# 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 - OUTER WING - INSPECT FRONT AND REAR SPAR BOTTOM BOOM - INBOARD AND OUTBOARD OF RIB 9 MODIFICATION No. : None This page transmits revision No. 04 of Service BuLLetin A300-57.6037. 

### ADDITIONAL WORK No additionaL work is required by this revision for aircraft inspected by any previousrevision

### REASON This Service BuLLetin has been issued at revision 04 to inform Operators that revised inspection threshoLds, repeat intervaLs and grace periods have been introduced to support aircraft operations to Extended Service GoaL 2 (ESG2). The new accomplishment timescaLes are different for normaL range or short range operations. ALso the Repair procedure has been revised. 

### CHANGES SUMMARY:

. AIRBUS address has been amended. - REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Text has been amended to add reference to the inspection threshoLds and repeat intervaLs. Modification 08842H5298 (Service BuLLetin A300-57-6039) sentence added.
DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 REVISION No. : 04 Feb 24/11 PAGE : 1 Printed in France

# îA300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

- EVALUATION TABLE . Potential AD changed to YES. - 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. (2)(a) 

### Effectivity has been 

### updated. Para. (2)(b) Effectivity has been updated. DESCRIPTION . Para. (9) reference to functionaL test deLeted and system Leak test added. COMPLIANCE ACCOMPLISHMENT TIMESCALE Para. (a) Airworthiness Directive (AD) statement has been updated. Para. (b) Text and Tables have been added to incLude the revised inspection

thresholds, repeat intervaLs and grace periods. . Para. (c) Text and table have been added for recommended embodiment of Mod.

08842H5298 (SB A300-57-6039). - APPROVAL . Approval statement has been amended. REFERENCES . References have been amended. DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 REVISION No. : 04 Feb 24/11 PAGE : 2 Printed in France

# A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

- ACCOMPLISHMENT INSTRUCTIONS - INSPECTION • Para. (2)(c) New paragraph reLated to post mod. 08842H5298

(SB A300-57-6039) has been added. - REPAIR . Repair procedure has been revised. - TEST System Leak test has been revised. FIGURE 4 . Figure 4 has been deLeted and Figure 6 becomes Figure 4. - FIGURE 5 . Figure 5 has been deLeted and new Figure has been added. REPORTING SHEET: . Airbus Industrie 

### becomes Airbus. AIRBUS address has been amended.
QUALITY PERCEPTION FORM:

AIRBUS address has been amended. FILING INSTRUCTIONS 1. Remove and destroy pages 1, 2 and 3 of the Summary, pages 1, 2, 3, 4, 5, 6, 9, 10, 11, 12, 13, 14, 15, 16, 19/20, 21/22 and 23 of the Service BuLLetin, page 1 of 1 of the Reporting Sheet and page 1 of 1 of the QuaLity Perception Form. 2. Insert pages 1, 2 and 3/4 of the Summary, pages 1, 2, 2a, 2b, 3, 4, 5, 6, 9, 10, 11, 12, 13, 14, 14a, 14b, 14c, 14d, 15, 16, 16a, 16b, 16c, 16d, 19 and 20 of the Service BuLLetin, page 1 of 1 of the Reporting Sheet and page 1 of 1 of the QuaLity Perception Form. DATE: Aug 01/94 SERVICE BULLETIN No. : A300.57-6037 REVISION No. : 04 Feb 24/11 PAGE : 3 Printed in France

# A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

Put this Revision TransmittaL Sheet in front of the Service BuLLetin. 

### HISTORY OF PREVIOUS REVISIONS This is only appLicabLe for Revision 04 and subsequent. If information is required for revisions issued previous to this, please check your copies of Revision TransmittaL Sheet or contact AIRBUS. 

### REVISION SEQUENCE ORIGINAL : 

### Aug 01/94 

### REVISION No. : Dl - 

### Aug 31/95 REVISION No. : 

### 02 - Jan 

### 09/01 REVISION 

### No. : 

### 03 - Jan 11/02 REVISION 

### No. : 

### 04 - Feb 24/11

DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 REVISION No. : 04 Feb 24/11 PAGE : 4 Printed in France

# A300-600 SERVICE BULLETIN SUMMARY

AIRBUS CUSTOMER SERVICES DIRECTORATE 1 

### Rond Point Maurice 

### Bellonte 31707 BLAGNAC 

### CEDEX FRANCE 

### Te L : (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 - WINGS - OUTER WING - INSPECT FRONT AND REAR SPAR BOTTOM BOOM - INBOARD AND OUTBOARD OF RIB 9 MODIFICATION No. : None 

### REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During full scale fatigue tests, cracks were found starting from the bolt holes, inboard and outboard of rib 9, on the front and rear spar bottom booms at 58,650 simuLated Flight CycLes (FC). There have been six reports of cracks found in the front and rear spar bottom booms at the rib 9 joint on A300-B2 aircraft 

### in service. The cracks were found at between 19,500 FC and 29,700 FC. There is a possibility of similar cracks on A300-600 aircraft which would need Lengthy and expensive repairs. Mandatory uLtrasonic inspections of the front and rear spar bottom boom inboard and outboard of rib 9 are to be done at the thresholds and repeat intervals given in the Accomplishment TimescaLe. Modification No. 08842H5298 (Service BuLLetin No. A300-57.6039) introduces first oversize fasteners with an option for fitting second oversize fasteners if first oversize fasteners have already been installed.

DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 REVISION No. : 04 Feb 24/11 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 YES ETOPS AFFECTED NO STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO
KIT PRICE (USD) NO KIT EFFECTIVITY This Service BuLLetin is applicable to these operators: AAL, AWW, ABD, AMU, BKV, CES, 

### DLH, F21, FDX, G8E, IRA, JAL, KAC, KAL, LAA, MON, 

### NSR, OHY, QTR, SUD, 

### TAR, THA, UZB NOTE : This Service BuLLetin is applicable to aircraft pre-modification

10161H5329_ The Modification 10161H5329 is embodied before delivery on aircraft MSN 0723 and subsequent. CONCURRENT. REQUIREMENTS None REFERENCES/REPERCUSSIONS TFU : None OEB : 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 OBRM : No

DATE : Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 REVISION No. : 04 Feb 24/11 Page : 2 Printed in France ©Airbus industrie 1994, Al rights reserved

### WA 

# L'7a Ti 

## WTaTa
SERVICE BULLETIN SUMMARY MANPOWER TOTAL MANHOURS 16.0 ELAPSED TIME (HOURS) 6.0 MATERIAL INFORMATION AIRCRAFT DATA None APPENDICES None

DATE : Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 REVISION No. : 04 Feb 24/11 Page : 3/4 Printed in France ©Airbus Industrie 1994, Al rights reserved

# 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 -- OUTER WING - INSPECT FRONT AND REAR SPAR BOTTOM BOOM - INBOARD

AND OUTBOARD OF RIB 9 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 written consent. 1. 

### PLANNING INFORMATION
A. 

### EFFECTIVITY (1) ModeLs B4-601, B4-603, B4-605R, B4-620, B4-622, B4.622R, C4-620 (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 0518 0521 0525 0529 DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57.6037 

# I REVISION No. : 04 Feb 24/11 PAGE : 1 Printed in France

# $A300 

# -boo
SERVICE BULLETIN 0530 0532 0536 0540 0543 0561 0563 0566 0569 0572 0604 0605 0606 0607 0608 0618 0619 0621 0623 0625 0637 0639 0641 0643 0645 0677 0679 0681 0683 0685 0709 0711 0713 0715 0717 0546 0553 0575 0577 0609 0610 0626 0627 0657 0659 0688 0692 0719 0721 0554

0579 0611 0628 0662 0694 0722 0555 0556 0581 0582 0612 0613 0629 0630 0664 0666 0696 0699 0557

0584 0614 0631 0668 0701 0558 D601 0615 0632 0670 0703 0559 0560 0602 0603 0616 0617 0633 0635 0673 0675 0705 0707



### NOTE : This Service BuLLetin is appLicabLe to aircraft premodification 10161H5329. The Modification 10161H5329 is embodied before deLivery on aircraft MSN 0723 and subsequent. (b) Effectivity by Operator 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 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

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
AAW 0354
ABD 0529 0557
AMU 0677
BKV 0411 0414 0546 0553 0608 

### CES 0521 0525 0532 0707
DLH 0380 0405 0408 0618 0623 0701 F21 0284 0294 0301 0307 0312 0317 0321 0336 0341 0348 0351

DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 REVISION No. : 04 Feb 24/11 PAGE : 2 Printed in France

# ^A3O0-boo SERVICE BULLETIN

OPERATOR MSN
FDX 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

G8E 0462 0465
IRA 0632 0696
JAL 0602 0617 0621 0637 0641 0670 0679 0683 0703 0711
KAC 0344 0673 0694 0699 0719 0721
KAL 0582 0609 0627 0631 0662 0685 0692
LAA 0601 0616 

### MON 0540 0556 0604 0605 MSR 0561 0607
OHY 0584 0603 QTR 0554 0560 0614 

### SUD 0666
TAR 0505 0558 0563
THA 0368 0398 0464 0518 0566 0569 0577 0628 0629 0635 0681 0705
UZB 0717 0722
(c) Effectivity by MSN and Kit/Configuration
None 

### DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 REVISION No. : 04 Feb 24/11 PAGE : 2a Printed in France

## S 

# A300-600 SERVICE BULLETIN (3) Spares
None
B. 

### CONCURRENT REQUIREMENTS
None

DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 

# I REVISION No. : 04 Feb 24/11 PAGE : 2b Printed in France

# A300-600

SERVICE BULLETIN

C. REASON (1) History During full scale fatigue tests, cracks were found starting from the bolt holes, inboard and outboard of rib 9, on the front and rear spar bottom booms at 58,650 simulated Flight Cycles (FC). There have been six reports of cracks found in the front and rear spar bottom booms at the rib 9 joint on A300-B2 aircraft in service. The cracks were found at between 19,500 FC and 29,700 FC. There is a possibility of similar cracks on A300-600 aircraft which would need Lengthy and expensive repairs. Modification No.08842H5298 (Service Bulletin No.A300-57-6039) introduces first oversize fasteners with an option for fitting second oversize fasteners if first oversize fasteners have already been installed. This modification does not take the aircraft to design Life goals. (2) Objective/Action To do an ultrasonic inspection of 2 hoLes inboard and 2 hoLes outboard of rib 9 on the front and rear spar bottom booms (8 hoLes per wing). (3) Advantages Early detection of cracks can prevent expensive and time consuming repai rs. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to: (1) Defuel the aircraft. (2) Remove the manhole covers 542EB, 543AB, 642EB and 643AB. (3) If required for access, remove the refuel/defueL pipes 

### in the inspection area. (4) Do an ultrasonic inspection of the fastener holes for cracks. (5) Do any necessary repairs. (6) If removed, install the refuel/defueL pipes in the inspection area. (7) InstalL the manhole covers 542EB, 543AB, 642EB and 643AB. (8) Refuel the aircraft. (9) If the refuel/defuel pipes were removed/installed, do a system Leak test of the refuel/defueL system. E. COMPLIANCE (1) Classification Mandatory

DATE : Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 

# I REVISION No. : 04 Feb 24/11 Page : 3 Printed in France © Airbus Industrie 1994, AlI rights reserved

# A300 

# -boa
SERVICE BULLETIN (2) AccompLishment TimescaLe

(a) Accomplishment of this 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. (b) Mandatory instructions of the front and rear spar bottom booms,

inboard and outboard of Rib 9, are to be done at or before the threshoLds and subsequent repeat intervals given in Tables 1 and 2.

