@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: 53

TITLE: INSPECTION HOLES FUSELAGE FRAME 47 SPLICE FITTING

BETWEEN STRINGERS 24 AND 26 LH AND RH SIDES.

MODIFICATION No.: None

This page transmits Revision No.06 of Service Bulletin No.A300-53-6123

ADDITIONAL WORK

**CONF ALL

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

REASON

Revision No. 06 issued to introduce minor improvements.

CHANGES

SUMMARY

EFFECTIVITY OPERATOR LIST UPDATED R

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Configuration definition

CONF 001 CONFIGURATION DEFINITION UPDATED

CONFIGURATION DESCRIPTION UPDATED

R

CONF 002 CONFIGURATION DEFINITION UPDATED

CONFIGURATION DESCRIPTION UPDATED

R

COMPLIANCE

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE 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: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 1

5

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@A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

HISTORY OF PREVIOUS REVISIONS

Revision No. 01 issued to inform the operators that Service Bulletin No. A300-53-6123 replaces the All

Operator Telex (AOT) A300-53A6123.

Revision No. 02 issued:

To inform the operators that this Service Bulletin is rendered mandatory by Airworthiness Directive

(Consigne de navigabilite) No. 2002-184(B)

To include minor improvements after validation of this Service Bulletin on A300-600 aircraft MSN 0635.

To add aircraft MSN 0834, 0835, 0839, 0840, 0841 for operator UPS and to add aircraft MSN 0836,

0837, 0838 for operator JAS.

Revision No. 03 issued to add operator AHK aircraft MSN 0855, 0856, 0857, 0858, 0859, 0860, and

aircraft MSN 0845, 0846, 0847, 0848, 0849, 0850, 0851, 0852, 0853, 0854, 0861, 0862, 0863, 0864 for

operator UPS.

Revision No. 04 issued to delete aircraft MSN 0377 for operator 98W, to add aircraft MSN 0870 and

0871 for operator AHK, to add aircraft MSN 0873 thru 0878 for operator FDX, to add aircraft MSN 0872

for operator GXY, to delete aircraft MSN 0690 for operator QTR to delete aircraft MSN 0371 for

operator THA and to add aircraft MSN 0866 thru 0869 for operator UPS.

Revision No. 05 issued to modify the threshold and interval of the inspection.

REVISION SEQUENCE

ORIGINAL: Oct 25/99

REVISION No.: 02 - Nov 12/02

REVISION No.: 03 - Aug 20/04

REVISION No.: 04 - Apr 25/08

REVISION No. : 05 - Aug 01/11

REVISION No. : 06 - Sep 28/11

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 2

5

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@A300-600

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: 53

TITLE: INSPECTION HOLES FUSELAGE FRAME 47 SPLICE FITTING

BETWEEN STRINGERS 24 AND 26 LH AND RH SIDES.

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Service Bulletin No. A300-53-0199 and A300-53-6131, modification No. 05890S6739, specifies cold

working of fastener holes in the splice fitting at FR47.

The Service Bulletin No.A300-53-0199 currently terminates the inspection requirements of Service

Bulletin No. Airplane Characteristics (AC) 53-0200. Cracks have been found on post Service Bulletin

No. A300-53-0199 aircraft in the fastener holes which attach the splice fitting to FR47 (ref. A300 SRM

53-15-00 Fig. 112 item 39 and A300-600 SRM 57-10-24 Fig. 8 item 125A).

A laboratory investigation has been performed on a cracked splice fitting, and the analysis of the crack

growth rate shows that an inspection program is required for post Service Bulletin No. A300-53-0199

B4/C4/F4 aircraft.

Due to the structural similarity, the inspection is also required on A300-600 aircraft.

All Operators Telex A300-53A350 and All Operators Telex A300-600-53A6123 were issued to call for a

one-time inspection of the splice fitting between stringers 24 and 26, LH and RH sides.

This Service Bulletin has been created to define a new inspection program for the pre-mod. and

post-mod. 05890S6739 aircraft (FUSELAGE - FRAME 47 - REINFORCE LATERAL SECTION BY

STRENTHENED FISH PLATE).

This Service Bulletin recommends an HFEC rotating probe inspection after bolt removals of the splice

fitting between stringers 24 and 26 and subsequent action in case of findings.

Accomplishment of this Service Bulletin permits early detection of cracking in the splice fitting to avoid

cracking in the FR47 which would require extensive repairs.

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 1

5

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

SERVICE BULLETIN

SUMMARY

According to an analysis performed in the frame of A300 ESG2 (Escalated Service Goal 2) activities,

This Service Bulletin is impacted by material data change and new range effect method. It is revised

accordingly by modifying the inspection thresholds and intervals and introducing the notion of SR and

LR aircraft.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) 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

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 536123A01R01 1 2,050.00 Pin, Nut, Washer

Kit 536123A02R01 1 946.00 Pin, Nut, Washer

Kit 536123A04R01 1 452.00 Pin, Nut, Washer

Kit 536123A06R01 1 1,620.00 Pin, Nut, Washer

Kit 536123A07R02 1 21,530.00 Pin, Nut, Washer

Kit 536123A08R00 1 1,970.00 Splice

Kit 536123A09R00 1 1,970.00 Splice

Kit 536123A10R01 2 10,160.00 Pin, Nut

Kit 536123A12R01 2 9,800.00 Pin, Nut

Kit 536123A13R01 2 3,160.00 Pin, Nut

TOTAL 53,658.00

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 536123A03R01 1 1,060.00 Pin, Nut, Washer

Kit 536123A05R01 1 1,100.00 Pin, Nut, Washer

Kit 536123A07R02 1 21,530.00 Pin, Nut, Washer

Kit 536123A08R00 1 1,970.00 Splice

Kit 536123A09R00 1 1,970.00 Splice

Kit 536123A11R01 2 5,860.00 Pin, Nut

Kit 536123A13R01 2 3,160.00 Pin, Nut

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 2

5

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

SERVICE BULLETIN

SUMMARY

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

TOTAL 36,650.00

EFFECTIVITY

**CONF ALL

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

30T 83V AAL ABD AHK AIB AMU BCS CES CSN F2I FDX G8E

IRA IRM JAL KAC KAL MNB MON MSR MXU OHY QTR RNV SUD

TAR THA TMA UPS UZB

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 536123-832-802-001: Inspection

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

Task 536123-833-802-001: Repair

TOTAL MANHOURS 204.00

ELAPSED TIME (HOURS) 34.00

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 3

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@A300-600

SERVICE BULLETIN

SUMMARY

**CONF 002

Task 536123-832-802-001: Inspection

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

Task 536123-833-802-001: Repair

TOTAL MANHOURS 116.00

ELAPSED TIME (HOURS) 34.00

APPENDICES

**CONF ALL

Inspection Report

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 4

5

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

SERVICE BULLETIN

SUMMARY

**CONF ALL

B

A

FR40 FR47

B

N

M

L

I J

K

G

STRG24

STRG25

C

RH SIDE SHOWN

LH SIDE SYMMETRICAL

SECTION

C

F

E

D

C

B

A

STRG26

H

A

B

HOLES TO BE INSPECTED

(A to N)

D_SB_536123_5_SAAA_01_00

Figure A-FSAAA - Sheet 01

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 5

5

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@A300-600

SERVICE BULLETIN

SUMMARY

This Page Intentionally Left Blank

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 6

5

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: 53

TITLE: INSPECTION HOLES FUSELAGE FRAME 47 SPLICE FITTING

BETWEEN STRINGERS 24 AND 26 LH AND RH SIDES.

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

**CONF ALL

A. EFFECTIVITY

(1) Models

B4-603 B4-605R B4-620 B4-622 B4-622R C4-605R/FC4-620 F4-605R

F4-622R

(2) Effectivity by MSN

0284 0294 0301 0307 0312 0317 0321 0336 0344 0348 0351 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 0602-0615 0617-0618 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 0752-0764 0766-0775 0777-0794

0797 0799-0841 0845-0878

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 1

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@A300-600

SERVICE BULLETIN

(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.

OPERATOR MSN

30T 0626 0643

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

0675

AAL 0517 0612

ABD 0529 0557

AHK 0855 0856 0857 0858 0859 0860 0870 0871

AIB 0507 0508 0515

AMU 0677 0743

BCS 0621 0637 0641 0670 0679 0711 0724 0729 0740

CES 0521 0525 0532 0707 0725 0732 0741 0746 0754 0763

CSN 0756

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

0606 0610 0645 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 0792 0793 0794 0799

0800 0801 0802 0803 0804 0873 0874 0875 0876 0877 0878

G8E 0462 0465 0469 0506 0509 0513 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 0683 0703 0730 0737 0783 0838

KAC 0344 0673 0694 0699 0719 0721

KAL 0582 0609 0627 0631 0662 0685 0692 0731

MNB 0733 0734 0739 0755 0758

MON 0540 0556 0604 0605

MSR 0561 0607

MXU 0767 0788 0797 0836 0837

OHY 0584 0603 0744 0747 0749 0764

QTR 0554 0560 0614

RNV 0464

SUD 0666 0775

TAR 0505 0558 0563

THA 0566 0569 0577 0628 0629 0635 0681 0705 0782 0784 0785 0786

0787

TMA 0872

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 2

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@A300-600

SERVICE BULLETIN

OPERATOR MSN

UPS 0805 0806 0807 0808 0809 0810 0811 0812 0813 0814 0815 0816

0817 0818 0819 0820 0821 0822 0823 0824 0825 0826 0827 0828

0829 0830 0831 0832 0833 0834 0835 0839 0840 0841 0845 0846

0847 0848 0849 0850 0851 0852 0853 0854 0861 0862 0863 0864

0865 0866 0867 0868 0869

UZB 0717 0722

(4) Configuration by MSN

MSN CONFIGURATION

0284 0294 0301 0307 0312 0317 0321 0336 0344 0348 0351

0358 0361 0365

001

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 0602 0603

0604 0605 0606 0607 0608 0609 0610 0611 0612 0613 0614

0615 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 0754 0755 0756 0757 0758 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 0788 0789 0790 0791 0792 0793 0794 0797

0799 0800 0801 0802 0803 0804 0805 0806 0807 0808 0809

0810 0811 0812 0813 0814 0815 0816 0817 0818 0819 0820

0821 0822 0823 0824 0825 0826 0827 0828 0829 0830 0831

0832 0833 0834 0835 0836 0837 0838 0839 0840 0841 0845

0846 0847 0848 0849 0850 0851 0852 0853 0854 0855 0856

0857 0858 0859 0860 0861 0862 0863 0864 0865 0866 0867

0868 0869 0870 0871 0872 0873 0874 0875 0876 0877 0878

002

(5) Configuration definition

**CONF 001

Config 001 is valid for aircraft on which Mod No. 05890S6739 (FUSELAGE - FRAME 47

- REINFORCE LATERAL SECTION BY STRENTHENED FISH PLATE) is not embodied.

**CONF 002

Config 002 is valid for aircraft on which Mod No. 05890S6739 (FUSELAGE - FRAME 47

- REINFORCE LATERAL SECTION BY STRENTHENED FISH PLATE) is embodied.

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 3

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@A300-600

SERVICE BULLETIN

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLA01 1

Kit 536123A01R01 1

Kit 536123A02R01 1

Kit 536123A04R01 1

Kit 536123A06R01 1

Kit 536123A07R02 1

Kit 536123A08R00 1

Kit 536123A09R00 1

Kit 536123A10R01 2

Kit 536123A12R01 2

Kit 536123A13R01 2

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLA01 1

Kit 536123A03R01 1

Kit 536123A05R01 1

Kit 536123A07R02 1

Kit 536123A08R00 1

Kit 536123A09R00 1

Kit 536123A11R01 2

Kit 536123A13R01 2

**CONF ALL

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

Service Bulletin No. A300-53-0199 and A300-53-6131, modification No. 05890S6739,

specifies cold working of fastener holes in the splice fitting at FR47.

The Service Bulletin No.A300-53-0199 currently terminates the inspection requirements

of Service Bulletin No. Airplane Characteristics (AC) 53-0200. Cracks have been found

on post Service Bulletin No. A300-53-0199 aircraft in the fastener holes which attach the

splice fitting to FR47 (ref. A300 SRM 53-15-00 Fig. 112 item 39 and A300-600 SRM

57-10-24 Fig. 8 item 125A).

A laboratory investigation has been performed on a cracked splice fitting, and the

analysis of the crack growth rate shows that an inspection program is required for post

Service Bulletin No. A300-53-0199 B4/C4/F4 aircraft.

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 4

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SERVICE BULLETIN

Due to the structural similarity, the inspection is also required on A300-600 aircraft.

All Operators Telex A300-53A350 and All Operators Telex A300-600-53A6123 were

issued to call for a one-time inspection of the splice fitting between stringers 24 and 26,

LH and RH sides.

This Service Bulletin has been created to define a new inspection program for the premod. and post-mod. 05890S6739 aircraft (FUSELAGE - FRAME 47 - REINFORCE

LATERAL SECTION BY STRENTHENED FISH PLATE).

(2) Objective/Action

This Service Bulletin recommends an HFEC rotating probe inspection after bolt removals

of the splice fitting between stringers 24 and 26 and subsequent action in case of

findings.

(3) Advantages

Accomplishment of this Service Bulletin permits early detection of cracking in the splice

fitting to avoid cracking in the FR47 which would require extensive repairs.

According to an analysis performed in the frame of A300 ESG2 (Escalated Service Goal

2) activities, This Service Bulletin is impacted by material data change and new range

effect method. It is revised accordingly by modifying the inspection thresholds and

intervals and introducing the notion of SR and LR aircraft.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 536123-832-802-001: Inspection

(1) Do a Special Inspection of the Holes Fuselage at FR47 Splice Fitting between STGR

24 and 26 LH and RH sides.

Task 536123-833-802-001: Repair

(1) Install new Fasteners of same Diameter for Aircraft having a Basic Splice and on

which Service Bulletin A300-53-6131 is not accomplished.

(2) Install new Fasteners of same Diameter for Aircraft having a Basic Splice and on

which Service Bulletin A300-53-6131 is accomplished.

(3) Install new Fasteners of same Diameter for Aircraft having a Reinforced Splice

(Replaced by Repair Instruction R53810423 SOL. A)

(4) Install new Fasteners of same Diameter for Aircraft having a Reinforced Splice

(Replaced by Repair Instruction R53810423 SOL. C)

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 5

5

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@A300-600

SERVICE BULLETIN

(5) Install new fasteners on the splice (transition fit)

(6) Replace splice, LH side (replace by Repair Instruction R53810423, SOL. A.)

(7) Replace splice, RH side (replace by Repair Instruction R53810423, SOL. A.)

(8) Replace splice, LH side (replace by Repair Instruction R53810423, SOL. C.)

