# @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



# MANDATORYMANDATORYMANDATORY 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. 

# MANDATORYMANDATORYMANDATORY 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

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# @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

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# @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 5

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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

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# @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

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# @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



# MANDATORYMANDATORYMANDATORY 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 0602-06150617-06180621 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 5

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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 050705080515 AMU 0677 0743 BCS 0621 0637 0641 067006790711 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 05060509 05130514 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 0733073407390755 0758 MON 0540 0556 0604 0605 MSR 0561 0607 MXU 0767 0788 079708360837 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 5

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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 5

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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 5

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# @A300-600 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 5

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# @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 underEASA Design Organisation ApprovalNo. 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 5

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# @A300-600 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

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# @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 5

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# @A300-600 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 5

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# @A300-600 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 5

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# @A300-600 SERVICE BULLETIN 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 5

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# @A300-600 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 5

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# @A300-600 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 5

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# @A300-600 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 5

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# @A300-600 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 5

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# @A300-600 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 5

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# @A300-600 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 5

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# @A300-600 SERVICE BULLETIN
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 5

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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 5

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# @A300-600 SERVICE BULLETIN
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 5

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# @A300-600 SERVICE BULLETIN
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 5

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# @A300-600 SERVICE BULLETIN
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 5

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# @A300-600 SERVICE BULLETIN 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 5

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# @A300-600 SERVICE BULLETIN 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 5

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# @A300-600 SERVICE BULLETIN
**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 5

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# @A300-600 SERVICE BULLETIN (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 toFig. A-FFAAA Sheet 01 andFig. 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 5

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# @A300-600 SERVICE BULLETIN

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 5

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# @A300-600 SERVICE BULLETIN
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 5

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# @A300-600 SERVICE BULLETIN
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 toFig. A-FFAAA Sheet 01 andFig. 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 5

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# @A300-600 SERVICE BULLETIN
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 5

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# @A300-600 SERVICE BULLETIN 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 systemsand 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 5

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# @A300-600 SERVICE BULLETIN
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 systemsand the aircraft to normal operating condition.

DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123 REVISION No.: 06 - Sep 28/11 Page: 33 5

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# @A300-600 SERVICE BULLETIN

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DATE: Oct 25/99 SERVICE BULLETIN No.: A300-53-6123 REVISION No.: 06 - Sep 28/11 Page: 34 5

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# @A300-600 SERVICE BULLETIN 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 5

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# @A300-600 SERVICE BULLETIN 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 5

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# @A300-600 SERVICE BULLETIN 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 5

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# @A300-600 SERVICE BULLETIN
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 5

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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 toFig. A-FBCAA Sheet 01 andFig. 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

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# @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

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# @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 toFig. A-FBCAA Sheet 01 andFig. 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

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# @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 toFig. A-FBCAA Sheet 01 andFig. 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

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# @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 toFig. A-FBCAA Sheet 01 andFig. 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

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# @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

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# @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

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# @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 andFig. 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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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 toFig. A-FBCAA Sheet 01 andFig. 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

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# @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 toFig. A-FBCAA Sheet 01 andFig. 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

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# @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

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# @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

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# @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 andFig. 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

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# @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

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# @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

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# @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

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# @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

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# @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 5

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# @A300-600 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 systemsand 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 systemsand 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 5

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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 **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 5

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# @A300-600 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 5

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# @A300-600 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 5

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# @A300-600 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

OR FSH 40% FSH 25%

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 5

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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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# @A300-600 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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# @A300-600 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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# @A300-600 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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# @A300-600 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 5

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# @A300-600 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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# @A300-600 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 5

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# @A300-600 SERVICE BULLETIN

**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

NSA5357−4−19 NSA5357−4−12 NSA5357−3−15 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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# @A300-600 SERVICE BULLETIN

**CONF ALL

B G I L A

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 5

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# @A300-600 SERVICE BULLETIN

**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 5

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# @A300-600 SERVICE BULLETIN

**CONF ALL

B G I L A

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 5

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# @A300-600 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 L, M, N H, J, K C, D, E, F

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 5

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# @A300-600 SERVICE BULLETIN

**CONF ALL

B G I L A

NSA5351−6−12 NSA5351−6−14 C ,D ,E ,F H ,J ,K M, N

NSA5357−5−19 NSA5357−5−12 NSA5351−5−12 NSA5351−6−13 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 5

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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 5

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# @A300-600 SERVICE BULLETIN

Inspection Report **CONF ALL The results of the inspection, including no findings, replacement or actions to be done, must be forwarded to airbusdept.SEES1, on theattached inspection.

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

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 5

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# @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_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

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# @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

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# @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 SPLICE CRACK ON FRAME 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

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# @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 BEembodied 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 BEENembodied 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

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# @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

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