TabLe 1 NormaL Range Operations ThreshoLd Repeat IntervaL Grace Period Inspection Inspection Method 

### FC FH FC FH FC FH Pre Mod. US 14,100 30,400 3,900 8,400 1,600 3,400 08842 Post Mod. 08842 or US 14,100 30,400 3,900 8,400 1,600 3,400 R571 40657 TabLe 2 Short Range Operations (Average Flight Time < 1-5 hours) ThreshoLd Repeat Interval Grace Period Inspection Inspection Method FC FH FC FH FC FH Pre Mod. US 15,200 22,800 4,200 6,300 1,700 2,500 08842 Post Mod. 08842 or US 15,200 22,800 4,200 6,300 1,700 2,500 R571 40657 (c) Modification 08842H5298 (SB A300-57-6039) is recommended for embodiment at the threshoLds given in TabLe 3. TabLe 3 Recommended Embodiment of Modification 08842H5298 (SB A300-57-6039) Embodiment Point NormaL Operation Short Range FC FH FC FH 14,100 30,400 15,200 22,800 DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57.6037 REVISION No. : 04 Feb 24/11 PAGE : 4 Printed in France

# A300 -600 SERVICE BULLETIN
(d) The number of touch and go flights can be ignored when they are

Less than five percent of the totaL number of fLights between two consecutive inspections. 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 in which an aircraft touches the runway and does not come to a fuLL stop before commencing an additional f Light. 

## F. APPROVAL Approved under EASA Design Organisation Approval EASA.21J.031. If the aircraft Listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, 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 Labour cost to do the work. These estimates assume that the work wiLL be done by experience 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 tools, drying time for paints, sealants etc and generaL administration work are aLso not included. Manhours:

Get access Inspection
Test CLose up
TOTAL MANHOURS ELAPSED TIME (HOURS)

DATE: Aug 

### 01/94 7.0 1.0 1.0 7.0 16.0 6.0

SERVICE BULLETIN No. : A300.57-6037 

# I REVISION No. : 04 Feb 

### 24/11 PAGE : 5 Printed in France

# A300-600 SERVICE BULLETIN

H.

I

J

K

L. 

### WEIGHT AND BALANCE

Not changed 

### ELECTRICAL LOAD DATA
None 

### REFERENCES Aircraft Maintenance Manual (AMM)

Structural Repair ManuaL (SRM)

Nondestructive Testing ManuaL (NTM)
Service Bulletin (SB) Repair Instruction Maintenance Review Board (MRB) Airworthiness Directive 

### PUBLICATIONS AFFECTED
None 

### INTERCHANGEABILITY/MIXABILITY
None 12-11-28 24-00-00 24-41-00 28.00-00 28-10-00 28-11-22 28.11-29 28-25-15 28-25-18 28-25-22 28-42-44 32-12-11 32-12-11 51-10-13 51-40 

### -21 51-40-44 51-40-47 51-43-00 51-75-10 51.75-20 51-76-20 51-10-01 Part 6 51-10-08 Part 6 57-21-04 Part 4 A300-57-6039 R571 40141 Section D, Para.8 94-208-169 (B)

DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 REVISION No. : 04 Feb 24/11 PAGE : 6 Printed in France

# A300-600
SERVICE BULLETIN
2. MATERIAL INFORMATION A. MATERIAL — PRICE AND AVAILABILITY (1) Material None (2) Price and Availability None B. INDUSTRY SUPPORT INFORMATION NOTE : Oversize fasteners (Operator supply) are Listed below. The

quantities required will depend on damage found.

Hole Nominal

Fastener First Oversize Fastener Second Oversize Fastener Nut Washer S NSA5486V6R18N NSA5487V6R18N NSA54SSV6R18N NSA5472-6K7 NSA5353DO6B T NSA5486V7R19N NSA5487V7R19N NSA5488V7R19N NSA5472-7K7 NSA5353DO7B U NSA5486V7R24N NSA5487V7R24N NSA5488V7R24N NSA5472-7K7 NSA5353D07B V NSA5486V6R21N NSA5487V6R21N NSA5488V6R21N NSA5472-6K7 NSA5353DO6B W NSA5486V6R18N NSA5487V6R18N NSA5488V6R18N NSA5472-6K7 NSA5353DO6B X NSA5486V7R21N NSA5487V7R21N NSA5488V7R21N N5A5472-7K7 NSA5353D07B Y NSA5486V7R21N NSA5487V7R21N NSA5488V7R21N NSA5472-7K7 NSA5353D07B Z NSA5486V6R18N NSA5487V6R18N NSA5488V6R18N NSA5472-6K7 NSA5353D06B
C. LIST OF COMPONENTS None D. LIST OF MATERIALS -- OPERATOR SUPPLIED Refer to para.2.B.INDUSTRY SUPPORT INFORMATION. E. PARTS TO BE RE IDENTIFIED BY THE OPERATOR None F. TOOLING — PRICE AND AVAILABILITY None G. SPECIAL TOOLS None

DATE . Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 REVISION No. : 04 Feb 24111 Page 7 Printed in France ©Airbus Industrie 1994, AlI rights reservedSERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Aug 01/94 

### SERVICE BULLETIN 

### No. : A300-57-6037 

# I REVISION No. : 04 Feb 24/11 Page : 8
Printed in France ©Airbus Industrie 1994, Al rights reserved

# W A300--600

SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS A. 