(9) Replace splice, RH side (replace by Repair Instruction R53810423, SOL. C.)

(10) Install new fasteners for the adjacent holes

**CONF 002

Task 536123-832-802-001: Inspection

(1) Do a Special Inspection of the Holes Fuselage at FR47 Splice Fitting between STGR

24 and 26 LH and RH sides.

Task 536123-833-802-001: Repair

(1) Install new Fasteners of same Diameter for Aircraft having a Reinforced Splice.

(2) Install new Fasteners of same Diameter for Aircraft having a Reinforced Splice

(Replaced by Repair Instruction R53810423 SOL. B)

(3) Install new fasteners on the splice (transition fit)

(4) Replace splice, LH side (replace by Repair Instruction R53810423, SOL. B.)

(5) Replace splice, RH side (replace by Repair Instruction R53810423, SOL. B.)

(6) Install new fasteners for the adjacent holes

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

THRESHOLD PRE-MOD. 05890 POST-MOD. 05890 or POST

Service Bulletin A300-53-6131

LR (AFT more than 1.5 hours) 2500 Flight Cycle (FC) / 5500

Flight hours (FH)

6800 FC / 14700 FH

SR (AFT less than or equal 1.5

hours)

2700 FC / 4100 FH 7300 FC / 11000 FH

TABLE 1 : THRESHOLD

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 6

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

SERVICE BULLETIN

POST-MOD. 05890 or POST Service Bulletin

A300-53-6131

INTERVAL PRE-MOD. 05890

BASIC SPLICE PN

A53834139-202/203

REINFORCED SPLICE

PN A53812635-200/201

or A53812635-202/203

LR (AFT more than 1.5

hours)

2000 FC / 4300 FH 1600 FC / 3500 FH

SR (AFT less than or

equal 1.5 hours)

2100 FC / 3200 FH 1700 FC / 2600 FH

TABLE 2 : INTERVAL

AFT : Average Flight Time

SR : Short Range

LR : Long Range

NOTE: A grace period of 800 FC / 1750 FH is granted to aircraft which have

exceeded the revised thresholds/intervals after receipt of the Service

Bulletin at revision No. 05 without exceeding previous Service Bulletin

value.

This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued

to confirm this classification. It is anticipated that the AD will confirm the (thresholds

and/or intervals and/or date) given above but reference should be made to the AD for

confirmation of 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 536123-832-802-001: Inspection

Get Access 4.00

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 7

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SERVICE BULLETIN

Task 536123-832-802-001: Inspection

On Aircraft

Do a Special Inspection of the Holes Fuselage at FR47

Splice Fitting between STGR 24 and 26 LH and RH

sides.

2.00

Close-Up 4.00

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

Task 536123-833-802-001: Repair

Get Access 4.00

On Aircraft

Install new Fasteners of same Diameter for Aircraft

having a Basic Splice and on which Service Bulletin

A300-53-6131 is not accomplished.

18.00

Install new Fasteners of same Diameter for Aircraft

having a Basic Splice and on which Service Bulletin

A300-53-6131 is accomplished.

18.00

Install new Fasteners of same Diameter for Aircraft

having a Reinforced Splice (Replaced by Repair

Instruction R53810423 SOL. A)

18.00

Install new Fasteners of same Diameter for Aircraft

having a Reinforced Splice (Replaced by Repair

Instruction R53810423 SOL. C)

18.00

Install new fasteners on the splice (transition fit) 10.00

Replace splice, LH side (replace by Repair Instruction

R53810423, SOL. A.)

26.00

Replace splice, RH side (replace by Repair Instruction

R53810423, SOL. A.)

26.00

Replace splice, LH side (replace by Repair Instruction

R53810423, SOL. C.)

26.00

Replace splice, RH side (replace by Repair Instruction

R53810423, SOL. C.)

26.00

Install new fasteners for the adjacent holes 10.00

Close-Up 4.00

TOTAL MANHOURS 204.00

ELAPSED TIME (HOURS) 34.00

NOTE: The total manhours and the elapsed time depends on the aircraft

configuration and on the result of the inspection.

**CONF 002

Task 536123-832-802-001: Inspection

Get Access 4.00

On Aircraft

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 8

5

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

SERVICE BULLETIN

Task 536123-832-802-001: Inspection

Do a Special Inspection of the Holes Fuselage at FR47

Splice Fitting between STGR 24 and 26 LH and RH

sides.

2.00

Close-Up 4.00

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

Task 536123-833-802-001: Repair

Get Access 4.00

On Aircraft

Install new Fasteners of same Diameter for Aircraft

having a Reinforced Splice.

18.00

Install new Fasteners of same Diameter for Aircraft

having a Reinforced Splice (Replaced by Repair

Instruction R53810423 SOL. B)

18.00

Install new fasteners on the splice (transition fit) 10.00

Replace splice, LH side (replace by Repair Instruction

R53810423, SOL. B.)

26.00

Replace splice, RH side (replace by Repair Instruction

R53810423, SOL. B.)

26.00

Install new fasteners for the adjacent holes 10.00

Close-Up 4.00

TOTAL MANHOURS 116.00

ELAPSED TIME (HOURS) 34.00

NOTE: The total manhours and the elapsed time depends on the aircraft

configuration and on the result of the inspection.

**CONF ALL

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 9

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SERVICE BULLETIN

J. REFERENCES

**CONF 001

Airplane Characteristics (AC) Airplane Characteristics (AC)

53-0200

Aircraft Maintenance Manual (AMM) 20-21-12 24-00-00 25-12-11

25-21-00 25-23-31 51-23-10

All Operators Telex (AOT) All Operators Telex A300-53A350

All Operators Telex

A300-600-53A6123

Consumable Material List (CML)

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

Non Destructive Test Manual (NTM) 51-10-01 51-10-07

Repair Instruction R53810423

Service Bulletin (SB) A300-53-0199

A300-53-6131

Standards Manual (SM)

Structural Repair Manual (SRM) 51-40-30 51-40-41

**CONF 002

Airplane Characteristics (AC) Airplane Characteristics (AC)

53-0200

Aircraft Maintenance Manual (AMM) 20-21-12 24-00-00 25-12-11

25-21-00 25-23-31 51-23-10

All Operators Telex (AOT) All Operators Telex A300-53A350

All Operators Telex

A300-600-53A6123

Consumable Material List (CML)

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

Non Destructive Test Manual (NTM) 51-10-01 51-10-07

Repair Instruction R53810423

Service Bulletin (SB) A300-53-0199

A300-53-6131

Standards Manual (SM)

Structural Repair Manual (SRM) 51-40-30 51-40-41

**CONF ALL

K. PUBLICATION AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 10

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Kit 536123A01R01

Kit 536123A02R01

Kit 536123A03R01

Kit 536123A04R01

Kit 536123A05R01

Kit 536123A06R01

Kit 536123A07R02

Kit 536123A08R00

Kit 536123A09R00

Kit 536123A10R01

Kit 536123A11R01

Kit 536123A12R01

Kit 536123A13R01

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 :

AIRBUS

MATERIEL SUPPORT CENTER

P.O. Box 630262

22312 HAMBURG

GERMANY

(2) Price and Availability

Kit 536123A01R01

Cost 2,050.00 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 the Kit(s) before this time, please include a retrofit planning

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

Kit 536123A02R01

Cost 946.00 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 the Kit(s) before this time, please include a retrofit planning

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

Kit 536123A03R01

Cost 1,060.00 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 the Kit(s) before this time, please include a retrofit planning

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

Kit 536123A04R01

Cost 452.00 USD

Availability 120 calendar days from receipt of order

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 11

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

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

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

Kit 536123A05R01

Cost 1,100.00 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 the Kit(s) before this time, please include a retrofit planning

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

Kit 536123A06R01

Cost 1,620.00 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 the Kit(s) before this time, please include a retrofit planning

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

Kit 536123A07R02

Cost 21,530.00 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 the Kit(s) before this time, please include a retrofit planning

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

Kit 536123A08R00

Cost 1,970.00 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 the Kit(s) before this time, please include a retrofit planning

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

Kit 536123A09R00

Cost 1,970.00 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 the Kit(s) before this time, please include a retrofit planning

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

Kit 536123A10R01

Cost 5,080.00 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 the Kit(s) before this time, please include a retrofit planning

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

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 12

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SERVICE BULLETIN

Kit 536123A11R01

Cost 2,930.00 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 the Kit(s) before this time, please include a retrofit planning

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

Kit 536123A12R01

Cost 4,900.00 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 the Kit(s) before this time, please include a retrofit planning

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

Kit 536123A13R01

Cost 1,580.00 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 the Kit(s) before this time, please include a retrofit planning

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

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

at the issue date of the Service Bulletin.

B. INDUSTRY SUPPORT INFORMATION

Airbus will not provide industrial support for accomplishment of this Service Bulletin.

C. LIST OF COMPONENTS

Kit 536123A01R01

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

NOTES

NSA5050-3 14 Nut

NSA5050-4 14 Nut

NSA5351-3-12 2 Pin

NSA5351-3-13 2 Pin

NSA5351-3-15 6 Pin

NSA5351-3-19 4 Pin

NSA5351-4-12 10 Pin

NSA5351-4-13 2 Pin

NSA5351-4-19 2 Pin

NSA5368PD10A 14 Washer

NSA5368PD416A 14 Washer

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 13

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SERVICE BULLETIN

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: Kit 536123A01R01 : In case of no crack findings at holes A to N. Valid

A/C MSN 0284 thru 0377, 0384, 0395 and 0398 . A/C having basic splice

A53834139202/203 (Service Bulletin No. A300-53-6131 not accomplished).

Kit 536123A02R01

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

NOTES

NSA5050-4 24 Nut

NSA5050-5 4 Nut

NSA5351-4-12 2 Pin

NSA5351-4-13 2 Pin

NSA5351-4-15 6 Pin

NSA5351-4-19 4 Pin

NSA5351-5-13 2 Pin

NSA5351-5-14 2 Pin

NSA5359-4-12 8 Pin

NSA5359-4-19 2 Pin

NSA5368PD416A 24 Washer

NSA5368PD516A 4 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: Kit 536123A02R01 : In case of no crack findings at holes A to N. Valid A/C

MSN 0284 thru 0377, 0384, 0388*, 0395 and 0398 . A/C having basic splice

A53834139202/203 (Service Bulletin No. A300-53-6131 accomplished).

Kit 536123A03R01

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

NOTES

NSA5050-4 16 Nut

NSA5050-5 12 Nut

NSA5351-4-12 2 Pin

NSA5351-4-13 2 Pin

NSA5351-4-16 6 Pin

NSA5351-4-18 6 Pin

NSA5351-5-12 8 Pin

NSA5351-5-13 2 Pin

NSA5351-5-14 2 Pin

NSA5368PD416A 16 Washer

NSA5368PD516A 12 Washer

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 14

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SERVICE BULLETIN

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: Kit 536123A03R01 : In case of no crack findings at holes A to N. Valid

A/C MSN 0252, 0380, 0391, 0401 thru 0878 . A/C having new splice

A53812635200/201 or 202/203

Kit 536123A04R01

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

NOTES

NSA5050-4 16 Nut

NSA5050-5 12 Nut

NSA5351-4-12 2 Pin

NSA5351-4-13 2 Pin

NSA5351-4-16 6 Pin

NSA5351-4-19 4 Pin

NSA5351-5-12 8 Pin

NSA5351-5-13 2 Pin

NSA5351-5-14 2 Pin

NSA5359-4-18 2 Pin

NSA5368PD416A 16 Washer

NSA5368PD516A 12 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: Kit 536123A04R01 : In case of no crack findings at holes A to N. Valid A/C

MSN 0284 thru 0377, 0384, 0388, 0395 and 0398 . A/C having new splice

A53812635200/201 or 202/203 (replaced by Repair Instruction R53810423

SOL. A).

Kit 536123A05R01

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

NOTES

NSA5050-4 16 Nut

NSA5050-5 12 Nut

NSA5357-4-11 2 Pin

NSA5357-4-12 2 Pin

NSA5357-4-14 6 Pin

NSA5357-4-16 6 Pin

NSA5357-5-11 2 Pin

NSA5357-5-12 2 Pin

NSA5357-5-9 8 Pin

NSA5368PD416A 16 Washer

NSA5368PD516A 12 Washer

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 15

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SERVICE BULLETIN

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: Kit 536123A05R01 : In case of no crack findings at holes A to N. Valid

A/C MSN 0252, 0380, 0391, 0401 thru 0878 . A/C having new splice

A53812635200/201 or 202/203 (replaced by Repair Instruction R53810423

SOL. B).

Kit 536123A06R01

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

NOTES

NSA5050-4 14 Nut

NSA5050-5 14 Nut

NSA5351-5-12 8 Pin

NSA5351-5-19 2 Pin

NSA5357-4-12 2 Pin

NSA5357-4-13 2 Pin

NSA5357-4-15 6 Pin

NSA5357-4-19 4 Pin

NSA5357-5-13 2 Pin

NSA5357-5-14 2 Pin

NSA5368PD416A 14 Washer

NSA5368PD516A 14 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: Kit 536123A06R01 : In case of no crack findings at holes A to N. Valid A/C

MSN 0284 thru 0377, 0384, 0388, 0395 and 0398 . A/C having new splice

A53812635200/201 or 202/203 (replaced by Repair Instruction R53810423

SOL. C).

Kit 536123A07R02

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

NOTES

NSA5050-3 14 Nut

NSA5050-4 28 Nut

NSA5050-5 28 Nut

NSA5050-6 12 Nut

NSA5351-4-12 2 Pin

NSA5351-4-13 2 Pin

NSA5351-4-15 6 Pin

NSA5351-4-19 4 Pin

NSA5351-5-11 2 Pin

NSA5351-5-12 12 Pin

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 16

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SERVICE BULLETIN

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

NOTES

NSA5351-5-13 4 Pin

NSA5351-5-14 6 Pin

NSA5351-5-15 6 Pin

NSA5351-5-16 6 Pin

NSA5351-5-18 6 Pin

NSA5351-5-19 6 Pin

NSA5351-6-11 2 Pin

NSA5351-6-12 10 Pin

NSA5351-6-13 4 Pin

NSA5351-6-14 2 Pin

NSA5351-6-9 8 Pin

NSA5357-3-12 2 Pin

NSA5357-3-13 2 Pin

NSA5357-3-15 6 Pin

NSA5357-3-19 4 Pin

NSA5357-4-12 12 Pin

NSA5357-4-13 4 Pin

NSA5357-4-15 6 Pin

NSA5357-4-16 6 Pin

NSA5357-4-18 6 Pin

NSA5357-4-19 6 Pin

NSA5357-5-11 2 Pin

NSA5357-5-12 12 Pin

NSA5357-5-13 4 Pin

NSA5357-5-14 6 Pin

NSA5357-5-15 6 Pin

NSA5357-5-16 6 Pin

NSA5357-5-18 6 Pin

NSA5357-5-19 6 Pin

NSA5359-3-12 2 Pin

NSA5359-3-13 2 Pin

NSA5359-3-15 6 Pin

NSA5359-3-19 4 Pin

NSA5359-4-11 2 Pin

NSA5359-4-12 12 Pin

NSA5359-4-13 4 Pin

NSA5359-4-14 6 Pin

NSA5359-4-15 6 Pin

NSA5359-4-16 6 Pin

NSA5359-4-18 6 Pin

NSA5359-4-19 6 Pin

NSA5359-5-11 2 Pin

NSA5359-5-12 10 Pin

NSA5359-5-13 4 Pin

NSA5359-5-14 2 Pin

NSA5359-5-9 8 Pin

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 17

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SERVICE BULLETIN

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

NOTES

NSA5368PD10A 14 Washer

NSA5368PD416A 28 Washer

NSA5368PD516A 28 Washer

NSA5368PD616A 12 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: Kit 536123A07R02 : In case of crack findings less than or equal to 0.8 mm

(0.315 in.) at holes A to N. Valid all A/C.

