@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 - STRUCTURE - MLG RIB 5 FURTHER SPOTFACING ON

BOTTOM FLANGE

MODIFICATION No.: 13534H5720

This page transmits Revision No.01 of Service Bulletin No.A300-57-6110

ADDITIONAL WORK

**CONF ALL

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

REASON

Revision 01 issued to add a rotating probe inspection in the bore of the removed fasteners and to

update the reason paragraph.

CHANGES

SUMMARY

REASON/DESCRIPTION/OPERATIONAL

CONSEQUENCES

REASON UPDATED R

MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

EFFECTIVITY OPERATOR LIST UPDATED R

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Material Effectivity MATERIAL EFFECTIVITY UPDATED

MATERIAL SET QUANTITY UPDATED

R

MATERIAL EFFECTIVITY UPDATED

MATERIAL SET QUANTITY UPDATED

R

REASON

Objective/Action OBJECTIVE/ACTION UPDATED R

COMPLIANCE

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 1

7

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@A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R

MANPOWER MANPOWER UPDATED R

MANPOWER UPDATED R

REFERENCES REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY

Procurement Addresses PROCUREMENT ADDRESSES UPDATED

MATERIAL SET UPDATED

R

LIST OF MATERIALS - OPERATOR

SUPPLIED

Consumable Materials

Consumable CMLB01 CONSUMABLE MATERIAL SET UPDATED

ITEM NUMBER UPDATED

R

TOOLING

Tooling - Price and Availability

Price and Availability PRICE AND AVAILABILITY UPDATED

MATERIAL PRICE UPDATED

R

Tools

Standard tool TOOLB01 TOOL MATERIAL SET UPDATED

QUANTITY UPDATED

R

ACCOMPLISHMENT INSTRUCTIONS

TASK 576110- 831-895-001-Modification

Subtask 576110-280-401-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 576110-831-402-002 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

MATERIAL LIST UPDATED

R

Subtask 576110-280-402-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 576110-280-401-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 576110-280-402-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 576110-831-403-001 SUBTASK SOLUTION UPDATED

ITEM NUMBER UPDATED

MATERIAL LIST UPDATED

R

FILLING 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.

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 2

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@A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

HISTORY OF PREVIOUS REVISIONS

No previous revision

REVISION SEQUENCE

ORIGINAL: Jun 07/10

REVISION No. : 01 - Jun 06/11

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 3

7

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 4

7

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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

ATA SYSTEM: 57

TITLE: WINGS - STRUCTURE - MLG RIB 5 FURTHER SPOTFACING ON

BOTTOM FLANGE

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR 13534H5720

MINOR None

NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the

mass, balance, structural strength, reliability, operational characteristics affecting the

airworthiness of the product. All other changes are major changes.

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

There have been several cases of in service occurrences of cracks in the Main Landing Gear

attachment fitting at Rib 5 on A300 aircraft. The cracks originated on the lower flange between the

attachment to the rear spar and the retraction jack attachment fitting. They where found in the gear rib

and not in the skin or reinforcing plate. Modification 11932 was previously introduced to prevent this.

However there have been cracks found on post 11932 Aircraft.

As Wide Body model families are of similar type design, the above conditions also exist on the model

family addressed in this Service Bulletin.

This retro-fit modification is to be applied to the MLG Support Rib aft of the rear spar. It increases the

diameter and the depth of the spotfaces at the holes 43, 47, 48, 49, 50, 52, 54, previously modified

under mod 11932 and installs 2nd oversize bolts.

The requirements of this Service Bulletin apply to both LH and RH Gear Ribs:

- Spotfaces of holes 43, 47, 48, 49, 50, 52 and 54.

- All aircraft that have not had an Airbus approved spot-face repair applied to applicable holes.

- All aircraft that have applied Airbus approved repairs to the bore of applicable holes.

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 1

7

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@A300-600

SERVICE BULLETIN

SUMMARY

In addition, the requirements of this Service Bulletin do not apply to:

- Aircraft on which MLG ribs 5 have been replaced in service via repair on both the left hand (LH)

and the right hand (RH) wings.

- Spotfaces of individual applicable holes that have previously been repaired as per Airbus approved

repair.

- Aircraft that are post-production mod 11912.

NOTE: If a new MLG rib 5 has been installed on one wing only then the mandatory actions

specified in this Service Bulletin are still required on the MLG rib 5 installed on the other

wing.

This modification re-lifes the MLG Rib 5 by increasing the diameter and the depth of the spotfaces at

specified holes.

If this modification is not accomplished, further failure of the aircraft structure is likely. In particular,

failure of the bolts through the rear spar, which could affect the integrity of the fuel tank and lead to fuel

loss.

Accomplishment of this Service Bulletin cancels the inspection requirements of Service Bulletin

A300-57-6101.

This Service Bulletin has been validated on A300-600 aircraft MSN 0605.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB YES

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

NOTE (1): Service Bulletin must be accomplished.

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 576110B02R01 2 14,660.00 Parallel Bolts, Nuts, Washers

Standard tool TOOLB01 2 1,274.00 Spotface cutter

TOTAL 15,934.00

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 2

7

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@A300-600

SERVICE BULLETIN

SUMMARY

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 576110B01R01 2 13,040.00 Taper-lok Bolts, Nuts, Washers

Standard tool TOOLB01 2 1,274.00 Spotface cutter

TOTAL 14,314.00

EFFECTIVITY

**CONF ALL

This Service Bulletin is applicable to this (these) operator(s) :

30T 83V 98W AAL AAW ABD AMU CES CSN F2I FDX G8E IRA

IRM JAL KAC KAL LAA MON MSR MXU OHY QTR SUD TAR THA

UZB

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU 57.20.30.001

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 576110-831-895-001: Modification

TOTAL MANHOURS 73.00

ELAPSED TIME (HOURS) 48

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 3

7

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@A300-600

SERVICE BULLETIN

SUMMARY

**CONF 002

Task 576110-831-895-001: Modification

TOTAL MANHOURS 71.00

ELAPSED TIME (HOURS) 45.5

APPENDICES

**CONF ALL

APPENDIX 1 Oversize TAPER-LOK Fasteners

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 4

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@A300-600

SERVICE BULLETIN

SUMMARY

**CONF ALL

RETRACTION JACK

ATTACHMENT POINT

REAR SPAR

DATUM

GEAR RIB 5

GEAR RIB 5

ALL VIEWS LEFT HAND,

RIGHT HAND SIMILAR

PLAN VIEW

LH WING

HOLE 47

REAR SPAR

DATUM

NOTE:

HOLE 48

HOLE 50

HOLE 54

PICK−UP FOR TWO

REACTION RODS

HOLE 43

HOLE 49

HOLE 52

MAIN LANDING

GEAR − REAR

BEARING LUGS

MAIN LANDING

GEAR − FRONT

TRUNNION BEARING

MAIN LANDING GEAR −

REAR BEARING LUGS

MAIN LANDING GEAR

NOT SHOWN FOR CLARITY

MODIFICATION

AREA

VIEW LOOKING OUTBOARD

D_SB_576110_7_AAAA_01_00

A

A

B

F

W

D

INBD

U

P

FWD

B

Figure A-UASAA - Sheet 01

- Area of modification.