### GENERA L WARNING : OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE

REFERENCED PROCEDURES. WARNING : PUT THE SAFETY DEVICES AND WARNING NOTICES IN POSITION BEFORE

YOU START A TASK ON OR NEAR: - THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES - LANDING GEAR AND RELATED DOORS - COMPONENTS THAT MOVE. WARNING : OBEY ALL THE FUEL SAFETY PROCEDURES (REFER TO AMM 28-00-00

Page block 301). (1) Preparation (a) Electrically ground the aircraft (Refer to AMM 24-00-00 Page block 301). (b) DefueL the aircraft (Refer to AMM 28-10-00 Page bLock 301 and AMM 28-25-00 Page bLock 301). (c) Put access platforms in position. (d) Remove the manhole covers 542EB, 543AB, 642EB and 643AB (Refer to AMM 28-11-22 Page bLock 401). (e) Identify the fastener hoLes to be inspected (Refer to Figure 1 and Figure 2). (f) If required, for better access to remove the sealant in the inspection area, remove and retain the applicable refueL/defueL pipes (Refer to Figure 3 and ANN 28-00-00 Page bLock 401). (g) Remove the seaLant from the spar fLanges at the bolt hoLes to be inspected. An area of 25.0mm (1.0in.) should be removed from the inboard and outboard side of the bolts. (2) Standard Practices (a) For fastener removal and installation refer to SRM 51-40-21 Page block 1. (b) For hole and drill data refer to SRM 51-40-44. (c) For countersinking procedures refer to SRM 51-40-47 Page bLock 1. (d) For torque values refer to SRM 51-43-00 Page block 1. (e) For the removal and application of seaLant refer to SRM 51-76-20 Page bLock 201. (f) For the removal of paint coatings refer to SRM 51-75-20 Page bLock 201. (g) For the repair and replacement of paint coatings refer to SRM 51-75-10 Page bLock 201. DATE : Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 

# I REVISION No. : 04 Feb 24/11 Page : 9
Printed in France ©Abus Industrie 1994, All rights reserved

# A300-600 SERVICE BULLETIN

B. 

### INSPECTION

(1) Do an inspection of the front and rear spar flange, adjacent to the fastener hoLes (Refer to 

### NTM 57-21-04, Part 4 if boLts are instaLLed, or NTM 51-10-01, Part 6 procedure C if boLts are removed), Refer to Figure 1 and Figure 2. (2) If a crack is detected, refer to paragraph 3.C.REPAIR and do one of the applicable worksteps that follows before the next flight: (a) If modification 08842H5298 (SB A300-57-6039) is not to be accompLished at the same time as this Service BuLLetin do the worksteps in para.C.REPAIR (1). (b) If modification 08842H5298 (SB A300-57-6039) is to be accompLished at the same time as this Service BuLLetin do the worksteps in para.C.REPAIR (2). 

# I (c) If modification 08842H5298 (SB A300-57-6039) has already been embodied do the worksteps in para.C.REPAIR (3). (3) If a crack is not detected, do paragraphs 3.D.TEST and 3.E.CLOSE UP.
C. 

### REPAIR CAUTION WHEN YOU DO ANY OF THE REPAIRS THAT FOLLOW, IT IS IMPORTANT THAT

ONLY ALTERNATE FASTENERS ARE REMOVED SO THAT CLAMPING IS MAINTAINED AT ALL TIMES. SUITABLE SLAVE BOLTING IS PERMITTED. 

### CAUTION ALL OVERSIZING INSTRUCTIONS IN THE REPAIR INSTRUCTIONS THAT FOLLOW

APPLY TO HOLES WHICH HAVE NOT BEEN OVERSIZED BEFORE. ANY HOLES FOUND TO HAVE BEEN OVERSIZED BEFORE MUST BE REPORTED TO AIRBUS BEFORE ANY FURTHER ACTION IS TAKEN. 

# I (1) To repair cracked fastener hoLes found during the inspection, do the worksteps that foLLow: (a) Remove the fastener where a crack was detected and do a roto 

### -probe inspection of the fastener hoLe to confirm the indication (Refer to NTM 51-10-01, Part 6, Procedure C). 1 If a crack is not indicated, ream the hoLe to the first oversize diameter and do a roto 

### -probe inspection of the reamed hoLe (Refer to NTM 51-10-01, Part 6, Procedure C). DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 REVISION No. : 04 Feb 24/11 PAGE : 10 Printed in France

# A300-600 SERVICE BULLETIN a If a crack is not indicated, instaLL the correct diameter fastener and continue with the inspection programme. b If a crack is indicated, do the worksteps in para. 

### C.(1) (b). 2 If a crack is indicated, do the worksteps in para. 

### C.(1) (b). (b) Remove the four adjacent fasteners on both sides of the cracked fastener hole. For hoLes which contain taper-Lok fasteners do workstep C.(1) (c). For hoLes which contain paraLLeL fasteners do workstep C.(1) (d). (c) Taper-Lok HoLes

Inspect the hoLes, where fasteners were removed in workstep C.(1) (b). for cracks (Refer to NTM 51-10-01, Part 6, Procedure C). If cracks are not indicated record aLL findings and contact AIRBUS for an approved repair to be embodied before the next fLight. b If cracks are indicated, do the worksteps in para.C.(1) (c) 2. 2 Inspect the top surface of the structure around the hoLe(s) circumference for cracks (Refer to 

## NTM 51-10-08, Part 6).

a If a crack is indicated, record aLL findings and contact AIRBUS for an approved repair to be embodied before the next fLight. b If additional cracks are not indicated, do the worksteps in para.C.(1) (c) 3 and 4. CAUTION 

### THE OVERSIZING PROCEDURE THAT FOLLOWS IS FOR HOLES WITH

NOMINAL FASTENER DIAMETERS OF 0.25 TO 0.75IN. (6.35 TO 19.05MM) ONLY. CAUTION 

### THE OVERSIZING THAT FOLLOWS MAY ONLY BE DONE IF THE

HOLE EDGE DISTANCE IS NOT LESS THAN 1.75D AND THE HOLE CENTER PITCH IS NOT LESS THAN 3.5D. 3 Ream the cracked fastener hoLe(s) to the first oversize diameter.
DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 REVISION No : 04 Feb 24/11 PAGE : 11 Printed in France

# A300-600 SERVICE BULLETIN 4 Inspect the oversize fastener hoLe(s) for cracks (Refer to

NTM 51-10-01, Part 6, Procedure C).
a If the cracks are completely removed by the first

oversizing, record aLL findings and actions taken and contact AIRBUS for an approved repair to be embodied before the next fLight. b If a crack is stiLL indicated, do the worksteps in

para.C.(1) (c) 5 and 6. 5 Ream the cracked fastener hoie(s) to the second oversize

diameter. 6 Inspect the oversize fastener hoLe(s) for cracks (Refer to

NTM 51-10-01, Part 6, Procedure C). Record aLL findings and actions taken and contact AIRBUS for an approved repair to be embodied before the next fLight. (d) ParalLeL HoLes

