AIRBUS 

ISiA310 

SERVICE BULLETIN 

REVISION TRANSMITTAL SHEET 

CUSTOMER SERVICES DIRECTORATE 

1 Rand Point Maurice 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 

MANDATORY MANDATORY 

TITLE : FUSELAGE· FR40 - INSPECT UPPER CORNER FITTING. 

MODIFICATION No. : None 

Th is page transmits Revision No. 02 of Service Bulletin No. A310-57-2064. 

ADDITIONAL WORK 

MANDATORY 

No additional work is required by this revision for aircraft modified by any previous issue. 

REASON 

Revision No. 02 issued to : 

Update inspection thresholds and intervals. 

Update Kits 572064A03 and 572084A04. 

Improve Noles in INSPECTION Paragraph 3.B. 

Review of flow charI. 

CHANGES 

SUMMARY: 

- REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES 

Text modified. 

EFFECTIVITY 

Operators NGA, RME and THA deleted. Operators updated. 

MANPOWER 

16.0 TOTAL MANHOURS becomes 17.0 and 12.0 ELAPSED TI ME hours becomes 13.0 for 

inspection. 

PLANNING INFORMATION : 

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

REVISION No. : 02 - Dec 21 /07 Page:lof3 

Printed in Franoll Q AIRBUS 2007 All nghts teserved 
• EFFECTIVITY 

($) A310 

SERVICE BULLETIN 

REVISION TRANSMITTAL SHEET 

Para. 1.A. Aircraft model 310-221 deleted. Operator NGA, aircraft MSN 0285 and 0340 deleted. 

Operator RME, aircraft MSN 0276 deleted. Operator THA, aircraft MSN 0424 deleted. Aircraft 

MSN 0442 deleted for operator AFL. Aircraft MSN 0504 deleted for operator AFR. Aircraft MSN 

0392 deleted for operator Ale. Aircraft MSN 0311 deleted for operator CNW. Aircraft MSN 0300 

and 0352 deleted for operator GYP. Aircraft 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 operator MEA. Aircraft MSN 0409 deleted for operator OAS. Aircraft MSN 

0295 and 0306 deleted for operator RJA. Aircraft MSN 0432, 0435 and 0440 deleted for operator 

ROY. Aircraft MSN 0363, 0433, 0493 and 0570 deleted for operator SIA. Aircraft MSN 0404 and 

0412 deleted for operator SWR. Effectivity updated. 

REASON 

Para. 1.C. Text modified. 

- COMPLIANCE 

Para. 1.E. Inspection thresholds and intervals updated. 

- MANPOWER 

Para. 1.G. 16.0 TOTAL MANHOURS becomes 17.0 and 12.0 ELAPSED TIME 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. 

PUBLICATIONS AFFECTED 

Para. 1.K. Reference MPD 57-10-25 added. 

MATERIAL INFORMATION: 

MATERIAL - PRICE AND AVAILABILITY 

Para. 2.A. Address updated. Prices and calendar days added for all kits. 

LIST OF COMPONENTS 

Para. 2.C. HL75-12 becomes HL75-12AVW in Kit 572064A03. HL375-12 becomes HL375-12AVW 

in Kit 572064A04. 

ACCOMPLISHMENT INSTRUCTIONS : 

GENERAL 

Para. 3.A. CAUTION added. 

PREPARATION 

DATE : Aug 24/95 

REVISION No. : 02 - Dec 21/07 

SERVICE BULLETIN No. : A310-57-2064 

Page : 2 

Printed in Francc Cl AtRBUS 2007 All rights rClcrvod 
A310 

SERVICE BULLETIN 

REVISION TRANSMITTAL SHEET 

Para. 3.A.(1) Step deleted. Steps added. 

INSPECTION 

Para. 3.8. Noles added. Notes modified. Steps added. Steps updated. 

REPAIR 

Para. 3.e. PN modified in Kits 572064A03 and 572064A04. 

TEST 

Para. 3.D. Job Set·up modified. Leak lest and replenishing of the fuellanks deleted. Test of 

manhole covers and access doors added, Leak lesl of air ducts added. 

CLOSE-UP 

Para. 3.E. Steps (d) to (il added. Step deleted 

ILLUSTRATIONS 

Figures 1, 3, 4, 5, 6 and 7 modified . 

NOTE: Layout changes due 10 computerization of this revision are not identified. 

FILING INSTRUCTIONS 

This Service Bulletin has been generated electronically and is reissued as a complete document. 

Replace the complete document. 

Put this Revision Transmittal Sheet in front of the Service Bulletin. 

HISTORY OF PREVIOUS REVISIONS 

Revision No. 01 issued to add Airworthiness Directive (Consigne de Navigabilile) No. 92-106-132(B) 

and aircraft post Service Bulletin No. A310-57-2067 (Mod. No. 11352S21172) and post Mod. No. 

11353S21173. Also, this revision is issued 10 update the inspection and repair actions. 

REVISION SEQUENCE 

ORIGINAL : Aug 24/95 

REVISION No. : 01 - Jan 05/01 

REVISION No. : 02 - Dec 21/07 

DATE : Aug 24/95 

REVISION No. : 02 - Dec 21107 

SERVICE BULLETIN No. : A310-S7-2064 

Page : 3 

Printed jn France 0 AIRBUS 2007 AS righl$ reservod 

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 BULLETIN 

SUMMARY 

This summary is for information only and is 

not approved for modification of the aircraft 

MANDATORY MANDATORY MANDATORY 

ATA SYSTEM : 57 

TITLE : FUSELAGE· FR40 • INSPECT UPPER CORNER FiniNG. 

MODIFICATION No. : None 

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES 

MANDATORY 

During inspections as per Maintenance Review Board (MRS) Structural Significant lIem (581) 57.10.25, two 

operators have reported cracks initialing from fastener holes located at the upper corner ang le at frame 40. 

The cracks were discovered on A310-200 alrcratl at 17,800 and 24,000 Flight Cycles (FC). 

I As a result of the in-service reports, the MRB program rules require that the inspection now has to be 

performed on all A310 aircratl. This Inspection Service Bulletin therefore supersedes MRB SSI 57.10.25. 

Cracks, if they remain undetected, could lead to extensive and time consuming repairs. 

This Inspection Service Bulletin is rendered mandatory by Airworthiness Directive (AD). 

Before release, this Service Bulletin has been va lidated by AIRBUS on aircratl MSN 0427. 

This Inspection Service Bulletin requires an eddy current inspection of the internal angle filling and the 

vertical tee at frame 40 on the LH and RH sides. 

This inspection will make it possible to detect crack propagation at an ea rly stage, thus avoiding an expensive 

repair. 

I This Inspection Service Bulletin has been modified in the frame of the A310 aircraft Extended Service 

Goal study. 