- Valid A/C having basic splice A53834139202/203 (Service Bulletin No.

A300-53-6131 not accomplished).

- Valid A/C having basic splice A53834139202/203 (Service Bulletin No.

A300-53-6131 accomplished).

- Valid A/C having new splice A53812635202/203 (Modification

No.05890S6739 embodied in production line).

- Valid A/C having new splice A53812635200/201 or 202/203 (replaced by

Repair Instruction R53810423 SOL. A).

- Valid A/C having new splice A53812635200/201 or 202/203 (replaced by

Repair Instruction R53810423 SOL. B).

- Valid A/C having new splice A53812635200/201 or 202/203 (replaced by

Repair Instruction R53810423 SOL. C).

Kit 536123A08R00

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

NOTES

A5381263520096 1 Splice

NOTE: Kit 536123A08R00 : In case of crack findings more than 0.8 mm (0.315 in.) at

holes A to N. Valid all A/C. Replacement splice, LH side.

Kit 536123A09R00

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

NOTES

A5381263520196 1 Splice

NOTE: Kit 536123A09R00 : In case of crack findings more than 0.8 mm (0.315 in.) at

holes A to N. Valid all A/C. Replacement splice, RH side.

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 18

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Kit 536123A10R01

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

NOTES

NAS1726-3E 18 Nut

NAS1726-4E 41 Nut

NAS1726-5E 6 Nut

NAS1727-4E 1 Nut

NSA5351-4-11 6 Pin

NSA5351-4-12 2 Pin

NSA5351-4-13 13 Pin

NSA5351-4-14 2 Pin

NSA5351-4-15 4 Pin

NSA5351-4-16 4 Pin

NSA5351-4-19 2 Pin

NSA5351-5-12 4 Pin

NSA5351-5-13 1 Pin

NSA5351-5-14 1 Pin

NSA5357-3-10 7 Pin

NSA5357-3-12 9 Pin

NSA5357-3-14 2 Pin

NSA5357-4-12 7 Pin

NSA5357-4-15 1 Pin

NSA5359-4-18 1 Pin

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: Kit 536123A10R01 : In case of crack findings more than 0.8 mm (0.315 in.) at

holes A to N. Valid A/C MSN 0284 thru 0377, 0384, 0388, 0395 and 0398 .

Bolts for replacement splice with Repair Instruction R53810423 SOL. A.

Kit 536123A11R01

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

NOTES

NAS1726-4E 42 Nut

NAS1726-5E 6 Nut

NAS1727-3E 18 Nut

NSA5357-4-11 7 Pin

NSA5357-4-12 9 Pin

NSA5357-4-13 12 Pin

NSA5357-4-14 5 Pin

NSA5357-4-15 5 Pin

NSA5357-4-16 4 Pin

NSA5357-5-11 1 Pin

NSA5357-5-12 1 Pin

NSA5357-5-9 4 Pin

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 19

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@A300-600

SERVICE BULLETIN

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

NOTES

NSA5359-3-10 7 Pin

NSA5359-3-12 9 Pin

NSA5359-3-14 2 Pin

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: Kit 536123A11R01 : In case of crack findings more than 0.8 mm (0.315 in.) at

holes A to N. Valid A/C MSN 0252, 0380, 0391, 0401 thru 0878 . Bolts for

replacement splice with Repair Instruction R53810423 SOL.B.

Kit 536123A12R01

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

NOTES

NAS1726-3E 18 Nut

NAS1726-4E 41 Nut

NAS1726-5E 7 Nut

NSA5351-4-11 6 Pin

NSA5351-4-12 1 Pin

NSA5351-4-13 12 Pin

NSA5351-4-14 2 Pin

NSA5351-4-15 4 Pin

NSA5351-4-16 1 Pin

NSA5351-5-12 4 Pin

NSA5351-5-19 1 Pin

NSA5357-3-10 7 Pin

NSA5357-3-12 9 Pin

NSA5357-3-14 2 Pin

NSA5357-4-12 8 Pin

NSA5357-4-13 1 Pin

NSA5357-4-15 4 Pin

NSA5357-4-19 2 Pin

NSA5357-5-13 1 Pin

NSA5357-5-14 1 Pin

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: Kit 536123A12R01 : In case of crack findings more than 0.8 mm (0.315 in.) at

holes A to N. Valid A/C MSN 0284 thru 0377, 0384, 0388, 0395 and 0398 .

Bolts for replacement splice with Repair Instruction R53810423 SOL. C.

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 20

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Kit 536123A13R01

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

NOTES

NSA5050-3 11 Nut

NSA5050-4 10 Nut

NSA5330-6 2 Nut

NSA5351-3-10 1 Pin

NSA5351-3-12 1 Pin

NSA5351-3-13 5 Pin

NSA5351-3-15 4 Pin

NSA5351-3-16 1 pin

NSA5351-4-13 5 Pin

NSA5351-4-15 4 Pin

NSA5351-4-16 1 Pin

NSA5357-3-10 1 Pin

NSA5357-3-12 1 Pin

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: Kit 536123A13R01 : In case of no crack findings in the adjacent holes. Valid

all A/C.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013 As required

Solvant General Purpose 11-026 As required

Anti-Corrosion Primer

(Polyurethane)

16-001 As required

Polyurethane Topcoatgrey (For

Internal Applic.)

16-002 As required

Wash Primer 16-020 As required

(2) Components

None

(3) Equipment

None

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 21

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E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

To accomplish this Service Bulletin it is necessary to use the following tools and

equipment listed in (Refer to NTM 51-10-01 and NTM 51-10-07).

Fatigue Technology Incorporated (FTI) has allocated tool kit number FTI-A300-53-6123-1

for accomplishment of this Service Bulletin. Operators interested in obtaining the FTI tool

kit should contact :

Fatigue Technology Inc.

100 Andover Park West

SEATTLE, WA 98188-2868

USA

Tel : (206) 246-2010

Telex: 321004

Fax : (206) 244-9886

(3) Special Tools

None

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 22

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 536123-832-802-001 - Inspection

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.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.

Task Associated Data

**CONF 001

Manpower

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

**CONF 002

Manpower

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 536123-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 23

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Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013 As required

Solvant General Purpose 11-026 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-40-30

(a) For the specification of the material numbers (Mat. No.), (Refer to Consumable

Material List (CML)).

(b) Clean surfaces to be sealed with :

Solvant General

Purpose

11-026 As required

(c) Apply sealant :

Corrosion Inhibiting

Brush Consistency

09-013 As required

(d) Torque the standard threaded fasteners (Refer to AMM 20-21-12).

(e) For alternative and substitute fasteners (Refer to SRM 51-40-30).

(f) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(2) Subtask 536123-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 002

(1) Subtask 536123-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 24

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Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013 As required

Solvant General Purpose 11-026 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-40-30

(a) For the specification of the material numbers (Mat. No.), (Refer to Consumable

Material List (CML)).

(b) Clean surfaces to be sealed with :

Solvant General

Purpose

11-026 As required

(c) Apply sealant :

Corrosion Inhibiting

Brush Consistency

09-013 As required

(d) Torque the standard threaded fasteners (Refer to AMM 20-21-12).

(e) For alternative and substitute fasteners (Refer to SRM 51-40-30).

(f) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(2) Subtask 536123-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 25

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**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 536123-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

25-12-11, Page Block 401

25-21-00, Page Block 401

25-23-31, Page Block 401

(a) Electrically ground the aircraft (Refer to AMM 24-00-00, Page Block 301).

(b) Put the access platform(s) in position.

(c) Remove row of passenger seats at Frame 47 on LH and RH sides (Refer to AMM

25-21-00, Page Block 401).

(d) Remove lower sidewall panels at Frame 47 on LH and RH sides (Refer to AMM

25-23-31, Page Block 401).

(e) Remove heat and sound insulation blankets at Frame 47 on LH and RH sides

(Refer to AMM 25-12-11, Page Block 401).

**CONF 002

(1) Subtask 536123-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

25-12-11, Page Block 401

25-21-00, Page Block 401

25-23-31, Page Block 401

(a) Electrically ground the aircraft (Refer to AMM 24-00-00, Page Block 301).

(b) Put the access platform(s) in position.

(c) Remove row of passenger seats at Frame 47 on LH and RH sides (Refer to AMM

25-21-00, Page Block 401).

(d) Remove lower sidewall panels at Frame 47 on LH and RH sides (Refer to AMM

25-23-31, Page Block 401).

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 26

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(e) Remove heat and sound insulation blankets at Frame 47 on LH and RH sides

(Refer to AMM 25-12-11, Page Block 401).

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 536123-280-001-001 - Do a Special Inspection of the Holes Fuselage at

FR47 Splice Fitting between STGR 24 and 26 LH and RH sides.

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills ELECTRICAL

References

Non Destructive Test Manual (NTM) 51-10-01 Part 1

51-10-07 Part 1

Repair Instruction R53810423

Fig. A-FBBAA

Location of Fastener Holes to be

Inspected

Sheet 01

Sheet 02

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

(a) For the inspection area, refer to Fig. A-FBBAA Sheet 01 and Fig. A-FBBAA Sheet

02.

(b) Do a rotating probe inspection, NTM 51-10-01 Part 1 and NTM 51-10-07 Part 1,

refer to Fig. A-FFAAA Sheet 01 and Fig. A-FFAAA Sheet 02

NOTE: During the reaming-up of the concerned holes, make sure not to

exceed the maximal diameter of 9.53 mm (0.03752 in.) for hole A to

F and 8.335 mm (0.03281 in.) for hole G to N.

1 If no crack is found :

a Install new fasteners of same diameter as original one as described in

subtasks :

- 536123-833-010

or

- 536123-833-011

or

- 536123-833-013

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 27

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or

- 536123-833-015

<1> Reinspect at interval given in the table 2 of PARA E.(2).

2 If crack is found with a depth inferior or equal at 0.8 mm (0.0315 in.) and if no

crack is found on the adjacent holes :

a Install new fasteners with transition fit as described in subtask

536123-833-016

and

Install new fasteners of same diameter in the adjacent hole as described

in subtask 536123-833-023.

<1> Reinspect at interval given in the table 2 of PARA E.(2).

3 If crack is found with a depth inferior or equal at 0.8 mm (0.0315 in.) and if no

crack is found on the adjacent holes but the Full Screen Height is superior at

40 percent :

a If crack is found on original hole on splice :

<1> Replace the splice refer to Repair Instruction R53810423 and as

described in subtask :

- 536123-833-017

or

- 536123-833-018

or

- 536123-833-021

or

- 536123-833-022

<2> Install new fasteners of same diameter in the adjacent hole as

described in subtask 536123-833-023.

<3> Reinspect at threshold given in the table 2 of PARA E.(2) counted

starting from splice replacement.

b If crack is found on original hole on frame :

<1> Contact AIRBUS before the next flight

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 28

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4 If crack is found with a depth inferior or equal at 0.8 mm (0.0315 in.) and if

crack is found on the adjacent holes :

a Contact AIRBUS before the next flight

5 If crack is found with a depth superior at 0.8 mm (0.0315 in.), no crack is

found on the adjacent holes and crack is found on original hole splice :

a Replace the splice refer to Repair Instruction R53810423 and as

described in subtask :

- 536123-833-017

or

- 536123-833-018

or

- 536123-833-021

or

- 536123-833-022

b Install new fasteners of same diameter in the adjacent hole as described

in subtask 536123-833-023.

<1> Reinspect at threshold given in the table 2 of PARA E.(2) counted

starting from splice replacement.

6 If crack is found with a depth superior at 0.8 mm (0.0315 in.), no crack is

found on the adjacent holes and crack is found on original hole frame

or

If crack is found with a depth superior at 0.8 mm (0.0315 in.) and crack is

found on the adjacent holes.

a Contact AIRBUS before next flight.

(c) For the inspection report refer to Inspection Report .

**CONF 002

(1) Subtask 536123-280-001-002 - Do a Special Inspection of the Holes Fuselage at

FR47 Splice Fitting between STGR 24 and 26 LH and RH sides.

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills ELECTRICAL

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 29

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References

Non Destructive Test Manual (NTM) 51-10-01 Part 1

51-10-07 Part 1

Repair Instruction R53810423

Fig. A-FBBAA

Location of Fastener Holes to be

Inspected

Sheet 01

Sheet 02

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

(a) For the inspection area, refer to Fig. A-FBBAA Sheet 01 and Fig. A-FBBAA Sheet

02.

(b) Do a rotating probe inspection, (Refer to NTM 51-10-01 Part 1 and NTM 51-10-07

Part 1), refer to Fig. A-FFAAA Sheet 01 and Fig. A-FFAAA Sheet 02.

NOTE: During the reaming-up of the concerned holes, make sure not to

exceed the maximal diameter of 9.53 mm (0.03752 in.) for hole A to

F and 8.335 mm (0.03281 in.) for hole G to N.

1 If no crack is found :

a Install new fasteners of same diameter as original one as described in

subtasks :

- 536123-833-012

or

- 536123-833-014

<1> Reinspect at interval given in the table 2 of PARA E.(2).

2 If crack is found with a depth inferior at 0.8 mm (0.0315 in.) and if no crack is

found on the adjacent holes :

a Install new fasteners with transition fit as described in subtask

536123-833-016

and

Install new fasteners of same diameter in the adjacent hole as described

in subtask 536123-833-023.

<1> Reinspect at interval given in the table 2 of PARA E.(2).

