# A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET AIRBUS CUSTOMER SERVICES DIRECTORATE 1 

### Rond Point Maurice BeLLonte 31707 BLAGNAC 

### CEDEX FRANCE TeL : (33) 5 61-93-33-33 TeLex: AIRBU 530526F Fax : (33) 5 61 93 42 51 

# MANDATORY MANDATORY MANDATORY
ATA SYSTEM : 57 TITLE: WINGS - INSPECT REAR SPAR FOR CRACKS AT BUILD SLOT MODIFICATION No. : None This page transmits revision No. 04 of Service BuLLetin A300-57-6059. 

### ADDITIONAL WORK No additional work is required by this revision for aircraft inspected/repaired by any previous revision. 

### REASON This Service BuLLetin is issued at revision 04 to inform operators that the inspection is re-instated for aircraft post Mod. No. 11130H5404 (Service BuLLetin No A300-57-6063) or post production Mod. 12102H5505. ALso new inspection thresholds, repeat intervaLs and grace periods have been added to enable the aircraft to operate beyond the Design Service GoaL (DSG). 

### CHANGES SUMMARY: AIRBUS address has been amended. - REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Text has been amended to re-instate the inspection and incLude post production modification 12102H5505 aircraft. Airworthiness Directive (AD) statement has been deLeted.

DATE: Aug 12/94 SERVICE BULLETIN No. : A300-57-6059 REVISION No. : 04 Feb 22/11 PAGE : 1 Printed in France

# A300 

# -boo
SERVICE BULLETIN REVISION TRANSMITTAL SHEET - EFFECTIVITY - Effectivity has been updated.
SERVICE BULLETIN: • AIRBUS address has been amended. - Airbus Industrie 

### has been changed to AIRBUS in 

### the copyright statement. PLANNING INFORMATION EFFECTIVITY - Para. (1) Effectivity has been updated. Para. (2)(a) Effectivity has been updated. Para. (2)(b) Airbus Industrie 

### has been changed to AIRBUS, effectivity

has been updated and Mod. No. 11130H54G4 paragraph removed. - REASON Text amended to re-instate the inspection and incLude post production

Modification 12102H5505 aircraft. - COMPLIANCE

Approval statement has been updated. . Accomplishment Timescale has been compLeteLy revised.
- ACCOMPLISHMENT INSTRUCTIONS - INSPECTION

Minor editorial corrections and AI/SE-A becomes AIRBUS. Revised inspection intervaLs for cracks within Limits for aircraft pre Mod. 11130H5404. . Revised actions for aircraft post Mod. 11130H5404.

DATE: Aug 12/94 SERVICE BULLETIN No. ; A300-57-6059 REVISION No. : 04 Feb 22/11 PAGE . 2 Printed in France

# A300 

# -boo
SERVICE BULLETIN REVISION TRANSMITTAL SHEET - REPAIR

. AI/SE-A becomes AIRBUS. . Revised aLLowabLe operation periods following temporary repair R571 50366.
- CLOSE UP

Minor editorial correction and AI/SE-A becomes AIRBUS. - FIGURE 1

Sheet 2 added to incLude post Mod. 11130H5404 (SB A300.57-6063) standard. FIGURE 2 . Sheet 2 added to incLude post Mod. 11130H5404 (SB A300.57-6063) standard.
- REPORTING SHEET

. Airbus 

### Industrie has been changed to AIRBUS. . AIRBUS address has been amended. - QUALITY PERCEPTION FORM:

AIRBUS address has been amended. 

### FILING INSTRUCTIONS 1. Remove and destroy pages 1 and 2 of the Summary, pages 1, 

### 2, 3, 4, 5, 6, 9, 10 and 11 of the Service BuLLetin, page 1 of the Reporting Sheet and page 1 of the QuaLity Perception Form_ 2. Insert pages 1, 2 and 3 of the Summary and pages 1, 2, 2a, 2b, 3, 4, 5, 5a, 5b, 6, 9, 10, 11, 12a and 13a of the Service BuLLetin, page 1 of the Reporting Sheet and page 1 of the QuaLity Perception Form. Put this Revision Transmittal Sheet in front of the Service BuLLetin. 

### HISTORY OF PREVIOUS REVISIONS Revision No. 01 of this Service BuLLetin was issued to incLude new access instructions for inspection.