EVALUATION TABLE 

COMPLIANCE Mandatory CANCELS INSPECTION SB No 

AD Yes AlC OPERATION AFFECTED No 

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

REVISION No. : 02 - Dec 21 /07 Page:1of5 

Printed in France Cl AIRBUS 2007 Al l rights reserved 
EVALUATION TABLE 

RELIABILITY AFFECTED 

COST SAVING 

STRUCTURAL LIFE EXTN 

KIT 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 R1T RJA ROT RZO S81 SGX SUD TAP THY TSC UAE UZB WHT 

CONCURRENT REQUIREMEN TS 

None 

REFERENCESIREPERCUSSIONS 

TFU : 57.10.00.005 

aEB : None 

AaT : None 

SIL : None 

LIFE LIMIT : None 

LINE MAINTENANCE AFFECTED : No 

OTHERS : None 

NATURE OF THE WORK 

AIRCRAFT : YES 

eQUIPMENT : NO 

HARD : NO 

SOFT : NO 

OBRM: NO 

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

REVISION No. : 02 - Dec 21/07 Page: 2 

Printed in Fr~ oca CI AIRBUS 2007 All rig ts reserV\!d 
MANPOWER 

Config. 01 Ihru Config. 03 , for inspection 

TOTAL MAN HOURS 

($;A310 

SERVICE BULLETIN 

SUMMARY 

ELAPSED TIME (HOURS) 

17.0 

13.0 

Config. 01 Ihru Config. 03 , for repair (Replacement of the internal angle tilling as specified in Repair 

Instruction No. 21R57110257 or No. 21R57110259 or No. 21R571 10266, on one side) 

TOTAL MAN HOURS 80.0 

ELAPSED TIME (HOURS) 40.0 

Config. 01 thru Config. 03 . for repair (Installation of the bushes in holes No.2 and 3 as specified in Repair 

Instruction No. 21 R5711 0260, on one side) 

TOTAL MAN HOURS 30.0 

ELAPSED TIME (HOURS) 15.0 

Config. 01 thru Config. 03 , for repair (Installation of the fasteners with high interference fit at rib 1 as 

specified in Repair Instruction No. 21 R57110266) 

TOTAL MAN HOURS 

ELAPSED TIME (HOURS) 

MATERIAL INFORMATION 

AIRCRAFT DATA 

Config. 01 thru Config. 03 , (if repair) 

Kit 572064A01ROO 

Internal angle fittings 

Kit 572064A02ROO 

Internal angle fittings 

Kit 572064A03R02 

Bolts, nuts, collar 

Kit 572064A04R04 

DATE: Aug 24/95 

REVISION No, : 02 - Dec 21107 

30.0 

15.0 

SERVICE BULLETIN No. : A310-57-2064 

Page: 3 

Prirl lod ~ Franco O AIRBUS 2007 All righl$ reserved 
Bolls, nuts, collar 

Kit 572064AOSROO 

Bolls, nuts 

Kit 572064A06ROO 

Bolt, nul 

APPENDICES 

Appendix 1 • Inspection Report 

DATE : Aug 24/95 

A310 

SERVICE BULLETIN 

SUMMARY 

SERVICE BULLETIN No. : A310-S7-2064 

REVISION No.: 02 - Dec 21/07 Page: 4 

Printed In 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 In Franc;e Cl AIRBUS 2007 All nghts rOSONQO 

AIRBUS 

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 

This document contains AIRBUS PROPRIETARY INFORMATION and sha ll a\ all limes remain the properly 

of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information 

contained in it. It is delivered on the express condition that said document and the information contained in 

it shall be treated as confidential, sha ll not be used for any purpose other than that for which it is hereby 

delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any 

manner (except for the purposes of performing the tasks described hereunder and provided that any recipient 

of such document shall comply with the conditions herein). without AIRBUS' 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) Aircraft 

(a) Effectivlly by MSN 

This Service Bulletin is applicable to aircraft MSN : 

01620191 0201 0217 0224 0230 0233 0237 0241 024502480251 025402570260 

02640267027302780281028302880291 0293029703030309031303160318 

032003260331 0333033503380339 0342034303450346034903530355-0357 

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 0697 

0698 0700 0702 0704 0706 

(b) Effectivity by Operator 

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

REVISION No.: 02 - Dec 21 /07 Page : 1 of 46 

Printed in FranclI CI AIRBUS 2007 All rights reserved 
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 information available to AIRBUS. Any future 

changes resulting from transfer of an aircraft from one operator to another will not be 

reflected in this list unless the Service Bulletin is revised for another reason. 

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 

Printed in Franoe 10 AtRBUS 2007 All rights 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 0661 

581 04270430045304680475048604870520 

SGX 05190562 

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 

WHT 0448 

(el Effectivity by MSN and KiUConfiguralion 

DATE ; Aug 24/95 

The Kits and configurations applicable to these MSNs are given al the end of this list 

016201910201 021702240230023302370241024502480251025402570260 

02640267027302780281 028302880291 0293029703030309031303160318 

SERVICE BULLETIN No. : A310-57-2064 

REVISION No. : 02 - Dec 21/07 Page : 3 

Printed in France C'J AIRBUS 2007 Alt righ ts resofV<ld 
~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 CONFIGURATION 

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 internal angle fitting as specified in Repair Instruction No. 

21 R57110257 or No. 21 R57110259 or No. 21R57110266. 

NOTE(02) Kit 572064A02ROO includes the parts necessary for the replacement 

of the RH internal angle fitting as specified in Repair Instruction No. 

21R57110257 or No. 21R57110259 or No. 21R57110266. 

NOTE(03) Kit 572064A03R02 includes the hardware necessary for the replacement 

of the LH or the RH internal angle filling (one Kit per side). This 

hardware, which concerns Repair Instruction No. 21R57110257 or No. 

21R57110259 or No. 21 R57110266, is applicable to the removed 

fasteners at 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 internal 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 BULLETIN No. : A310-57-2064 

REVISION No. : 02 - Dec 21f07 Page : 4 

Printed in Franoll Cl AtRBUS 2007 All ri9hts rc 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 

fasteners at the second oversize (hardware identified (el in the parts 

lists 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). 

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(01) 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 necessary 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 internal 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 the removed 

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

REVISION No. : 02 - Dec 21/07 Page: 5 

Printed In france C AIRBUS 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 replacement 

of the LH or the RH internal angle fitling (one Kit per side). This 

hardware, which concerns Repair Instruction 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) Kit 572064A06ROO includes the hardware 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 

0700 

KIT No. QTY PER AlC CONFIGURATION 

572064A01 ROO 02 

572064A02ROO 02 

572064A03R02 2 02 

572064A04R04 2 02 

572064A05ROO 2 02 

572064A06ROO 2 02 

NOTE(01) Kit 572064A01ROO includes the parts necessary for the replacement 

of the LH internal angle fitting as specified in Repair Instruction No. 

21R57110257 or No. 21 R57110259 or No. 21 R57110266. 

NOTE(02) Kit 572064A02ROO includes the parts necessary for the replacement 

of the RH internal angle fitling as specified in Repa ir Instruction No. 

21R5711 0257 or No. 21R57110259 or No. 21R57110266. 

NOTE(03) Kit 572064A03R02 includes the hardware necessary for the replacement 

of the LH or the RH internal angle fitting (one Kit per side). This 

hardware, which concerns Repa ir Instruction No, 21R571 10257 or No. 

21 R57110259 or No, 21 R57110266, is applicable to the removed 

fasteners at 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 internal angle fitling (one Kit per side), This 

hardware, wh ich concerns Repair Instruction No. 21R57110257 or No. 

21 R57110259 or No. 21 R57110266, is applicable to the removed 

fasteners at the first oversize (hardware identified (b) in the parts lists of 

the Repair Instructions), 

DATE: Aug 24195 SERVICE BULLETIN No. : A310-57-2064 

REVISION No. : 02 - Dec 21107 Page ; 6 

Printed in France = AIRBUS 2007 All riQhts reserved 
I 

~A310 

SERVICE BULLETIN 

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

of the LH or the RH internal angle fitting (one Kit per side). This 

hardware, which concerns Repair Instruction No. 21R57110257 or No. 

21 R57110259 or No. 21 R57110266, is applicable to the removed 

fasteners at the second oversize (hardware identified (el in the paris 

lisls 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 valid 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. This 

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 FITTING (PRODUCTION SOLUTION» is embodied. This 

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 reports, 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 undetected, could lead to extensive and time consuming repairs. 