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 5

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SERVICE BULLETIN

SUMMARY

This Page Intentionally Left Blank

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 6

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All 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 - STRUCTURE - MLG RIB 5 FURTHER SPOTFACING ON

BOTTOM FLANGE

MODIFICATION No.: 13534H5720

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

**CONF ALL

A. EFFECTIVITY

(1) Models

B4-603 B4-605R B4-620 B4-622 B4-622R C4-620 F4-605R

(2) Effectivity by MSN

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

0380 0388 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 0601-0618 0621 0623 0625-0633

0635 0637 0639 0641 0643 0645 0657 0659 0662 0664 0666 0668 0670 0673 0675

0677 0679 0681 0683 0685 0688 0692 0694 0696 0699 0701 0703 0705 0707 0709

0711 0713 0715 0717 0719 0721-0750 0752-0754 0756-0757 0759-0764 0766-0775

0777-0787 0789-0791

(3) 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: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 1

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@A300-600

SERVICE BULLETIN

OPERATOR MSN

30T 0626 0643

83V 0423 0459 0460 0463 0466 0470 0474 0510 0511 0512 0615 0639

0675

98W 0740

AAL 0506 0507 0508 0513 0515 0517 0612

AAW 0354

ABD 0529 0557

AMU 0677 0743

CES 0521 0525 0532 0707 0725 0732 0741 0746 0754 0763

CSN 0733 0734 0739 0756

F2I 0284 0294 0301 0307 0312 0317 0321 0336 0348 0351 0461 0518

0606 0610 0637 0641 0645 0711 0724 0729 0753 0770

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 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

G8E 0462 0465 0469 0509 0514 0516

IRA 0632 0696 0723 0727

IRM 0380 0401 0405 0408 0411 0414 0546 0553 0608 0618 0623 0701

0750 0762 0773

JAL 0602 0617 0621 0670 0679 0683 0703 0730 0737 0783

KAC 0344 0673 0694 0699 0719 0721

KAL 0582 0609 0627 0631 0662 0685 0692 0731

LAA 0601 0616

MON 0540 0556 0604 0605

MSR 0561 0607

MXU 0767

OHY 0584 0603 0744 0747 0749 0764

QTR 0554 0560 0614

SUD 0666 0775

TAR 0505 0558 0563

THA 0464 0566 0569 0577 0628 0629 0635 0681 0705 0782 0784 0785

0786 0787

UZB 0717 0722

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 2

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@A300-600

SERVICE BULLETIN

(4) Configuration by MSN

MSN CONFIGURATION

0284 0294 0301 0307 0312 0317 0321 0336 0344 0348 0351

0354 0358 0361 0365 0380 0388 0401 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 0530

0532 0536 0540 0543 0546 0553 0554 0555 0556 0557 0558

0559 0560 0561 0563 0566 0569 0572 0575 0577 0579 0581

0582 0584 0601 0602 0603 0604 0605 0606 0607 0608 0609

0610 0611 0612 0613 0614 0615 0616 0617 0618 0621 0623

0625 0626 0627 0628 0629 0630 0631 0632 0633 0635 0637

0639 0641 0643 0645 0657 0659 0662 0664 0666 0668 0670

0673 0675 0677 0679 0681 0683 0685 0688 0692 0694 0696

0699 0701 0703 0705 0707 0709 0711 0713 0715 0717 0719

0721 0722 0723 0724 0725 0726 0727 0728 0729 0730 0731

0732 0733 0734 0735 0736 0737 0738 0739 0740 0741 0742

0743 0744 0745 0746 0747 0748 0749 0750 0752 0753

002

0754 0756 0757 0759 0760 0761 0762 0763 0764 0766 0767

0768 0769 0770 0771 0772 0773 0774 0775 0777 0778 0779

0780 0781 0782 0783 0784 0785 0786 0787 0789 0790 0791

001

(5) Configuration definition

**CONF 001

Config 01 is for aircraft which are post-modification 10768. These aircraft are fitted with

parallel bolts.

**CONF 002

Config 02 is for aircraft which are pre-modification 10768. These aircraft are fitted with

Taper-lok bolts.

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Kit 576110B02R01 2

Consumable CMLB01 1

Standard tool TOOLB01 2

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Kit 576110B01R01 2

Consumable CMLB01 1

Standard tool TOOLB01 2

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 3

7

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@A300-600

SERVICE BULLETIN

**CONF ALL

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

There have been several cases of in service occurrences of cracks in the Main Landing

Gear attachment fitting at Rib 5 on A300 aircraft. The cracks originated on the lower

flange between the attachment to the rear spar and the retraction jack attachment fitting.

They where found in the gear rib and not in the skin or reinforcing plate. Modification

11932 was previously introduced to prevent this. However there have been cracks found

on post 11932 Aircraft.

As Wide Body model families are of similar type design, the above conditions also exist

on the model family addressed in this Service Bulletin.

(2) Objective/Action

This retro-fit modification is to be applied to the MLG Support Rib aft of the rear spar. It

increases the diameter and the depth of the spotfaces at the holes 43, 47, 48, 49, 50,

52, 54, previously modified under mod 11932 and installs 2nd oversize bolts.

The requirements of this Service Bulletin apply to both LH and RH Gear Ribs:

- Spotfaces of holes 43, 47, 48, 49, 50, 52 and 54.

- All aircraft that have not had an Airbus approved spot-face repair applied to

applicable holes.

- All aircraft that have applied Airbus approved repairs to the bore of applicable holes.

In addition, the requirements of this Service Bulletin do not apply to:

- Aircraft on which MLG ribs 5 have been replaced in service via repair on both the

left hand (LH) and the right hand (RH) wings.

- Spotfaces of individual applicable holes that have previously been repaired as per

Airbus approved repair.

- Aircraft that are post-production mod 11912.

NOTE: If a new MLG rib 5 has been installed on one wing only then the

mandatory actions specified in this Service Bulletin are still required on

the MLG rib 5 installed on the other wing.

(3) Advantages

This modification re-lifes the MLG Rib 5 by increasing the diameter and the depth of the

spotfaces at specified holes.

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 4

7

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@A300-600

SERVICE BULLETIN

If this modification is not accomplished, further failure of the aircraft structure is likely. In

particular, failure of the bolts through the rear spar, which could affect the integrity of the

fuel tank and lead to fuel loss.

(4) Operational/Maintenance Consequences

Accomplishment of this Service Bulletin cancels the inspection requirements of Service

Bulletin A300-57-6101.

This Service Bulletin has been validated on A300-600 aircraft MSN 0605.

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 576110-831-895-001: Modification

(1) Remove existing Fasteners

(2) Inspect the spotfaces and the holes for cracks

(3) Re-cut the spotface

(4) Inspect the re-cut spotfaces and the holes for cracks

(5) Apply surface protection

(6) Install new fasteners

**CONF 002

Task 576110-831-895-001: Modification

(1) Remove existing Fasteners

(2) Inspect the spotfaces and the holes for cracks

(3) Re-cut the spotface.

(4) Inspect the re-cut spotfaces and the holes for cracks

(5) Apply surface protection

(6) Install new fasteners

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 5

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SERVICE BULLETIN

(2) Accomplishment Timescale

This Service Bulletin has been classified 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 mandated accomplishment timescale.

F. APPROVAL

Approved under 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.