DATE: Aug 12/94 SERVICE BULLETIN No. : A300-57-6059 REVISION No. : 04 Feb 22/11 PAGE : 3 Printed in France

# A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Revision No. 02 of this Service BuLLetin was issued to incLude information on Modification No. 11130H5404 (Service BuLLetin No. A300-57-6063). Revision No. 03 of this Service BuLLetin was issued to incLude aircraft modeL C4-605R/F and MSN 0755 and MSN 0758 in the effectivity. ALso to inform operators that the compLiance is rendered Mandatory by Airworthiness Directive (Consigne 

### de NavigabiLite) CN 97-375- 

### 239(B)R2. REVISION SEQUENCE ORIGINAL : Aug 12/94 REVISION No. : 

### 01 - Jan 

### 17/95 REVISION No. : 

### 02

- Jul 

### 21195 REVISION No. : 

### 03 - Oct 

### 25/99 REVISION No. : 04
- Feb 

### 22/11

DATE: Aug 12/94 SERVICE BULLETIN No. : A300-57-6059 REVISION No. : 04 Feb 22/11 PAGE : 4 Printed in France

# A3OO-6OO SERVICE BULLETIN SUMMARY AIRBUS CUSTOMER SERVICES DIRECTORATE 1 

### Rond Point Maurice BeLLonte 31707 BLAGNAC 

### CEDEX FRANCE TeL : (33) 5 61-93-33-33 TeLex: AIRBU 530526F Fax : (33) 5 61 93 42 51 This summary is for information onLy and is not approved for modification of the aircraft 

# MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 57 TITLE : WINGS - INSPECT REAR SPAR FOR CRACKS AT BUILD SLOT MODIFICATION No. : None 

### REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES Cracks have been found in the rear spar web between Ribs 1 and 2 on both the in-service aircraft and the fatigue test wing. In aLL reported cases the cracks span the tip of the buiLd sLot and the nearest adjacent fastener hoLes. The cracks are considered to initiate at the tip of the buiLd sLot and to be the result of fatigue damage created by high shear stress experienced during the Landing cycle. The earliest in-service damage was found on an A300 B2 aircraft which had achieved 21,500 Flight CycLes (FC)_ The crack in the fatigue test wing was discovered at 50,000 simulated FC and monitored for a further 12,000 FC with no evidence of continued crack growth from the hoLe. Modification No. 11130H5404 (Service BuLLetin No. A300-57-6063) has been introduced to enlarge the end of the build sLot and cold expand seven hoLes adjacent to the buiLd sLot. Embodiment of Modification No 11130H5404 (Service BuLLetin No. A300-57-6063) extends the inspection threshold. Mandatory High Frequency Eddy Current (HFEC) inspections are required of the aft face of the rear spar web in the area immediately adjacent to the outboard end and bottom face of the build sLot. Inspections are required at the threshoLds and repeat intervals given in TabLes 1, 

### 2, 3 and 4. Production Modification 12102H5505 has been introduced on MSN 805. However, to support operations beyond the Design Service GoaL (DSG), aircraft post production Modification 12101H5505 will need to be inspected using this Service Bulletin.

DATE: Aug 12/94 SERVICE BULLETIN No. : A300-57-6059 REVISION No. : 04 Feb 22/11 PAGE : 1
Printed in France

# A300-600 SERVICE BULLETIN SUMMARY

EVALUATION TABLE COMPLIANCE Mandatory CANCELS INSPECTION SB No POTENTIAL AD Yes A/C OPERATION AFFECTED No RELIABILITY AFFECTED No PAX COMFORT AFFECTED No COST SAVING No ETOPS AFFECTED No STRUCTURAL LIFE EXTN No VENDOR SB INVOLVED No 

### EFFECTIVITY This Service Bulletin is applicable to these Customers: AAL, AAW, ABD, AHK, AMU, BKV, CES, CSN, DLH, F21, FDX, GBE, IRA, JAL, KAC, KAL, LAA, MNB, MON, MSR, MXU, OHY, QTR, SUD, TAR, THA, UZB 

### SERVICE BULLETIN TO BE ACCOMPLISHED PREVIOUSLY OR SIMULTANEOUSLY None REFERENCES/REPERCUSSIONS TFU : 571104001 DEB : None AOT : None SIL None LIFE LIMIT None LINE MAINTENANCE AFFECTED : No OTHER : None 

### NATURE OF THE WORK AIRCRAFT : YES EQUIPMENT : NO HARD : NO

SOFT : NO DATE: Aug 12/94 SERVICE BULLETIN No. : A300.57.6059 REVISION No. : 04 Feb 22/11 PAGE : 2

Printed in France

# A300 

# -boo SERVICE BULLETIN SUMMARY OBRM : NO 

### MANPOWER TOTAL MANHOURS 3.0 ELAPSED TIME (HOURS) 2.0 MATERIAL INFORMATION AIRCRAFT DATA None 

### APPENDICES None

DATE: Aug 12/94 SERVICE BULLETIN No. : A300-57-6059 

# I REVISION No. : 04 Feb 22/11 PAGE : 3
Printed in France

# A300-600 SERVICE BULLETIN AIRBUS CUSTOMER SERVICES DIRECTORATE 1 

### Rond Point Maurice 

### Bellonte 31707 BLAGNAC 

### CEDEX FRANCE TeL : (33) 5 61-93 

### -33-33 TeLex: AIRBU 530526F Fax : (33) 5 61 93 42 51 

# MANDATORY MANDATORY MANDATORY
ATA SYSTEM : 57 TITLE: 

### WINGS - INSPECT REAR SPAR FOR CRACKS AT BUILD SLOT MODIFICATION No. : None This document contains AIRBUS PROPRIETARY INFORMATION and shaLL at aLL times remain the property of AIRBUS; no intellectual property right or License 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, shaLL 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 writtenconsent1. 