This Inspection Service Bulletin is rendered mandatory by Airworthiness Directive (AD). 

Before release, this Service 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 

This Inspection Service Bulletin requires an eddy current inspection of the internal angle 

filling and the vertical tee al frame 40 on the LH and RH sides. 

Advantages 

This inspection will make it possible to detect crack propagation a\ an early stage. thus 

avoiding an expensive repair. 

This Inspection Service Bulletin has been modified in 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) INSPECTION 

(a) Config. 01 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 Aviation 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 thresholds 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 

Table A 

Thresholds in relation with aircraft configuration 

Aircraft configuration Th resholds 

A310-200 (see Note (01)) Config. 01 15, 100 Fe/3D,30D FH 

A310-300 (SR) (see Notes (02) and (03)) Config. 01 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 18,000 FC190,400 FH 

Table B 

Intervals for subsequent inspection after no crack finding or after repair 

Aircraft configuration Intervals 

A310-200 (see Note (01)) 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 

NOTE: This Service Bulletin is required at the given thresholds and intervals in Flight 

Cycles (FC) or Flight Hours (FH) whichever occurs firsl. 

NOTE(01) The A31 0-200 aircraft type concerns aircraft models 310-203, 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 310-325. 

NOTE(03) For Average Flight Time (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 optimized at AFT=3.23 FHfFC for threshold 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, the first inspection is to be 

performed within 1,500 FC/3,100 FH after 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 BULLETIN No. : A310-S7-2064 

REVISION No. : 02 - Dec 21/07 Page : 9 

Printed in Fran<:\! Cl AIRBUS 2007 All rights reser""d 
I 

I 

F. APPROVAL 

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 Service 

Bulletin without exceeding the value of the previous revision of this Inspection 

Service Bulletin. 

If aircraft have exceeded the threshold by more than 1,200 Fe or 3,600 FH, the 

first inspection is to be performed within 600 Fell,BOO FH after receipt of this 

Inspection Service Bulletin. 

For A310-300 Long Range (lR) aircraft: 

For aircraft which have performed 1,000 Fe or 5,300 FH below the threshold 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 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 1,000 FC or 5,300 FH, the 

first inspection is to be periormed within 500 FC/2,650 FH after receipt of this 

Inspection Service Bulletin. 

Approved under EASA Design Organization Approval No. EASA 21J.031. 

If an aircrafllisted in the effectivity has a modification or repair embodied thai is not of AIRBUS 

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 incorporation 

of the Service Bulletin. 

G. MANPOWER 

The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the 

work. These estimates assume that the work will be done by experienced personnel. and may 

need to be revised upwards to suit operator's circumstances. The estimates do not include the 

time to prepare, plan or inspect the work. Manufacture and procurement of parts and lools, drying 

times for paints, sealants, etc, and general administration work are also not included. 

Config. 01 thru Config. 03 , for inspection 

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 SERVICE BULLETIN No. : A3 10-57-2064 

REVISION No. : 02 - Dec 21107 Page: 10 

Printed in France ICI AIRBUS 2007 AU ri9~ ts ",served 
I 

($;A310 

SERVICE BULLETIN 

ELAPSED TIME (HOURS) 13.0 

Config. 01 thru Config. 03, for repair (Replacement of the internal angle filting as specified in 

Repair Instruction No. 21 R5711 0257 or No. 21 R5711 0259 or No. 21 R57 110266, on one side) 

Replacement of internal angle filling 80.0 

TOTAL MANHOURS 80.0 

ELAPSED TIME (HOURS) 40.0 

Config. 01 Ihru Config. 03 , for repair (Installation of the bushes in holes NO. 2 and 3 as specified 

in Repa ir Instruction No. 21R57 110260, on one side) 

Installation of the bushes 30.0 

TOTAL MAN HOURS 30.0 

ELAPSED TIME (HOURS) 15.0 

Config. 01 thru Config, 03 , for repair (Installation of the fasteners with high interference fit al rib 1 

as specified in Repair Instruction No. 21RS7 11 0266) 

Inslal lal ion of the fasteners 

TOTAL MAN HOURS 

ELAPSED TIME (HOURS) 

H. WEIGHT AND BALANCE 

Not changed 

J. ELECTRICAL LOAD DATA 

Not changed 

J. REFERENCES 

Aircraft Maintenance Manual (AMM) 

Consumable Material list (CML) 

Elec. Std. Practices Manual (ESPM) 

Illustrated Parts Catalog (IPC) 

Non destructive Testing Manual (NTM) 

Standards Manual (SM) 

DATE : Aug 24f95 

REVISION No. : 02 - Dec 21/07 

30.0 

30.0 

15.0 

: 12-11-28 12-33-21 24-00-00 24-41-00 

28-00-00 28-10-00 28-11-22 28-11-29 

28-25-0052-10-0052-30-00 

: 20-55-00 

: 21-28-0357-45-1 1 

: 51-10-0857-10-25 

SERVICE BULLETIN No. : A3 10-57-2064 

Page : l1 

Printed In France 10 AIRBUS 2007 All rights re rve<l 
I 

($!A310 

SERVICE BULLETIN 

Structural Repair Manual (SRM) 

Maintenance Review Board (MRS) 57.10.25 

Maintenance Review Board (MRS) Section 0, Para 8 

Repair Instruction No. 21R57110257 

Repair Instruction No. 21R5711Q259 

Repair Instruction No. 21R57110260 

Repair Instruction No. 21R571 10266 

Service Bulietin No. A310-57-2067 

Appendix 1 

K. PUBLICATIONS AFFECTED 

Maintenance Planning Document (MPD) 

Structural Repair Manual (SRM) 

L. INTERCHANGEABILlTYfMIXABIUTY 

Nol applicable 

: 51-43-0051 -76·20 

: 57-10-25 

: 57-10-24 

DATE : Aug 24f95 SERVICE BULLETIN No. : A3 10-S7-2064 

REVISION No. : 02 - Dec 21107 Page : 12 

Printed in Frarn;e CI AIRBUS 2007 All light! rnorvod 
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I 

~A310 

SERVICE BULLETIN 

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 with 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 dollars 

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. If you require the Kit(s) before this time, please include a retrofit planning schedule 

with your order so that we can try to comply with your requirements. 

The sales terms (costs and availability) are 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 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 thai we can try to comply with your requirements. 

The sales terms (costs and availability) are estimated in relation to economic conditions 

at the issue date of the Service Bulletin. 

Kit 572064A04RQ4 

Cost : 8,710.00 US dollars 

Availability: 90 calendar 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, please include a retrofit planning schedule 

with your order so that we can try to comply with your requirements. 

The sates terms (costs and availabil ity) are estimated in relation to economic conditions 

at the issue date of the Service Bulletin. 

Kit 572064A05ROO 

Cost : 5,660.00 US dollars 

Availability: gO calendar days from receipt of order 

The Kit availability given above is the standard lead time from the date of your purchase 

order. If you require the Kit(s) before this time, please include a retrofit planning schedule 

with your order so that we can try to comp!y with your requirements. 

The sales terms (costs and availability) are estimated in relation to economic conditions 

at the issue date of the Service Bulletin. 

Kit 572064A06ROO 

Cost : 207.00 US dollars 

Availability : gO calendar days from receipt of order 

The Kit availability given above is the standard lead time from the date of your purchase 

order. If you require the Kit(s) before this time, please include a retrofit planning schedule 

with your order so that we can try to comply with your requirements. 

The sales terms (costs and availability) are estimated in relation to economic conditions 

at the issue date of the Service Bulletin. 

B. INDUSTRY SUPPORT INFORMATION 

AIRBUS will not provide industry support for accomplishment of this Service Bulletin. 

