A300-600 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 MANDATORY

ATA SYSTEM : 57

TITLE : WINGS - INSPECTION OF THE CENTER SPAR SEALING ANGLES ADJACENT TO PYLON

REAR ATTACHMENT FITTING

MODIFICATION No. : None

This page transmits Revision No. 07 of Service Bulletin No. A300-57-6027

ADDITIONAL WORK

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

REASON

Further to the Extended Service Goal 2 (ESG2) study, new timescales/intervals are introduced to enable

aircraft to operate to the new Service Goal. Flight Hour (FH) conversion for inspection thresholds and

intervals given in Flight Cycles (FC) are also included.

CHANGES

SUMMARY :

- REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

. Thresholds updated. Para relating to ESG added.

- EFFECTIVITY

. Effectivity updated.

PLANNING INFORMATION :

- EFFECTIVITY

. 1.A. Effectivity updated.

- REASON

. 1.C. Thresholds updated. Para relating to ESG added.

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

REVISION No. : 07 - Jun 06/11 Page : 1 of 3

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

- COMPLIANCE

- Accomplishment Timescale

. 1.E.(2) New statement added referring to AD. Thresholds and intervals updated.

- REFERENCES

. 1.J. ESPM and SB reference added.

ACCOMPLISHMENT INSTRUCTIONS :

- GENERAL

. 3.A. CAUTION added.

- INSPECTION

. 3.B.(2)(a) Reference to Table 6 added.

- Figure 1

. Replaced by updated Flow Chart.

- Figure 4

. Reference to Table 6 added.

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 02 was issued to:

- include changes to the effectivity list.

- reduce the pre modification 08609H5276 (SB A300-57-6033) inspection threshold from 12,000

FC to 10,600FC.

- reduce the post modification 08609H5276 (SB A300-57-6033) inspection threshold from 15,000

to 13,200 FC.

- reduce the recommended embodiment point for modification 08609H5276 (SB A300-57-6033) to

comply with the reduced inspection threshold.

Revision 03 was issued to:

- include reference to a new repair, R571 50404, which supersedes repair R571 40942.

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

REVISION No. : 07 - Jun 06/11 Page : 2

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

- include the post repair inspection requirements for post repair R571 50404.

- include the Change Notice 2A which introduced inspection limits for aircraft which have exceeded

the initial threshold.

Revision 04 was issued to:

- include aircraft MSN 0521 in the aircraft effectivity.

Revision 05 was issued to:

- clarify the crack length in the sealing angle.

- add a new illustration to show possible crack situations at the sealing angle and the applicable

actions required.

Revision 06 was issued to add the inspection threshold and interval requirement of repair R571 50404

for aircraft which have exceeded their design service goal.

REVISION SEQUENCE

ORIGINAL : Oct 08/91

REVISION No. : 01 - Nov 24/93

REVISION No. : 02 - Sep 13/94

REVISION No. : 03 - Jan 22/97

REVISION No. : 04 - Aug 04/99

REVISION No. : 05 - Nov 21/02

REVISION No. : 06 - Mar 02/05

REVISION No. : 07 - Jun 06/11

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

REVISION No. : 07 - Jun 06/11 Page : 3

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SERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

REVISION No. : 07 - Jun 06/11 Page : 4

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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 MANDATORY

ATA SYSTEM : 57

TITLE : WINGS - INSPECTION OF THE CENTER SPAR SEALING ANGLES ADJACENT TO PYLON

REAR ATTACHMENT FITTING

MODIFICATION No. : None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During full scale fatigue testing, a crack was found in the vertical web of a center spar sealing angle adjacent

to Rib 8. Approximately 45,000 simulated flight cycles (FC) had been completed. At 72,000 FC a crack

was found in a sealing angle on the opposite wing. In both cases the cracks started in the vertical web of

the sealing angle.

Since the initial issue of this Service Bulletin four operators have reported cracking of the sealing angles. The

cracks were discovered between 5,540 and 21,200 FC and between 11,616 and 21,250 flight hours. Analysis

of these findings has resulted in the need to lower the inspection thresholds.

Modification No. 08609H5276 (SB A300-57-6033) has been introduced to improve the structure in this area.

Modification No. 08609H5276 (SB A300-57-6033) cold expands fastener holes in the sealing angle vertical

flange outboard of Rib 8. This modification is required to be embodied following first inspection, at or before

the recommended thresholds given in Para.1.E.(2)(c) Table 3.