**CONF 001

Task 576110-831-895-001: Modification

Get Access 10

On Aircraft

Remove existing Fasteners 10

Inspect the spotfaces and the holes for cracks 10

Re-cut the spotface 12

Inspect the re-cut spotfaces and the holes for cracks 10

Apply surface protection 1

Install new fasteners 10

Close-Up 10

TOTAL MANHOURS 73.00

ELAPSED TIME (HOURS) 48

NOTE: The total manhours estimate is 73 manhours for the L/H side and 73

manhours for the R/H side.

**CONF 002

Task 576110-831-895-001: Modification

Get Access 10

On Aircraft

Remove existing Fasteners 10

Inspect the spotfaces and the holes for cracks 10

Re-cut the spotface. 12

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 6

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

Task 576110-831-895-001: Modification

Inspect the re-cut spotfaces and the holes for cracks 10

Apply surface protection 1

Install new fasteners 8

Close-Up 10

TOTAL MANHOURS 71.00

ELAPSED TIME (HOURS) 45.5

NOTE: The total manhours estimate is 71 manhours for the L/H side and 71

manhours for the R/H side.

**CONF ALL

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 07-11-00 24-00-00 32-31-46

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

Non Destructive Test Manual (NTM) 51-10-01 57-51-34

Standards Manual (SM)

Structural Repair Manual (SRM) 51-21-10 51-40-21 51-40-44

51-40-47 51-49-00

**CONF 002

Aircraft Maintenance Manual (AMM) 07-11-00 24-00-00 32-31-46

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

Non Destructive Test Manual (NTM) 51-10-01 57-51-34

Standards Manual (SM)

Structural Repair Manual (SRM) 51-21-10 51-40-21 51-40-44

51-40-47 51-49-00

**CONF ALL

K. PUBLICATION AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 7

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@A300-600

SERVICE BULLETIN

M. SPARES

None

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 8

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Customers with aircraft shown in the effectivity of this Service Bulletin should send a

purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is:

Kit 576110B01R01

Kit 576110B02R01

AIRBUS

Material Logistics and Suppliers

Weg beim Jaeger 150

D-22335 Hamburg

Germany

For ordering by internet:

http://spares.airbus.com

For ordering modification kits by fax: +49 40

50 76 25 90

For ordering of single spares by fax: +49 40

50 76 40 13

(2) Price and Availability

NOTE: One kit will only modify one Gear Rib.

Kit 576110B01R01

Cost 6,520.00 USD

Availability 120 calendar days from receipt of order

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

order. If you require Kits before this time, please include a retrofit planning schedule with

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

Kit 576110B02R01

Cost 7,330.00 USD

Availability 120 calendar days from receipt of order

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

order. If you require Kits before this time, please include a retrofit planning schedule with

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

B. INDUSTRY SUPPORT INFORMATION

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

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 9

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@A300-600

SERVICE BULLETIN

C. LIST OF COMPONENTS

Kit 576110B01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

1 4TL330-12-38N 3 BOLT

2 4TL330-12-40N 2 BOLT

3 4TL330-12-42N 1 BOLT

4 4TL330-12-44N 1 BOLT

5 NSA5472-12K7 7 NUT

6 NSA5368-1216AX 14 WASHER

7 NSA5368-1216BX 7 WASHER

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

NOTE: This Kit contains 2nd oversize fasteners. If 3rd oversize fasteners are

required, they will be supplied, on request, from AIRBUS (Refer to the

Accomplishment Instructions of this Service Bulletin).

Kit 576110B02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

1 NSA5483PN12-38 3 BOLT

2 NSA5483PN12-40 2 BOLT

3 NSA5483PN12-42 1 BOLT

4 NSA5483PN12-44 1 BOLT

5 NSA5472-12K7 7 NUT

6 NSA5368-1216A 14 WASHER

7 NSA5368-1216B 7 WASHER

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

NOTE: This Kit contains 2nd oversize fasteners. If 3rd oversize fasteners are

required, they will be supplied, on request, from AIRBUS (Refer to the

Accomplishment Instructions of this Service Bulletin).

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 10

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@A300-600

SERVICE BULLETIN

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

01 Solvent General Purpose 11-026 As required

02 Lint-Free Cotton Cloth 19-003 As required

03 Chemical Conversion Coating

Yellow Aluminum

13-002 As required

04 Anti-Corrosion Primer (epoxyImprvdadhesion)16-006 As required

05 Fuel Tank Sealant Polysulfide 09-001 As required

(2) Components

None

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

(a) Procurement Addresses

Standard tool TOOLB01 AIRBUS

MATERIAL SUPPORT CENTER

P.O.Box 630262

22312 HAMBURG

GERMANY

(b) Price and Availability

Standard tool TOOLB01

Cost 637.00 USD

Availability 60 calendar days from receipt of order

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 11

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

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

purchase order. If you require Kits before this time, please include a retrofit

planning schedule with your order so that we can try to comply with your

requirements.

This tool is available to loan, lead time 2 weeks.

(2) Tools

Standard tool TOOLB01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

01 STD58-284 Spotface Cutter 1

(3) Special Tools

None

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 12

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@A300-600

SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 576110-831-895-001 - Modification

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

INCLUDED IN THE REFERENCED PROCEDURES.

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.

Task Associated Data

**CONF 001

Manpower

TOTAL MANHOURS 73.00

ELAPSED TIME (HOURS) 48

**CONF 002

Manpower

TOTAL MANHOURS 71.00

ELAPSED TIME (HOURS) 45.5

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 576110-839-401-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

(a) Write in the applicable records that you have done all the work given in this Service

Bulletin.

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 13

7

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@A300-600

SERVICE BULLETIN

(2) Subtask 576110-910-401-001 - Standard Practices

Manpower Resources

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-21-10

51-40-21

51-40-44

51-40-47

51-49-00

(a) Install temporary caps or plugs on any open end lines.

(b) For the protection of bare metal surfaces (Refer to SRM 51-21-10).

(c) For the removal and installation of fasteners (Refer to SRM 51-40-21) or the

alternative procedure in the Appendix at the end of this Service Bulletin.

(d) For fastener hole and drill data (Refer to SRM 51-40-44).

(e) For torque values (Refer to SRM 51-49-00).

(f) For countersinking (Refer to SRM 51-40-47).

**CONF 002

(1) Subtask 576110-839-401-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

(a) Write in the applicable records that you have done all the work given in this Service

Bulletin.

(2) Subtask 576110-910-401-001 - Standard Practices

Manpower Resources

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-21-10

51-40-21

51-40-44

51-40-47

51-49-00

(a) Install temporary caps or plugs on any open end lines.

(b) For the protection of bare metal surfaces (Refer to SRM 51-21-10).

(c) For the removal and installation of fasteners (Refer to SRM 51-40-21) or the

alternative procedure in the Appendix at the end of this Service Bulletin.

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 14

7

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@A300-600

SERVICE BULLETIN

(d) For fastener hole and drill data (Refer to SRM 51-40-44).

(e) For torque values (Refer to SRM 51-49-00).

(f) For countersinking (Refer to SRM 51-40-47).

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 576110-941-401-001 - Job Set-up

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 07-11-00, Page Block 001

24-00-00, Page Block 301

32-31-46, Page Block 401

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

Block 301).

(b) Jack the aircraft on the main jacks (Refer to AMM 07-11-00, Page Block 001).

(c) Put warning notices in the flight compartment to tell persons not to operate the

flight controls.