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 30

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3 If crack is found with a depth inferior or equal at 0.8 mm (0.0315 in.) and if no

crack is found on the adjacent holes but the Full Screen Height is superior at

40 percent :

a If crack is found on original hole on splice :

<1> Replace the splice refer to Repair Instruction R53810423 and as

described in subtask :

- 536123-833-019

or

- 536123-833-020

<2> Install new fasteners of same diameter in the adjacent hole as

described in subtask 536123-833-023.

<3> Reinspect at threshold given in the table 2 of PARA E.(2) counted

starting from splice replacement.

b If crack is found on original hole on frame :

<1> Contact AIRBUS before the next flight

4 If crack is found with a depth inferior or equal at 0.8 mm (0.0315 in.), and

crack is found on the adjacent holes :

a Contact AIRBUS before the next flight

5 If crack is found with a depth superior at 0.8 mm (0.0315 in.), no crack is

found on the adjacent holes and crack is found on original hole splice :

a Replace the splice refer to Repair Instruction R53810423 and as

described in subtask :

- 536123-833-019

or

- 536123-833-020

b Install new fasteners of same diameter in the adjacent hole as described

in subtask 536123-833-023.

<1> Reinspect at threshold given in the table 2 of PARA E.(2) counted

starting from splice replacement.

6 If crack is found with a depth superior at 0.8 mm (0.0315 in.), no crack is

found on the adjacent holes and crack is found on original hole frame

or

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 31

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If crack is found with a depth superior at 0.8 mm (0.0315 in.) and crack is

found on the adjacent holes.

a Contact AIRBUS before next flight.

(c) For the inspection report refer to Inspection Report .

**CONF ALL

D. TEST

**CONF 001

None

**CONF 002

None

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 536123-942-009-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 25-12-11, Page Block 401

25-21-00, Page Block 401

25-23-31, Page Block 401

(a) Install heat and sound insulation blankets (Refer to AMM 25-12-11, Page Block

401).

(b) Install lower sidewall panels (Refer to AMM 25-23-31, Page Block 401).

(c) Install row of passenger seats (Refer to AMM 25-21-00, Page Block 401).

(d) Remove the access platforms.

(e) Restore the systems and the aircraft to normal operating condition.

**CONF 002

(1) Subtask 536123-942-009-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 32

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References

Aircraft Maintenance Manual (AMM) 25-12-11, Page Block 401

25-21-00, Page Block 401

25-23-31, Page Block 401

(a) Install heat and sound insulation blankets (Refer to AMM 25-12-11, Page Block

401).

(b) Install lower sidewall panels (Refer to AMM 25-23-31, Page Block 401).

(c) Install row of passenger seats (Refer to AMM 25-21-00, Page Block 401).

(d) Remove the access platforms.

(e) Restore the systems and the aircraft to normal operating condition.

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 33

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This Page Intentionally Left Blank

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 34

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Task 536123-833-802-001 - Repair

**CONF ALL

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 204.00

ELAPSED TIME (HOURS) 34.00

**CONF 002

Manpower

TOTAL MANHOURS 116.00

ELAPSED TIME (HOURS) 34.00

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 536123-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 35

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Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Anti-Corrosion Primer

(Polyurethane)

16-001 As required

Polyurethane Topcoatgrey

(For Internal Applic.)

16-002 As required

Wash Primer 16-020 As required

References

Aircraft Maintenance Manual (AMM) 51-23-10

Structural Repair Manual (SRM) 51-40-41

(a) Renew protective finish (Refer to AMM 51-23-10) using :

Wash Primer 16-020 As required

Anti-Corrosion

Primer

(Polyurethane)

16-001 As required

and

Polyurethane

Topcoatgrey (For

Internal Applic.)

16-002 As required

(b) Do the cold expansion of the fastener holes (Refer to SRM 51-40-41).

(2) Subtask 536123-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 002

(1) Subtask 536123-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 36

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Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Anti-Corrosion Primer

(Polyurethane)

16-001 As required

Polyurethane Topcoatgrey

(For Internal Applic.)

16-002 As required

Wash Primer 16-020 As required

References

Aircraft Maintenance Manual (AMM) 51-23-10

Structural Repair Manual (SRM) 51-40-41

(a) Renew protective finish (Refer to AMM 51-23-10) using :

Wash Primer 16-020 As required

Anti-Corrosion

Primer

(Polyurethane)

16-001 As required

and

Polyurethane

Topcoatgrey (For

Internal Applic.)

16-002 As required

(b) Do the cold expansion of the fastener holes (Refer to SRM 51-40-41).

(2) Subtask 536123-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 536123-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 37

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References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

25-12-11, Page Block 401

25-21-00, Page Block 401

25-23-31, Page Block 401

(a) Electrically ground the aircraft (Refer to AMM 24-00-00 Page Block 301).

(b) Put the access platforms in position.

(c) Remove row of passenger seats at FR47 on LH and RH sides (Refer to AMM

25-21-00 Page Block 401).

(d) Remove lower sidewall panels at FR47 on LH and RH sides (Refer to AMM

25-23-31 Page Block 401).

(e) Remove heat and sound insulation blankets at FR47 on LH and RH sides (Refer to

AMM 25-12-11 Page Block 401).

**CONF 002

(1) Subtask 536123-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

25-12-11, Page Block 401

25-21-00, Page Block 401

25-23-31, Page Block 401

(a) Electrically ground the aircraft (Refer to AMM 24-00-00 Page Block 301).

(b) Put the access platforms in position.

(c) Remove row of passenger seats at FR47 on LH and RH sides (Refer to AMM

25-21-00 Page Block 401).

(d) Remove lower sidewall panels at FR47 on LH and RH sides (Refer to AMM

25-23-31 Page Block 401).

(e) Remove heat and sound insulation blankets at FR47 on LH and RH sides (Refer to

AMM 25-12-11 Page Block 401).

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 38

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@A300-600

SERVICE BULLETIN

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 536123-833-010-001 - Install new Fasteners of same Diameter for Aircraft

having a Basic Splice and on which Service Bulletin A300-53-6131 is not

accomplished.

Manpower Resources

Manhours 18.00

Minimum number of person 1

Subtask elapsed time 18.00

Skills AIRFRAME

Material necessary to do the job

Kit 536123A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA5050-3 14 Nut

NSA5050-4 14 Nut

NSA5351-3-12 2 Pin

NSA5351-3-13 2 Pin

NSA5351-3-15 6 Pin

NSA5351-3-19 4 Pin

NSA5351-4-12 10 Pin

NSA5351-4-13 2 Pin

NSA5351-4-19 2 Pin

NSA5368PD10A 14 Washer

NSA5368PD416A 14 Washer

NOTE: Kit 536123A01R01 : In case of no crack findings at holes A to N.

Valid A/C MSN 0284 thru 0377, 0384, 0395 and 0398 . A/C having

basic splice A53834139202/203 (Service Bulletin No. A300-53-6131 not

accomplished).

References

Fig. A-FBCAA

Replacement of Fasteners

Sheet 01

Fig. A-FBDAA

Install New Fasteners, KIT A01

Sheet 01

(a) Install new fasteners of same diameter, refer to Fig. A-FBCAA Sheet 01 and Fig. AFBDAA Sheet 01 :

10 Pin-Hi Lok NSA5351-4-12

2 Pin-Hi Lok NSA5351-4-13

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 39

5

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

SERVICE BULLETIN

6 Pin-Hi lok NSA5351-3-15

2 Pin-Hi Lok NSA5351-4-19

4 Pin-Hi Lok NSA5351-3-19

2 Pin-Hi lok NSA5351-3-12

2 Pin-Hi lok NSA5351-3-13

14 Nut NSA5050-3

14 Nut NSA5050-4

14 Washer NSA5368PD10A

14 Washer NSA5368PD416A

NOTE: Use washer NSA5368 only if the fasteners are too long.

(2) Subtask 536123-833-011-001 - Install new Fasteners of same Diameter for

Aircraft having a Basic Splice and on which Service Bulletin A300-53-6131 is

accomplished.

Manpower Resources

Manhours 18.00

Minimum number of person 1

Subtask elapsed time 18.00

Skills AIRFRAME

Material necessary to do the job

Kit 536123A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA5050-4 24 Nut

NSA5050-5 4 Nut

NSA5351-4-12 2 Pin

NSA5351-4-13 2 Pin

NSA5351-4-15 6 Pin

NSA5351-4-19 4 Pin

NSA5351-5-13 2 Pin

NSA5351-5-14 2 Pin

NSA5359-4-12 8 Pin

NSA5359-4-19 2 Pin

NSA5368PD416A 24 Washer

NSA5368PD516A 4 Washer

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 40

5

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

SERVICE BULLETIN

NOTE: Kit 536123A02R01 : In case of no crack findings at holes A to N. Valid

A/C MSN 0284 thru 0377, 0384, 0388*, 0395 and 0398 . A/C having

basic splice A53834139202/203 (Service Bulletin No. A300-53-6131

accomplished).

References

Fig. A-FBCAA

Replacement of Fasteners

Sheet 01

Fig. A-FBEAA

Install New Fasteners, KIT A02

Sheet 01

(a) Install new fasteners of same diameter, refer to Fig. A-FBCAA Sheet 01 and Fig. AFBEAA Sheet 01 :

8 Pin-Hi Lok NSA5359-4-12

6 Pin-Hi Lok NSA5351-4-15

2 Pin-Hi Lok NSA5359-4-19

2 Pin-Hi Lok NSA5351-4-12

2 Pin-Hi Lok NSA5351-4-13

2 Pin-Hi Lok NSA5351-5-13

4 Pin-Hi Lok NSA5351-4-19

2 Pin-Hi Lok NSA5351-5-14

24 Nut NSA5050-4

4 Nut NSA5050-5

24 Washer NSA5368PD416A

4 Washer NSA5368PD516A

NOTE: Use washer NSA5368 only if the fasteners are too long.

(3) Subtask 536123-833-013-001 - Install new Fasteners of same Diameter for Aircraft

having a Reinforced Splice (Replaced by Repair Instruction R53810423 SOL. A)

Manpower Resources

Manhours 18.00

Minimum number of person 1

Subtask elapsed time 18.00

Skills AIRFRAME

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 41

5

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

SERVICE BULLETIN

Material necessary to do the job

Kit 536123A04R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA5050-4 16 Nut

NSA5050-5 12 Nut

NSA5351-4-12 2 Pin

NSA5351-4-13 2 Pin

NSA5351-4-16 6 Pin

NSA5351-4-19 4 Pin

NSA5351-5-12 8 Pin

NSA5351-5-13 2 Pin

NSA5351-5-14 2 Pin

NSA5359-4-18 2 Pin

NSA5368PD416A 16 Washer

NSA5368PD516A 12 Washer

NOTE: Kit 536123A04R01 : In case of no crack findings at holes A to N.

Valid A/C MSN 0284 thru 0377, 0384, 0388, 0395 and 0398 . A/C

having new splice A53812635200/201 or 202/203 (replaced by Repair

Instruction R53810423 SOL. A).

References

Fig. A-FBCAA

Replacement of Fasteners

Sheet 01

Fig. A-FBGAA

Install New Fasteners, KIT A04

Sheet 01

(a) Install new fasteners of same diameter, refer to Fig. A-FBCAA Sheet 01 and Fig. AFBGAA Sheet 01 :

2 Pin-Hi Lok NSA5351-5-14

2 Pin-Hi Lok NSA5351-5-13

8 Pin-Hi Lok NSA5351-5-12

2 Pin-Hi Lok NSA5351-4-12

6 Pin-Hi Lok NSA5351-4-16

2 Pin-Hi Lok NSA5351-4-13

2 Pin-Hi Lok NSA5359-4-18

4 Pin-Hi Lok NSA5351-4-19

16 Nut NSA5050-4

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 42

5

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

SERVICE BULLETIN

12 Nut NSA5050-5

16 Washer NSA5368PD416A

12 Washer NSA5368PD516A

NOTE: Use washer NSA5368 only if the fasteners are too long.

(4) Subtask 536123-833-015-001 - Install new Fasteners of same Diameter for Aircraft

having a Reinforced Splice (Replaced by Repair Instruction R53810423 SOL. C)

Manpower Resources

Manhours 18.00

Minimum number of person 1

Subtask elapsed time 18.00

Skills AIRFRAME

Material necessary to do the job

Kit 536123A06R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA5050-4 14 Nut

NSA5050-5 14 Nut

NSA5351-5-12 8 Pin

NSA5351-5-19 2 Pin

NSA5357-4-12 2 Pin

NSA5357-4-13 2 Pin

NSA5357-4-15 6 Pin

NSA5357-4-19 4 Pin

NSA5357-5-13 2 Pin

NSA5357-5-14 2 Pin

NSA5368PD416A 14 Washer

NSA5368PD516A 14 Washer

NOTE: Kit 536123A06R01 : In case of no crack findings at holes A to N.

Valid A/C MSN 0284 thru 0377, 0384, 0388, 0395 and 0398 . A/C

having new splice A53812635200/201 or 202/203 (replaced by Repair

Instruction R53810423 SOL. C).

References

Fig. A-FBCAA

Replacement of Fasteners

Sheet 01

Fig. A-FBJAA

Install New Fasteners, KIT A06

Sheet 01

(a) Install new fasteners of same diameter, refer to Fig. A-FBCAA Sheet 01 and Fig. AFBJAA Sheet 01 :

2 Pin-Hi Lok NSA5357-5-14

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 43

5

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

SERVICE BULLETIN

2 Pin-Hi Lok NSA5357-5-13

8 Pin-Hi Lok NSA5351-5-12

2 Pin-Hi Lok NSA5357-4-12

2 Pin-Hi Lok NSA5357-4-13

6 Pin-Hi Lok NSA5357-4-15

4 Pin-Hi Lok NSA5357-4-19

2 Pin-Hi Lok NSA5351-5-19

14 Nut NSA5050-4

14 Nut NSA5050-5

14 Washer NSA5368PD416A

14 Washer NSA5368PD516A

NOTE: Use washer NSA5368 only if the fasteners are too long.