### PLANNING INFORMATION
A. 

### EFFECTIVITY (1) ModeLs B4-601, B4-603, B4-605R, B4-620, B4.622, B4-622R, C4-605R/F, C4-620, F4.605R (2) Aircraft (a) Effectivity by MSN The Service BuLLetin is applicable to aircraft MSN: 0284 0294 0301 0307 0312 0317 0321 0336 0341 0344 0348 0351 0354 0358 0361 0365 0368 0380 0388 0398 0405 0408 0411 0414 0417 0423 0459 0460 0461 0462 0463 0464 0465 0466 0469 0470 0474 0477 0479 0505 0506 0507 0508 0509 0510 0511 0512 0513 0514 0515 0516 0517 DATE: Aug 

### 12/94 SERVICE BULLETIN No. : A300-57-6059 

# I REVISION No. : 04 Feb 22/11 PAGE : 1 Printed in France

# ^A300 -600 SERVICE BULLETIN 0518 0521 0525 0529 0556 0557 0558 0559 0581 0582 0584 0601 0611 0612 0613 0614 0627 0628 0629 0630 0657 0659 0662 0664 0685 0688 0692 0694 0715 0717 0719 0721 0731 0732 0733 0734 0744 0745 0746 0747 0758 0759 0760 0761 0772 0773 0774 0775 0786 0787 0788 0789 0802 0803 0804 0836 0871 0873 0874 0875 0530 0560 0602 0615 0631 0666 0696 

### 0722 0735 0748 0762 0777 0790 0837 0876 0532 0561 0603 0616 0632 0668 0699 0723 0736 0749 0763 0778 0791 0838 0877 0536 0540 0563 0566 0604 0605 0617 0618 0633 0635 0670 0673 0701 0703 0724 0725 0737 0738 0750 0752 0764 0766 0779 0780 0792 0793 0855 0856 0878 0543

0569 0606 0619 0637 0675 0705 0726 0739 0753 0767 0781 0794 0857 0546 0572 0607 0621 0639 0677 0707 0727 0740 0754 0768 0782 0797 0858 0553 0554 0555 0575 0577 0579 0608 0609 061C 0623 0625 062E 0641 0643 0645 0679 0681 0683 0709 0711 0713 0728 0729 073C 0741 0742 0743 0755 0756 0757 0769 0770 0771 0783 0784 0785 0799 0800 0801 0859 0860 0870
(b) The Operator MSN relationship is provided for information onLy and

is correct at the time of issue in accordance with the information avaiLabLe to AIRBUS. Any further 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

AAL 0423 0459 0460 0461 0463 0466 0469 0470 0474 0506 0507 0508 0509 0510 0511 0512 0513 0514 0515 0516 0517 0606 0610 0612 0615 0619 0626 0639 0643 0645 0675
AWW 0354
ABD 0529 0557 0755
AHK 0855 0856 0857 0858 0859 0860 0870 0871
AMU 0677 0743
BKV 0411 0414 0546 0553 0608 

### CES 0521 0525 0532 0707 0725 0732 0741 0746 0754 0763
DATE: Aug 12/94 SERVICE BULLETIN No. : A300-57-6059 

# I REVISION No. : 04 Feb 22/11 PAGE : 2 Printed in France

# A300-600 SERVICE BULLETIN OPERATOR MSN 

### CSN 0733 0734 0739 0750 0756 0762
DLH 0380 0405 0408 0618 0623 0701 0773 F21 0284 0294 0301 0307 0312 0317 0321 0336 0341 0348 0351 FOX 0358 0361 0365 0388 0417 0477 0479 0530 0536 0543 0555 0559 0572 0575 0579 0581 0611 0613 0625 0630 0633 0657 0659 0664 0668 0688 0709 0713 0715 0726 0728 0735 0736 0738 0742 0745 0748 0752 0757 0759 0760 0761 0766 0768 0769 0771 0772 0774 0777 0778 0779 0780 0781 0789 0790 0791 0792 0793 0794 0799 0800 0801 0802 0803 0804 0873 0874 0875 0876 0877 0878 G8E 0462 0465
IRA 0632 0696 0723 0727
JAL 0602 0617 0621 0637 0641 0670 0679 0683 0703 0711 0724 0729 0730 0737 0740 0753 0770 0783 0797 0836 0837 0838 KAC 0344 0673 0694 0699 0719 0721
KAL 0582 0609 0627 0631 0662 0685 0692 0731 LAA 0601 0616
MNB 0758 