(d) Put an access platform in position below the area of Gear Rib 5.

(e) Remove the MLG Actuating-Cylinder Assembly from the MLG (Refer to AMM

32-31-46, Page Block 401).

(f) Remove the two flexible hydraulic pipes, that attach to the MLG Actuating-Cylinder

Assembly, from the MLG bay.

**CONF 002

(1) Subtask 576110-941-401-001 - Job Set-up

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 07-11-00, Page Block 001

24-00-00, Page Block 301

32-31-46, Page Block 401

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

Block 301).

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 15

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@A300-600

SERVICE BULLETIN

(b) Jack the aircraft on the main jacks (Refer to AMM 07-11-00, Page Block 001).

(c) Put warning notices in the flight compartment to tell persons not to operate the

flight controls.

(d) Put an access platform in position below the area of Gear Rib 5.

(e) Remove the MLG Actuating-Cylinder Assembly from the MLG (Refer to AMM

32-31-46, Page Block 401).

(f) Remove the two flexible hydraulic pipes, that attach to the MLG Actuating-Cylinder

Assembly, from the MLG bay.

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 576110-831-401-001 - Remove existing Fasteners

Manpower Resources

Manhours 10

Minimum number of person 2

Subtask elapsed time 10

Skills AIRFRAME

Material necessary to do the job

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

01 Solvent General Purpose 11-026

02 Lint-Free Cotton Cloth 19-003

References

Structural Repair Manual (SRM) 51-40-21

Fig. A-UAAAA

Area of Modification - Hole Positions

Sheet 01

NOTE: The mechanical instructions that follow are for the LH wing, RH similar.

NOTE: If a repair has been previously embodied to increase the depth of the

spotface, the spotface must not be modified by this Service Bulletin.

NOTE: If:

- Any fastener hole that is 2nd oversize or greater

or:

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 16

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@A300-600

SERVICE BULLETIN

- If a crack is found during accomplishment of this Service Bulletin,

contact AIRBUS for any corrective actions.

(a) Remove the Fasteners (Refer to Fig. A-UAAAA Sheet 01).

CAUTION: YOU MUST TAKE EXTREME CARE WHEN REMOVING FASTENERS

TO AVOID DAMAGE TO THE STRUCTURE.

(b) Remove and discard the bolts from fastener holes 43, 47, 48, 49, 50, 52 and 54

(Refer to SRM 51-40-21).

NOTE: Make sure that you make a note of the part number and the position of

each fastener when you remove it.

1 Clean and degrease the areas in and around the holes where you have removed

the fasteners using

Item 01 Solvent General

Purpose

11-026 As required

Item 02 Lint-Free Cotton

Cloth

19-003 As required

(2) Subtask 576110-280-401-001 - Inspect the spotfaces and the holes for cracks

Manpower Resources

Manhours 10

Minimum number of person 1

Subtask elapsed time 10

Skills NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) 51-10-01 Part 6, Procedure C

57-51-34, Page Block 901

(a) Do an inspection for cracks in the spotface of each hole where you have removed

the fasteners (Refer to NTM 57-51-34, Page Block 901). If any cracks are found

contact AIRBUS for corrective actions.

(b) Do a rotating probe inspection for cracks in the bore of the holes where you have

removed the fasteners (Refer to NTM 51-10-01 Part 6, Procedure C). If any cracks

are found, contact AIRBUS for further instructions.

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 17

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@A300-600

SERVICE BULLETIN

(3) Subtask 576110-831-402-002 - Re-cut the spotface

Manpower Resources

Manhours 12

Minimum number of person 2

Subtask elapsed time 6

Skills AIRFRAME

Material necessary to do the job

Standard tool TOOLB01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

01 STD58-284 Spotface Cutter

References

Structural Repair Manual (SRM) 51-40-21

Fig. A-UBAAG

Parallel bush.

Sheet 03

Fig. A-UCAAA

Recut the spotface.

Sheet 01

(a) Increase the depth of the spotface and the diameter of the hole (refer to Fig. AUCAAA Sheet 01).

CAUTION: THE DEPTH OF THE SPOTFACE SHOULD BE INCREASED IN

INCREMENTS TO MAKE SURE THAT THE MAXIMUM PERMITTED

DEPTH IS NOT EXCEEDED.

(b) Use a Vernier Caliper to measure the stack length of the holes and record findings.

(c) Increase the depth of the existing spotface by 0.060in,+/-0.010in (1,5mm

+/-0,25mm) and the diameter to 1.80in (45,72mm) with a corner radius of 0.25in

(6,35mm) as follows :

1

NOTE: Parallel bush to be manufactured locally.

2 Install the parallel bush into the hole.

3 Recut the spotface to the dimensions detailed using:

Item 01 STD58-284 Spotface Cutter 1

To a surface finish of 63 micro inches (1.6 microns).

4 Remove the parallel bush.

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 18

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@A300-600

SERVICE BULLETIN

(d) Use a Vernier Caliper to measure the new stack length. Compare the measurement

with the first measurement (which you recorded) to make sure that the correct

amount of material has been removed.

NOTE: If holes 47 and/or 54 have previously had 2nd oversize fasteners

installed in them, they must now be increased to 3rd oversize. 3rd

oversize fasteners and drill, ream and countersink data will be supplied,

on request, from AIRBUS.

(e) Drill, ream and countersink each parallel hole for a second oversize parallel Bolt

(Refer to SRM 51-40-21) or the alternative procedure in the Appendix of this

Service Bulletin.

(f) Remove the burrs from each hole.

(4) Subtask 576110-280-402-001 - Inspect the re-cut spotfaces and the holes for

cracks

Manpower Resources

Manhours 10

Minimum number of person 1

Subtask elapsed time 10

Skills NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) 51-10-01 Part 6, Procedure C

57-51-34, Page Block 901

(a) Inspect the recut spotfaces for cracks (Refer to NTM 57-51-34, Page Block 901). If

any cracks are found contact AIRBUS for corrective actions.

(b) Do a rotating probe inspection for cracks in the bore of the holes.(Refer to NTM

51-10-01 Part 6, Procedure C) If any cracks are found, contact AIRBUS for further

instructions.

(5) Subtask 576110-916-401-001 - Apply surface protection

Manpower Resources

Manhours 1

Minimum number of person 2

Subtask elapsed time 0.5

Skills AIRFRAME

Material necessary to do the job

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

03 Chemical Conversion

Coating Yellow Aluminum

13-002 As required

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 19

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@A300-600

SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

04 Anti-Corrosion Primer

(epoxy-Imprvdadhesion)

16-006 As required

(a) Apply to all bare metal:

Item 03 Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

and

Item 04 Anti-Corrosion

Primer (epoxyImprvdadhesion)

16-006 As required

(6) Subtask 576110-831-403-002 - Install new fasteners

Manpower Resources

Manhours 10

Minimum number of person 2

Subtask elapsed time 5

Skills AIRFRAME

Material necessary to do the job

Kit 576110B02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 NSA5483PN12-38 3 BOLT

2 NSA5483PN12-40 2 BOLT

3 NSA5483PN12-42 1 BOLT

4 NSA5483PN12-44 1 BOLT

5 NSA5472-12K7 7 NUT

6 NSA5368-1216A 14 WASHER

7 NSA5368-1216B 7 WASHER

NOTE: This Kit contains 2nd oversize fasteners. If 3rd oversize fasteners are

required, they will be supplied, on request, from AIRBUS (Refer to the

Accomplishment Instructions of this Service Bulletin).