(5) Subtask 536123-833-016-001 - Install new fasteners on the splice (transition fit)

Manpower Resources

Manhours 10.00

Minimum number of person 1

Subtask elapsed time 10.00

Skills AIRFRAME

Material necessary to do the job

Kit 536123A07R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA5050-3 14 Nut

NSA5050-4 28 Nut

NSA5050-5 28 Nut

NSA5050-6 12 Nut

NSA5351-4-12 2 Pin

NSA5351-4-13 2 Pin

NSA5351-4-15 6 Pin

NSA5351-4-19 4 Pin

NSA5351-5-11 2 Pin

NSA5351-5-12 12 Pin

NSA5351-5-13 4 Pin

NSA5351-5-14 6 Pin

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 44

5

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

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA5351-5-15 6 Pin

NSA5351-5-16 6 Pin

NSA5351-5-18 6 Pin

NSA5351-5-19 6 Pin

NSA5351-6-11 2 Pin

NSA5351-6-12 10 Pin

NSA5351-6-13 4 Pin

NSA5351-6-14 2 Pin

NSA5351-6-9 8 Pin

NSA5357-3-12 2 Pin

NSA5357-3-13 2 Pin

NSA5357-3-15 6 Pin

NSA5357-3-19 4 Pin

NSA5357-4-12 12 Pin

NSA5357-4-13 4 Pin

NSA5357-4-15 6 Pin

NSA5357-4-16 6 Pin

NSA5357-4-18 6 Pin

NSA5357-4-19 6 Pin

NSA5357-5-11 2 Pin

NSA5357-5-12 12 Pin

NSA5357-5-13 4 Pin

NSA5357-5-14 6 Pin

NSA5357-5-15 6 Pin

NSA5357-5-16 6 Pin

NSA5357-5-18 6 Pin

NSA5357-5-19 6 Pin

NSA5359-3-12 2 Pin

NSA5359-3-13 2 Pin

NSA5359-3-15 6 Pin

NSA5359-3-19 4 Pin

NSA5359-4-11 2 Pin

NSA5359-4-12 12 Pin

NSA5359-4-13 4 Pin

NSA5359-4-14 6 Pin

NSA5359-4-15 6 Pin

NSA5359-4-16 6 Pin

NSA5359-4-18 6 Pin

NSA5359-4-19 6 Pin

NSA5359-5-11 2 Pin

NSA5359-5-12 10 Pin

NSA5359-5-13 4 Pin

NSA5359-5-14 2 Pin

NSA5359-5-9 8 Pin

NSA5368PD10A 14 Washer

NSA5368PD416A 28 Washer

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 45

5

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

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA5368PD516A 28 Washer

NSA5368PD616A 12 Washer

NOTE: Kit 536123A07R02 : In case of crack findings less than or equal to 0.8

mm (0.315 in.) at holes A to N. Valid all A/C.

- Valid A/C having basic splice A53834139202/203 (Service Bulletin

No. A300-53-6131 not accomplished).

- Valid A/C having basic splice A53834139202/203 (Service Bulletin

No. A300-53-6131 accomplished).

- Valid A/C having new splice A53812635202/203 (Modification

No.05890S6739 embodied in production line).

- Valid A/C having new splice A53812635200/201 or 202/203

(replaced by Repair Instruction R53810423 SOL. A).

- Valid A/C having new splice A53812635200/201 or 202/203

(replaced by Repair Instruction R53810423 SOL. B).

- Valid A/C having new splice A53812635200/201 or 202/203

(replaced by Repair Instruction R53810423 SOL. C).

References

Fig. A-FBCAA

Replacement of Fasteners

Sheet 01

Fig. A-FBKAA

Install New Fasteners, KIT A07

Sheet 01

Fig. A-FBLAA

Install New Fasteners, KIT A07

Sheet 01

Fig. A-FBMAA

Install New Fasteners, KIT A07

Sheet 01

Fig. A-FBNAA

Install New Fasteners, KIT A07

Sheet 01

Fig. A-FBPAA

Install New Fasteners, KIT A07

Sheet 01

Fig. A-FBRAA

Install New Fasteners, KIT A07

Sheet 01

Fig. A-FBTAA

Holes Tolerances in case of Splice

replacement

Sheet 01

(a) Install new fasteners on the splice, refer to Fig. A-FBCAA Sheet 01, Fig. A-FBKAA

Sheet 01, Fig. A-FBLAA Sheet 01, Fig. A-FBMAA Sheet 01, Fig. A-FBNAA Sheet

01, Fig. A-FBPAA Sheet 01, Fig. A-FBRAA Sheet 01 and Fig. A-FBTAA Sheet 01 :

4 Pin-Hi Lok NSA5357-4-13

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 46

5

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

SERVICE BULLETIN

4 Pin-Hi Lok NSA5359-4-13

4 Pin-Hi Lok NSA5351-5-13

4 Pin-Hi Lok NSA5357-5-13

2 Pin-Hi Lok NSA5351-4-13

2 Pin-Hi Lok NSA5359-3-13

2 Pin-Hi Lok NSA5357-3-13

2 Pin-Hi Lok NSA5359-5-13

2 Pin-Hi Lok NSA5351-6-13

12 Pin-Hi Lok NSA5357-4-12

12 Pin-Hi Lok NSA5359-4-12

12 Pin-Hi Lok NSA5351-5-12

12 Pin-Hi Lok NSA5357-5-12

10 Pin-Hi Lok NSA5359-5-12

10 Pin-Hi Lok NSA5351-6-12

2 Pin-Hi Lok NSA5351-4-12

2 Pin-Hi LoK NSA5359-3-12

2 Pin-Hi Lok NSA5357-3-12

6 Pin-Hi Lok NSA5357-4-19

6 Pin-Hi Lok NSA5359-4-19

6 Pin-Hi Lok NSA5351-5-19

6 Pin-Hi Lok NSA5357-5-19

4 Pin-Hi Lok NSA5351-4-19

4 Pin-Hi Lok NSA5359-3-19

4 Pin-Hi Lok NSA5357-3-19

6 Pin-Hi Lok NSA5357-3-15

6 Pin-Hi Lok NSA5359-3-15

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 47

5

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

SERVICE BULLETIN

6 Pin-Hi Lok NSA5351-4-15

6 Pin-Hi Lok NSA5357-4-15

6 Pin-Hi Lok NSA5359-4-15

6 Pin-Hi Lok NSA5351-5-15

6 Pin-Hi Lok NSA5357-5-15

6 Pin-Hi Lok NSA5357-5-14

2 Pin-Hi Lok NSA5359-5-14

2 Pin-Hi Lok NSA5351-6-14

6 Pin-Hi Lok NSA5351-5-14

6 Pin-Hi Lok NSA5359-4-14

6 Pin-Hi Lok NSA5357-4-16

6 Pin-Hi Lok NSA5359-4-16

6 Pin.Hi-Lok NSA5351-5-16

6 Pin-Hi Lok NSA5357-5-16

6 Pin-Hi Lok NSA5357-4-18

6 Pin-Hi Lok NSA5359-4-18

6 Pin-Hi Lok NSA5351-5-18

6 Pin-Hi Lok NSA5357-5-18

2 Pin-Hi Lok NSA5359-5-11

2 Pin-Hi Lok NSA5351-6-11

8 Pin-Hi Lok NSA5359-5-9

8 Pin.Hi-Lok NSA5351-6-9

2 Pin-Hi Lok NSA5359-4-11

2 Pin-Hi Lok NSA5351-5-11

2 Pin-Hi Lok NSA5357-5-11

2 Pin-Hi Lok NSA5359-5-13

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 48

5

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

SERVICE BULLETIN

2 Pin-Hi Lok NSA5351-6-13

14 Nut NSA5050-3

28 Nut NSA5050-4

28 Nut NSA5050-5

12 Nut NSA5050-6

14 Washer NSA5368PD10A

28 Washer NSA5368PD416A

28 Washer NSA5368PD516A

12 Washer NSA5368PD616A

(6) Subtask 536123-833-017-001 - Replace splice, LH side (replace by Repair

Instruction R53810423, SOL. A.)

Manpower Resources

Manhours 26.00

Minimum number of person 1

Subtask elapsed time 26.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 536123A08R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A5381263520096 1 Splice

NOTE: Kit 536123A08R00 : In case of crack findings more than 0.8 mm (0.315

in.) at holes A to N. Valid all A/C. Replacement splice, LH side.

Kit 536123A10R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NAS1726-3E 18 Nut

NAS1726-4E 41 Nut

NAS1726-5E 6 Nut

NAS1727-4E 1 Nut

NSA5351-4-11 6 Pin

NSA5351-4-12 2 Pin

NSA5351-4-13 13 Pin

NSA5351-4-14 2 Pin

NSA5351-4-15 4 Pin

NSA5351-4-16 4 Pin

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 49

5

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

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA5351-4-19 2 Pin

NSA5351-5-12 4 Pin

NSA5351-5-13 1 Pin

NSA5351-5-14 1 Pin

NSA5357-3-10 7 Pin

NSA5357-3-12 9 Pin

NSA5357-3-14 2 Pin

NSA5357-4-12 7 Pin

NSA5357-4-15 1 Pin

NSA5359-4-18 1 Pin

NOTE: Kit 536123A10R01 : In case of crack findings more than 0.8 mm (0.315

in.) at holes A to N. Valid A/C MSN 0284 thru 0377, 0384, 0388,

0395 and 0398 . Bolts for replacement splice with Repair Instruction

R53810423 SOL. A.

References

Repair Instruction R53810423

(a) Replace splice, LH side (replace by Repair Instruction R53810423, SOL.A.) :

1 Splice A5381263520096

attach with :

2 Pin-Hi Lok NSA5351-4-12

2 Pin-Hi Lok NSA5351-4-19

4 Pin-Hi Lok NSA5351-5-12

1 Pin-Hi Lok NSA5351-5-13

1 Pin-Hi Lok NSA5359-4-18

7 Pin-Hi Lok NSA5357-4-12

1 Pin-Hi Lok NSA5357-4-15

1 Pin-Hi Lok NSA5351-5-14

7 Pin-Hi Lok NSA5357-3-10

9 Pin-Hi Lok NSA5357-3-12

2 Pin-Hi Lok NSA5357-3-14

6 Pin-Hi-Lok NSA5351-4-11

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 50

5

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

SERVICE BULLETIN

13 Pin-Hi Lok NSA5351-4-13

2 Pin-Hi Lok NSA5351-4-14

4 Pin-Hi Lok NSA5351-4-15

4 Pin-Hi Lok NSA5351-4-16

18 Nut NAS1726-3E

41 Nut NAS1726-4E

6 Nut NAS1726-5E

1 Nut NAS1727-4E

(7) Subtask 536123-833-018-001 - Replace splice, RH side (replace by Repair

Instruction R53810423, SOL. A.)

Manpower Resources

Manhours 26.00

Minimum number of person 1

Subtask elapsed time 26.00

Skills AIRFRAME

Material necessary to do the job

Kit 536123A09R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A5381263520196 1 Splice

NOTE: Kit 536123A09R00 : In case of crack findings more than 0.8 mm (0.315

in.) at holes A to N. Valid all A/C. Replacement splice, RH side.

Kit 536123A10R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NAS1726-3E 18 Nut

NAS1726-4E 41 Nut

NAS1726-5E 6 Nut

NAS1727-4E 1 Nut

NSA5351-4-11 6 Pin

NSA5351-4-12 2 Pin

NSA5351-4-13 13 Pin

NSA5351-4-14 2 Pin

NSA5351-4-15 4 Pin

NSA5351-4-16 4 Pin

NSA5351-4-19 2 Pin

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 51

5

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

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA5351-5-12 4 Pin

NSA5351-5-13 1 Pin

NSA5351-5-14 1 Pin

NSA5357-3-10 7 Pin

NSA5357-3-12 9 Pin

NSA5357-3-14 2 Pin

NSA5357-4-12 7 Pin

NSA5357-4-15 1 Pin

NSA5359-4-18 1 Pin

NOTE: Kit 536123A10R01 : In case of crack findings more than 0.8 mm (0.315

in.) at holes A to N. Valid A/C MSN 0284 thru 0377, 0384, 0388,

0395 and 0398 . Bolts for replacement splice with Repair Instruction

R53810423 SOL. A.

References

Repair Instruction R53810423

(a) Replace splice, RH side, (replace by Repair Instruction R53810423, SOL.A.) :

1 Splice A5381263520196

attach with :

2 Pin-Hi Lok NSA5351-4-12

2 Pin-Hi Lok NSA5351-4-19

4 Pin-Hi Lok NSA5351-5-12

1 Pin-Hi Lok NSA5351-5-13

1 Pin-Hi Lok NSA5359-4-18

7 Pin-Hi Lok NSA5357-4-12

1 Pin-Hi Lok NSA5357-4-15

1 Pin-Hi Lok NSA5351-5-14

7 Pin-Hi Lok NSA5357-3-10

9 Pin-Hi Lok NSA5357-3-12

2 Pin-Hi Lok NSA5357-3-14

6 Pin-Hi-Lok NSA5351-4-11

13 Pin-Hi Lok NSA5351-4-13

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 52

5

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

SERVICE BULLETIN

2 Pin-Hi Lok NSA5351-4-14

4 Pin-Hi Lok NSA5351-4-15

4 Pin-Hi Lok NSA5351-4-16

18 Nut NAS1726-3E

41 Nut NAS1726-4E

6 Nut NAS1726-5E

1 Nut NAS1727-4E

(8) Subtask 536123-833-021-001 - Replace splice, LH side (replace by Repair

Instruction R53810423, SOL. C.)

Manpower Resources

Manhours 26.00

Minimum number of person 1

Subtask elapsed time 26.00

Skills AIRFRAME

Material necessary to do the job

Kit 536123A08R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A5381263520096 1 Splice

NOTE: Kit 536123A08R00 : In case of crack findings more than 0.8 mm (0.315

in.) at holes A to N. Valid all A/C. Replacement splice, LH side.

Kit 536123A12R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NAS1726-3E 18 Nut

NAS1726-4E 41 Nut

NAS1726-5E 7 Nut

NSA5351-4-11 6 Pin

NSA5351-4-12 1 Pin

NSA5351-4-13 12 Pin

NSA5351-4-14 2 Pin

NSA5351-4-15 4 Pin

NSA5351-4-16 1 Pin

NSA5351-5-12 4 Pin

NSA5351-5-19 1 Pin

NSA5357-3-10 7 Pin

NSA5357-3-12 9 Pin

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 53

5

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

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA5357-3-14 2 Pin

NSA5357-4-12 8 Pin

NSA5357-4-13 1 Pin

NSA5357-4-15 4 Pin

NSA5357-4-19 2 Pin

NSA5357-5-13 1 Pin

NSA5357-5-14 1 Pin

NOTE: Kit 536123A12R01 : In case of crack findings more than 0.8 mm (0.315

in.) at holes A to N. Valid A/C MSN 0284 thru 0377, 0384, 0388,

0395 and 0398 . Bolts for replacement splice with Repair Instruction

R53810423 SOL. C.