1 Inspect the hoLes, where fasteners were removed in workstep

C.(1) (b), for cracks (Refer to NTM 51-10-01, Part 6, Procedure A)-

a If cracks are not indicated, record aLL findings and

contact AIRBUS for an approved repair to be embodied before the next fLight. b If a crack is indicated, do the worksteps in

para.C. (1) (d) 2. 2 Inspect the top surface of the structure around the hoLe(s)

circumference for cracks (Refer to 

### NTM 51-10-08, Part 6).
a If a crack is indicated, record aLL findings and

contact AIRBUS for an approved repair to be embodied before the next fLight. b If additionaL cracks are not indicated at the top

surface to the worksteps in para.C.(1) 

### Cd) 3 and 4.

DATE: Aug 01/94 SERVICE BULLETIN No. : 

### A300-57-6037 REVISION No. : 04 Feb 24/11 PAGE : 12 Printed in France

# A300-600 SERVICE BULLETIN



### CAUTION THE OVERSIZING THAT FOLLOWS MAY ONLY BE DONE IF THE

HOLE EDGE DISTANCE IS NOT LESS THAN 1.75D AND THE HOLE CENTER PITCH IS NOT LESS THAN 3.5D. 

### CAUTION CONTACT AIRBUS BEFORE YOU DO THE COLD EXPANSION THAT

FOLLOWS. 3 Oversize the cracked fastener hole(s) to the coLd expansion

start hoLe diameter for the first oversize fastener. 4 Inspect the oversize fastener hoLe(s) for cracks (Refer to

NTM 51-10-01, Part 6, Procedure A)-

a If aLL crack indications have been removed, record aLL

findings and actions taken and contact AIRBUS for an approved repair to be embodied before the next fLight. b If a crack is stiLL indicated, do the worksteps in

para.C.C1) 

### Cd) 5 and 6. 5 Ream the cracked fastener hoLe(s) to the second oversize

coLd working start diameter. 6 Inspect the oversize fastener hole(s) for cracks (Refer to

NTM 51-10-01, Part 6, Procedure A).

a If a crack is stiLL indicated do the worksteps on

para.C.(1) (d) 7 and 8. b If the cracks are compLeteLy removed by second

oversizing record aLL findings and actions taken and contact AIRBUS for an approved repair which is to be embodied before the next fLight. 7 Ream the cracked fastener hole(s) to the next nominal coLd

working start diameter. 8 Inspect the oversize fastener hoLe(s) for cracks (Refer to

NTM 51-10-01, Part 6, Procedure A).

a If the cracks are not removed by oversizing, record aLL

findings and actions taken and contact AIRBUS for an approved repair to be embodied before the next fLight.

DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 

# I REVISION No. . 04 Feb 24/11 PAGE : 13 Printed in France

# } A300-600 SERVICE BULLETIN

b If the cracks are compLeteLy removed by oversizing

record all findings and actions taken and contact AIRBUS for an approved repair to be embodied before the next flight. (2) To repair cracked holes found during accomplishment of Modification No. 08842H5298 (SB A3D0-57-6039), do the worksteps that foLLow: (a) Inspect the top surface of the structure around the hoLe(s)

circumference for cracks (Refer to NTM 51-10-08, Part 6). 1 If a crack is indicated at the top surface do the

requirements of workstep C.(2) (f). 2 If cracks are not indicated at the top surface do the

worksteps in para.C.(2) (b) and (c). 

### CAUTION THE OVERSIZING PROCEDURE THAT FOLLOWS IS FOR HOLES WITH

NOMINAL FASTENER DIAMETERS OF 0.25 TO 0.75IN. (6.35 TO 19.05MM) ONLY. 

### CAUTION THE OVERSIZING THAT FOLLOWS MAY ONLY BE DONE IF THE HOLE EDGE

DISTANCE IS NOT LESS THAN 1.75D AND THE HOLE CENTER PITCH IS NOT LESS THAN 3.5D. (b) Ream the cracked fastener hoLe(s) to the first oversize diameter. (c) Inspect the oversize fastener hoLe(s) for cracks (Refer to 

### NTM 51-

10-01, Part 6, Procedure C). 1 If the crack indications are compLeteLy removed do para.C.(2)

(f). 2 If a crack is stilL indicated do the worksteps in para.C.(2)

(d) and (e). (d) Ream the cracked fastener hoLe(s) to the second oversize diameter. (e) Inspect the oversize fastener hoLe(s) for cracks (Refer to

NTM 51-10-01, Part 6, Procedure C).
1 On completion of the inspection do para.C.(2) (f).
DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 REVISION No. : 04 Feb 24/11 PAGE : 14 Printed in France

# A300-600 SERVICE BULLETIN

(f) Remove the four adjacent fasteners on both sides of the cracked fastener hoLe. For hoLes which contained taper-Lok fasteners do the worksteps in para.C.(2) (g). For hoLes which contained paraLLeL fasteners do the worksteps in para.C.(2) (h). (g) Taper-Lok HoLes 1 Inspect the hoLes, where fasteners were removed in workstep C.(2) (f), for cracks (Refer to NTM 51-10-01, Part 6, Procedure C).
a If cracks are not indicated record aLL findings and contact AIRBUS for an approved repair to be embodied before the next fLight. b If the crack is indicated do the worksteps in para.C.(2) (g) 2. 2 Inspect the top surface of the structure around the hoLe(s) circumference for cracks (Refer to NTM 51-10-08, Part 6).

a If a crack is indicated at the top surface, record aLL findings and contact AIRBUS for an approved repair to be embodied before the next fLight. b If additional cracks are not indicated at the top surface, do the worksteps in para.C.(2) (g) 3 and 4. CAUTION THE OVERSIZING PROCEDURE THAT FOLLOWS IS FOR HOLES WITH

NOMINAL FASTENER DIAMETERS OF 0.25 TO 0.751N. (6.35 TO 19.05MM) ONLY. CAUTION THE OVERSIZING THAT FOLLOWS MAY ONLY BE DONE IF THE

HOLE EDGE DISTANCE IS NOT LESS THAN 1.75D AND THE HOLE CENTER PITCH IS NOT LESS THAN 3.5D. 3 Ream the cracked fastener hoLe(s) to the first oversize diameter. 4 Inspect the oversize fastener hoLe(s) for cracks (Refer to NTM 51-10-01, Part 6, Procedure C).

DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 REVISION No. : 04 Feb 24/11 PAGE : 14a Printed in France

# A3oo - 600 SERVICE BULLETIN 

# I a If the crack indications are compLeteLy removed by first oversizing, record aLL findings and actions taken and contact AIRBUS for an approved repair to be embodied before the next fLight. b If a crack is stiLL indicated, do the worksteps in

para.C.(2) (g) 5 and 6. 

# J 5 Ream the cracked fastener hoLe(s) to the second oversize diameter. 6 Inspect the oversize fastener hole(s) for cracks (Refer to

NTM 51-10-01, Part 6, Procedure C). Record aLL findings and actions taken and contact AIRBUS for an approved repair to be embodied before the next flight. (h) ParaLLeL Holes

1 Inspect the holes, where fasteners were removed in workstep

C.(2) (f), for cracks (Refer to NTM 51-10-01, Part 6, Procedure A).

a If cracks are not indicated, record aLL findings and

contact AIRBUS for an approved repair to be embodied before the next Right. b If a crack is indicated at the fastener hoLe(s), do the

worksteps in para.C.(2) (h) 2. 2 Inspect the top surface of the structure around the hoLe(s)

circumference for cracks (Refer to NTM 51-10-08, Part 6).

a If the crack is indicated, record aLL findings and

contact AIRBUS for an approved repair to be embodied before the next fLight. b If additional cracks are not indicated at the top

surface do the worksteps in para.C.(2) (h) 3 and 4. 

### CAUTION THE OVERSIZING PROCEDURE THAT FOLLOWS IS FOR HOLES WITH NOMINAL FASTENER DIAMETERS OF 0.25 TO 0,75IN. (6.35 TO 19.05MM) ONLY.

DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 REVISION No. : 04 Feb 24/11 PAGE : 14b Printed in France

# A300-600 SERVICE BULLETIN 

### CAUTION CONTACT AIRBUS BEFORE YOU DO THE COLD EXPANSION

THAT FOLLOWS. 3 Oversize the cracked fastener hole(s) to the coLd expansion start

hole diameter for the first oversize fastener. 4 Inspect the oversize fastener hoLe(s) for cracks (Refer to NTM

51-10-01, Part 6, Procedure A).

a If aLL crack indications have been removed, record aLL

findings and actions taken and contact AIRBUS for an approved repair to be embodied before the next fLight. b If a crack is stiLL indicated, do the worksteps 

### in para.C.(2)

(h) 5 and 6. 5 Ream the cracked fastener hoLe(s) to the second oversize coLd

working start diameter. 6 Inspect the oversize fastener hoLe(s) for cracks (Refer to

NT1 51-10-01, Part 6, Procedure A).

a If a crack is still indicated do the worksteps on para.C.(1)

(h) 7 and 8. b If the cracks are compLeteLy removed by second oversizing

record aLl findings and actions taken and contact AIRBUS for an approved repair to be embodied before the next flight. 7 Ream the cracked fastener hoLe(s) to the next nominal coLd working

start diameter. 8 Inspect the oversize fastener hoLe(s) for cracks (Refer to

NTM 51-10-01, Part 6, Procedure A).

a If the cracks are not removed by oversizing, record all

findings and actions taken and contact AIRBUS for an approved repair to be embodied before the next fLight. b If the cracks are completely removed by oversizing

record aLL findings and actions taken and contact AIRBUS for an approved repair to be embodied before the next ftight.

DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 REVISION No. : 04 Feb 24/11 PAGE : 14c Printed in France

# 'A3oo 

# -boo
SERVICE BULLETIN

(3) Remove the fastener where a crack was detected and do a roto -probe inspection to confirm the indication (Refer to NTM 51-10-01, Part 6, Procedure C). (a) If a crack is not indicated, contact AIRBUS for an approved repair

to be embodied before the next fLight. (b) If a crack is indicated, inspect the top surface around the cracked

fastener hoLe (Refer to NTM 51-10-08, Part 6). Remove the four adjacent fasteners on both sides of the cracked fastener hoLe. Do a roto -probe inspection of the eight fastener hoLes (Refer to NTM 51-10-10, Part 6, Procedure C). 1 If cracks are not indicated in the eight fastener hoLes, record alL

findings and contact AIRBUS for an approved repair to be embodied before the next fLight. 2 If cracks are indicated, inspect the top surface around the cracked

fastener hoLes (Refer to NTM 51-10-08, Part 6). Record aLL findings and contact AIRBUS for an approved repair to be embodied before the next fLight. (4) ResuLts of inspections, including niL findings and repair actions, must be sent

immediately to AIRBUS after compLetion of the inspection/repairs. Use the Inspection Report (Figure 4) provided in this Service BuLLetin. DetaiLs of hoLes that are stiLL cracked, edge margins, pitch and hoLe diameters, must also be included (Refer to SRM 51-10-13 Page bLock 1).

DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 

# I REVISION No. : 04 Feb 24/11 PAGE : 14d Printed in France

# A300-600 SERVICE BULLETIN

D. 

### TEST

(1) If you removed the refueL/defueL pipes for access, compLete the worksteps in para.E.CLOSE UP and do a system Leak test. 

### Note : This procedure is applicable to aircraft with the refuel coupling

is on the RH wing. (a) Job Set-Up 1 Open access door 144DR. 

### 2 On panel 110VU, make sure that TRANSF. VALVE switch is in CLOSED position and guarded. 3 Defuel all tanks (Refer to AMM 28-25.00 Page bLock 301). 