References

Structural Repair Manual (SRM) 51-21-10

(a) Install the following fasteners in the holes specified:

1 For hole 43,

1 Bolt-Hi Lok NSA5483PN12-44 Item 4

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 20

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@A300-600

SERVICE BULLETIN

2 For hole 47,

1 Bolt-Hi Lok NSA5483PN12-42 Item 3

3 For hole 48,

1 Bolt-Hi Lok NSA5483PN12-38 Item 1

4 For hole 49,

1 Bolt-Hi Lok NSA5483PN12-38 Item 1

5 For hole 50,

1 Bolt-Hi Lok NSA5483PN12-40 Item 2

6 For hole 52,

1 Bolt-Hi Lok NSA5483PN12-40 Item 2

7 For hole 54,

1 Bolt-Hi Lok NSA5483PN12-38 Item 1

NOTE: To enable the correct grip length, these washers can be used if

required:

14 WASHER NSA5368-1216A Item 6

7 WASHER NSA5368-1216B Item 7

NOTE: The maximum washer stack allowed is 1x AX + 1x BX. Not 2x BX.

If it is not possible to correctly install the washer in the spotface:

- Fettle the washer to fit

- Reprotect the bare metal (Refer to SRM 51-21-10).

8 With,

7 Nut NSA5472-12K7 Item 5

Torque tighten the nuts to 1240lbf.in. - 1420lbf.in.

9 Paint the heads of the bolts and the nuts.

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 21

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@A300-600

SERVICE BULLETIN

**CONF 002

(1) Subtask 576110-831-401-001 - Remove existing Fasteners

Manpower Resources

Manhours 10

Minimum number of person 2

Subtask elapsed time 10

Skills AIRFRAME

Material necessary to do the job

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

01 Solvent General Purpose 11-026

02 Lint-Free Cotton Cloth 19-003

References

Structural Repair Manual (SRM) 51-40-21

Fig. A-UAAAA

Area of Modification - Hole Positions

Sheet 01

NOTE: The mechanical instructions that follow are for the LH wing, RH similar.

NOTE: If a repair has been previously embodied to increase the depth of the

spotface, the spotface must not be modified by this Service Bulletin.

NOTE: If:

- Any fastener hole that is 2nd oversize or greater

or:

- If a crack is found during accomplishment of this Service Bulletin,

contact AIRBUS for any corrective actions.

(a) Remove the Fasteners (Refer to Fig. A-UAAAA Sheet 01).

CAUTION: YOU MUST TAKE EXTREME CARE WHEN REMOVING FASTENERS

TO AVOID DAMAGE TO THE STRUCTURE.

(b) Remove and discard the bolts from fastener holes 43, 47, 48, 49, 50, 52 and 54

(Refer to SRM 51-40-21).

NOTE: Make sure that you make a note of the part number and the position of

each fastener when you remove it.

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 22

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

1 Clean and degrease the areas in and around the holes where you have removed

the fasteners using

Item 01 Solvent General

Purpose

11-026 As required

Item 02 Lint-Free Cotton

Cloth

19-003 As required

(2) Subtask 576110-280-401-001 - Inspect the spotfaces and the holes for cracks

Manpower Resources

Manhours 10

Minimum number of person 1

Subtask elapsed time 10

Skills NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) 51-10-01 Part 6, Procedure C

57-51-34, Page Block 901

(a) Do an inspection for cracks in the spotface of each hole where you have removed

the fasteners (Refer to NTM 57-51-34, Page Block 901). If any cracks are found

contact AIRBUS for corrective actions.

(b) Do a rotating probe inspection for cracks in the bore of the holes where you have

removed the fasteners (Refer to NTM 51-10-01 Part 6, Procedure C). If any cracks

are found, contact AIRBUS for further instructions.

(3) Subtask 576110-831-402-001 - Re-cut the spotface.

Manpower Resources

Manhours 12

Minimum number of person 2

Subtask elapsed time 6

Skills AIRFRAME

Material necessary to do the job

Standard tool TOOLB01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

01 STD58-284 Spotface Cutter 1

References

Structural Repair Manual (SRM) 51-40-21

Fig. A-UBAAF

Tapered bush.

Sheet 02

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 23

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@A300-600

SERVICE BULLETIN

References

Fig. A-UCAAA

Recut the spotface.

Sheet 01

(a) Increase the depth of the spotface and the diameter of the hole (Refer to Fig. AUCAAA Sheet 01).

CAUTION: THE DEPTH OF THE SPOTFACE SHOULD BE INCREASED IN

INCREMENTS TO MAKE SURE THAT THE MAXIMUM PERMITTED

DEPTH IS NOT EXCEEDED.

(b) Use a Vernier Caliper to measure the stack length of the holes and record findings.

(c) Increase the depth of the existing spotface by 0.060in,+/-0.010in (1,5mm

+/-0,25mm) and the diameter to 1.80in (45,72mm) with a corner radius of 0.25in

(6,35mm) as follows :

1

NOTE: Tapered bush to be manufactured locally.

2 Recut the spotface to the dimensions detailed using:

Item 01 STD58-284 Spotface Cutter 1

To a surface finish of 63 micro inches (1.6 microns).

3 Remove the tapered bush.

(d) Use a Vernier Caliper to measure the new stack length. Compare the measurement

with the first measurement (which you recorded) to make sure that the correct

amount of material has been removed.

NOTE: If holes 47 and/or 54 have previously had 2nd oversize fasteners

installed in them, they must now be increased to 3rd oversize. 3rd

oversize fasteners and drill, ream and countersink data will be supplied,

on request, from AIRBUS.

(e) Drill, ream and countersink each tapered hole for a second oversize Taper-lok

fastener (Refer to SRM 51-40-21) or the alternative procedure in the Appendix at

the end of this Service Bulletin.

(f) Remove the burrs from each hole.

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 24

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

(4) Subtask 576110-280-402-001 - Inspect the re-cut spotfaces and the holes for

cracks

Manpower Resources

Manhours 10

Minimum number of person 1

Subtask elapsed time 10

Skills NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) 51-10-01 Part 6, Procedure C

57-51-34, Page Block 901

(a) Inspect the recut spotfaces for cracks (Refer to NTM 57-51-34, Page Block 901). If

any cracks are found contact AIRBUS for corrective actions.

(b) Do a rotating probe inspection for cracks in the bore of the holes.(Refer to NTM

51-10-01 Part 6, Procedure C) If any cracks are found, contact AIRBUS for further

instructions.

