# @A300-600 SERVICE BULLETIN SUMMARY AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 This summary is for information only and is not approved for modification of the aircraft. 

# MANDATORY MANDATORY MANDATORY ATA SYSTEM: 53 

### TITLE: FUSELAGE - CENTER FUSELAGE - INSPECT LOWER FRAME BASE FITTING BETWEEN FRAMES 41 AND 46 **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During a routine maintenance on A300-600 aircraft, operators have reported separate instances of cracks in the Frame feet fittings, connecting the Frame lower positions to the centre wing box (air conditioning bay). Since this time, AIRBUS has carried out a sampling inspection program on both aircraft types (A300 and A300-600). During this sampling program, twenty three A300-600 aircraft were inspected and cracks were found on the lower Frame fittings of Frame 44 to Frame 46 (LH and RH) on twenty two of the inspected aircraft. The aircraft with the findings have accumulated between 8000 and 21000 Flight Cycles (FC) and the lengths of the cracks varied between 12 mm and 18 mm (0.472 in. and 0.709 in.). Service Bulletin No. A300-53-6111 was created in order to treat the affected areas by repetitive inspection and also repair in case of crack finding. Repaired Frames were no longer inspected up to aircraft Limit of Validity (LoV). Further to new findings on repaired Frame feet, a new detailed Finite Element Model (FEM) study was performed. Outcomes of this study led Airbus to review the inspection program. The aim of the Service Bulletin, depending of the accomplishment of Service Bulletin No. A300-53-6111, is to perform a Detailed Inspection (DET) of the lower Frame feet fittings between Frame 41 and Frame 46 for the entire fleet. In case of crack finding, two options are possible: - The cracked Frame foot is replaced by an identical new one and the Inspection Service Bulletin (ISB) No. A300-53-6177 is still applicable.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 1 5

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# @A300-600 SERVICE BULLETIN SUMMARY - All Frame feet are replaced by new optimized parts as per Modification Service Bulletin No. A300-53-6176 (Mod. No. 13721S22901). In this case, no further inspection is necessary. Any findings (including Nil findings) are to be reported to AIRBUS. Service Bulletin No. A300-53-6111 is therefore cancelled and superseded by this new ISB. In addition to this new inspection program, Airbus designed new Frame feet. Their installation is proposed through a dedicated modification Service Bulletin No. A300-53-6176. Accomplishment of Modification Service Bulletin No. A300-53-6176 cancels the requirements of this ISB. Accomplishment of this ISB will allow early detection of cracks in order to avoid possible occurrence of crack propagation which can lead to costly and time-consuming repairs. 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 DE-FUELLING/VENTILATION YES 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 536177A03R00 1 8,100.00 Frame foot, Screws, Nuts, Rivets Kit 536177A06R00 1 8,900.00 Frame foot, Screws, Nuts, Rivets Kit 536177A09R00 1 7,600.00 Frame foot, Screws, Nuts, Rivets Kit 536177A12R00 1 7,300.00 Frame foot, Screws, Nuts, Rivets Kit 536177A15R00 1 7,900.00 Frame foot, Screws, Nuts, Rivets Kit 536177A18R00 1 8,700.00 Frame foot, Screws, Nuts, Rivets Kit 536177A21R00 1 8,100.00 Frame foot, Screws, Nuts, Rivets Kit 536177A24R00 1 9,000.00 Frame foot, Screws, Nuts, Rivets Kit 536177A27R00 1 7,600.00 Frame foot, Screws, Nuts, Rivets Kit 536177A30R00 1 7,300.00 Frame foot, Screws, Nuts, Rivets Kit 536177A33R00 1 7,900.00 Frame foot, Screws, Nuts, Rivets Kit 536177A36R00 1 8,700.00 Frame foot, Screws, Nuts, Rivets TOTAL 97,100.00 Component COMPA01 2 See SB Screws, Nuts, Rivets Component COMPA02 4 See SB Screws, Nuts, Rivets Component COMPA03 2 See SB Screws, Nuts, Rivets

