Franco Ie AIRBU S 2007 A ll rig hts reserved

# $ A310 SERVICE BULLE T IN

TABLE 5 DIAMETER OF HO LES No.2 AND No.3 IN T ERVAl I NTERVAL INTERVAL IN VEATICAL TEE A3,Q-200 A31o-300(SA) A31Q-300(LR) 

### mm in. 

### FC FH FC FH FC FH 11. 1 " 0 

### < 12.7 0.437 " 0 

### < 0.5 8 ,750 17,550 

## s.e00 16.300 4,800 24 ,050 12.7 (0<13 O.S " 0 

### < 0 . 512 8 ,200 16,400 5,400 15.200 4,450 22,450

13(0<13 .5 0.5 12 " 0 

### < 0.531 8 ,0 50 16 ,150 5,350 15,000 4,400 22,150 13 .5(0<14 0 .531 " 0 

### < O,SSI 7 ,900 lS ,BOO 5,200 14.700 4,300 21,650

14 (0< 14 .5 0 .551 " 0 

### < 0,571 7,700 15,450 5,100 14.350 4,200 21,150 14. 5(0<15 0 .571 " 0 

### < 0,591 7 ,550 lS ,I00 

### 5.000 14,000 4 , 100 20,650

15 (0<1 5.5 0.591 " 0 

### < 0 .610 7,350 14,750 ' ,650 13.700 ' ,000 20,150 15 .5 (0<16 0 .610 " 0 

### < 0 .630 7 ,200 14 ,400 4 ,750 13 ,350 3 ,900 19,700

16(0<16.5 0.630 .. 0 ( 0.650 7 ,000 14 ,000 ' ,650 13 ,050 3.800 19,200 16. 5(0<17 0.650 .. 0 ( 0.669 

### 6.800 13,650 

## •.soo 12.700 3,700 16,700

17 ( 0 < 17.5 0 .669 .. 0 

### < 0 .689 6 ,&sO 13 ,300 4 ,400 12,350 3,650 18,250 17 . S .. 0 

### < 17 . 8 0 .669 .. 0 < 0.70\ 6 ,450 12,950 4 ,300 12,050 3,550 17 ,750 17 .8 , 0 , 18.2 0.701 , 0 ( 0.717 6 ,300 1 2,600 4,150 11 ,700 3,450 17.300 18 .2 < 0 ( 18 .5 0.717 < 0 ( 0.728 6,150 12,300 4 ,050 11,400 3,350 16.800 18,5<0 ( 19 0.726 < 0 .. 0 .748 5 ,950 11.950 3,950 11 , 100 3.250 16.350

19<0,19 .5 0.748 < 0 , 0 .768 5,800 11.600 3,650 10.750 3 .150 15.900 19.5<0,20 0.768 < 0 , 0 .787 5 ,600 11.250 3.700 10.450 3,050 15,400



### Fi gure 7, Shee t 1 Config. 01 thru 03 : Inspection In l ervals Fo r The Hole No.1
DATE : Aug 

### 24/95 SERVICE BULLETIN No . : A310-57-2064

REVISION No . : 02 - Dec 21107 Page: 44 Printed In F ran"" Cl AtRBUS 2001 All righ ts reserve d

## (20) (22 ) (2 1) (22 ) c 

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FR40

# A310 SERV ICE BULLETIN

FWD CARGO COMPARTMENT lH SIDE - VIEW LOOKING AFT



### - -----f'-- -

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### o@ If)@ @

Figure 8, Sheet 1 (J)



### Contig . 01 Ih ru 03 : Fasteners To Push Back For Access 

## " 

# I

DATE: Aug 

### 24/95 SERVICE BU LLETIN No . : A310 -57-2064

REVIS I ON No. : 02 - Dec 2 1/07 

### Page : 45 Printed i n France**RBUS** 2007 AI ri ghts reserved

# A310 SERV I CE BULLE T I N



### Th is Page I nte ntiona ll y Le ft B la n k



### DA T E : Aug 

### 24/ 95 SERVI C E BU LL E T IN No . : A310 - 57 -2064 REV I SIO N No. : 02 - Dec 211 0 7 

### Page: 46 Prin l ed in fr ance CI AIR8US 2007 A ll rig hl s raservOd

### AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellante 31707 BLAGNAC CEDEX FRANCE 

### Tel : (33) 5 61 93 33 33 Telex: AIRBU 530526F 

### Fax: (33) 5 61 93 42 51 ATA SYSTEM : 57

# ~A310 SERV I CE BULLETIN 

### AP P ENDIX 1

TITLE: FUSELAGE - FR40 - INSPECT UPPER CORNER FITTING. MODIFICATION No. : None 

### 1. INSPECTION REPORT The results of th e i nspection, incl uding no findings, replacement or actions to be done, must be forwarded to A I RBUS Department SEE81, on the attached inspection report sheet.