Aircraft which have been repaired under Repair Drawing R571 40588 or R571 40942 may be considered as

having embodied Modification No. 08609H5276 (SB A300-57-6033).

The sealing angle repair R571 40942 replaces cracked sealing angles with sealing angles of the same

standard.

Repair R571 50404 has now been issued to introduce replacement sealing angles with a thicker vertical

flange. Repair R571 50404 supersedes repair R571 40942.

In some cases (depending on individual aircraft) it may be necessary to do repair R571 50413 at the same

time as repair R571 50404. Repair R571 50413 provides instructions for bushing of the skin, butt strap,

stringer 12 and external doubler.

Installation of repair R571 50404 will improve the first inspection threshold. However, if bushing of the skin,

butt strap, stringer 12 and external doubler are required in accordance with repair R571 50413 some aircraft

may have to be inspected earlier (See Tables 1 and 2).

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

REVISION No. : 07 - Jun 06/11 Page : 1 of 3

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SERVICE BULLETIN

SUMMARY

Modification No. 08608H5275 has been introduced on production. Aircraft post this production modification

do not have to comply with the requirements of this Service Bulletin.

This Service Bulletin takes into account the Extended Service Goal 2 (ESG2) study, to enable aircraft to

operate to the new Service Goal.

This Service Bulletin has been issued for mandatory inspections of the center spar sealing angle. The

inspections are to be at the vertical flange of the sealing angle outboard of Rib 8 and are by High Frequency

Eddy Current (HFEC).

Early detection of cracks can prevent damage extending to adjacent structural elements and the necessity

of costly and time consuming repairs.

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

DEFUELLING /

VENTILATION

YES

KIT PRICE (USD) No AIRBUS kit

EFFECTIVITY

This Service Bulletin is applicable to these operators :

AAL AAW ABD CES DLH F2I FDX G8E IRA IRM JAL KAC KAL LAA MON MSR OHY QTR TAR THA

CONCURRENT REQUIREMENTS

None

REFERENCES/REPERCUSSIONS

TFU : 576008001

576008002

OEB : None

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

REVISION No. : 07 - Jun 06/11 Page : 2

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SERVICE BULLETIN

SUMMARY

AOT : None

SIL : 57-065

LIFE LIMIT : None

LINE MAINTENANCE AFFECTED : No

OTHERS : None

NATURE OF THE WORK

AIRCRAFT : Yes

EQUIPMENT : No

HARD : No

SOFT : No

OBRM : No

MANPOWER

TOTAL MANHOURS 12.0

ELAPSED TIME (HOURS) 6.0

MATERIAL INFORMATION

AIRCRAFT DATA

None

APPENDICES

None

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

REVISION No. : 07 - Jun 06/11 Page : 3

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SERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

REVISION No. : 07 - Jun 06/11 Page : 4

Printed in France © AIRBUS 2008 All rights reserved
A300-600 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 MANDATORY

ATA SYSTEM : 57

TITLE : WINGS - INSPECTION OF THE CENTER SPAR SEALING ANGLES ADJACENT TO PYLON

REAR ATTACHMENT FITTING

MODIFICATION No. : None

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property

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, 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

This Service Bulletin is applicable to aircraft MSN :

0284 0294 0301 0307 0312 0317 0321 0336 0344 0348 0351 0354 0358 0361 0365

0368 0380 0388 0398 0401 0405 0408 0411 0414 0417 0423 0459-0466 0469 0470

0474 0477 0479 0505-0518 0521 0525 0529 0530 0532 0536 0540 0543 0546

0553-0561 0563 0566 0569 0572 0575 0577 0579 0581 0582 0584 0601-0619 0621

0623 0625-0633 0635 0637 0639 0641 0643

(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.

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

REVISION No. : 07 - Jun 06/11 Page : 1 of 17

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A300-600 A300-600

SERVICE BULLETIN

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

AAW 0354

ABD 0529 0557

CES 0521 0525 0532

DLH 0380 0401 0405 0623

F2I 0284 0294 0301 0307 0312 0317 0321 0336 0348 0351 0408 0618

FDX 0358 0361 0365 0388 0417 0477 0479 0530 0536 0543 0555 0559

0572 0575 0579 0581 0611 0613 0625 0630 0633

G8E 0462 0465

IRA 0632

IRM 0411 0414 0546 0553 0608

JAL 0602 0617 0621 0637 0641

KAC 0344

KAL 0582 0609 0627 0631

LAA 0601 0616

MON 0540 0556 0604 0605

MSR 0561 0607

OHY 0584 0603

QTR 0554 0560 0614

TAR 0505 0558 0563

THA 0368 0398 0464 0518 0566 0569 0577 0628 0629 0635

Aircraft MSN 0645 and subsequent have had Modification 08608H5275 embodied

in production and therefore the inspection requirements of this Service Bulletin

are not required.