References

Repair Instruction R53810423

(a) Replace splice, LH side (replace by Repair Instruction R53810423, SOL.C.) :

1 splice A5381263520096

attach with :

6 Pin-Hi-Lok NSA5351-4-11

1 Pin-Hi Lok NSA5351-4-12

12 Pin-Hi Lok NSA5351-4-13

2 Pin-Hi Lok NSA5351-4-14

4 Pin-Hi Lok NSA5351-4-15

1 Pin-Hi Lok NSA5351-4-16

4 Pin-Hi Lok NSA5351-5-12

1 Pin-Hi Lok NSA5351-5-19

7 Pin-Hi Lok NSA5357-3-10

9 Pin-Hi Lok NSA5357-3-12

2 Pin-Hi Lok NSA5357-3-14

8 Pin-Hi Lok NSA5357-4-12

1 Pin-Hi Lok NSA5357-4-13

4 Pin-Hi Lok NSA5357-4-15

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 54

5

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

SERVICE BULLETIN

2 Pin-Hi Lok NSA5357-4-19

1 Pin-Hi Lok NSA5357-5-14

1 Pin-Hi Lok NSA5357-5-13

18 Nut NAS1726-3E

41 Nut NAS1726-4E

7 Nut NAS1726-5E

(9) Subtask 536123-833-022-001 - Replace splice, RH side (replace by Repair

Instruction R53810423, SOL. C.)

Manpower Resources

Manhours 26.00

Minimum number of person 1

Subtask elapsed time 26.00

Skills AIRFRAME

Material necessary to do the job

Kit 536123A09R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A5381263520196 1 Splice

NOTE: Kit 536123A09R00 : In case of crack findings more than 0.8 mm (0.315

in.) at holes A to N. Valid all A/C. Replacement splice, RH side.

Kit 536123A12R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NAS1726-3E 18 Nut

NAS1726-4E 41 Nut

NAS1726-5E 7 Nut

NSA5351-4-11 6 Pin

NSA5351-4-12 1 Pin

NSA5351-4-13 12 Pin

NSA5351-4-14 2 Pin

NSA5351-4-15 4 Pin

NSA5351-4-16 1 Pin

NSA5351-5-12 4 Pin

NSA5351-5-19 1 Pin

NSA5357-3-10 7 Pin

NSA5357-3-12 9 Pin

NSA5357-3-14 2 Pin

NSA5357-4-12 8 Pin

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 55

5

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

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA5357-4-13 1 Pin

NSA5357-4-15 4 Pin

NSA5357-4-19 2 Pin

NSA5357-5-13 1 Pin

NSA5357-5-14 1 Pin

NOTE: Kit 536123A12R01 : In case of crack findings more than 0.8 mm (0.315

in.) at holes A to N. Valid A/C MSN 0284 thru 0377, 0384, 0388,

0395 and 0398 . Bolts for replacement splice with Repair Instruction

R53810423 SOL. C.

References

Repair Instruction R53810423

(a) Replace splice, RH side (replace by Repair Instruction R53810423, SOL.C.) :

1 Splice A5381263520196

attach with :

6 Pin-Hi-Lok NSA5351-4-11

1 Pin-Hi Lok NSA5351-4-12

12 Pin-Hi Lok NSA5351-4-13

2 Pin-Hi Lok NSA5351-4-14

4 Pin-Hi Lok NSA5351-4-15

1 Pin-Hi Lok NSA5351-4-16

4 Pin-Hi Lok NSA5351-5-12

1 Pin-Hi Lok NSA5351-5-19

7 Pin-Hi Lok NSA5357-3-10

9 Pin-Hi Lok NSA5357-3-12

2 Pin-Hi Lok NSA5357-3-14

8 Pin-Hi Lok NSA5357-4-12

1 Pin-Hi Lok NSA5357-4-13

4 Pin-Hi Lok NSA5357-4-15

2 Pin-Hi Lok NSA5357-4-19

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 56

5

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

SERVICE BULLETIN

1 Pin-Hi Lok NSA5357-5-14

1 Pin-Hi Lok NSA5357-5-13

18 Nut NAS1726-3E

41 Nut NAS1726-4E

7 Nut NAS1726-5E

(10) Subtask 536123-833-023-001 - Install new fasteners for the adjacent holes

Manpower Resources

Manhours 10.00

Minimum number of person 1

Subtask elapsed time 10.00

Skills AIRFRAME

Material necessary to do the job

Kit 536123A13R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA5050-3 11 Nut

NSA5050-4 10 Nut

NSA5330-6 2 Nut

NSA5351-3-10 1 Pin

NSA5351-3-12 1 Pin

NSA5351-3-13 5 Pin

NSA5351-3-15 4 Pin

NSA5351-3-16 1 pin

NSA5351-4-13 5 Pin

NSA5351-4-15 4 Pin

NSA5351-4-16 1 Pin

NSA5357-3-10 1 Pin

NSA5357-3-12 1 Pin

NOTE: Kit 536123A13R01 : In case of no crack findings in the adjacent holes.

Valid all A/C.

(a) Install fasteners for the adjacent holes :

Kit 536123A13R01

1 Pin-Hi lok NSA5351-3-10

1 Pin-Hi lok NSA5351-3-12

5 Pin-Hi lok NSA5351-3-13

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 57

5

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

SERVICE BULLETIN

4 Pin-Hi lok NSA5351-3-15

1 Pin-Hi Lok NSA5351-3-16

5 Pin-Hi Lok NSA5351-4-13

4 Pin-Hi Lok NSA5351-4-15

1 Pin-Hi Lok NSA5351-4-16

11 Nut NSA5050-3

10 Nut NSA5050-4

1 Pin-Hi Lok NSA5357-3-10

1 Pin-Hi Lok NSA5357-3-12

2 Nuts NSA5330-6

**CONF 002

(1) Subtask 536123-833-012-002 - Install new Fasteners of same Diameter for Aircraft

having a Reinforced Splice.

Manpower Resources

Manhours 18.00

Minimum number of person 1

Subtask elapsed time 18.00

Skills AIRFRAME

Material necessary to do the job

Kit 536123A03R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA5050-4 16 Nut

NSA5050-5 12 Nut

NSA5351-4-12 2 Pin

NSA5351-4-13 2 Pin

NSA5351-4-16 6 Pin

NSA5351-4-18 6 Pin

NSA5351-5-12 8 Pin

NSA5351-5-13 2 Pin

NSA5351-5-14 2 Pin

NSA5368PD416A 16 Washer

NSA5368PD516A 12 Washer

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 58

5

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

SERVICE BULLETIN

NOTE: Kit 536123A03R01 : In case of no crack findings at holes A to N. Valid

A/C MSN 0252, 0380, 0391, 0401 thru 0878 . A/C having new splice

A53812635200/201 or 202/203

References

Fig. A-FBCAA

Replacement of Fasteners

Sheet 01

Fig. A-FBFAA

Install New Fasteners, KIT A03

Sheet 01

(a) Install new fasteners of same diameter, refer to Fig. A-FBCAA Sheet 01 and Fig. AFBFAA Sheet 01 :

8 Pin-Hi Lok NSA5351-5-12

2 Pin-Hi Lok NSA5351-5-13

2 Pin-Hi Lok NSA5351-5-14

2 Pin-Hi Lok NSA5351-4-12

6 Pin-Hi Lok NSA5351-4-16

6 Pin-Hi Lok NSA5351-4-18

2 Pin-Hi Lok NSA5351-4-13

16 Nut NSA5050-4

12 Nut NSA5050-5

16 Washer NSA5368PD416A

12 Washer NSA5368PD516A

NOTE: Use washer NSA5368 only if the fasteners are too long.

(2) Subtask 536123-833-014-002 - Install new Fasteners of same Diameter for Aircraft

having a Reinforced Splice (Replaced by Repair Instruction R53810423 SOL. B)

Manpower Resources

Manhours 18.00

Minimum number of person 1

Subtask elapsed time 18.00

Skills AIRFRAME

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 59

5

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

SERVICE BULLETIN

Material necessary to do the job

Kit 536123A05R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA5050-4 16 Nut

NSA5050-5 12 Nut

NSA5357-4-11 2 Pin

NSA5357-4-12 2 Pin

NSA5357-4-14 6 Pin

NSA5357-4-16 6 Pin

NSA5357-5-11 2 Pin

NSA5357-5-12 2 Pin

NSA5357-5-9 8 Pin

NSA5368PD416A 16 Washer

NSA5368PD516A 12 Washer

NOTE: Kit 536123A05R01 : In case of no crack findings at holes A to N.

Valid A/C MSN 0252, 0380, 0391, 0401 thru 0878 . A/C having new

splice A53812635200/201 or 202/203 (replaced by Repair Instruction

R53810423 SOL. B).

References

Fig. A-FBCAA

Replacement of Fasteners

Sheet 01

Fig. A-FBHAA

Install New Fasteners, KIT A05

Sheet 01

(a) Install new fasteners of same diameter, refer to Fig. A-FBCAA Sheet 01 and Fig. AFBHAA Sheet 01 :

2 Pin-Hi Lok NSA5357-4-12

2 Pin-Hi Lok NSA5357-5-12

2 Pin-Hi Lok NSA5357-5-11

8 Pin-Hi Lok NSA5357-5-9

2 Pin-Hi Lok NSA5357-4-11

6 Pin-Hi Lok NSA5357-4-14

6 Pin-Hi Lok NSA5357-4-16

16 Nut NSA5050-4

12 Nut NSA5050-5

16 Washer NSA5368PD416A

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 60

5

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

SERVICE BULLETIN

12 Washer NSA5368PD516A

NOTE: Use washer NSA5368 only if the fasteners are too long.

(3) Subtask 536123-833-016-001 - Install new fasteners on the splice (transition fit)

Manpower Resources

Manhours 10.00

Minimum number of person 1

Subtask elapsed time 10.00

Skills AIRFRAME

Material necessary to do the job

Kit 536123A07R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA5050-3 14 Nut

NSA5050-4 28 Nut

NSA5050-5 28 Nut

NSA5050-6 12 Nut

NSA5351-4-12 2 Pin

NSA5351-4-13 2 Pin

NSA5351-4-15 6 Pin

NSA5351-4-19 4 Pin

NSA5351-5-11 2 Pin

NSA5351-5-12 12 Pin

NSA5351-5-13 4 Pin

NSA5351-5-14 6 Pin

NSA5351-5-15 6 Pin

NSA5351-5-16 6 Pin

NSA5351-5-18 6 Pin

NSA5351-5-19 6 Pin

NSA5351-6-11 2 Pin

NSA5351-6-12 10 Pin

NSA5351-6-13 4 Pin

NSA5351-6-14 2 Pin

NSA5351-6-9 8 Pin

NSA5357-3-12 2 Pin

NSA5357-3-13 2 Pin

NSA5357-3-15 6 Pin

NSA5357-3-19 4 Pin

NSA5357-4-12 12 Pin

NSA5357-4-13 4 Pin

NSA5357-4-15 6 Pin

NSA5357-4-16 6 Pin

NSA5357-4-18 6 Pin

NSA5357-4-19 6 Pin

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 61

5

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

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA5357-5-11 2 Pin

NSA5357-5-12 12 Pin

NSA5357-5-13 4 Pin

NSA5357-5-14 6 Pin

NSA5357-5-15 6 Pin

NSA5357-5-16 6 Pin

NSA5357-5-18 6 Pin

NSA5357-5-19 6 Pin

NSA5359-3-12 2 Pin

NSA5359-3-13 2 Pin

NSA5359-3-15 6 Pin

NSA5359-3-19 4 Pin

NSA5359-4-11 2 Pin

NSA5359-4-12 12 Pin

NSA5359-4-13 4 Pin

NSA5359-4-14 6 Pin

NSA5359-4-15 6 Pin

NSA5359-4-16 6 Pin

NSA5359-4-18 6 Pin

NSA5359-4-19 6 Pin

NSA5359-5-11 2 Pin

NSA5359-5-12 10 Pin

NSA5359-5-13 4 Pin

NSA5359-5-14 2 Pin

NSA5359-5-9 8 Pin

NSA5368PD10A 14 Washer

NSA5368PD416A 28 Washer

NSA5368PD516A 28 Washer

NSA5368PD616A 12 Washer

NOTE: Kit 536123A07R02 : In case of crack findings less than or equal to 0.8

mm (0.315 in.) at holes A to N. Valid all A/C.

- Valid A/C having basic splice A53834139202/203 (Service Bulletin

No. A300-53-6131 not accomplished).

- Valid A/C having basic splice A53834139202/203 (Service Bulletin

No. A300-53-6131 accomplished).

- Valid A/C having new splice A53812635202/203 (Modification

No.05890S6739 embodied in production line).

- Valid A/C having new splice A53812635200/201 or 202/203

(replaced by Repair Instruction R53810423 SOL. A).

- Valid A/C having new splice A53812635200/201 or 202/203

(replaced by Repair Instruction R53810423 SOL. B).

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 62

5

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

SERVICE BULLETIN

- Valid A/C having new splice A53812635200/201 or 202/203

(replaced by Repair Instruction R53810423 SOL. C).