(5) Subtask 576110-916-401-001 - Apply surface protection

Manpower Resources

Manhours 1

Minimum number of person 2

Subtask elapsed time 0.5

Skills AIRFRAME

Material necessary to do the job

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

03 Chemical Conversion

Coating Yellow Aluminum

13-002 As required

04 Anti-Corrosion Primer

(epoxy-Imprvdadhesion)

16-006 As required

(a) Apply to all bare metal:

Item 03 Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

and

Item 04 Anti-Corrosion

Primer (epoxyImprvdadhesion)

16-006 As required

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 25

7

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@A300-600

SERVICE BULLETIN

(6) Subtask 576110-831-403-001 - Install new fasteners

Manpower Resources

Manhours 8

Minimum number of person 2

Subtask elapsed time 4

Skills AIRFRAME

Material necessary to do the job

Kit 576110B01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 4TL330-12-38N 3 BOLT

2 4TL330-12-40N 2 BOLT

3 4TL330-12-42N 1 BOLT

4 4TL330-12-44N 1 BOLT

5 NSA5472-12K7 7 NUT

6 NSA5368-1216AX 14 WASHER

7 NSA5368-1216BX 7 WASHER

NOTE: This Kit contains 2nd oversize fasteners. If 3rd oversize fasteners are

required, they will be supplied, on request, from AIRBUS (Refer to the

Accomplishment Instructions of this Service Bulletin).

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

05 Fuel Tank Sealant

Polysulfide

09-001

References

Structural Repair Manual (SRM) 51-21-10

(a) Put sealant,

Item 05 Fuel Tank Sealant

Polysulfide

09-001 As required

under the heads of the bolts.

NOTE: Make sure you do not get sealant on the shank of the bolts.

(b) Install the following fasteners in the holes specified:

1 For hole 43,

1 Bolt-Taper Shank 4TL330-12-44N Item 4

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

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SERVICE BULLETIN

2 For hole 47,

1 Bolt-Taper Shank 4TL330-12-42N Item 3

3 For hole 48,

1 Bolt-Taper Shank 4TL330-12-38N Item 1

4 For hole 49,

1 Bolt-Taper Shank 4TL330-12-38N Item 1

5 For hole 50,

1 Bolt-Taper Shank 4TL330-12-40N Item 2

6 For hole 52,

1 Bolt-Taper Shank 4TL330-12-40N Item 2

7 For hole 54,

1 Bolt-Taper Shank 4TL330-12-38N Item 1

8 To enable the correct grip length, these washers can be used if required:

14 WASHER NSA5368-1216AX Item 6

7 WASHER NSA5368-1216BX Item 7

NOTE: The maximum washer stack allowed is 1x AX + 1x BX. Not 2x

BX.

If it is not possible to correctly install the washer in the

spotface:

- Fettle the washer to fit

- Reprotect the bare metal (Refer to SRM 51-21-10).

9 With,

7 Nut NSA5472-12K7 Item 5

Torque tighten the nuts to 2500lbf.in. +/- 250lbf.in. (28.25m.daN +/-

2.82m.daN).

10 Paint the heads of the bolts and the nuts.

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 27

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**CONF ALL

D. TEST

**CONF 001

(1) Subtask 576110-720-401-001 - Test

Manpower Resources

Skills AIRFRAME

(a) Perform the tasks detailed in the installation of the MLG Actuating CylinderAssembly below.

**CONF 002

(1) Subtask 576110-720-401-001 - Test

Manpower Resources

Skills AIRFRAME

(a) Perform the tasks detailed in the installation of the MLG Actuating CylinderAssembly below.

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 576110-942-401-001 - Close-up

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 07-11-00

32-31-46, Page Block 401

(a) Install the MLG Actuating Cylinder-Assembly and the two flexible Hydraulic pipes

and perform the applicable tests (Refer to AMM 32-31-46, Page Block 401).

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

(c) Remove the access platform(s) from below the area of Gear Rib 5.

(d) Lower the aircraft off the main jacks (Refer to AMM 07-11-00).

(e) Remove the warning notices from the Flight compartment.

(f) Put the systems and the aircraft in a normal operating condition.

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 28

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**CONF 002

(1) Subtask 576110-942-401-001 - Close-up

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 07-11-00

32-31-46, Page Block 401

(a) Install the MLG Actuating Cylinder-Assembly and the two flexible Hydraulic pipes

and perform the applicable tests (Refer to AMM 32-31-46, Page Block 401).

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

(c) Remove the access platform(s) from below the area of Gear Rib 5.

(d) Lower the aircraft off the main jacks (Refer to AMM 07-11-00).

(e) Remove the warning notices from the Flight compartment.

(f) Put the systems and the aircraft in a normal operating condition.

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 29

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**CONF ALL

RETRACTION JACK

ATTACHMENT POINT

REAR SPAR

DATUM

GEAR RIB 5

GEAR RIB 5

ALL VIEWS LEFT HAND,

RIGHT HAND SIMILAR

PLAN VIEW

LH WING

HOLE 47

REAR SPAR

DATUM

NOTE:

HOLE 48

HOLE 50

HOLE 54

PICK−UP FOR TWO

REACTION RODS

HOLE 43

HOLE 49

HOLE 52

MAIN LANDING

GEAR − REAR

BEARING LUGS

MAIN LANDING

GEAR − FRONT

TRUNNION BEARING

MAIN LANDING GEAR −

REAR BEARING LUGS

MAIN LANDING GEAR

NOT SHOWN FOR CLARITY

MODIFICATION

AREA

VIEW LOOKING OUTBOARD

D_SB_576110_7_AAAA_01_00

A

A

B

F

W

D

INBD

U

P

FWD

B

Figure A-UAAAA - Sheet 01

Area of Modification - Hole Positions

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 30

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SERVICE BULLETIN

**CONF 001

L

*NOTE:

DIA. A

DIA. B

CUT THE PARALLEL

BUSH TO THE LENGTH

REQUIRED FOR THE

HOLE THAT YOU

ARE WORKING ON.

TOOL LIST

REF.

MATERIAL − L64,L65

2014T4XXX, 2014T6XXX

OR 2024T351X

CHS366A−14*

1st OVERSIZE

A

INCHES

D_SB_576110_7_AAAA_03_00

(mm)

B

INCHES

(mm)

L

INCHES

(mm)

*NOTE: 0.760/0.762

(19.30/19.35)

0.376/0.381

(9.55/9.68)

NUMBER

Figure A-UBAAG - Sheet 03

Parallel bush.

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 31

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SERVICE BULLETIN

**CONF 002

*NOTE:

DIA. A

DIA. B

BUSH TO THE LENGTH

REQUIRED FOR THE

HOLE THAT YOU

ARE WORKING ON.

TOOL LIST

REF.

MATERIAL − L64,L65

2014T4XXX, 2014T6XXX

OR 2024T351X

CHS405A−51*

A

INCHES

NUMBER (mm)

B

INCHES

(mm)

L

INCHES

(mm)

*NOTE: 0.833/0.835

(21.16/21.21)

0.376/0.381

(9.55/9.68)

L

THE RATIO OF THE TAPER FOR

THE OUTSIDE DIA. IS 1 IN 48.

CUT THE TAPERED

D_SB_576110_7_AAAA_02_00

Figure A-UBAAF - Sheet 02

Tapered bush.

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 32

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**CONF ALL

GEAR RIB 5 SPOTFACE CUTTER

BOTTOM SKIN

REINFORCING PLATE

TAPERED BUSH ARBOR

STD. DRILL

INCREASED

SPOTFACE

DIAMETER

AFTER

BEFORE

CUTTER

DIAMETER

SPOTFACE

DIAMETER

0.25in.(6.35mm)

CORNER RADIUS

TYPICAL SECTION THROUGH BOLT HOLE

MEASURE THIS DIMENSION

BEFORE REMOVING ANY MATERIAL

THIS FINAL MEASUREMENT TO BE

0.060in. (1.50mm) LESS THAN THE

MEASUREMENT TAKEN BEFORE

THE SPOTFACE WAS RECUT

0.25in.(6.35mm)

CORNER RADIUS

D_SB_576110_7_AAAE_01_00

Figure A-UCAAA - Sheet 01

Recut the spotface.