### MON 0540 0556 0604 0605 MSR 0561 0607
MXU 0767 0788

DATE: Aug 12/94 SERVICE BULLETIN No. : A300 -57-6059 REVISION No. : 04 Feb 22/11 PAGE : 2a Printed in France

# A300 - 600 SERVICE BULLETIN

OPERATOR MSN
OHY 0584 0603 0744 0747 0749 0764 QTR 0554 0560 0614 

### SUD 0666 0775
TAR 0505 0558 0563
THA 0368 0398 0464 0518 0566 0569 0577 0628 0629 0635 0681 0705 0782 0784 0785 0786 0787
UZB 0717 

### 0722 Effectivity by MSN and Kit/Configuration
None (3) SPARES
None 

### B. CONCURRENT REQUIREMENTS

None 

### C. REASON

(1) Cracks have been found 

### in the rear spar web between Ribs 1 and 2 on both

the in-service aircraft and the fatigue test wing. In aLL reported cases the cracks span the tip of the buiLd sLot and the nearest adjacent fastener hoLe. The cracks are considered to initiate at the tip of the buiLd sLot and to be the result of fatigue damage created by high shear stress experienced during the Landing cycle. The earLiest in-service damage was found on an A300 B2 aircraft which had achieved 21,500 FLight cycles (FC). The crack in the fatigue test wing was discovered at 50,000 simulated FC and monitored for a further 12,000 FC with no evidence of continued crack growth from the hoLe.

DATE: Aug 12/94 SERVICE BULLETIN No. : A300-57 

### -6059 REVISION No. : 04 Feb 22/11 PAGE : 2b

(c)

Printed in France

# ,I 

# A300 

# -boa
SERVICE BULLETIN

Modification No. 11130H5404 (Service Bulletin No. A300-57.6063) has been introduced to enlarge the end of the build sLot and coLd expand seven hoLes adjacent to the buiLd sLot. Embodiment of Modification No. 11130H5404 (Service BuLLetin No. A300-57-6063) extends the inspection threshold. Production Modification 12102H5505 has been introduced on MSN 805. However, to support operations beyond the Design Service Goal (DSG), aircraft post production Modification 12102H5505 will need to be inspected using this Service BuLLetin. (2) Objective/Action

To carry out High Frequency Eddy Current (HFEC) inspections of the aft face of the rear spar web in the area immediately adjacent to the outboard end and bottom face of the buiLd sLot. (3) Advantages

EarLy detection of cracks can prevent the necessity for expensive and time consuming repairs. (4) Operational/Maintenance Consequences

None
D. 

### DESCRIPTION

To accompLish this Service BuLLetin it is necessary to: (1) Open the Main Landing Gear (MLG) doors. (2) Position the access pLatforms and remove the access paneLs. (3) Do an HFEC inspection of the aft face of the rear spar web in the area

immediately adjacent to the outboard end and bottom face of the buiLd sLot. (4) Do any necessary repairs. (5) RepLace access paneLs and remove the access pLatforms.

DATE: Aug 12/94 SERVICE BULLETIN No. : A300-57-6059 REVISION No. : 04 Feb 22/11 PAGE : 3 Printed in France

# 1A300-600 SERVICE BULLETIN (6) Close the MLG doors. E. 

### COMPLIANCE (1) Classification Mandatory (2) Accomplishment TimescaLe

(a) Accomplishment of this Service BuLLetin wiLL be 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 timesca Le. (b) Mandatory HFEC inspections of the aft face of the rear spar web in the area immediateLy adjacent to the outboard end and bottom face of the build slot are required. The inspection thresholds, repeat intervaLs and grace periods are given in Tables 1, 2, 3 and 4.

Table 1 A300F4-605R (Pre Mod. 12699) - Normal Range Operations ThreshoLd Repeat Interval Grace Period Inspection Inspection Method FC FH FC FH FC FH
Pre Mod. 11130 HFEC 21,600 46,600 5,700 12,300 1,000 2,100 (SB A300-57-6063) Post Mod. 11130 (SB A300-57-6063) HFEC 35,900 77,500 6,100 13,100 800 1,700 or Prod Mod. 12102

DATE: Aug 12/94 SERVICE BULLETIN No. : A300-57-6059

REVISION No. : 04 Feb 22/11 

### PAGE : 4
Printed in France

# A300-600 SERVICE BULLETIN TabLe 2 A300F4-605R (Pre Mod. 12699) - Short Range Operations

(Average FLiqht Time < 1.5 hours) ThreshoLd Repeat IntervaL Grace Period Inspection Inspection Method FC FH FC 