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 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 Component COMPA04 2 See SB Screws, Nuts, Rivets Component COMPA05 2 See SB Screws, Nuts, Rivets **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 536177A02R00 1 7,600.00 Frame foot, Screws, Nuts, Rivets Kit 536177A05R00 1 8,200.00 Frame foot, Screws, Nuts, Rivets Kit 536177A08R00 1 7,100.00 Frame foot, Screws, Nuts, Rivets Kit 536177A11R00 1 6,700.00 Frame foot, Screws, Nuts, Rivets Kit 536177A14R00 1 7,300.00 Frame foot, Screws, Nuts, Rivets Kit 536177A17R00 1 8,200.00 Frame foot, Screws, Nuts, Rivets Kit 536177A20R00 1 7,600.00 Frame foot, Screws, Nuts, Rivets Kit 536177A23R00 1 8,200.00 Frame foot, Screws, Nuts, Rivets Kit 536177A26R00 1 7,100.00 Frame foot, Screws, Nuts, Rivets Kit 536177A29R00 1 6,700.00 Frame foot, Screws, Nuts, Rivets Kit 536177A32R00 1 7,300.00 Frame foot, Screws, Nuts, Rivets Kit 536177A35R00 1 8,200.00 Frame foot, Screws, Nuts, Rivets TOTAL 90,200.00 Component COMPA01 2 See SB Screws, Nuts, Rivets Component COMPA02 4 See SB Screws, Nuts, Rivets Component COMPA03 2 See SB Screws, Nuts, Rivets Component COMPA04 2 See SB Screws, Nuts, Rivets Component COMPA05 2 See SB Screws, Nuts, Rivets **CONF 003 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 536177A01R00 1 7,400.00 Frame foot, Screws, Nuts, Rivets Kit 536177A04R00 1 8,100.00 Frame foot, Screws, Nuts, Rivets Kit 536177A07R00 1 7,000.00 Frame foot, Screws, Nuts, Rivets Kit 536177A10R00 1 6,600.00 Frame foot, Screws, Nuts, Rivets Kit 536177A13R00 1 7,200.00 Frame foot, Screws, Nuts, Rivets Kit 536177A16R00 1 8,200.00 Frame foot, Screws, Nuts, Rivets Kit 536177A19R00 1 7,400.00 Frame foot, Screws, Nuts, Rivets Kit 536177A22R00 1 8,100.00 Frame foot, Screws, Nuts, Rivets Kit 536177A25R00 1 7,000.00 Frame foot, Screws, Nuts, Rivets DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 3 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 Kit 536177A28R00 1 6,600.00 Frame foot, Screws, Nuts, Rivets Kit 536177A31R00 1 7,200.00 Frame foot, Screws, Nuts, Rivets Kit 536177A34R00 1 8,100.00 Frame foot, Screws, Nuts, Rivets TOTAL 88,900.00 Component COMPA01 2 See SB Screws, Nuts, Rivets Component COMPA02 4 See SB Screws, Nuts, Rivets Component COMPA03 2 See SB Screws, Nuts, Rivets Component COMPA04 2 See SB Screws, Nuts, Rivets Component COMPA05 2 See SB Screws, Nuts, Rivets **CONF 004 No Material EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

06P 67Q ABR AHK BCS F2I FDX IRA IRM KAC MNB MRJ MSR OHY SUD TAR THA UPS UQA URS UTP UZB CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 4 5

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# @A300-600 SERVICE BULLETIN SUMMARY MANPOWER **CONF 001 Task 536177-832-801-001: Detailed Inspection of the Frame foot TOTAL MANHOURS 8.00 ELAPSED TIME (HOURS) 2.50 Task 536177-833-801-001: Repair TOTAL MANHOURS 541.00 ELAPSED TIME (HOURS) 42.00 **CONF 002 Task 536177-832-801-001: Detailed Inspection of the Frame foot TOTAL MANHOURS 8.00 ELAPSED TIME (HOURS) 2.50 Task 536177-833-801-001: Repair TOTAL MANHOURS 541.00 ELAPSED TIME (HOURS) 42.00 **CONF 003 Task 536177-832-801-001: Detailed Inspection of the Frame foot TOTAL MANHOURS 8.00 ELAPSED TIME (HOURS) 2.50 Task 536177-833-801-001: Repair TOTAL MANHOURS 541.00 ELAPSED TIME (HOURS) 42.00 **CONF 004 Task 536177-839-801-001: Contact and Report to AIRBUS TOTAL MANHOURS 0.50 ELAPSED TIME (HOURS) 0.50 APPENDICES **CONF ALL Appendix 01 - Elapsed Time Assumptions

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 5 5

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# @A300-600 SERVICE BULLETIN SUMMARY

**CONF ALL

FR41 FR42 FR43 FR44 FR45 FR46

FR47

FR40

FR46 FR45 FR44 FR43 FR42 FR41

AREAS TO BE INSPECTED C L 

## A

B Z140 

### A

B

D_SB_536177_5_SAAA_01_01 Figure A-FSAAA - Sheet 01
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 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