(c) Effectivity by MSN and Kit/Configuration

No AIRBUS kit is required for the accomplishment of this Service Bulletin

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

REVISION No. : 07 - Jun 06/11 Page : 2

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SERVICE BULLETIN

(3) Spares

None

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During full scale fatigue testing, a crack was found in the vertical web of a center spar

sealing angle adjacent to Rib 8. Approximately 45,000 simulated flight cycles (FC) had

been completed. At 72,000 FC a crack was found in a sealing angle on the opposite wing.

In both cases the cracks started in the vertical web of the sealing angle.

Since the initial issue of this Service Bulletin four operators have reported cracking of the

sealing angles. The cracks were discovered between 5,540 and 21,200 FC and between

11,616 and 21,250 flight hours. Analysis of these findings has resulted in the need to

lower the inspection thresholds.

Modification No. 08609H5276 (SB A300-57-6033) has been introduced to improve the

structure in this area. Modification No. 08609H5276 (SB A300-57-6033) cold expands

fastener holes in the sealing angle vertical flange outboard of Rib 8. This modification is

required to be embodied following first inspection, at or before the recommended thresholds

given in Para.1.E.(2)(c) Table 3

Aircraft which have been repaired under Repair Drawing R571 40588 or R571 40942 may

be considered as having embodied Modification No. 08609H5276 (SB A300-57-6033).

The sealing angle repair R571 40942 replaces cracked sealing angles with sealing angles

of the same standard.

Repair R571 50404 has now been issued to introduce replacement sealing angles with a

thicker vertical flange. Repair R571 50404 supersedes repair R571 40942.

In some cases (depending on individual aircraft) it may be necessary to do repair R571

50413 at the same time as repair R571 50404. Repair R571 50413 provides instructions for

bushing of the skin, butt strap, stringer 12 and external doubler.

Installation of repair R571 50404 will improve the first inspection threshold. However, if

bushing of the skin, butt strap, stringer 12 and external doubler are required in accordance

with repair R571 50413 some aircraft may have to be inspected earlier (See Tables 1 and 2).

Modification No. 08608H5275 has been introduced on production. Aircraft post this

production modification do not have to comply with the requirements of this Service Bulletin.

This Service Bulletin takes into account the Extended Service Goal 2 (ESG2) study, to

enable aircraft to operate to the new Service Goal.

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

REVISION No. : 07 - Jun 06/11 Page : 3

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A300-600 A300-600

SERVICE BULLETIN

(2) Objective/Action

This Service Bulletin has been issued for mandatory inspections of the center spar sealing

angle. The inspections are to be at the vertical flange of the sealing angle outboard of Rib 8

and are by High Frequency Eddy Current (HFEC).

(3) Advantages

Early detection of cracks can prevent damage extending to adjacent structural elements

and the necessity of costly and time consuming repairs.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

(1) Defuel and vent the wing fuel tanks.

(2) Get access to the LH and RH outer wing fuel tanks.

(3) Remove all sealant covering the first 3 fasteners in the sealing angle vertical webs

immediately outboard of Rib 8.

(4) Do an HFEC inspection of the sealing angle vertical webs immediately outboard of Rib 8.

(5) If cracks are found replace the sealing angles.

(6) Replace any removed sealant.

(7) Close-up.

(8) Re-fuel the aircraft.

(9) Do a leak test of any repaired areas.

E. COMPLIANCE

(1) Classification

Mandatory

(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) Refer to Tables 1 and 2 for Inspection Accomplishment Timescales:

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

REVISION No. : 07 - Jun 06/11 Page : 4

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SERVICE BULLETIN

Table 1: Normal Range Operations

Inspection Threshold Inspection Repeat Interval Grace Period

Method FC FH FC FH FC FH

Pre Mod

8609

HFEC 9,000 18,600 5,100 10,500 1,700 3,500

Post Mod

8609 or

R57140588

or

R57140942

HFEC 11,300 23,300 5,100 10,500 1,700 3,500

Post

R57150404

& Post 1st

Inspection

& Pre

R57150413.

See NOTE

01 & 02.