## FH FC FH Pre Mod. 11130 HFEC 23,300 34,900 6,100 9,200 1,000 1,600 (SB A300.57-6063) Post Mod. 11130 (SB A300-57-6063) HFEC 38,700 58,100 6,500 9,800 800 1,200 or Prod Mod. 12102

TabLe 3 A30064-600(R). A300C4-600(R) - NormaL Ranae Operations ThreshoLd Repeat IntervaL Grace Period Inspection Inspection Method FC FH FC FH FC FH Pre Mod. 11130 HFEC 18,000 38,800 4,800 10,300 1,000 2,100 (SB A300.57-6063) Post Mod. 11130 (SB A300-57-6063) HFEC 29,900 64,500 5,100 11,000 800 1,700 or Prod Mod. 12102

TabLe 4 A300B4-600(R), A30004-600(R) - Short Range Operations (Average FLiqht Time < 1.5 hours) ThreshoLd Repeat Interval Grace Period Inspection Inspection Method FC FH FC FH FC FH Pre Mod. 11130 HFEC 19,400 29,100 5,100 7,700 1,000 1,600 (SB A300-57-6063) Post Mod. 11130 (SB A300-57-6063) HFEC 32,200 48,400 5,500 8,200 1,000 1,200 or Prod Mod. 12102 (c) The number of touch and go fLights can be negLected when they are Less than five percent of the total number of fLights between two consecutive inspections. DATE: Aug 12/94 SERVICE BULLETIN No. : A300-57-6059 REVISION No. : 04 Feb 22/11 PAGE : 5

Printed in France

# SA300-600 SERVICE BULLETIN When the percentage of touch and go fLights is more than five percent of the total number of fLights between two consecutive inspections, each touch and go fLight beyond five percent has to be counted as a fLight cycLe. A touch and go is a Landing which the aircraft touches the runway and does not come to a fuLL stop before commencing an additional fLight. (d) Modification 11130H5404 (SB A300-57-6063) is recommended for

embodiment at the threshoLds given in TabLe 5. TabLe 5 Recommended Embodiment of Modification 11130H5404 (SB A300-57-6063) A300F4-605R (pre Mod. 12699) A300B4-600(R), A300C4-600(R) NormaL Operation Short Range NormaL Operation Short Range FC FH FC FH FC 

### FH FC FH 21,600 46,600 23,300 34,900 18,000 38,800 19,400 29,100

(e) For aircraft Pre Mod. 11130H5404 (Service BuLLetin

No. A300-57-6063) only which have a crack that does not extend to an adjacent fastener hoLe and has not crossed the boundary shown in Figure 2, operation many continue. But the crack is to be inspected at the repeat intervaLs detaiLed in Table 6 (Refer to NTM 51-10-08, Part 1 Page block 601). TabLe 6 Inspection Requirements of a Known Crack with Limitations A300F4-605R 

### (pre Mod. 12699) A300B4-600(R), A300C4-600(R) Normal Operation Short Range Normal Operation Short Range FC FH FC FH FC FH FC FH 250 540 270 400 200 430 200 300

(f) If the rear spar is repaired in accordance with Repair

Instruction R571 50366. Temporary operation may then continue for the periods detailed in TabLe 7 after which time AIRBUS are to be contacted for an approved repair which is to be embodied before further flight. Table 7 ALLowable FC/FH Limits for Temporary Repair R571 50366 A300F4-605R (pre Mod. 12699) A300B4-600(R), A300C4-600(R) NormaL Operation Short Range NormaL Operation Short Range FC FH FC FH FC FH FC FH 2,500 5,400 2,700 4,000 2,000 4,300 2,100 3,200 DATE: Aug 12/94 SERVICE BULLETIN No. : A300-57-6059 

# I REVISION No. : 04 Feb 22/11 PAGE : 5a
Printed in France

# A3on 

# -boo
SERVICE BULLETIN F

G. APPROVAL STATEMENT

Approved under EASA Design Organization ApprovaL No. EASA 21J.031. If an aircraft Listed in the effectivity has a modification or repair embodied that 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 an adaptation necessary before incorporation of the Service BulLetin. MANPOWER The manpower estimates given in this Service BuLLetin are based on the direct Labour 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 operators' circumstances. The estimates do not incLude the time to prepare, pLan or inspect the work. Manufacture and procurement of parts and tooLs, drying times for paints, sealants, etc, and general administration work are aLso not included. Gain access 0.5

Inspection 2.0 CLose-up 0.5 TOTAL MANHOURS 3.0 ELAPSED TIME (HOURS) 2.0 

### H. WEIGHT AND BALANCE

None 

### I. ELECTRICAL LOAD DATA

None
J. 