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 33

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This Page Intentionally Left Blank

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 34

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APPENDIX 1 Oversize TAPER-LOK Fasteners

**CONF ALL

(1) This procedure defines general operations to oversize TAPER- LOK to R1 or R2.Fig. A-USUAA Fig.

A-USUAA Sheet 01and Fig. A-USUAA Sheet 02If it is necessary to create a tapered hole starting from

a hole, then specific adaptations are required.

(2) Tools and MaterialFig. A-USUAA Fig. A-USUAA Sheet 03

NOTE: Re-grinding of tools can only be handled by the tooling manufacturer. Tools should not

be re-ground by operators. Handle the tools carefully to prevent them from falling.

NOTE: Contact the tooling manufacturer to order tooling with appropriate part numbers and

following data: - Original TAPER-LOK data (head-and bolt end marking), - Repair

TAPER-LOK data (head-and bolt end marking), - Access constrains (could influence

reamer length), - Tools part number last digit figure in tool designation, when required,

corresponds to an attachment code. It will be defined by the manufacturer itself.

For Tooling Contact refer to: CAPAERO S.A.S - Siege Social: Le Ray - 33550 CAPIAN

- France Tel.: +33.5.56.72.62.93 - Fax: +33.5.40.16.02.37 http://www.capaero.com - email: contact@capaero.com SAS au capital de 37000 Euros - RCS Bordeaux 482 442

746 Code APE 7112B - NCAGE: FARC9 - Siret 482 442 746 00012

(3) Hole Reaming

(a) Select the applicable Single Flute Reamer.

(b) Perform a reaming test on a piece of material that is of the same type and thickness as the material

to be fastened. Do this step until you have reached the final hole dimension required for the repair

Taper-lok.

NOTE: This step will familiarize the operator with tools and method. A test specimen per tool

drawing 98D571030010000 can be used.

(c) Progressive hole reaming with regular protrusion checking using the repair Taper-Lok:

1 Put the final repair Taper-Lok into the original hole to assess the amount off material to be reamed.

2 Put the reamer accurately over the hole. Make sure that the reamer is in line with the vertical axis of

the hole.

3 Progressively ream the hole. Use a cutting lubricant during this step. Make sure that the drill reamer

moves through the material slowly, but with a constant hand pressure applied in the axis of the hole.

Regularly stop reaming to remove metallic chips and check the repair Taper-Lok protrusion. To do this

check, install the repair Taper-Lok in the cleaned hole. The measured protrusion must be within the

range indicated. That defines when the reaming is finished.

NOTE: Keep on rotating the reamer in the same direction when removing the reamer from the

hole for quality reasons.Fig. A-USUAA Fig. A-USUAA Sheet 04 Fig. A-USUAA Sheet 05

(4) Deburr the edges of the hole (entry and exit slide) then clean and dry the hole to remove chips and

grease that could affect next measurement.

(5) Do the steps that follow on all the prepared holes to make sure that they have the correct

interference fit.

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

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APPENDIX 1 Oversize TAPER-LOK Fasteners

(a) If available, install the plug gauge into the Blueing Gauge Holder BGH-***.

(b) Attach the Blueing Gauge Holder BGH-*** to the hammering tool HAMT-5.

(c) Apply a layer of engineers blue dye (recommended ref.: Prussian Blue Permatex ref.: 80038 or

Orapi ref.: Bleu de prusse 975 - 1 tube included in SOA kit ) to the face of the applicable plug gauge.

(d) Put the Blueing Gauge into the hole and lightly tap it with the hammering tool.

NOTE: CAUTION: TAKE CARE NOT TO CHANGE THE MARKS IN THE ENGINEERS BLUE

ON THE PLUG GAUGE WHEN YOU PERFORM THIS STEP.

(e) Carefully extract the plug gauge from the hole with the hammering tool.

(f) Look at the marks in the engineers blue on the shank of the plug gauge. If the marks show that:

- 60% or more of the plug gauge shank touched the face of the hole, the hole is satisfactory,

- less than 60% of the plug gauge shank touched the face of the hole, slightly manually re-machine the

hole to get the correct quality. The minimum bolt protrusion must be fulfilled.

(g) If reading is difficult (too much Prussian Blue used for example), then clean the hole and the gauge

and perform the verification again.Fig. A-USUAA Fig. A-USUAA Sheet 06

(4) Countersink Machining (For Countersunk Head Taperloks only)

(a) Select the relevant countersink depth gauge. Put it into countersink hole to assess the amount of

material to be removed to ensure a flush installation. It will be necessary to remove omly a small

amount of material for the next oversize.Fig. A-USUAA Fig. A-USUAA Sheet 07

(b) Install the relevant tapered guide into the tapered hole.Fig. A-USUAA Fig. A-USUAA Sheet 08

(c) Install the 100 degree Countersink Cutter in a pneumatic drill machine. A low rotation speed for the

pneumatic drill machine must be selected for quality reasons (150-200 rpm).

(d) Align the cutter pilot in the tapered guide bushing to control the cutter position.

(e) Progressively machine the countersink to the required depth defined by the adapted depth gauge.

Use a cutting lubricant. Machining must be stopped on a regular basis to check the countersink

dimension with the countersink depth gauge.

NOTE: This step is essential to guarantee the correct final dimension of the countersink. Take

care not to exceed the required dimension.Fig. A-USUAA Fig. A-USUAA Sheet 09

(f) Under-Head Chamfer Machining (For Countersunk and Protruding Head TAPER-LOK).

(g) Slightly manually machine the under-head chamfer using the 60 degree or 90 degree countersink

cutter keeping a good alignment of the tool and hole axis.Fig. A-USUAA Fig. A-USUAA Sheet 10

(h) Visual confirmation is considered as sufficient for approximate values specified in the following table.

The objective of the chamfer is to avoid sharp edges and stress concentration below fastener heads.

(i) Deburr the edges of the hole.Fig. A-USUAA Fig. A-USUAA Sheet 11

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 2

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APPENDIX 1 Oversize TAPER-LOK Fasteners

DIAMETER DIAMETER COUNTERSUNK

HEAD

COUNTERSUNK

HEAD

PROTRUDING

HEAD

PROTRUDING

HEAD

x x x x

in. (1/16) mm mm in. mm in.