C. LIST OF COMPONENTS 

Kit 572064A01 ROO 

DATE : Aug 24/95 

REVISION No. : 02 - Dec 21/07 

SERVICE BULLETIN No.: A310-57-2064 

Page : 14 

Printed in Franco CI AtRBUS 2007 All fightS 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 112VF16-20 

Hl 112VF16-23 

HL112VF16-28 

Hl75-12AVW 

Hl87-12 

HL87-14 

HL87-16 

A310 

SERVICE BULLETIN 

QTY UM KEYWORD ITEM 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 

Boll 

Bolt 

Boll 

Collar 

Collar 

Collar 

Collar 

ITEM OLD PART No. 

INT INST DISP 

INT INST DISP 

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. The 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 

Prultcd In Ftance Cl AlRBUS 2007 All rights reserved 
I 

ITEM NEW PART No. 

Hl375-12AVW 

Hl 412V8J12-10 

Hl412V8J12-14 

HL412V8J12-16 

A310 

SERVICE BULLETIN 

QTY UM KEYWORD ITEM OLD PART No. 

3 

4 

3 

3 

Collar 

Bolt 

Bolt 

Bolt 

Hl 412V8J12-17 1 Bolt 

Hl412V8J12-19 2 Bolt 

Hl412VBJ12-20 3 Bolt 

HL412V8J12-27 1 Bolt 

HL412VF14-19 2 Bolt 

HL412VF14-20 1 Bolt 

HL412VF14-23 5 Bolt 

HL412VF16-20 1 Bolt 

HL412VF16-23 4 Boll 

HL4 12VF16-28 1 Boll 

HL93-12 11 Collar 

HL93-14 8 Collar 

HL93-16 6 Collar 

NAS l 726-6E 4 Nul 

NAS1726-8E 8 Nul 

NAS1727-6E 2 Nul 

NSA5479BV6-1 5X 2 Bolt 

NSA5479BV6·19X 2 Bolt 

NSA5479BV6-20X Bolt 

NSA5479BV6-27X 1 Bolt 

NSA5479BV8-20X 1 Screw 

NSA5479BV8-23X 6 Bolt 

INT INST OISP 

NOTE : Refer to the AIRBUS Standards Manual (8M) if you find pari numbers of hardware 

components in the related kit(s) which you cannot identify in the LIST OF 

COMPONENTS of this Service Bulletin. The SM will give you the correct part number 

to part number relationship. 

Kit 572064A05ROO 

ITEM NEW PART No. 

ASNA2027T8-19 

ASNA2027T8-20 

ASNA2027T8-23 

ASNA2027V7 -10 

ASNA2027V7 -14 

ASNA2027V7 -16 

ASNA2027V7 -17 

ASNA2027V7 -19 

ASNA2027V7-20 

ASNA2027V7-27 

ASNA2531-7 

ASNA2531 -8 

ASNA2532-7 

NASl726-6E 

NASl 726-8E 

DATE : Aug 24f95 

QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 

2 

2 

5 

4 

3 

3 

1 

2 

4 

11 

8 

3 

4 

8 

Boll 

Bolt 

Bolt 

Bolt 

Bolt 

Bolt 

Boll 

Bolt 

Bolt 

Bolt 

N,I 

N,I 

N,I 

N,I 

N,I 

SERVICE BULLETIN No. : A310-57-2064 

REVISION No. : 02 - Dec 21 /07 Page : 16 

Printed In France Cl AIRBUS 2001 All ri~h s reserved 
ITEM 

($;A310 

SERVICE BULLETIN 

NEW PART No. a TY UM KEYWORD ITEM OLD PART No. tNT INST DISP 

NAS1727-6E 2 Nul 

NASl727-7E 3 Nul 

NSA54798VG-15Y 2 Bolt 

NSA5479BV6-19Y 2 Bolt 

NSA5479BV6-20Y Bolt 

NSA5479BV6-27Y I Bolt 

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 

COMPONEN TS of this Service Bulletin. The SM will give you the correct part number 

to part number relationship. 

Kit 572064A06ROO 

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 

A$NAZ027T7 ·28 

ASNA2S3 1-7 

2 

2 

Boll 

Nul 

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware 

components in Ihe related kil(S) which you cannot identify in the UST OF 

COMPONENTS of this Service Bulletin. The SM will give you the correct part number 

to part number relationship. 

D. LIST OF MATERIALS· OPERATOR SUPPLIED 

(1) Consumable Materials 

DESCRIPTION 

Solvent General Purpose 

REFERENCE TO CML 

MAT No. 

Mat. No. 11 ·026 

QTY PER AlC INSTIDISP 

As required 

NOTE : To accomplish this Service Bulletin, it is necessary to use the expendable parts 

listed in the SRM 51·76-20, AMM 28-11 -22, AMM 28-11 -29 and in Repair 

Instructions No. 21 R571 10257, No. 21 R57110259, No. 21 R57110260 and 

No. 21R57 11 0266. 

(2) Components 

None 

E. PARTS TO BE RE-tDENTlFIED BY THE OPERATOR 

None 

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

REVISION No. : 02 - Dec 21/07 Page: 17 

Pti~l d in France O AIRBUS 2007 All "," hll tOliOtvod 
(tJA310 

SERVICE BULLETIN 

F. TOOLING· PRICE AND AVAILABILITY 

To accomplish this Service Bulletin it is necessary to use the IDOls listed in NTM 57· 10·25, Page 

block 601 and NTM 51-1 0-08, Page block 601. 

G. SPECIAL TOOLS 

None 

DATE: Aug 24/95 SERVICE BULLETIN No. : A3 10-57-2064 

REVISION No. : 02 - Dec 21107 Page : 18 

Printed in France (l AIRBUS 2007 All rights reserved 
I 

A310 

SERVICE BULLETIN 

3. ACCOM PLISHMENT INSTRUCTIONS 

A. GENERAL 

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS 

INCLUDED IN THE REFERENCED PROCEDURES. 

WARNING: BEFORE YOU DO WORK IN A FUEL TANK, MAKE SURE THAT YOU OBEY ALL 

THE SAFETY PROCEDURES. THIS WILL PREVENT INJURY TO PERSONS 

AND/OR DAMAGE TO THE AIRCRAFT. 

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL 

WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY 

SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR 

MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND 

THE WORK AREA AS CLEAN AS POSSIBLE, TO DO THIS: 

PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS 

NECESSARY ON WIRING AND COMPONENTS. 

REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER 

CONTAMINATION. 

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND 

DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. 

IF THERE IS CONTAMINATION REFER TO ESPM 20-55-00. 

(1) Preparation 

PANEL 

131VU 

131VU 

131VU 

(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 Put 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 

VENTILATION/AVIONICS BLOWER/LO 65HQ 060 

SPD 

VENTILATION/AVIONICS BLOWER/HI 48HQ 064 

SPD 

VENTILATION/AVIONICS BLOWER 49HQ 062 

CONTROL 

~ Open, safety and tag the circuit breakers listed in AMM 28-11-22, Page block 

401 , AMM 28-11-29, Page block 401 and AMM 28-25-00, Page block 301. 

DATE : Aug 24/95 SERVICE BULLETIN 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 

IPe 21-28-03. 

11 Open the forward cargo compartment door 811 (Refer to AMM 52-30-00, Page 

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 (Mat. 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 

applicable 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 inspection 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 : 

Immediately (maximum within 48 hours) in case of damage which is more than the 

permitted or rework limits 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 AIRBUS 2007 All righls rese"'ed 
I 

I$iA310 

SERVICE BULLETIN 

After completion of the corrective action when damage is either in the permitted or 

rework limits, or repaired as specified with the Service Bulletin instructions, 

In case of no findings, you must send the inspection report as soon as the 

maintenance check or inspection report is completed. To prepare these documents, 

refer to this Service Bulletin. 