References

Fig. A-FBCAA

Replacement of Fasteners

Sheet 01

Fig. A-FBKAA

Install New Fasteners, KIT A07

Sheet 01

Fig. A-FBLAA

Install New Fasteners, KIT A07

Sheet 01

Fig. A-FBMAA

Install New Fasteners, KIT A07

Sheet 01

Fig. A-FBNAA

Install New Fasteners, KIT A07

Sheet 01

Fig. A-FBPAA

Install New Fasteners, KIT A07

Sheet 01

Fig. A-FBRAA

Install New Fasteners, KIT A07

Sheet 01

Fig. A-FBTAA

Holes Tolerances in case of Splice

replacement

Sheet 01

(a) Install new fasteners on the splice, refer to Fig. A-FBCAA Sheet 01, Fig. A-FBKAA

Sheet 01, Fig. A-FBLAA Sheet 01, Fig. A-FBMAA Sheet 01, Fig. A-FBNAA Sheet

01, Fig. A-FBPAA Sheet 01, Fig. A-FBRAA Sheet 01 and Fig. A-FBTAA Sheet 01 :

4 Pin-Hi Lok NSA5357-4-13

4 Pin-Hi Lok NSA5359-4-13

4 Pin-Hi Lok NSA5351-5-13

4 Pin-Hi Lok NSA5357-5-13

2 Pin-Hi Lok NSA5351-4-13

2 Pin-Hi Lok NSA5359-3-13

2 Pin-Hi Lok NSA5357-3-13

2 Pin-Hi Lok NSA5359-5-13

2 Pin-Hi Lok NSA5351-6-13

12 Pin-Hi Lok NSA5357-4-12

12 Pin-Hi Lok NSA5359-4-12

12 Pin-Hi Lok NSA5351-5-12

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 63

5

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

SERVICE BULLETIN

12 Pin-Hi Lok NSA5357-5-12

10 Pin-Hi Lok NSA5359-5-12

10 Pin-Hi Lok NSA5351-6-12

2 Pin-Hi Lok NSA5351-4-12

2 Pin-Hi LoK NSA5359-3-12

2 Pin-Hi Lok NSA5357-3-12

6 Pin-Hi Lok NSA5357-4-19

6 Pin-Hi Lok NSA5359-4-19

6 Pin-Hi Lok NSA5351-5-19

6 Pin-Hi Lok NSA5357-5-19

4 Pin-Hi Lok NSA5351-4-19

4 Pin-Hi Lok NSA5359-3-19

4 Pin-Hi Lok NSA5357-3-19

6 Pin-Hi Lok NSA5357-3-15

6 Pin-Hi Lok NSA5359-3-15

6 Pin-Hi Lok NSA5351-4-15

6 Pin-Hi Lok NSA5357-4-15

6 Pin-Hi Lok NSA5359-4-15

6 Pin-Hi Lok NSA5351-5-15

6 Pin-Hi Lok NSA5357-5-15

6 Pin-Hi Lok NSA5357-5-14

2 Pin-Hi Lok NSA5359-5-14

2 Pin-Hi Lok NSA5351-6-14

6 Pin-Hi Lok NSA5351-5-14

6 Pin-Hi Lok NSA5359-4-14

6 Pin-Hi Lok NSA5357-4-16

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 64

5

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

SERVICE BULLETIN

6 Pin-Hi Lok NSA5359-4-16

6 Pin.Hi-Lok NSA5351-5-16

6 Pin-Hi Lok NSA5357-5-16

6 Pin-Hi Lok NSA5357-4-18

6 Pin-Hi Lok NSA5359-4-18

6 Pin-Hi Lok NSA5351-5-18

6 Pin-Hi Lok NSA5357-5-18

2 Pin-Hi Lok NSA5359-5-11

2 Pin-Hi Lok NSA5351-6-11

8 Pin-Hi Lok NSA5359-5-9

8 Pin.Hi-Lok NSA5351-6-9

2 Pin-Hi Lok NSA5359-4-11

2 Pin-Hi Lok NSA5351-5-11

2 Pin-Hi Lok NSA5357-5-11

2 Pin-Hi Lok NSA5359-5-13

2 Pin-Hi Lok NSA5351-6-13

14 Nut NSA5050-3

28 Nut NSA5050-4

28 Nut NSA5050-5

12 Nut NSA5050-6

14 Washer NSA5368PD10A

28 Washer NSA5368PD416A

28 Washer NSA5368PD516A

12 Washer NSA5368PD616A

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 65

5

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@A300-600

SERVICE BULLETIN

(4) Subtask 536123-833-019-002 - Replace splice, LH side (replace by Repair

Instruction R53810423, SOL. B.)

Manpower Resources

Manhours 26.00

Minimum number of person 1

Subtask elapsed time 26.00

Skills AIRFRAME

Material necessary to do the job

Kit 536123A08R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A5381263520096 1 Splice

NOTE: Kit 536123A08R00 : In case of crack findings more than 0.8 mm (0.315

in.) at holes A to N. Valid all A/C. Replacement splice, LH side.

Kit 536123A11R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NAS1726-4E 42 Nut

NAS1726-5E 6 Nut

NAS1727-3E 18 Nut

NSA5357-4-11 7 Pin

NSA5357-4-12 9 Pin

NSA5357-4-13 12 Pin

NSA5357-4-14 5 Pin

NSA5357-4-15 5 Pin

NSA5357-4-16 4 Pin

NSA5357-5-11 1 Pin

NSA5357-5-12 1 Pin

NSA5357-5-9 4 Pin

NSA5359-3-10 7 Pin

NSA5359-3-12 9 Pin

NSA5359-3-14 2 Pin

NOTE: Kit 536123A11R01 : In case of crack findings more than 0.8 mm (0.315

in.) at holes A to N. Valid A/C MSN 0252, 0380, 0391, 0401 thru 0878 .

Bolts for replacement splice with Repair Instruction R53810423 SOL.B.

References

Repair Instruction R53810423

(a) Replace splice, LH side (replace by Repair Instruction R53810423, SOL.B.) :

1 Splice A5381263520096

attach with :

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 66

5

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

SERVICE BULLETIN

7 Pin-Hi Lok NSA5357-4-11

9 Pin-Hi Lok NSA5357-4-12

5 Pin-Hi Lok NSA5357-4-14

1 Pin-Hi Lok NSA5357-5-11

1 Pin-Hi Lok NSA5357-5-12

7 Pin-Hi Lok NSA5359-3-10

9 Pin-Hi LoK NSA5359-3-12

2 Pin-Hi Lok NSA5359-3-14

12 Pin-Hi Lok NSA5357-4-13

5 Pin-Hi Lok NSA5357-4-15

4 Pin-Hi Lok NSA5357-4-16

4 Pin-Hi Lok NSA5357-5-9

42 Nut NAS1726-4E

6 Nut NAS1726-5E

18 Nut NAS1727-3E

(5) Subtask 536123-833-020-002 - Replace splice, RH side (replace by Repair

Instruction R53810423, SOL. B.)

Manpower Resources

Manhours 26.00

Minimum number of person 1

Subtask elapsed time 26.00

Skills AIRFRAME

Material necessary to do the job

Kit 536123A09R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A5381263520196 1 Splice

NOTE: Kit 536123A09R00 : In case of crack findings more than 0.8 mm (0.315

in.) at holes A to N. Valid all A/C. Replacement splice, RH side.

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 67

5

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

SERVICE BULLETIN

Kit 536123A11R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NAS1726-4E 42 Nut

NAS1726-5E 6 Nut

NAS1727-3E 18 Nut

NSA5357-4-11 7 Pin

NSA5357-4-12 9 Pin

NSA5357-4-13 12 Pin

NSA5357-4-14 5 Pin

NSA5357-4-15 5 Pin

NSA5357-4-16 4 Pin

NSA5357-5-11 1 Pin

NSA5357-5-12 1 Pin

NSA5357-5-9 4 Pin

NSA5359-3-10 7 Pin

NSA5359-3-12 9 Pin

NSA5359-3-14 2 Pin

NOTE: Kit 536123A11R01 : In case of crack findings more than 0.8 mm (0.315

in.) at holes A to N. Valid A/C MSN 0252, 0380, 0391, 0401 thru 0878 .

Bolts for replacement splice with Repair Instruction R53810423 SOL.B.

References

Repair Instruction R53810423

(a) Replace splice, RH side (replace by Repair Instruction R53810423, SOL.B.) :

1 Splice A5381263520196

attach with :

7 Pin-Hi Lok NSA5357-4-11

9 Pin-Hi Lok NSA5357-4-12

5 Pin-Hi Lok NSA5357-4-14

1 Pin-Hi Lok NSA5357-5-11

1 Pin-Hi Lok NSA5357-5-12

7 Pin-Hi Lok NSA5359-3-10

9 Pin-Hi LoK NSA5359-3-12

2 Pin-Hi Lok NSA5359-3-14

12 Pin-Hi Lok NSA5357-4-13

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 68

5

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@A300-600

SERVICE BULLETIN

5 Pin-Hi Lok NSA5357-4-15

4 Pin-Hi Lok NSA5357-4-16

4 Pin-Hi Lok NSA5357-5-9

42 Nut NAS1726-4E

6 Nut NAS1726-5E

18 Nut NAS1727-3E

(6) Subtask 536123-833-023-001 - Install new fasteners for the adjacent holes

Manpower Resources

Manhours 10.00

Minimum number of person 1

Subtask elapsed time 10.00

Skills AIRFRAME

Material necessary to do the job

Kit 536123A13R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA5050-3 11 Nut

NSA5050-4 10 Nut

NSA5330-6 2 Nut

NSA5351-3-10 1 Pin

NSA5351-3-12 1 Pin

NSA5351-3-13 5 Pin

NSA5351-3-15 4 Pin

NSA5351-3-16 1 pin

NSA5351-4-13 5 Pin

NSA5351-4-15 4 Pin

NSA5351-4-16 1 Pin

NSA5357-3-10 1 Pin

NSA5357-3-12 1 Pin

NOTE: Kit 536123A13R01 : In case of no crack findings in the adjacent holes.

Valid all A/C.

(a) Install fasteners for the adjacent holes :

Kit 536123A13R01

1 Pin-Hi lok NSA5351-3-10

1 Pin-Hi lok NSA5351-3-12

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 69

5

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

SERVICE BULLETIN

5 Pin-Hi lok NSA5351-3-13

4 Pin-Hi lok NSA5351-3-15

1 Pin-Hi Lok NSA5351-3-16

5 Pin-Hi Lok NSA5351-4-13

4 Pin-Hi Lok NSA5351-4-15

1 Pin-Hi Lok NSA5351-4-16

11 Nut NSA5050-3

10 Nut NSA5050-4

1 Pin-Hi Lok NSA5357-3-10

1 Pin-Hi Lok NSA5357-3-12

2 Nuts NSA5330-6

**CONF ALL

D. TEST

**CONF 001

None

**CONF 002

None

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 536123-942-027-001

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 25-12-11, Page Block 401

25-21-00, Page Block 401

25-23-31, Page Block 401

(a) Install heat and sound insulation blankets (Refer to AMM 25-12-11 Page Block

401).

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 70

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SERVICE BULLETIN

(b) Install lower sidewall panels (Refer to AMM 25-23-31 Page Block 401).

(c) Install row of passenger seats (Refer to AMM 25-21-00 Page Block 401).

(d) Remove the access platforms.

(e) Restore the systems and the aircraft to normal operating condition.

**CONF 002

(1) Subtask 536123-942-027-001

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 25-12-11, Page Block 401

25-21-00, Page Block 401

25-23-31, Page Block 401

(a) Install heat and sound insulation blankets (Refer to AMM 25-12-11 Page Block

401).

(b) Install lower sidewall panels (Refer to AMM 25-23-31 Page Block 401).

(c) Install row of passenger seats (Refer to AMM 25-21-00 Page Block 401).

(d) Remove the access platforms.

(e) Restore the systems and the aircraft to normal operating condition.

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 71

5

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@A300-600

SERVICE BULLETIN

**CONF ALL

SECTION

A−A

11mm

(0.433in.)

BASIC SPLICE PN: A53834139202/203

A

A

STGR26

SECTION

A−A

A

A

STGR26

16mm

(0.630in.)

STGR24 STGR24

REINFORCED SPLICE PN:

D_SB_536123_5_BAAA_01_01

A53812635200/201 OR A35812635202/203

Figure A-FBAAA - Sheet 01

Identification Splice

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 72

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SERVICE BULLETIN

**CONF ALL

B

A

FR40 FR47

B

N

M

L

I J

K

G

STRG24

STRG25

C

G

G

RH SIDE SHOWN

LH SIDE SYMMETRICAL

SECTION

C

D E

E

D

F

F

F

E

D

C

B

A

STRG26

H

A

B

HOLES TO BE INSPECTED

(A to N)

ADJACENT HOLES

D_SB_536123_5_BBAA_01_00

Figure A-FBBAA - Sheet 01

Location of Fastener Holes to be Inspected

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 73

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SERVICE BULLETIN

**CONF ALL

4mm (0.15in.)

SECTION

SPLICE

FRAME

4mm (0.15in.)

SECTION

SPLICE

FRAME

F−F

SECTION

SPLICE

FRAME

E−E

12mm (0.47in.)

SECTION

SPLICE

FRAME

G−G

4mm (0.15in.)

D−D

DEPTH: A

LENGHT:B

CRACK MEASUREMENT

D_SB_536123_5_BBAA_02_00

Figure A-FBBAA - Sheet 02

Location of Fastener Holes to be Inspected

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 74

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SERVICE BULLETIN

**CONF ALL

CRACK

FINDING

OR

INSPECT HOLES BY

ROTATING PROBE

INSTALL NEW FASTENERS

OF SAME DIAMETER IN

THE ADJACENT HOLES

REAM UP ORIGINAL HOLE TO THE NEXT

OVERSIZE NOT EXCEEDING DIA. MAXI:

HOLE A to F: 9.49mm (0.3736in.)

to 9.53mm (0.3752in.)

HOLE G to N: 8.296mm (0.3266in.)

to 8.335mm (0.3281in.)

AT FR47, BETWEEN STGR24 AND STGR26.

INSPECTION OF SPLICE AND FRAME AT

HOLE A TO N, BY ROTATING PROBE

REFER TO FIG. A−FBAAA AND A−FBBAA

CRACK DEPTH

 0.8mm (0.0315in.)

CRACK DEPTH

 0.8mm (0.0315in.)

NO YES

YES

CONTACT AIB

BEFORE

NEXT FLIGHT

RE−INSPECT AT INTERVAL,

AS DESCRIBED IN

PARA E.(2). TABLE 2.

CHECK ADJACENT HOLES

BY ROTATING PROBE

REFER TO FIG. A−FBBAA SHEET 01

INSTALL NEW FASTENERS

OF SAME DIAMETER AS

ORIGINAL ONES

(AS DESCRIBED IN SUBTASK

CRACK

FINDING ON

ADJACENT

HOLES

D_SB_536123_5_FAAA_01_00

536123−833−010 OR 536123−833−011

OR 536123−833−012 OR 536123−833−013

OR 536123−833−014 OR 536123−833−015)

NO

GO TO

SHEET 2

A

GO TO

SHEET 2

B

(AS DESCRIBED IN SUBTASK

536123−833−023)

Figure A-FFAAA - Sheet 01

Flow Chart

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 75

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SERVICE BULLETIN

**CONF ALL

QUESTION

ACTION

FINDING

CONTACT AIB

BEFORE

NEXT FLIGHT

B

CRACK DEPTH

 0.8mm (0.0315in.)

CRACK

FINDING

INSPECT HOLES BY

ROTATING PROBE

A

NO

YES

FSH 25% OR FSH 40%

25% FSH 40%

RE−INSPECT AT THRESHOLD

(AS DESCRIBED IN

COUNTED STARTING

FROM SPLICE

REPLACEMENT

FSH: FULL SCREEN HEIGHT

CONTINUATION OF SHEET 1

RE−INSPECT AT INTERVAL

REMOVE CRACK BY REREAMING

STEP BY STEP NOT EXCEEDING

DIA. MAXI.

HOLE A to F: 9.49mm (0.3736 in.)

to 9.53mm (0.3752 in.)

HOLE G to N: 8.296mm (0.3266in.)

to 8.335mm (0.3281 in.)