### DATE: Aug 

### 24/ 95 SERV I CE BULLET I N No . : A310-S7-2064 REVIS I ON No . : 0 2 - Dec 21 / 07 

### Page : 1

Prin te d I n Fra nco lC> AIRBUS 2007 All n ghls roserve d

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# " ($;A310 SERVICE BULLETIN REPORTING SHEET

TITLE: FUSELAGE· FR40 • INSPECT UPPER CORNER FITTING. MODIFICATION No. : None Please complete the appropriate item (A or B) : 

### A - S8 W I LL BE embodied ... .......... . .. .. .. .. .. .. . .. .. ................ . .. .... . YES/NO (if 

### NO p lease comment) If YES, aircraft concerned (as per S8 effectivity by default) and planned dales (month/year) of embodiemeni:
B - S8 HAS BEEN embodied on aircraft: Operator comments: .................. "' ............. .. From Airline: .... NamefTitle: . Signature: .. 

### Dale : ............. . . .. .. .. .. ... .. ... . If operat i onal documentation is affected (see 

### Paragraph 1 . K of this S8): If information is needed prior to next 

### normal revision 

### or prior to S8 embodiment, p lease indicate required service(s): Either : Advance data . ... . ..... ...... .. . ....... . ... . ... . .. . .. .. ...... . .... ....... YES/NO Or : Inte rmediatefTemporary revision. . ........ . ... . . . .... .................. YES/NO Importan t Informat ion: This S8 will on ly be i ncorporated in your maintenance and operational documentation if this sheet is returned to Airbus and signed by a duly authorised representative . With the next feas i ble revision, this wi ll result in

- updating of maintenance documentation to show pre and post S8 data .

- updating of maintenance and operational documentation to show post SB data after embodiment. If th is SB requires previous or simultaneous accomplishment of other SBs , Airbus shall automatically include them in the manual revis ions. Refer to SIL 00-037 for detai led information . Please return this completed sheet to : AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn : SDC32 Technica l Data and Documentation Services FAX: (+33) 5 61 932806 e-mail: sb.reporting@airbus.com Or via your Resident Customer Support Office. Alternative ly, S8 lists via letters or fax are also accepted.

DATE: Aug 24/95 SERVICE BULLETIN No. : A310-57-2064

REVISION No . : 02 - Dec 21107 

### Page:1of1**rio ~d**  In Franca O A I RBUS 2007 All**righ~** reserve<.!

# A310 SERVICE BULLE T IN REPORTING QUALITY

TITLE : FUSELAGE - FR40 - INSPECT UPPER CORNER FITTING . MODIFICATION No . : None Use th is form to te ll us what is your perception of Ihe qua l ity of th is Service B ulietin .The repor ted da ta t hat you provide us will be used to analyse areas of d ifficulties and to lake corrective action to futher improve I he qua l ity 

### of our Service Bulletins . We thank you for the lime you have taken in completing this form . 

### (Please rate on a scale of 1 to 4, with 4 being Ih e highest score) -Quali ty rating of this S8

- Quali ty ra t ing of Ihe Accomplis h me nt Ins truct ions

- Quality rating of the Illustrations -I s this 58 easy to understand? 

### 432 432 4 32 YIN If 

### you have had difficulties in I he a ccomplishment of this 56 please quote be low t he area(s) a nd give a short description of the issue .

Plan n i ng X Effec livi l y X Reason X Manpower X References X Publi cation Commen ts:

Operator : NamefTiUe : Ma terial X Kit Co nte nt X lisl of Malerials

Opera tor Suppl ied X Re-identificat ion X T ooling

Please re l u r n this form to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rand Point Maurice Bell a nte 3 1707 BLAGNAC CEDEX FRANCE Alln : SEM4 Service Bulle tins Management FAX : (1-33) 5 61 93425 1 Or via your Res id e nt Customer Support Office . I ns lructions X Preparation X Mod /lnspecli o n X T es l X Close-up X Illustrat ions

Date :

DA TE : Aug 

### 24/95 SERVICE BUL L ETIN No . : A3 1 0-57-206 4 REV ISIO N No . : 02 - Dec 2 1/07 Page:lof l Prin ted I n**Fra~ce** C AlRBUS 200 7 Ali**rig ~** **r(!,~ vcd**