(a) For the inspection 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 holes to inspect. 

NOTE(02) If repair bushes are installed in the holes No.2 and 3, remove them 

when inspection is necessary in these holes. If you don't know when 

the existing bushes were installed or when the repair as specified 

in Repair Instruction 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 is found: 

~ Install the new nominal fasteners in relation to the removed fasteners. 

Q Do the subsequent inspection of the holes No.1, 2, 3 and 4, in relation to 

the aircraft configuration at the interval given in PLANNING INFORMATION 

paragraph E.(2) Table B. 

f. Or accomplish Service 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 

Printed in FIance AIRBUS 2007 All rights reserved 
A310 

SERVICE BULLETIN 

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

and interval given in PLANNING INFORMATION paragraph E,(2) Tables 

A and B . 

.1. If crack is found: 

!! Crack only in the hole No.1 , in the internal angle filling, no crack in the 

holes No. 2 and 3 and no bushes installed in these holes 

Refer to ACCOMPLISHMENT INSTRUCTIONS, paragraph B.(1 )(b)S. 

Q. Crack in 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 ACCOMPLISHMENT INSTRUCTIONS, paragraph B.( 1)(b)6. 

f. Crack or bushes in the hole No.2 and/or 3, in the verlicallee 

Refer to ACCOMPLISHMENT INSTRUCTIONS, paragraph B.(1 )(b)7. 

Q. Crack in the hole No.4, in the vertical tee 

Contact AIRBUS. 

!! Or crack in other(s) part(s) 

Contact AIRBUS. 

5 Crack only in the hole No.1. in the internal angle fitting. no crack in the holes 

No.2 and 3 and no bushes installed in these holes: 

Replace the internal angle filling and install in the applicable holes the fasteners 

with high interference fit as specified in Repair Instruction No. 21R57110257 

(Refer to ACCOMPLISHMENT INSTRUCTIONS paragraph C.(1 )(a) (Refer 

to Note». 

The aircraft becomes in Config. 02 (refer to Config. 02 ) : 

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

interval given in PLANNING INFORMATION paragraph E.(2) Tables A and B. 

NOTE : Replacement of the internal angle filling as specified in Repair 

Instruction No. 21 R57110257 includes the installation with high 

interference fit of some fasteners at FR40 and rib 1. 

§. Crack in the hole No. 1. in the internal angle fitting, and crack in the holes No. 2 

and 3 or bushes installed in these holes : 

~ Replace the internal angle filling and install the fasteners with high 

interference fit at rib 1 as specified in Repair Instruction No. 21 R57110266 

procedure A (Refer to ACCOMPLISHMENT INSTRUCTIONS paragraph 

C.(1)(a» and do the instructions for the holes No.2 and No.3 as specified in 

ACCOMPLISHMENT INSTRUCTIONS, paragraph B.(l )(a)7. 

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

REVISION No. : 02· Dec 21/07 Page : 22 

Pnnlcd In France IC AIRBUS 2007 All nghlS reserved 
I 

DATE: Aug 24/95 

~A310 

SERVICE BULLETIN 

12. Do the subsequent inspection of the hole No. 1 at the applicable threshold 

specified in Table 2 (Refer to fjgure 4) . 

.£ 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. 

g Do the subsequent inspection of the holes NO.2 and NO.3 as specified in 

ACCOMPLISHMENT INSTRUCTIONS, paragraph B.(1 )(a)7. 

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

~ If there is also a crack in the hole No.1, at first refer to ACCOMPLISHMENT 

INSTRUCTIONS, paragraph B.(1 )(b)6. 

Q Find the crack length in the holes No. 2 and 3 (Refer to NTM 51-10-08, 

Page block 601) and calculate A 

Refer to figure 2 

~ If A is less than or equal to 9.15 mm (0.360 in.) : 

Remove the crack(s) and install the bushes in the holes No.2 and 

3 as specified in Repair Instruction No. 21R57110260 (Refer to 

ACCOMPLISHMENT INSTRUCTIONS paragraph C.(l )(a». 

Install the fasteners with high interference fit at rib 1 as specified in 

Repair Instruction No. 21 R57110266 (Refer to ACCOMPLISHMENT 

INSTRUCTIONS paragraph C.(l)(a». 

Do the subsequent inspection of the holes No.2 and 3 at the applicable 

threshold specified in Table 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 inspection of the hole No. 1: 

if the internal angle is replaced, refer to ACCOMPLISHMENT 

INSTRUCTIONS paragraph B.(l )(b)6, 

if the internal angle is not replaced, at the applicable interval specified 

in Table 5 (Refer to figu re 7). 

Q If A is more than 9.15 mm (0.360 in.) : 

If A is more than 9.15 mm (0.360 in.) only for a crack which propagates 

upward (crack at 12 o'clock) from the hole No.2. 

Install the bushes in the holes No. 2 and 3 as specified in Repair 

Instruction No. 21R57110260 (Refer to ACCOMPLISHMENT 

INSTRUCTIONS paragraph C.{l )(a)). 

SERVICE BULLETIN No. : A310-S7-2064 

REVISION No. : 02 - Dec 21/07 Page: 23 

Printed In France ICI AIRBUS 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 INSTRUCTIONS paragraph C.(l)(a». 

Do the subsequent inspection of the holes No.2 and 3 at the applicable 

interval specified in Table 4 (Refer to figure 6). 

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. 

Do the subsequent inspection of the hole NO. 1: 

. if the internal angle is replaced, refer to ACCOMPLISHMENT 

INSTRUCTIONS paragraph 8.(1 )(b)6, 

. if the inlernal angle is not replaced, at the applicable interval specified 

in Table 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 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 

Q Install : 

2 N"I 

NOTE : Item (22) was retained at removal. 

Item (20) 

Item (21) 

Item (22) 

(c) For the Inspection Report, refer to Appendix 1. 

(2) Config. 02 

NOTE : When the work is completed, you must report the inspection 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 : 

Immediately (maximum within 48 hours) in case of damage which is more than the 

permitted or rework limits for further 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 Bulletin instructions. 

SERVICE BULLETIN No. : A310-57-2064 

REVISION No.: 02 - Dec 21/07 Page: 24 

Prin ted in Franoe C AIRBUS 2007 All rights reserved 
~A310 

SERVICE BULLETIN 

In case of no findings, you must send the inspection report as soon as the 

maintenance check or inspection report is completed. To prepare these documents, 

refer to this Service Bulletin. 

(a) For the inspection area, refer to figure 2. 

(b) Do an eddy current inspection of the upper corner angle al FR40 on the LH and 

RH sides. 

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. 

Refer to figure 2 

NOTE(01) For the subsequent inspections. remove the fasteners only from 

the holes to inspect. 

NOTE(02) If repa ir bushes are installed in the holes NO. 2 and 3, remove them 

when inspection is necessary in these holes. If you don'l know when 

the existing bushes were installed or when the repair as specified 

in Repair Instruction No. 21 R57110260 or Repair Instruction No. 

21 R57110266 was done, contact AIRBUS. 

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

2 

Refer to figure 8 

~ Remove : 

N,I 

Q. Push back (do not remove) : 

Screw 

Screw 

Item (22) 

Item (20) 

Item (21) 

Retain 

;i If no crack is found : 

~ Instali the new nominal fasteners in relation to the removed fasteners. 

b Do the subsequent inspection of the holes No. 1, 2, 3 and 4, in relation to 

the aircraft configuration at the interval given in PLANNING INFORMATION 

paragraph E.(2) Table B. 