### 4 Open main landing gear bay door (Refer to AMM 32-12-11 Page block 301) and position access platform. 5 Open, safety and tag the foLLowing circuit breakers:


### PANEL SERVICE IDENT LOCATION 22VU FUEL/OUTR TK PUMP 2/L TK/CTL 61QA 201/J15 22VU FUEL/OUTR TK PUMP 2/R TK/CTL 68QA 201/J18 132VU FUEL/CTR TK/L PUMP CTL 63QA 322/N58 132VU FUEL/CTR TK/R PUMP CTL 64QA 323/M59 132VU FUEL/L INR TK/PUMP 1/CTL 69QA 322/N60 132VU FUEL/R INT TK/PUMP 1/CTL 60QA 322/N62 132VU FUEL/L INR TK/PUMP 2/CTL 59QA 323/M61 132VU FUEL/R INT TK/PUMP 2/CTL 704A 323/M63 132VU FUEL/L OUTR TK/PUMP 1/CTL 67QA 322/N56 132VU FUEL/R OUTR TK/PUMP 1/CTL 62QA 323/M57 132VU FUEL/X FEED VALVE/MOTOR 1 2QE 324/L60

DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 REVISION No. : 04 Feb 24/11 PAGE : 15 Printed in France

# A300-600 SERVICE BULLETIN 

### PANEL SERVICE IDENT LOCATION 132VU FUEL/X FEED VALVE/MOTOR 2 1QE 324/L61 132VU FUEL/FUELLING/XFR/VALVE 2QU 321/P55 6 Position access pLatforms 4.5m (15ft) at each wing. 

### 7 Remove wing tank manhoLe covers 542 CB, (642 CB) between STA71 (RIB 2) and STA 142 (RIB 3) (Refer to AMM 28-11-22 Page bLock 401). 

### 8 Remove center tank manhoLe cover 147AZ (Refer to AMM 28-11-29 Page bLock 401). 9 Remove cadensicon (Refer to AMM 28-42-44 Page bLock 401). 10 Remove drain valve (2) (Refer to AMM 28-25-18 Page bLock 401) and bLank refuel gallery drain Line (1). Refer to Figure 5. 11 Remove the diffusers (Refer to AMM 28-25-15, Page block 401). 

### 12 Install a bLank, complete with a bleed valve, on each diffuser Line end (3). 13 Remove reLevant wing tank manhole covers (Refer to AMM 28-11-22 Page bLock 401) to allow inspection of refuel/defuel Lines. 

### 14 Connect fuel system pressurization unit to one refueL/defueL coupling. 15 Energize the aircraft electrical network and make certain that electronic racks are ventilated (Refer to AMM 24-41-00 Page bLock 301). 16 Make certain that the following circuit breaker is closed:



### PANEL SERVICE IDENT LOCATION 132VU FUEL/FUELLING/CTL & REFUEL VALVE 1QU 321/P56 WARNING: BEFORE PRESSURIZING THE AIRCRAFT SYSTEM, THE FUEL SYSTEM PRESSURIZATION UNIT SAFETY SYSTEM MUST BE SET AND TESTED TO 4 BAR (58 psi), AND ALL BLANKS SAFELY INSTALLED AND TIGHTENED. DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 

# I REVISION No. : 04 Feb 24/11 PAGE : 16 Printed in France

# A300-600 SERVICE BULLETIN

(b) Test 

### ACTION RESULT 1. On paneL 110VU: - make certain that PWR SUPPLY switch is in NORM position and guarded. - raise guard and pLace MODE SELECTOR in REFUEL position. - raise guard and place right outer tank REFUEL/DEFUEL VALVES switch in OPEN position. 2. Using fuel system pressurization unit, fiLL right outer tank refuel Line with fuel. Bleed at diffuser line end until Line is fuLL, then tighten bLeed valve. 3. On paneL 110VU: - raise guards and pLace each tank REFUEL/DEFUEL VALVES switch in OPEN position and fill each tank refuelling line in sequence. - bLeed at diffuser blank bLeed valves. - Pressurize system to 3.5 bar No Leaks permitted (51 psi) and maintain pressure For 15 min. - Release pressure by opening diffuser blank bLeed valves. 4. On panel 110VU: - place aLL REFUEL/DEFUEL VALVES switches is in NORMAL position and guarded. - place MODE SELECTOR switch in OFF position and guarded.

DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 REVISION No. : 04 Feb 24/11 PAGE : 16a Printed in France

# A300-600 SERVICE BULLETIN

(c) CLose-Up

1 De-energize the aircraft eLectricaL network (Refer to AMM 24-41-00 Page bLock 301). 2 Disconnect fuel system pressurization unit.
CAUTION: DURING THIS OPERATION THE CONTENTS OF THE REFUEL LINES WILL DRAIN INTO THE TANKS. 3 Remove blanks from diffuser Line ends (3). 4 InstalL the diffusers (Refer to AMM 28-25-15 Page bLock 401). 5 Remove blank from refuel gaLLery drain (1) and instatL drain valve (2) (Refer to AMM 28-25-18 Page bLock 401). 6 Install cadensicon (Refer to 

### AMM 28-42-44 Page bLock 401). 7 Make certain that working area is clean and cLear of tooLs and miscellaneous items of equipment. 8 Install manhole covers (Refer to AMM 28-11-22 Page bLock 401) and (Refer to AMM 28-11-29 Page bLock 401). 9 Remove safety cLips and tags and cLose circuit breakers 61QA, 68QA, 63QA, 64QA, 69QA, 59QA, 60QA, 70QA, 67QA, 62QA, 2QE, 1QE, 2QU. 10 Remove access platforms from each wing. 11 Remove access platform and cLose main Landing gear bay door (Refer to AMM 32-12-11 Page bLock 301).

DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 REVISION No. : 04 Feb 24/11 PAGE : 16b Printed in France

# A300-600 SERVICE BULLETIN

E. 