### REFERENCES

Aircraft Maintenance ManuaL (AMM)

Non-destructive Testing ManuaL (NTM) Structure Repair ManuaL (SRM) 06-41-57 12-11-28 24-00-00 28-00-00 28-10-00 28-11-22 32-12-11 51-10-01 51-10-07 51-10-08 51-10-13 51-40-21

DATE: Aug 12/94 SERVICE BULLETIN No. : A300-57-6059 REVISION No. : 04 Feb 22/11 PAGE : 5b
Printed in France

# A300-600 SERVICE BULLETIN Service Bulletin (SB) A300-57-6063 Repair Instruction R571 50366 

## K. PUBLICATIONS AFFECTED

None 

## L. INTERCHANGEABILITY/MIXABILITY None

DATE: Aug 12/94 SERVICE BULLETIN No. : A300-57-6059 

# I REVISION No. : 04 Feb 22/11 PAGE : 6

Printed in France

# © 

# A300_600
SERVICE BULLETIN


### 2. MATERIAL INFORMATION A. MATERIAL - 

### PRICE AND AVAILABILITY None 

### B. INDUSTRY SUPPORT INFORMATION None C. LIST 

### OF COMPONENTS None D. LIST OF MATERIALS - OPERATOR SUPPLIED None E. PARTS TO BE RE IDENTIFIED BY THE OPERATOR None F. TOOLING - PRICE AND AVAILABILITY None G. SPECIAL TOOLS None

DATE : Aug 12/94 SERVICE BULLETIN No. : A300-57-6059 

# I REVISION No. : 04 Feb 22/11 Page : 7 Printed in France © Airbus Industrie 1994, All rights reserved

# 0 A300-600
SERVICE BULLETIN

This Page IntentionaLLy Left Blank

DATE : Aug 12/94 SERVICE BULLETIN No. : 

### A300-57-6059 

# I REVISION No. : 04 Feb 22/11 Page : 8 Printed in France © Airbus Industrie 1994, All rights reserved

# 0 A300-600
SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURE. WARNING : MAKE SURE THAT THE GROUND SAFETY LOCKS ARE CORRECTLY INSTALLED

ON THE LANDING GEAR. WARNING : MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE

IN POSITION BEFORE YOU START A TASK ON OR NEAR: - THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES - THE LANDING GEAR AND RELATED DOORS - COMPONENTS THAT MOVE MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS. (1) Preparation (a) Electrically ground the aircraft (Refer to AMM 24-00-00 Page bLock 301). (b) Open the MLG doors (Refer to AMM 32-12-11 Page block 301). (c) Put the access platforms in position. 

### (d) Remove the access panels 571AB (LH) and 671AB (RH) (Refer to AMM 06-41-57 Page block 1). (2) Standard Practices (a) Removal and installation of fasteners (Refer to SRM 51-40-21 Page bLock 1). B. INSPECTION NOTE : The worksteps that follow are for both the LH and RH wings. (1) Do an HFEC inspection of the aft face of the rear spar web in the area immediately adjacent to the outboard end and bottom face of the buiLd slot (Refer to NTM 51-10-08, Part 6 Page bLock 601). Refer to Figure 1 and Figure 2. (a) If a crack is indicated, do an HFEC inspection to discover the extent of cracking (Refer to NTM 51-10-07, Part 6 Page bLock 601). (b) If the crack extends to an adjacent fastener hoLe, do the actions in paragraph C. REPAIR. (2) For aircraft Pre. Mod. 11130H5404 (Service Bulletin No. A300-57-6063) only. (a) If the crack does not extend to an adjacent fastener hoLe and has not crossed the boundary shown in Figure 2, operation may continue with the folLowing Limitations : 1 The crack is inspected at the repeat intervals detailed in Table 6 (Refer to NTM 51-10-08, Part 1 Page bLock 601).
DATE : Aug 12/94 SERVICE BULLETIN No. : A300-57-6059 

# I REVISION No. : 04 Feb 22/11 Page : 9 Printed in France ©Airbus Industrie 1994, All rights reserved

# OA300-600 SERVICE BULLETIN

Table 6 Inspection Requirements of a Known Crack with Limitations A300F4-605R (pre-mod. 12699) A300B4-600(R), A30004-600(R) NormaL Operation Short Range NormaL Operation Short Range FC EH FC EH FC EH FC FR 250 540 270 400 200 430 200 300 (b) If the crack has extended beyond the boundary shown in Figure 2, 

# I contact AIRBUS for an approved repair which is to be embodied before further flight. (c) If the crack has extended into 

### an adjacent fastener hoLe, but not

beyond the hoLe, carry out the actions in paragraph C. REPAIR. (3) For aircraft post Mod. 11130H5404 (Service Bulletin No. A300-57-6063)

only. (a) If the crack has extended beyond the boundary shown in Figure 2,

contact AIRBUS for an approved repair which is to be embodied before further fLight. (b) If the crack has extended into an adjacent fastener hoLe, but not

beyond the hoLe, carry out the actions in paragraph C. REPAIR. (4) If no crack is indicated, refer to paragraph E. and cLose up. C. 