4 6.35 0.2

0.1

0.008

0.004

0.5

0.4

0.0197

0.0157

5 7.92 0.25

0.15

0.010

0.006

0.6

0.5

0.0236

0.0197

6 9.52 0.25

0.15

0.010

0.006

0.6

0.5

0.0236

0.0197

7 11.1 0.3

0.2

0.012

0.008

0.6

0.5

0.0236

0.0197

8 12.7 0.3

0.2

0.012

0.008

0.6

0.5

0.0236

0.0197

9 14.3 0.45

0.35

0.018

0.014

0.75

0.65

0.0295

0.0256

10 15.9 0.45

0.35

0.018

0.014

0.75

0.65

0.0295

0.0256

12 19.1 0.6

0.5

0.024

0.020

1

0.9

0.0394

0.0354

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

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APPENDIX 1 Oversize TAPER-LOK Fasteners

**CONF ALL

TO ASSESS THE AMOUNT OF MATERIAL TO BE MACHINED

CHECK PROTRUSION WITH REPAIR TAPERLOK IN EXISTING HOLE

REAM TAPERED HOLE TO 0.02mm (0.0008in.) TOLERANCE CHECK FASTENER PROTRUSION

NOTE:

STOP MACHINING WHEN PROTRUSION IS WITHIN MINIMUM AND MAXIMUM OF GAGE

INSPECT HOLE FOR BEARING

STEP 1

STEP 2

STEP 3

D_SB_576110_7_SUAA_01_00

Figure A-USUAA - Sheet 01

Oversize TAPER-LOK Fasteners

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 4

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APPENDIX 1 Oversize TAPER-LOK Fasteners

**CONF ALL

NOTE:

STEP 1

COUNTERSINK USING

GUIDED 100° CUTTER

COUNTERSINK CHECK

GAGE INSTALLED

FLUSH

STOP MACHINING WHEN COUNTERSINK CHECK GAGE CAN INSTALL FLUSH

STEP 2

NOTE:

SLIGHTLY MACHINE THE

WITH 60° OR 90° CUTTER

TO COUNTERSINK AREA

SLIGHTLY MACHINE HOLE

INSTALL COUNTERSINK CHECK

GAGE TO ASSESS THE AMOUNT

STEP 3

STEP 4

OF MATERIAL TO BE MACHINED

TORQUE−UP FASTENER

UNDER−HEAD CHAMFER MACHINING BOTH FOR PROTRUDING AND COUNTERSUNK TAPERLOKS

D_SB_576110_7_SUAA_02_00

Figure A-USUAA - Sheet 02

Oversize TAPER-LOK Fasteners

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

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APPENDIX 1 Oversize TAPER-LOK Fasteners

**CONF ALL

ITEM TOOLING DESIGNATION TOOLING REFERENCE SYSTEM TOOLING EXAMPLE FOR A 7/16 in. TL945 GROUP 3

OR

COUNTERSINK

CUTTER 100° CC100*

COUNTERSINK RANGE

2

TGB*G*TL*

DIAMETER GROUP

MULTI−GROUP

SINGLE GROUP

OR DIAMETER GROUP(S)

4 COUNTERSINK CUTTER

60° OR 90°

CC100B

COUNTERSINK RANGE

CC60B

1 SINGLE FLUTE REAMER

SFR*G*TL*

SFR*G*−*TL*

REAMER

REAMER

MULTI−GROUP

SINGLE GROUP

OR

SFR7G3TL2

SFR7G1−4TL2

DIAMETER GROUP(S) REAMER ATTACHMENT

5 BLUEING GAUGE

BG*G*TL*

BG*G*−*TL*

GAUGE

GAUGE

BG7G3TL2

BG7G1−4TL2

GAUGE ATTACHMENT

3 TAPERED GUIDE

BUSHING

TGB7G3TL

DIAMETER GROUP

OR

CC60*

CC90* FOR PROTRUDING

HEAD TAPERLOKS

6 COUNTERSINK DEPTH

GAUGE

CDG*G*TL

CDG*G*TL300

FOR TENSION

HEAD

TAPERLOKS

CDG7G3TL

9 HAMMERING TOOL

HAMMER TOOL HAMT−5 HAMT−5

7 PROTRUSION GAUGE PG* PG7 DIAMETER

9A

9B

8 REAMER MANUAL

ADAPTER / HANDLE RMA* RMA2 REAMER ATTACHMENT

BLUEING GAUGE

HOLDER BGH* BGH2 BLUEING GAUGE ATTACHMENT

HOLDING SYSTEM:

BLUEING GAUGE

HOLDER

HAMMERING TOOL

+

9B

9A

8

6

1

2

7

4

3 8

5

9

D_SB_576110_7_SUAA_03_00

Figure A-USUAA - Sheet 03

Oversize TAPER-LOK Fasteners

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 6

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APPENDIX 1 Oversize TAPER-LOK Fasteners

**CONF ALL

D_SB_576110_7_SUAA_04_00

Figure A-USUAA - Sheet 04

Oversize TAPER-LOK Fasteners

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

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APPENDIX 1 Oversize TAPER-LOK Fasteners

**CONF ALL

P

PROTRUSION BEFORE TAPERLOK INSTALLATION

DIAMETER P MIN P MAX

in. (1/16) mm in. mm in. mm

4

5

6

7

8

9

10

12

6.4

7.9

9.5

11.1

12.7

14.3

15.9

19

0.086

0.101

0.115

0.130

0.144

0.158

0.173

0.202

2.18

2.56

2.92

3.30

3.66

4.01

4.39

5.13

0.202

0.230

0.259

0.288

0.317

0.346

0.374

0.432

5.13

5.84

6.58

7.31

8.05

8.79

9.50

10.97

P

P MIN

P MAX

D_SB_576110_7_SUAA_05_00

Figure A-USUAA - Sheet 05

Oversize TAPER-LOK Fasteners

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 8

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APPENDIX 1 Oversize TAPER-LOK Fasteners

**CONF ALL

BEARING SURFACE (GREY COLORED)

NON−BEARING SURFACE (BLUE COLORED)

D_SB_576110_7_SUAA_06_00

Figure A-USUAA - Sheet 06

Oversize TAPER-LOK Fasteners

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

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APPENDIX 1 Oversize TAPER-LOK Fasteners

**CONF ALL

D_SB_576110_7_SUAA_07_00

Figure A-USUAA - Sheet 07

Oversize TAPER-LOK Fasteners

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 10

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APPENDIX 1 Oversize TAPER-LOK Fasteners

**CONF ALL

CUTTER PILOT

ATTACHMENT FOR

PNEUMATIC DRILL

MACHINE

TAPERED GUIDE

BUSHING

COUNTERSINK

CUTTER 100°

D_SB_576110_7_SUAA_08_00

Figure A-USUAA - Sheet 08

Oversize TAPER-LOK Fasteners

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

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APPENDIX 1 Oversize TAPER-LOK Fasteners

**CONF ALL

D_SB_576110_7_SUAA_09_00

Figure A-USUAA - Sheet 09

Oversize TAPER-LOK Fasteners

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

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APPENDIX 1 Oversize TAPER-LOK Fasteners

**CONF ALL

D_SB_576110_7_SUAA_10_00

Figure A-USUAA - Sheet 10

Oversize TAPER-LOK Fasteners

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 13

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APPENDIX 1 Oversize TAPER-LOK Fasteners

**CONF ALL

X

2°

X

60° 2° 90°

D_SB_576110_7_SUAA_11_00

Figure A-USUAA - Sheet 11

Oversize TAPER-LOK Fasteners

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 14

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@A300-600

SERVICE BULLETIN

REPORTING SHEET

TITLE: WINGS - STRUCTURE - MLG RIB 5 FURTHER SPOTFACING ON

BOTTOM FLANGE

MODIFICATION No.: 13534H5720

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:

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: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate 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 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: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 1

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@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 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- 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 Operator Supplied X Mod/Inspection

X Manpower X Industry support 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 : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Jun 07/10 SERVICE BULLETIN No.: A300-57-6110

REVISION No.: 01 - Jun 06/11 Page: 1

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.