### CLOSE UP (1) RepLace any fasteners that have been removed. (2) In the inspection area, appLy sealant as required. (3) If removed for access, install the refueL/defueL pipes (Refer to AMM 28-00- 00 Page bLock 401). (4) RepLace paint coatings as required. (5) Make sure that the work areas are clean and clear of tooLs and other items of equipment. (6) InstaLL the manhole covers 542EB, 543AB, 642EB and 643AB (Refer to AMM 28- 11-22 Page bLock 401). (7) Refuel the aircraft (Refer to AMM 12-11-28 Page bLock 1). (8) Do an external inspection for fuel Leaks- (9) Remove the access platforms.
F. 

### DOCUMENTATION Write in the appLicabLe aircraft records that you have done aLL the work given in this Service BuLLetin.

DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 

# I REVISION No. : 04 Feb 24/11 

### PAGE : 16c Printed in France

# © A300-600
SERVICE BULLETIN

INNER !AP STRAP FRONT

U

NQ 

### •o ti ti 

### HOLE POSITION S T U V BOLT LOCATION NO. (REFER 163 164 R571 40141 SHEET 12) 

### BOLT LOCATION NO. (REFER 7 8 R571 40141 SHEET 16)


### WING DATUM PLANE B 

# ® ;
II 1 VIEW ON I i i 0 0 O Q II I I li FWD. FACE F RONT of SPAR 

## ,^^,^O O'

, 

## 000 0 o 0OoÔ 

## io+'r

0)0000 oo Ooh { J 5 

### Î ^"`— I O O 

### O ` 

### O _ y 

### Q O O b 

# i ^ -^ L^_^[ I 

### c --SKIN 4 A I ^ 

### OUTER JOINT STRAP (REF) UNDER SPAR STRAP (REF) INNER JOINT STRAP (REF)



### Figure 1 Sheet 1 HoLes To Be Inspected - Front Spar Bottom Boom
DATE : Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 

### REVISION No. : 04 Feb 24/11 Page : 16d Printed in France © Airbus Industrie 1994, Al rights reserved

### 1R

HOLE X
u HOLE W

u ^y ¢ i ti M
ti 

# © A300-600
SERVICE BULLETIN



### INTERNAL EXTERNAL r UNDER SPAR JOINT PLATE JOINT PLATE STRAP HOLE POSITION W X Y 2 BOLT LOCATION NO. (REFER 939 937 R571 40141 SHEET 15) BOLT LOCATION NO. (REFER 558 557 R571 40141 SHEET 16)
RIB 9 DATUM



# o r 

## ¢° 0 0 

## 0 01 0 o 0 O 

# Oo Q 

# o 0 

# o



# o© OUT 

# o ER REAR INNER REAR SPAR n SPAR A FOR WARD


### INBOARD 

# A'
HOLE Y A,.-l--HOLE Z

Figure 2 Sheet 1 Holes To Be Inspected - Rear Spar Bottom Boom

DATE : Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 

# I REVISION No. : 04 Feb 24/11 Page : 17 Printed in France ©Airbus Industrie 1994, All rights reservedN D

, O ti 

### FR( Sr CEN' TAI VEI 

# S A300-600
SERVICE BULLETIN

FUEL RIB 10 RTR Q 

### FEED

Figure 3 Sheet 1 RemovaL of the RefueL/Defuel Pipes for Access
DATE : Aug 01/94 SERVICE BULLETIN No. A300-57 -6037 

# I REVISION No. : 04 Feb 24/11 Page : 18 Printed in France © Arrbus Industrie 1994, AJI rights reservedDB7 57 6037 AG AA C

A300 SB No. 

### A/C MSN
FLIGHT CYCLES FLIGHT HOURS


### FINDINGS : A300-57-6037



### YES ❑ NO ❑ INSPECTION 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 ❑ SRM AIB INSTRUCTION 

## D 8

C N 7 C 

# m_

ur

Sll to (D C/)

m r) m m I

I

ni
H z z 

### o E-4

N to C fD f7 r+
o N A (p CD CD 'a rt o rF ^

10 w 0 0 T i o` 0 w ti n m W C I

I

ni H z 70 m
N H O z z o

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### r T (DoN) 

# v b m

o 0S4o 

## .1(-

# SA300 

# -boo SERVICE BULLETIN

CAL



## Li Figure 5 Sheet 1 RefueL / DefueL System - Leak Test DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 REVISION No. : 04 Feb 24/11 PAGE: 20 Printed in France

# © A300-600

SERVICE BULLETIN REPORTING SHEET TITLE : WINGS - OUTER WING - INSPECT FRONT AND REAR SPAR BOTTOM BOOM - INBOARD

AND OUTBOARD OF RIB 9 MODIFICATION No. : None Please complete the appropriate 

### item (A or B): A - SB WILL BE embodied . . . . . . . . . . . . . .YES/NO (if NO pLease comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiment : . . . . . . . . . . . . . . . . . . . . . . . . . .

B - SB HAS BEEN embodied on aircraft:

. . . . . . . . . . . . . . . . . . .

. . . . . . . . . . . . . . . . . . . Operator comments: . . . . . . . . .

. . . . . . . . . . . . . . . . . .

. . . . . . . . . . . . . . . . . . FromAirline . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Name/Title : . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Signature : . . . . . . . . . . . . Date: . . . . . . . . . . . If operationaL documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service(s): Either: Advance data . . . . . . . . . . . . . . . . . . . . . . YES/NO Or : Intermediate/Temporary revision . . . . . . . . . . . . YES/NO 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: SDC32 

### 1 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 01/94 SERVICE BULLETIN No. : A300-57-6037 

# I REVISION No. : 04 Feb 24/11 Page : 1 of 1 Printed in France©Airbus Industrie 1994, At rights reserved

# A3

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 : SEM4 Service Bulletins Management FAX : (33) 5 61 93 42 51 or via your Resident Customer Support Office.

7 DATE : Aug 01/94 SERVICE BULLETIN No. : A300-57-6037 

# I REVISION No. : 04 Feb 24/11 Page : 1 of 1
Printed in France ©Airbus Industrie 1994, AJI rights reserved