HFEC 19,500 40,300 5,100 10,500 1,700 3,500

Table 2: Short Range Operations (Average Flight Time < 1.5h)

Inspection Threshold Inspection Repeat Interval Grace Period

Method FC FH FC FH FC FH

Pre Mod

8609

HFEC 10,600 15,900 6,000 9,000 2,000 3,000

Post Mod

8609 or

R57140588

or

R57140942

HFEC 13,300 20,000 6,000 9,000 2,000 3,000

Post

R57150404

& Post 1st

Inspection

& Pre

R57150413.

See NOTE

01 & 02.

HFEC 23,000 34,500 6,000 9,000 2,000 3,000

NOTE(01) If the repair R571 50404 is done at or after the first inspection required

by this Service Bulletin, and repair R571 50413 is required to be done,

there may be future inspection requirements. Report details of corrective

action taken in accordance with R571 50413 to AIRBUS SEE for possible

further inspection requirements (Refer to SRM 51-10-13, Page Block 1).

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

REVISION No. : 07 - Jun 06/11 Page : 5

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SERVICE BULLETIN

NOTE(02) If the repair R571 50404 is done before the first inspection required

by this Service Bulletin, there may be further inspection requirements.

Report details to AIRBUS SEE for possible further inspection

requirements (Refer to SRM 51-10-13, Page Block 1).

(c) Embodiment of Modification No. 08609H5276 is recommended at the thresholds

give in Table 3:

Table 3: Mod. No. 08609H5276 Embodiment Point

Embodiment Point

Normal Operation Short Range

FC FH FC FH

9,000 18,600 10,600 15,900

(d) If a crack is found in the vertical web of the sealing angle and it extends upwards

but has not broken through the free edge of the vertical flange, a repair must be

done within the limits given in Table 4:

Table 4: Limits to Repair a Known Crack

Normal Operation Short Range

FC FH FC FH

80 160 90 140

(e) If a crack is found in the sealing angle and it has broken through the free edge of the

vertical flange, a repair must be done before the next flight.

F. APPROVAL

Approved under the authority of the EASA Design Organisation 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 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 tools, drying

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

Get Access 2.0

Inspection 4.0

Close Up 2.0

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

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SERVICE BULLETIN

TOTAL MANHOURS 8.0

ELAPSED TIME (HOURS) 4.0

H. WEIGHT AND BALANCE

Not changed

I. ELECTRICAL LOAD DATA

None

J. REFERENCES

Aircraft Maintenance Manual (AMM) : 12-11-28 24-00-00 28-00-00 28-10-00

28-11-22 28-25-00

Elec. Std. Practices Manual (ESPM) : 20-55-00

Non destructive Testing Manual (NTM) : 57-21-84

Service Information Letter (SIL) : 57-065

Structural Repair Manual (SRM) : 51-10-13 51-76-20

Service Bulletin A300-57-6033

K. PUBLICATIONS AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

None

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

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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 : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

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3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL

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

IN THE REFERENCED PROCEDURES.

WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY INSTALLED

ON THE LANDING GEAR. THIS PREVENTS UNWANTED MOVEMENT OF THE

LANDING GEAR.

WARNING : PUT THE SAFETY DEVICES AND WARNING NOTICES IN POSITION BEFORE

YOU START A TASK OR GO NEAR THE FLIGHT CONTROLS.

WARNING : OBEY THE SAFETY PRECAUTIONS IN AMM 28-00-00, Page block 301.

WARNING : BEFORE ENTERING FUEL TANKS REFER TO AMM 28-00-00, Page block 301.

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, CLEANING.

(1) Preparation

(a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

block 301).

(b) De-fuel and vent the wing tanks (Refer to AMM 28-25-00, Page block 301 and AMM

28-10-00, Page block 301).

(c) Put the access platforms in position.

(d) Remove and retain the access panels 542EB and 642EB (Refer to AMM 28-11-22,

Page block 401).

(e) Identify the inspection area (Refer to Figure 2 and Figure 3).

(f) Use a non metallic spatula, to remove sealant from the inspection area (Refer

to Figure 2).

(2) Standard Practices

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

REVISION No. : 07 - Jun 06/11 Page : 11

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SERVICE BULLETIN

(a) For removal and application of sealant, refer to SRM 51-76-20, Page block 201.

(3) Work Breakdown

(a) The various inspection/repair steps described in this SB are indicated in the

Inspection Flow Chart (Refer to Figure 1).

B. INSPECTION

NOTE : The following work is applicable to the LH and RH wings.