~ If crack is found: 

~ Crack only in the hole No.1 , in the internal angle filting, no crack in the 

holes No. 2 and 3 and no bushes installed in these holes 

Refer to ACCOMPLISHMENT INSTRUCTIONS, paragraph B.(2)(b)5. 

b Crack in the hole No. 1, in the internal angle, and crack or bushes in the hole 

No. 2 and/or 3, in the vertical tee 

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

REVISION No. : 02 - Dec 21 /07 Page : 25 

Prinled In France (l AIRBUS 2007 All rights reserved 
I 

A310 

SERVICE BULLETIN 

Refer 10 ACCOMPLISHMENT INSTRUCTIONS, paragraph B.(2)(b)6. 

f. Crack or bushes in the hole No. 2 andlor 3, in the vertical tee 

Refer to ACCOMPLISHMENT INSTRUCTIONS. paragraph B.(2)(b)7. 

Q. Crack in the hole No.4, in the verlical lee 

Contact AIRBUS. 

~ Or crack in other(s) part(s) 

Contact AIRBUS. 

~ Crack only in the hole No.1, in the internal angle fitting, no crack in the holes 

No. 2 and 3 and no bushes in these holes : 

~ Replace the inlernal angle fitting as specified in Repair Instruction No. 

21 R57110259 (Refer to ACCOMPLISHMENT INSTRUCTIONS paragraph 

C.(2)(a)). 

!! 00 the subsequent inspection of the hole No. 1 althe applicable threshold 

specified in Table 1 (Refer to figure 3). 

f 00 the subsequent inspection of the holes No. 2 and 3 at the applicable 

threshold specified in Table 3 (Refer to figure 5). 

Q. 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. 

§. Crack in the hole No. 1, in the internal angle fitting, and crack in the holes No. 2 

and 3 or bushes installed In these holes 

~ Replace the internal angle fitting as specified in Repair Instruction No. 

21R57110259 (Refer to ACCOMPLISHMENT INSTRUCTiONS paragraph 

C.(2)(a)). 

2. Do the subsequent inspection of the hole No. 1 at the applicable threshold 

specified in Table 1 (Refer to figure 3) . 

.£ 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. 

Q. Do the subsequent inspection and instructions of the holes No. 2 and No. 3 

as specified in ACCOMPLISHMENT INSTRUCTIONS, paragraph B.(2)(a)7. 

I Crack or bushes in the holes No. 2 and 3, in the vertical tee 

~ If there is also a crack in the hole No. 1, at first refer to ACCOMPLISHMENT 

INSTRUCTIONS, paragraph B.(2)(b)6. 

b Find the crack length in the holes No. 2 and 3 (Refer to NTM 51-10-08, 

Page block 601) and calculate A. 

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

REVISION No. : 02 - Dec 21/07 Page: 26 

PriMed In France Cl AIRBUS 2007 An rign ls rlllOMld 
I 

DATE: Aug 24/95 

A310 

SERVICE BULLETIN 

Refer to figure 2 

£ If A is less than or equal to 9.15 mm (0.360 in.) : 

Remove the crack(s) and install the bushes in the holes No.2 and 

3 as specified in Repair Instruction No. 21 R57110260 (Refer to 

ACCOMPLISHMENT INSTRUCTIONS paragraph C.(2)(a)). 

Do the subsequent inspection of the holes No.2 and 3 althe applicable 

threshold specified in Table 3 (Refer to figure 5), 

Do the subsequent inspection of the hole No.1 althe applicable threshold 

specified in Table 1 (Refer to figure 3). 

Do the inspection of the hole No.4, in relation to the aircraft configuration 

althe interval given in PLANNING INFORMATION paragraph E.{2) 

Table B. 

Q If A is more than 9.15 mm (0.360 in.) : 

If A is more than 9.15 mm (0.360 in.) only for a crack which propagates 

upward (crack at 12 o'clock) from the hole No.2. 

Install the bushes in the holes No.2 and 3 as specified in Repair 

Instruction No. 21R57110260 (Refer to ACCOMPLISHMENT 

INSTRUCTIONS paragraph C.(2)(a». 

Do the subsequent inspection of the holes No.2 and 3 at the applicable 

interval specified in Table 4 (Refer to figure 6). 

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. 

Do the subsequent inspection 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 12 o'clock in 

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 (21) 

Item (22) 

SERVICE BULLETIN No. : A310-57-2064 

REVISION No. : 02 - Dec 21/07 Page: 27 

Printed In France = AIRBUS 2007 AD rignls resorved 
I 

A310 

SERVICE BULLETIN 

NOTE: Item (22) was retained al removal. 

(e) For the Inspection Report, refer to Appendix 1. 

C. REPAIR 

(1) Config. 01 and Config. 03 

(a) Do the applicable Repair Instruction(s). 

DATE : Aug 24f95 

Refer to ACCOMPLISHMENT 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 angle filling as specified in Repair Instruction No. 

21R571 10257 or Repair Instruction No. 21R57110266, use the necessary 

parts below: 

9. Kit 572064A01 ROO, for the LH side: 

Shim 

Fitting 

A5711242720096 

A571 1206120602 

b Kit 572064A02ROO, for the RH side : 

Shim 

Fitting 

A5711242720196 

A5711206120S02 

£ Kit 572064A03R02, for one side (LH or RH) : 

Coliar HL7S-12AVW 

Collar HL87-14 

Coliar HL87-12 

Collar HL87-16 

N,t A8NA2532-8 

N,t ASNA2532-S 

N,t A8NA2S31-6 

N,t ASNA2531 -7 

N,t ASNA2531-8 

Bolt Hl112VBJ12-10 

Bolt Hl112VBJ12-14 

Bolt HL112VBJ 12-16 

Bolt Hl112VBJ1 2-17 

Bolt Hl112VBJ12-19 

Bolt HL1 12VBJ12-20 

Boll HL1 12VF14-19 

Boll ASNA2027T8-20 

Boll HL112VF14-20 

Boll ASNA2027T8-28 

Boll ASNA2027V6-27 

Bolt ASNA2027V6-20 

Boll ASNA2027V6-15 

Bolt ASNA2027V6-19 

Boll ASNA2027T8-23 

Bolt HL 112VF14-23 

Boll HL112VF16-28 

SERVICE BULLETIN No. : A310-57-2064 

REVISION No. : 02 - Dec 21/07 Page : 28 

Printed In France IO AIRBUS 2007 All rights reserved 
A310 

SERVICE BULLETIN 

2 Bolt ASNA2027T7 ·28 

1 Bo[t Hl112VBJ12·27 

1 Boll HL112VF16-20 

4 Bolt HL112VF16-23 

~ Kit 572064A04R04, for one side (LH or RH) : 

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 Collar HL93·12 

6 Collar Hl93-16 

4 Bolt Hl412V8J12-10 

3 Bolt HL412VBJ12-14 

3 Bolt Hl412V8J12-16 

1 Bolt Hl41 2V8J12-17 

3 Bolt Hl412VBJ12-20 

2 Bolt Hl412VBJ12-1 9 

2 Boll HL412VF14-19 

1 Boll HL412VF14-20 

1 Boll NSA54 798V6-27X 

1 Boll NSA5479BV6·20X 

1 Screw NSA5479BV6·20X 

2 Bolt NSA54 79BV6-15X 

2 Bolt NSA54 798V6-19X 

6 Boll NSA54 798V8-23X 

5 Bolt HL41 2VF14·23 

1 Bolt HL41 2VF16-28 

Bolt HL412V8J12·27 

Boll HL412VF16·20 

4 Boll HL412VF16·23 

• Kit 572064AOSROO, for one side (LH or RH) : 

3 N"I ASNA2S32-7 

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 ASNA2531-7 

B N"I ASNA2531·8 

4 Bolt ASNA2027V7·1 0 

3 Bolt ASNA2027V7 ·14 

3 Bolt ASNA2027V7 · 16 

1 Bolt ASNA2027V7 ·17 

4 Boll ASNA2027V7 ·20 

2 Bolt ASNA2027V7· 19 

2 Boll ASNA2027T8·19 

2 Bolt ASNA2027T8·20 

Bolt NSA5479BV6·27Y 

Boll NSA5479BV6·20Y 

DATE : AU9 24/95 SERVICE BULLETIN No. : A310·57·2064 

REVISION No. : 02 · Dec 21/07 Page: 29 

rir1 tc~ In Franca CI AIRBUS 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 internal angle and install fasteners with high interference fit al 

some specified holes. 