### REPAIR WARNING : OBSERVE THE SAFETY PRECAUTIONS IN AMM 28-00-00 Page bLock 301. (1) Defuel the aircraft (Refer to AMM 28-10-00 Page bLock 301). (2) Remove the manhole covers 542CB and 642CB (Refer to AMM 28-11-22 Page

bLock 401). (3) Remove the fastener and do an HFEC Rototest inspection to confirm that

the crack has not grown beyond the hoLe (Refer to NTM 51-10-08, Part 6, Procedure B). (a) If the crack extends beyond the hoLe, contact AIRBUS for an

approved repair which is to be embodied before further fLight.

DATE: Aug 12/94 SERVICE BULLETIN No. : A300-57-6059 REVISION No. : 04 Feb 22/11 PAGE : 10
Printed in France

# A300 

# -boo SERVICE BULLETIN
(b) If the crack does not extend beyond the hole, the rear spar may be

repaired in accordance with Repair Instruction R571 50366. Temporary operation may then continue for the periods detailed in TabLe 7 after which time AIRBUS are to be contacted for an approved repair which is to be embodied before further fLight. TabLe 7 Allowable FC/FH Limits for Temoorary Reoair R571 50366 A300F4-605(R) (pre-mod. 12699) A300B4-600(R), A300C4-600(R) NormaL Operation Short Range NormaL Operation Short Range FC EH 

### FC EH FC EH FC EH 2,500 5,400 2,700 4,000 2,000 4,300 2,100 3,200 

### D. TEST

None 

### E. CLOSE UP

(1) Make sure that the work areas are cLean and cLear of tools and other

items of equipment. (2) If the aircraft has been repaired in accordance with the actions in

paragraph C. REPAIR, do the foLLowing: (a) InstaLL the manhoLe covers 542CB and 642CB (Refer to AMM 28-11-22

Page bLock 401). (b) Refuel the aircraft (Refer to AMM 12-11-28 Page block 1). (c) Do an external inspection of the manhoLe covers for fuel Leaks. (3) InstaLL the access paneLs 

### 571AB (LH) and 671AB (RH) (Refer to AMM 06-41-

57 Page bLock 1). (4) Remove the access platforms. (5) CLose the MLG doors (Refer to AMM 32-12-11 Page bLock 301). (6) Report aLL findings, including niL findings, to AIRBUS (Refer to Figure 3 and SRM 51-10-13 Page bLock 1)_ F. 

### DOCUMENTATION Write in the applicable aircraft records that you have done aLL the work given in this Service BuLLetin. DATE: Aug 12/94 SERVICE BULLETIN No. : A300.57-6059 REVISION No : 04 Feb 22/11 PAGE 11
Printed in France

# So A300-600
SERVICE BULLETIN

RH WING SIMILAR o^

REAR SPAR AFT FACE 

### © o 0 P 0 0 0 O O O O O O O O 0 00 0 000 

# a 1 g BUILD SLOT

VIEW SHOWN PRE OUTBOARD MOD.No.11130H5404 

### (PRE SB A300-57-b063)



# C

10 REFER TO FIGURE 2 TYPICAL CRACK N- FOR VIEW C L ti

Figure 1 Sheet 1 Location of Inspection Area


### DATE : Aug 12/94 SERVICE BULLETIN No. : A300-57-6059 I REVISION No. : 04 Feb 22/11 Page 12
Printed in France © Airbus Industrie 1994, All rights reserved

# A300-600 SERVICE BULLETIN

BtJ LD SLOT

\. °^ cco^.-000

^ n a0o'ac op 

# ® J 

# !

LH %"G Sf IOW 9H NO SI/ LAR

INBD ^^/ tiPARJFTFACE



### I'3 €i 

# Q

B RE-FRDF{4w48LOT lNBD ` EI VII W SHUY.1 T MOD N I 14 -54 IPOST SE A3;:6-57-Ctt631 roorE; FIFER ro FIGURO 2 FOR VIEW G.