Refer to Figure 2, Figure 3 and Figure 4.

(1) Do an HFEC inspection of the sealing angle vertical webs adjacent to the sealing bolt and

each bolt immediately inboard and outboard (Refer to NTM 57-21-84 Part 6). The fastener

hole positions are identified as 57, 58 and 59 on drawing R571 50422.

NOTE : The sealing bolt and hole may not exist on some aircraft.

The sealing bolt is the second bolt in the sealing angle vertical webs outboard

of Rib 8. It has a smaller diameter and edge distance than the adjacent bolts.

Give special attention to possible cracks that extend from the holes, and their spotface

radius, up in the direction of the top edge of the vertical web and down in the direction of

the horizontal web.

(2) If there are any crack indications find the ends of the crack and do the repair procedure in

paragraph 3.C. at these times:

Refer to Figure 4.

(a) If cracks do not extend to the free edge of the sealing angle vertical flange (Refer to

View A), repair at or before the thresholds given in Para. 1.E.(2)(d) Table 4.

(b) If cracks extend to the free edge of the vertical flange, repair before the next flight

(Refer to View B).

(3) If a sealing angle is found cracked right through, additional inspections for cracks of the

underlying butt strap and skin panel will be required. The inspection details are contained in

the sealing angle Repair Drawing R571 50404.

(4) If there are no crack indications, close up as in paragraph 3.E.

C. REPAIR

Repair is by replacement of both the forward and aft sealing angles with improved sealing

angles and cold expansion of the attachment holes. The repair procedure is covered by Repair

Drawing R571 50404.

Repair Drawing R571 40942 replaces the sealing angles with sealing angles of the same standard.

Repair R571 50404 supersedes repair R571 40942.

D. TEST

None

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

REVISION No. : 07 - Jun 06/11 Page : 12

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A300-600 A300-600

SERVICE BULLETIN

E. CLOSE UP

(1) Make sure that the work areas are clean and clear of tools and other items of equipment.

(2) Replace any removed sealant (Refer to SIL 57-065, Technique No. 17).

(3) Install access panels 542EB and 642EB (Refer to AMM 28-11-22, Page block 401).

(4) Refuel the aircraft (Refer to AMM 12-11-28, Page block 301).

(5) Do an external inspection of any repaired areas for leaks.

(6) Remove the access platforms.

(7) Report all findings including nil findings to AIRBUS SE-A (Refer to SRM 51-10-13, Page

block 1).

F. DOCUMENTATION

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

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

REVISION No. : 07 - Jun 06/11 Page : 13

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A300-600 A300-600

SERVICE BULLETIN

Figure 1, Sheet 1

Inspection Flow Chart

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

REVISION No. : 07 - Jun 06/11 Page : 14

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A300-600 A300-600

SERVICE BULLETIN

Figure 2, Sheet 1

View of Inspection Area - Looking Aft

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

REVISION No. : 07 - Jun 06/11 Page : 15

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A300-600 A300-600

SERVICE BULLETIN

Figure 3, Sheet 1

View of Inspection Area - Looking Forward

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

REVISION No. : 07 - Jun 06/11 Page : 16

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 4, Sheet 1

Sealing Angle Crack Examples

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

REVISION No. : 07 - Jun 06/11 Page : 17

Printed in France © AIRBUS 2008 All rights reserved
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SERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

REVISION No. : 07 - Jun 06/11 Page : 18

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SERVICE BULLETIN

REPORTING SHEET

TITLE : WINGS - INSPECTION OF THE CENTER SPAR SEALING ANGLES ADJACENT TO PYLON

REAR ATTACHMENT FITTING

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 embodiement:

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

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

B - SB HAS BEEN embodied on aircraft: ............................................................................................................

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

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

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

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

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

From Airline: ........................................................................................................................................................

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: SEDCC1 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

Or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

REVISION No. : 07 - Jun 06/11 Page : 1 of 1

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A300-600 A300-600

SERVICE BULLETIN

REPORTING QUALITY

TITLE : WINGS - INSPECTION OF THE CENTER SPAR SEALING ANGLES ADJACENT TO PYLON

REAR ATTACHMENT FITTING

MODIFICATION No. : None

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 futher 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 FRANCE

Attn: SEMB Service Bulletins Management

FAX: (+33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE : Oct 08/91 SERVICE BULLETIN No. : A300-57-6027

REVISION No. : 07 - Jun 06/11 Page : 1 of 1

Printed in France © AIRBUS 2008 All rights reserved