Refer to Repair Instruction No. 21R57110257 

NOTE: This repair is only applicable when there are no cracks and no repa ir 

bushes in Ihe holes No. 2 and 3. 

~ Instalilhe shim and the fasteners with high interference fit al some specified 

holes al rib 1 only. 

Refer to Repair Instruction No. 21 R57110266 

NOTE(01) This repair can include the replacement of the internal angle fitting 

when crack is found at the hole NO.1. 

NOTE(02) For this 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 Install the repair bushes in the holes No.2 and No. 3. 

2 

2 

Refer to Repair Instruction 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 washers with : 

Boll 

Not 

ASNA2027T7·28 

ASNA2531·7 

(2) Config. 02 

(a) Do the applicable Repair Instruction(s). 

DATE : Aug 24/95 

Refer to ACCOMPLISHMENT INSTRUCTIONS, paragraph 8.(2) 

To replace the internal angle fitling as specified in Repair Instruction No. 

21 R57110259, use the necessary parts below: 

~ Kit 572064A01 ROO, for the LH side: 

Shim 

Fitting 

A5711242720096 

A5711206120602 

SERVICE BULLETIN No. : A310·57·2064 

REVISION No. : 02· Dec 21/07 Page : 30 

Pr;nted In Frante C AIRBUS 2007 All rights reserved 
($)A310 

SERVICE BULLETIN 

!> Kit 572064A02ROO, for the RH side : 

Shim A5711242720196 

Fitting A5711206120502 

£ Kit 572064A03R02, for one 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 Nut ASNA2532-6 

4 Nut ASNA2531-6 

2 Nut ASNA2531-7 

12 Nut ASNA2531-B 

4 Bolt HL 112V8J12-10 

3 Bolt HL 112V8J12-14 

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 Boll ASNA2027T8-28 

1 Bolt ASNA2027V6-27 

1 Boll ASNA2027V6-20 

2 Boll ASNA2027V6-15 

2 Boll ASNA2027V6-19 

7 Boll ASNA2027TB-23 

5 Boll Hl112VF14-23 

1 Boll Hl112VF16-28 

2 Boll ASNA2027T7·28 

1 Boll Hl112VBJ12-27 

1 Boll Hl112VF16-20 

4 Boll Hl112VF16-23 

Q Kit 572064A04R04, for one side (LH or RH) : 

I Collar HL375-12AVW 

4 Nut NAS1726-6E 

8 Nut NAS1726-8E 

2 Nut NAS1727-6E 

8 Collar HL93-14 

11 Collar HL93-12 

6 Collar HL93-16 

4 Bolt HL412VBJ12-10 

3 Bolt HL412VBJ12-14 

3 Bolt HL412VBJ12-16 

1 Bolt HL412VBJ12-17 

3 Bolt HL412VBJ 12-20 

2 Bolt HL412VBJ12-19 

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

REVISION No. : 02 - Dec 21107 Page: 31 

Printed in f rance O AIRBUS 2()()7 All righls 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 

Boll 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 ASNA2531·8 

Boll ASNA2027V7·10 

Boll ASNA2027V7·14 

Boll ASNA2027V7 ·16 

Boll ASNA2027V7 ·17 

Bolt 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 

Replace the inlernal angle fitting and inslall the bushes in Ihe holes No. 2 and 3. 

Refer to Repair Instruction No. 21 R57110259 

Instalilhe repair bushes in Ihe holes No.2 and No. 3. 

Refer to Repair Instruction No. 21R57110260 

~ Make Ihe bushes and Ihe washers as specified in the Repa ir Instruction 

No. 21 R57110260. 

12. Kit 572064A06ROO, for one side (LH or RH) 

Install the bushes and the washers with: 

SERVICE BULLETIN No. : A310-57-2064 

REVISION No. : 02 - Dec 21f07 Page : 32 

Pri nted in France BU S 2007 Alt 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 

(Refer to AMM 28-11 -29, Page block 401). 

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

2. Do the pre-conditioning through the Low Pressure (LP) ground connection 

(Refer to AMM 12-33-21). 

Q. Do a check for leaks at the duct connections. 

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 tools and other items of 

equipment. 

(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) Close the access doors 540AB and 640AB on the lower surfaces of the wing, (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 

Printed in France C AtRBUS 2001 All rights reserved 
PANEL 

131VU 

131VU 

131VU 

A310 

SERVICE BULLETIN 

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

(9) Remove the safely clips and lags and close these circuit breakers: 

DESIGNATION FIN LOCATION 

VENTllATIONfAVIONICS BLOWER/LO 65HQ 060 

SPD 

VENTILATION/AVIONICS BLOWER/HI 48HQ 06. 

SPD 

VENTILATION/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 301. 

{il Close the passenger/crew door (Refer to AMM 52-10-00). 

(j) Disconnect the aircraft electrical ground connection, {Refer to AMM 24-00-00, 

Page block 301 J. 

(k) Restore systems and aircraft in normal operating condition. 

(I) Remove the access platforms. 

F. DOCUMENTATION 

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

DATE: Aug 24f95 SERVICE BULLETIN No. : A310·57·2064 

REVISION No. : 02 • Dec 21107 Page : 34 

PriOled In France O AIRBUS 2007 All rig hl$ reserved 
I 

i 

, 

i 

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C-

A310 

SERVICE BULLETIN 

SECTION 

A-A 

(EXAMPLE OF CRACK fiNDING) 

R 

HOLE No.1 

o 

R 

[

VERTICAL TEE 

REAR finiNG OF FR40 

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 SIDE SHOWN 

HOLE NO.2 

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

t:)B 

INTERNAl 

ANGLE FlmNG 

DATE : Aug 24f95 SERVICE BULLETIN No. : A31O-57-2064 

REVISION No. : 02 - Dec 21/07 Page: 39 

Pnnlcd In Franco C AIRBUS 2007 All ngnls resc'vod 
($JA310 

SERVICE BULLETIN 

TABLE \ 

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

IN VERTICAL TEE A31Q-2QO A31Q-300(SR) 

mm in, 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 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 0.610 , 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 APPLICABLE THRESHOLD ABOVE WHEN 

YOU REPLACE THE INTERNAL ANGLE FiniNG. BUT IF YOU MODIFY 

THE DIAMETER OF THE HOLES NO.2 and NO.3 BETWEEN 2 INSPECTIONS 

OF THE HOLE No.1. CONTACT AIRBUS TO ADJUST THIS THRESHOLD. 