AFTER EACH STEP, PERFORM

ROTOTEST INSPECTION

CHECK ADJACENT HOLES

BY ROTATING PROBE

REFER TO FIG. A−FBBAA SHEET 01

CRACK ON

ORIGINAL HOLE

ON FRAME

CRACK ON ORIGINAL

HOLE ON SPLICE

NO

YES

CONTACT AIB

BEFORE

NEXT FLIGHT

INSTALL NEW FASTENERS

WITH TRANSITION FIT

CHANGE SPLICE

REFER TO REPAIR

INSTRUCTION R53810423

CRACK

FINDING ON 

ADJACENT

HOLES

INSTALL NEW FASTENERS

OF SAME DIAMETER IN

THE ADJACENT HOLES

D_SB_536123_5_FAAA_02_00

(AS DESCRIBED IN SUBTASK

536123−833−013)

(AS DESCRIBED IN

PARA E.(2). TABLE 2)

OR

(AS DESCRIBED IN

SUBTASK 536123−833−023)

(AS DESCRIBED IN SUBTASK

536123−833−017 OR

536123−833−018 OR

536123−833−019 OR

536123−833−020 OR

536123−833−021 OR

536123−833−022)

PARA E.(2). TABLE 1),

Figure A-FFAAA - Sheet 02

Flow Chart

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 76

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@A300-600

SERVICE BULLETIN

**CONF ALL

B

A

FR40 FR47

B

N

M

L

I J

K

G

STRG24

STRG25

C

RH SIDE SHOWN

LH SIDE SYMMETRICAL

SECTION

F

STRG26

H

A

B

N N

N N

N

N

N

N

F

E

D

C

B

A

F

F

F

F

F

C

C−C

N

F

HEAD VISIBLE

HEAD HIDDEN

D_SB_536123_5_BCAA_01_00

Figure A-FBCAA - Sheet 01

Replacement of Fasteners

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 77

5

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SERVICE BULLETIN

**CONF 001

A NSA5351−4−13

NSA5351−4−12

NSA5351−3−15

NSA5351−4−19

NSA5351−3−19

NSA5351−3−12

NSA5351−3−13

L

G

I

B, C, D, E, F

H, J, K

M, N

USE NUTS NSA5050−3 OR NSA5050−4

D_SB_536123_5_BDAA_01_00

Figure A-FBDAA - Sheet 01

Install New Fasteners, KIT A01

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 78

5

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SERVICE BULLETIN

**CONF 001

A

B

NSA5351−5−14

G

I

L

NSA5351−4−13

NSA5351−4−12

NSA5351−4−15

NSA5351−4−19

NSA5351−5−13

NSA5359−4−19

USE NUTS NSA5050−4 OR NSA5050−5

C ,D ,E ,F

H, J ,K

M ,N

NSA5359−4−12

D_SB_536123_5_BEAA_01_00

Figure A-FBEAA - Sheet 01

Install New Fasteners, KIT A02

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 79

5

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SERVICE BULLETIN

**CONF 002

A

B

G

I NSA5351−4−13

NSA5351−4−18

NSA5351−4−16

NSA5351−4−12

NSA5351−5−12

NSA5351−5−13

NSA5351−5−14

USE NUTS NSA5050−4 OR NSA5050−5

L ,M ,N

H ,J ,K

C, D, E, F

D_SB_536123_5_BFAA_01_00

Figure A-FBFAA - Sheet 01

Install New Fasteners, KIT A03

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 80

5

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SERVICE BULLETIN

**CONF 001

A

B

NSA5351−5−14

G

I

L

NSA5351−4−19

NSA5351−5−13

NSA5351−4−13

NSA5351−4−16

NSA5351−4−12

NSA5351−5−12

NSA5359−4−18

USE NUTS NSA5050−4 OR NSA5050−5

M, N

H, J, K

C, D, E, F

D_SB_536123_5_BGAA_01_00

Figure A-FBGAA - Sheet 01

Install New Fasteners, KIT A04

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 81

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SERVICE BULLETIN

**CONF 002

A

B

G

I

NSA5357−4−14

NSA5357−4−12

NSA5357−4−11

NSA5357−5−11

NSA5357−5−12

NSA5357−4−16

NSA5357−5−9

USE NUTS NSA5050−4 OR NSA5050−5

C ,D ,E ,F

H, J, K

L, M, N

D_SB_536123_5_BHAA_01_00

Figure A-FBHAA - Sheet 01

Install New Fasteners, KIT A05

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 82

5

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SERVICE BULLETIN

**CONF 001

A

B

G

USE NUTS NSA5050−4 OR NSA5050−5

C, D, E, F

NSA5351−5−19

NSA5357−4−19

NSA5357−4−15

NSA5357−4−13

NSA5357−4−12

NSA5351−5−12

NSA5357−5−13

NSA5357−5−14

L

H ,J ,K

M ,N

I

D_SB_536123_5_BJAA_01_00

Figure A-FBJAA - Sheet 01

Install New Fasteners, KIT A06

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 83

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**CONF ALL

NSA5359−5−13

NSA5351−6−13

NSA5357−5−13

A

NSA5357−4−13

NSA5359−4−13

NSA5351−5−13

NSA5359−4−19

NSA5351−5−19

NSA5357−5−19

NSA5359−5−12

NSA5351−6−12

NSA5359−4−12

NSA5351−5−12

NSA5357−5−12

NSA5359−3−15

NSA5351−4−15

NSA5357−4−15

NSA5359−4−15

NSA5351−5−15

NSA5357−5−15

L

NSA5357−4−12 NSA5357−3−15 NSA5357−4−19

G I

NSA5357−3−19 NSA5357−3−12 NSA5357−3−13

B, C, D,

E, F H, J, K M, N

NSA5359−3−19 NSA5359−3−12 NSA5359−3−13

NSA5351−4−19 NSA5351−4−12 NSA5351−4−13

NSA5357−4−19 NSA5357−4−12 NSA5357−4−13

NSA5359−4−19 NSA5359−4−12 NSA5359−4−13

NSA5351−5−19 NSA5351−5−12 NSA5351−5−13

NSA5357−5−19 NSA5357−5−12 NSA5357−5−13

VALID A/C HAVING BASIC SPLICE A53834139202/203

 (SB A300−53−6131 NOT ACCOMPLISHED)

USE NUTS NSA5050−3 OR NSA5050−4 OR NSA5050−5 OR NSA5050−6

D_SB_536123_5_BKAA_01_00

Figure A-FBKAA - Sheet 01

Install New Fasteners, KIT A07

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 84

5

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SERVICE BULLETIN

**CONF ALL

A B G I L

NSA5351−6−12

NSA5357−5−14

NSA5359−5−14

NSA5351−6−14

NSA5357−5−13

NSA5351−5−12

NSA5357−5−12 NSA5357−4−15

NSA5351−5−15

NSA5357−5−15

NSA5357−4−12 NSA5357−4−13

NSA5351−5−19

NSA5357−5−19

NSA5357−4−19

C ,D ,E ,F H ,J ,K M, N

NSA5351−5−12 NSA5351−5−13 NSA5351−5−19

NSA5357−5−12 NSA5357−5−13 NSA5357−5−19

VALID A/C HAVING BASIC SPLICE A53834139202/203

(SB A300−53−6131 ACCOMPLISHED)

NSA5359−5−13 NSA5359−5−12

NSA5351−6−13

NSA5359−4−15 NSA5359−4−12 NSA5359−4−13 NSA5359−4−19

USE NUTS NSA5050−3 OR NSA5050−4 OR NSA5050−5 OR NSA5050−6

D_SB_536123_5_BLAA_01_00

Figure A-FBLAA - Sheet 01

Install New Fasteners, KIT A07

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 85

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**CONF ALL

A I

NSA5357−5−14

NSA5359−5−14

NSA5351−6−14

NSA5357−5−13

NSA5359−5−13

NSA5351−6−13 NSA5351−6−12

NSA5359−5−12

NSA5357−5−12

B G

NSA5357−4−12

NSA5359−4−12

NSA5351−5−12

NSA5357−5−12

NSA5357−4−16 NSA5357−4−18 NSA5357−4−13

C, D, E, F H, J, K L, M, N

NSA5359−4−16 NSA5359−4−18 NSA5359−4−13

NSA5351−5−16 NSA5351−5−18 NSA5351−5−13

NSA5357−5−16 NSA5357−5−18 NSA5357−5−13

VALID A/C HAVING NEW SPLICE A53812635200/201 OR 202/203

(MOD.05890S6739 EMBODIED IN PRODUCTION LINE)

USE NUTS NSA5050−3 OR NSA5050−4 OR NSA5050−5 OR NSA5050−6

D_SB_536123_5_BMAA_01_00

Figure A-FBMAA - Sheet 01

Install New Fasteners, KIT A07

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 86

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**CONF ALL

A B G I L

NSA5357−5−14

NSA5359−5−14

NSA5351−6−14

NSA5357−5−13

NSA5351−6−13

NSA5359−5−13

NSA5357−5−12

NSA5359−5−12

NSA5351−6−12

NSA5357−4−12

NSA5359−4−12

NSA5351−5−12

NSA5357−5−12

NSA5351−5−18

NSA5357−5−18

NSA5357−4−19

C, D, E, F H, J, K M, N

NSA5357−4−13 NSA5357−4−16

NSA5359−4−13 NSA5359−4−16 NSA5359−4−19

NSA5351−5−13 NSA5351−5−16 NSA5351−5−19

NSA5357−5−13 NSA5357−5−16 NSA5357−5−19

VALID A/C HAVING NEW SPLICE A53812635200/201 OR 202/203

(REPLACED BY REPAIR INSTRUCTION R53810423 SOL. A)

USE NUTS NSA5050−3 OR NSA5050−4 OR NSA5050−5 OR NSA5050−6

D_SB_536123_5_BNAA_01_00

Figure A-FBNAA - Sheet 01

Install New Fasteners, KIT A07

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 87

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SERVICE BULLETIN

**CONF ALL

A B G I

NSA5359−5−12

NSA5351−6−12

NSA5359−5−11 NSA5359−5−9

NSA5351−6−9

NSA5359−4−11

NSA5351−5−11

NSA5357−5−11

NSA5359−4−12

NSA5351−5−12

NSA5357−5−12

NSA5359−4−14

NSA5351−5−14

NSA5357−5−14

NSA5359−4−16

NSA5351−5−16

NSA5357−5−16

C, D, E, F H, J, K L, M, N

NSA5351−6−11

VALID A/C HAVING NEW SPLICE A53812635200/201 OR 202/203

(REPLACED BY REPAIR INSTRUCTION R53810423 SOL. B)

USE NUTS NSA5050−3 OR NSA5050−4 OR NSA5050−5 OR NSA5050−6

D_SB_536123_5_BPAA_01_00

Figure A-FBPAA - Sheet 01

Install New Fasteners, KIT A07

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 88

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SERVICE BULLETIN

**CONF ALL

A B G I L

NSA5351−6−14 NSA5351−6−12

C ,D ,E ,F H ,J ,K M, N

NSA5357−5−12 NSA5357−5−19

NSA5351−6−13 NSA5351−5−12

NSA5359−5−14 NSA5359−5−13 NSA5359−5−12 NSA5359−4−12

NSA5357−5−12

NSA5359−4−13 NSA5359−4−15 NSA5359−4−19

NSA5351−5−13 NSA5351−5−15 NSA5351−5−19

NSA5357−5−13 NSA5357−5−15 NSA5357−5−19

VALID A/C HAVING NEW SPLICE A53812635200/201 OR 202/203

(REPLACE BY REPAIR INSTRUCTION R53810423 SOL. C)

USE NUTS NSA5050−3 OR NSA5050−4 OR NSA5050−5 OR NSA5050−6

D_SB_536123_5_BRAA_01_00

Figure A-FBRAA - Sheet 01

Install New Fasteners, KIT A07

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 89

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@A300-600

SERVICE BULLETIN

**CONF ALL

mm in.

DIA. MIN.

mm in.

DIA. MAX.

NSA5351−4

NSA5357−4

NSA5359−4

NSA5351−5

NSA5357−5

NSA5359−5

NSA5351−6

6.31

6.705

7.10

7.90

8.295

8.69

9.49

0.2484

0.264

0.2795

0.311

0.3266

0.3421

0.3736

6.35

6.745

7.14

7.94

8.335

8.73

9.53

0.25

0.2655

0.2811

0.3126

0.3281

0.3437

0.3752

TRANSITION FIT

D_SB_536123_5_BTAA_01_00

Figure A-FBTAA - Sheet 01

Holes Tolerances in case of Splice replacement

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 90

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SERVICE BULLETIN

Inspection Report

**CONF ALL

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

forwarded to airbus dept. SEES1, on the attached inspection.

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 1

5

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SERVICE BULLETIN

Inspection Report

**CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A300−53−6123

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE −

INSPECTION METHOD :

CENTER WING BOX (WB/LR)

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

D_SB_536123_5_RAAA_01_00

ROTATING PROBE

N

M

L

I J

K

G

STRG24

STRG25

SECTION

F

E

D

C

B

A

STRG26

H

A

LH SIDE SHOWN

MARK LOCATION AND DEPTH OF CRACK.

A−A

A

Figure A-FRAAA - Sheet 01

Inspection Report

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 2

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SERVICE BULLETIN

Inspection Report

**CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A300−53−6123

DATE OF INSPECTION :

RETURN TO :

INSPECTION METHOD : ROTATING PROBE

D_SB_536123_5_RAAA_02_00

N

M

L

I J

K

G

STRG24

STRG25

SECTION

F

E

D

C

B

A

STRG26

H

A

RH SIDE SHOWN

MARK LOCATION AND DEPTH OF CRACK.

A−A

A

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE −

CENTER WING BOX (WB/LR)

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

Figure A-FRAAA - Sheet 02

Inspection Report

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 3

5

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

SERVICE BULLETIN

Inspection Report

**CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A300−53−6123

DATE OF INSPECTION :

RETURN TO :

INSPECTION METHOD : ROTATING PROBE

D_SB_536123_5_RAAA_03_00

H

O

L

E

NO CRACK

CRACK 0.8mm (0.0315in.)

FSH 25% 25% FSH 40% FSH 40%

A

B

C

D

E

F

G

H

I

J

K

L

M

N

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE −

CENTER WING BOX (WB/LR)

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

Figure A-FRAAA - Sheet 03

Inspection Report

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 4

5

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

SERVICE BULLETIN

Inspection Report

**CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A300−53−6123

DATE OF INSPECTION :

RETURN TO :

INSPECTION METHOD : ROTATING PROBE

D_SB_536123_5_RAAA_04_00

H

O

L

E

CRACK 0.8mm (0.0315in.)

A

B

C

D

E

F

G

H

I

J

K

L

M

N

REPLACEMENT

SPLICE CRACK ON FRAME CRACK ON SPLICE

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE −

CENTER WING BOX (WB/LR)

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

Figure A-FRAAA - Sheet 04

Inspection Report

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 5

5

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

SERVICE BULLETIN

REPORTING SHEET

TITLE: INSPECTION HOLES FUSELAGE FRAME 47 SPLICE FITTING

BETWEEN STRINGERS 24 AND 26 LH AND RH SIDES.

MODIFICATION No.: None

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

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: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 1

5

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: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123

REVISION No.: 06 - Sep 28/11 Page: 1

5

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