### Figure 1 Sheet 2 Location of Inspection Area

DATE: Aug 12/94 SERVICE BULLETIN No. : A300-57-6059 REVISION No. : 04 Feb 22/11 PAGE 12a Printed in France

# J A300-600
SERVICE BULLETIN



### BOUNDARY FOR CRACK GROWTH AREA TO BE INSPECTED 

### BUILD SLOT

i
18.Omm 

### (0.7in) —^ 56 .Omm



### (2.2în) 228.6mm {9.Din)
----- OUTBOARD LEFT WING



### PRE MODIFICATION No. 11130H5404 (PRE SB A300-57-6063)

a

U ah Ln 0 10 

### r
u-,Na 

### Figure 2 Sheet 1 Area to be Inspected
DATE : Aug 12/94 SERVICE BULLETIN No. : A300-57-6059 

### REVISION No. : 04 Feb 22/11 Page 13 Printed in France © Airbus Industrie 1994, All rights reserved

# A300-600 SERVICE BULLETIN

MEA lo HET^C7 su1wn star



# Q Q 

# oo

f[-Po6m © SLAT iNBd7 F PO$T OC TUN hk:. t? 13Q 15 4 POST SB A'M-57-8 1



### Figure 2 Sheet 2 Area to be Inspected

DATE: Aug 12/94 SERVICE BULLETIN No. : A300-57-6059 REVISION No. : 04 Feb 22/11 PAGE : 13a Printed in FranceDB7 57 6059 AE AA A

A300 SB No. A/C MSN FLIGHT CYCLES FLIGHT HOURS

FINDINGS A300-57-6059

YES ❑ NO ❑ INSPE 

### C TI 

### ON REPORT DATE OF INSPECTION INSPECTION METHOD : VISUAL NDT (SPECIFY METHOD) IF YES, CRACK CONFIRMED BY (SPECIFY METHOD) ILLUSTRATION WHICH DEFINES THE PARAMETER TABLE TO INSERT RECORDS OF REQUIRED TO BE RECORDED (E.G. CRACK LENGTH, CRACK PARAMETERS (E.G. HOLE No., CRACK LENGTH, DEPTH, EDGE MARGIN ETC.). REPAIR BY OVERSIZE ETC.).

PLEASE LIST OTHER FINDINGS, EXCLUDING CRACK. AREA REPAIRED IN ACCORDANCE WITH, SB 

# a SRM 

# El AIB INSTRUCTION ❑ PU m
H 

# o z z o

0

o Q

N N a
m 

# (n

N 

## 0

0) 10 CD m

m W c r r rn
H z z o T 

# min (D C C

- ) -, 00 âW (f) (I) 3 . (DO (DO 

# F

W
u, o' 0 u, 10 cn m C 

# A

tu 

# O c 

# O

r 

# N m

# © A300-600
SERVICE BULLETIN REPORTING SHEET TITLE : WINGS - INSPECT REAR SPAR FOR CRACKS AT BUILD SLOT MODIFICATION No. : None
Please complete the appropriate item : Accepted for embodiment ...........YES/NO Embodied on MSN ..................................

.................................................. Rejected YES/NO If YES, pLease provide short explanation FromAirline . .............................................................. Name/Title . .............................................................. Signature . ..................... Date . ............. Important Information : This SB 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 SB 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 : AI/SE-D32 TechnicaL Data and Documentation Services FAX : (+33) 5 61 93 28 06 or via your Resident Customer Support Office. ALternativeLy, SB Lists via Letters or fax are also accepted.

7 DATE : Aug 12/94 SERVICE BULLETIN No. : A300-57-6059 

# I REVISION No. : 04 Feb 22/11 Page : 1 of 1
Printed in France © Airbus industrie 1994, All rights reserved

# j A300-600
SERVICE BULLETIN QUALITY PERCEPTION FORM
Use this form to tell us what is your perception of the quaLity of this Service Bulletin. The reported data that you provide us wiLL be used to analyse areas of difficulties and to take corrective action to further improve the quaLity of our Service BuLLetins. We thank you for the time you have taken in completing this form. (PLease rate on a scale of 1 to 4, with 4 being the highest score)

— Quality rating of this SB 4 3 2 1

— QuaLity rating of the Accomplishment Instructions 4 3 2 1

— QuaLity rating of the Illustrations 4 3 2 1

— Is this SB easy to understand ? Y / N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue. Planning Material Instructions X Effectivity X Kit Content X Preparation X Reason X List of Materials X Mod/Inspection X Manpower Operator Supplied X Test X References X Re—identification X Close—up X Publication X Tooling X Illustrations Comments

Operator : Date: Name/Title PLease return this form to AIRBUS CUSTOMER SERVICES DIRECTORATE 1 

### Rond Point Maurice 

### Bellonte 31707 BLAGNAC 

### CEDEX Attn : SDC-32 Service BuLLetins Management FAX : (33) 5 61 93 42 51 or via your Resident Customer Support Office.

7 DATE : Aug 12/94 SERVICE BULLETIN No. : A300-57-6059 

# I REVISION No. : 04 Feb 22/11 Page : 1 of 1
Printed in France © Airbus Industrie 1994, All rights reserved