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 41,900 

8.100 40,500 

7,800 39,000 

7.500 37.600 

7.200 36.200 

Config. 02 : Inspection Thresholds For Hole NO. 1 After Repair As Specified in 21 R571 10259 

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

REVISION No, : 02 - Dec 21/07 Page: 40 

Printnd in Franco C AIRBUS 2007 AU rights reserved 
!$!A310 

SERVICE BULLETIN 

TABLE 2 

DIAMETER OF HOLES No.2 AND NO.3 THRESHOLD THRESHOLD 

IN 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 SELECTION OF THE APPLICABLE THRESHOLD ABOVE WHEN 

YOU REPLACE TI-lE INTERNAL ANGLE FITTING. BUT IF YOU MODIFY 

THE DIAMETEA OF THE HOLES NO.2 and NO.3 BETWEEN 2 INSPECTIONS 

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 

13,500 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 53,100 

10.200 51,100 

Config. 01 and 03 : Inspection Thresholds For Hole No.1 After Repair As Specified in 21R571 10266 

(Config. 01 and Config. 03) 

DATE: Aug 24195 SERVICE BULLETIN No. : A310-57-2064 

REVISION No. : 02 - Dec 21/07 Page: 41 

Prinled In France Cl A1RBUS 2007 All MghlS reserved 
($;A310 

SERVICE BULLETIN 

TABLE 3 

DIAMETER OF HOLES No.2 AND NO.3 THRESHOLD THRESHOLD 

IN VERTICAL TEE A31o-2DO A31o-300{SR) 

mm in. 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 0.531 , 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 0.717 < 0 ,0.728 26.900 53.900 26.100 73.400 

18.5< 0 '19 0 ,728 < 0 , 0,748 26,100 52.200 25,300 71.000 

19<0,19.5 0.74B < 0,0.768 25,200 SO.5OO 24,SOO 68,700 

19.5<0(20 0.768 < 0,0.787 24,300 48,700 23.600 66.300 

NOTE : THE THRESHOLD SPECtFtED tN THIS TABLE ARE GIVEN FROM THE 

CRACK REPAJR IN THE HOLES NO.2 AND No.3 , 

Figure 5, Sheet 1 

THRESHOLD 

A31Q.300(LR) 

FC FH 

12,800 ".000 

16,500 62,500 

17,200 66,000 

18,300 91.800 

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 

23.400 117,400 

22,700 113,800 

22.000 110,100 

21,300 106,500 

20,500 102.900 

Config, 01 thru 03 : Inspection Thresholds For Holes No.2 And No. 3 After Repair As Specified in 

21 R57110259 andlor 21 R57110260 

DATE : Aug 24195 SERVICE BULLETIN No.: A310·57·2064 

REVISION No. : 02 - Dec 21107 Page: 42 

Printed in France C AIRBUS 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 0.571 <: 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 THIS TASLE ARE APPLICASLE WHEN THE CRACK 

IN THE 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 Hole No.2 

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

REVISION No.: 02 - Dec 21/07 Page: 43 

Printed In Franco Ie AIRBUS 2007 All rig hts reserved 
$ A310 

SERVICE BULLETIN 

TABLE 5 

DIAMETER OF HOLES No.2 AND No.3 INTERVAl INTERVAL 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 0.512 " 0 < 0.531 8,050 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<15.5 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 12,600 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 

Figure 7, Sheet 1 

Config. 01 thru 03 : Inspection Inlervals For The Hole No.1 

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

REVISION No. : 02 - Dec 21107 Page: 44 

Printed In Fran"" Cl AtRBUS 2001 All righ ts reserved 
(20) 

(22) 

(21) 

(22) 

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FR40 

A310 

SERVICE BULLETIN 

FWD CARGO COMPARTMENT 

lH SIDE - VIEW LOOKING AFT 

- -----f'-- -

i 

0 

i I @ @) 

o@ 

If)@ 

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Figure 8, Sheet 1 

(J) 

Contig. 01 Ihru 03 : Fasteners To Push Back For Access 

" 

I 

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

REVISION No. : 02 - Dec 21/07 Page : 45 

Printed in France RBUS 2007 AI rights reserved 
A310 

SERVICE BULLETIN 

This Page Intentionally Left Blank 

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

REVISION No. : 02 - Dec 21107 Page: 46 

Prinled in france CI AIR8US 2007 All rig hls 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 

SERVICE BULLETIN 

APPENDIX 1 

TITLE: FUSELAGE - FR40 - INSPECT UPPER CORNER FITTING. 

MODIFICATION No. : None 

1. INSPECTION REPORT 

The results of the inspection, including no findings, replacement or actions to be done, must be 

forwarded to AIRBUS Department SEE81, on the attached inspection report sheet. 

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

REVISION No. : 02 - Dec 21 /07 Page : 1 

Printed In Franco lC> AIRBUS 2007 All nghls roserved 
§ D 

. 

i ~ , , 8 • u , 

< . • U , 

D 

, 

~t - " " • 

~ ~§ 

5 i~ 

i i I!+, ++-H 

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1 , 

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s · .. • • • Z N ~ 

~ 0; 

w ~ 

g " 


" ($;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 WILL BE embodied ............. ..... .... ..... . .................... ....... YES/NO (if NO please 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 operational documentation is affected (see Paragraph 1.K of this S8): If information is needed prior to next 

normal revision or prior to S8 embodiment, please indicate required service(s): 

Either : Advance data..... ..... ......... . ............... .. ... ........ ............ YES/NO 

Or : IntermediatefTemporary revision. . . ............ ........................ YES/NO 

Important Information: This S8 will only be incorporated in your maintenance and operational documentation 

if this sheet is returned to Airbus and signed by a duly authorised representative. With the next feasible 

revision, this will 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 this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically include 

them in the manual revisions. Refer to SIL 00-037 for detailed information. 

Please return this completed sheet to: 

AIRBUS 

CUSTOMER SERVICES DIRECTORATE 

1 Rond Point Maurice Bellonte 

31707 BLAGNAC CEDEX FRANCE 

Attn: SDC32 Technical Data and Documentation Services 

FAX: (+33) 5 61 932806 

e-mail: sb.reporting@airbus.com 

Or via your Resident Customer Support Office. 

Alternatively, 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 AIRBUS 2007 All righ~ reserve<.! 
A310 

SERVICE BULLETIN 

REPORTING QUALITY 

TITLE : FUSELAGE - FR40 - INSPECT UPPER CORNER FITTING. 

MODIFICATION No. : None 

Use this form to tell us what is your perception of Ihe quality of this Service Bulietin.The reported data that you 

provide us will be used to analyse areas of difficulties and to lake corrective action to futher improve Ihe quality 

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 Ihe highest score) 

-Quality rating of this S8 

-Quality rating of Ihe Accomplishment Instructions 

-Quality rating of the Illustrations 

-Is this 58 easy to understand? 

432 

432 

4 32 

YIN 

If you have had difficulties in Ihe accomplishment of this 56 please quote below the area(s) and give a short 

description of the issue. 

Planning 

X Effeclivily 

X Reason 

X Manpower 

X References 

X Publication 

Comments: 

Operator : 

NamefTiUe : 

Material 

X Kit Content 

X lisl of Malerials 

Operator Supplied 

X Re-identification 

X Tooling 

Please relurn this form to: 

AIRBUS 

CUSTOMER SERVICES DIRECTORATE 

1 Rand Point Maurice Bellante 

31707 BLAGNAC CEDEX FRANCE 

Alln: SEM4 Service Bulletins Management 

FAX: (1-33) 5 61 934251 

Or via your Resident Customer Support Office. 

Inslructions 

X Preparation 

X Mod/lnspeclion 

X Tesl 

X Close-up 

X Illustrations 

Date: 

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

REVISION No. : 02 - Dec 21/07 Page:lof l 

Printed In Fra~ce C AlRBUS 2007 Ali rig ~ r(!,~ vcd