# MANDATORY MANDATORY MANDATORY ATA SYSTEM: 53 

### TITLE: FUSELAGE - CENTER FUSELAGE - INSPECT LOWER FRAME BASE FITTING BETWEEN FRAMES 41 AND 46 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/F C4-620 F4-605R F4-622R (2) Effectivity by MSN 0294 0344 0358 0361 0365 0380 0388 0401 0405 0408 0411 0414 0417 0477 0479 0505 0521 0525 0529-0530 0532 0536 0543 0546 0553 0555 0557-0559 0561 0563 0572 0575 0579 0581 0584 0602-0603 0607-0608 0611 0613 0617-0618 0621 0623 0625-0626 0629-0630 0632-0633 0637 0641 0643 0657 0659 0664 0666 0668 0670 0673 0677 0679 0683 0688 0694 0696 0699 0701 0703 0707 0709 0711 0713 0715 0717 0719 0721-0730 0732-0750 0752-0764 0766 0768-0775 0777-0794 0797 0799-0840 0845-0878 (3) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 1 5

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# @A300-600 SERVICE BULLETIN
OPERATOR MSN 06P 0788 67Q 0584 0603 0744 0749 0764 ABR 0677 0743 AHK 0683 0770 0855 0856 0857 0858 0859 0860 0870 0871 BCS 0529 0557 0602 0617 0621 0637 0641 0670 0679 0703 0711 0724 0729 0730 0737 0740 0753 0783 0797 0836 0837 0872 F2I 0294 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 IRA 0632 0696 0723 0727 IRM 0380 0401 0405 0408 0411 0414 0546 0553 0608 0618 0623 0701 0773 0838 KAC 0344 0673 0694 0699 0719 0721 MNB 0521 0525 0532 0734 0739 0755 0756 0758 MRJ 0750 0762 MSR 0561 0607 OHY 0747 SUD 0666 0775 TAR 0505 0558 0563 THA 0629 0782 0784 0785 0786 0787 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 0845 0846 0847 0848 0849 0850 0851 0852 0853 0854 0861 0862 0863 0864 0865 0866 0867 0868 0869 UQA 0626 0643 URS 0733 UTP 0707 0725 0732 0741 0746 0754 0763 UZB 0717 0722

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 2 5

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# @A300-600 SERVICE BULLETIN (4) Configuration by MSN MSN CONFIGURATION 0294 0344 0358 0361 0365 0380 0388 0401 0405 0408 0411 0414 0417 0477 0479 0505 0521 0525 0529 0530 0532 0536 0543 0546 0553 0555 0557 0558 0559 0561 0563 0572 0575 0579 0581 0584 0602 0603 0607 0608 0611 0613 0617 0618 0621 0623 0625 0626 0629 0630 0632 0633 0637 0641 0643 0657 0659 0664 0666 0668 0670 0673 0677 0679 0683 0688 0694 0696 0699 0701 0703 0707 0709 0711 0713 0715 0717 0719 0721 0722 0723 0724 0725 0726 0727 0728 0729 0730 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 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 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 001 002 003 004

(5) Configuration definition NOTE : Each Frame Foot is independent, operator must define which repair has been applied or not on each frame foot and choose the configuration defined below that applies for each frame foot. **CONF 001 Config. 001 is valid for Frame foot never repaired (either already inspected as per Service Bulletin No. A300-53-6111 or not). **CONF 002 Config. 002 is valid for Frame foot preventively repaired (no crack) as per Service Bulletin No. A300-53-6111. **CONF 003 Config. 003 is valid for Frame foot repaired in Area 1 as per Service Bulletin No. A300-53-6111 or as per R53810322 or R53810323 or R53810329 or R53810330 or R53810331 or R53810332. **CONF 004 Config. 004 is valid for Frame foot in any other situation (not covered by Config. 001, Config. 002 or Config. 003).

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 3 5

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# @A300-600 SERVICE BULLETIN (6) Material Effectivity **CONF 003 MATERIAL QTY PER A/C SEE NOTES Consumable CMLA01 1 Component COMPA01 2 Component COMPA02 4 Component COMPA03 2 Component COMPA04 2 Component COMPA05 2 Kit 536177A01R00 1 Kit 536177A04R00 1 Kit 536177A07R00 1 Kit 536177A10R00 1 Kit 536177A13R00 1 Kit 536177A16R00 1 Kit 536177A19R00 1 Kit 536177A22R00 1 Kit 536177A25R00 1 Kit 536177A28R00 1 Kit 536177A31R00 1 Kit 536177A34R00 1 **CONF 002 MATERIAL QTY PER A/C SEE NOTES Consumable CMLA01 1 Component COMPA01 2 Component COMPA02 4 Component COMPA03 2 Component COMPA04 2 Component COMPA05 2 Kit 536177A02R00 1 Kit 536177A05R00 1 Kit 536177A08R00 1 Kit 536177A11R00 1 Kit 536177A14R00 1 Kit 536177A17R00 1 Kit 536177A20R00 1 Kit 536177A23R00 1 Kit 536177A26R00 1 Kit 536177A29R00 1 Kit 536177A32R00 1 Kit 536177A35R00 1

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 4 5

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# @A300-600 SERVICE BULLETIN
**CONF 001 MATERIAL QTY PER A/C SEE NOTES Consumable CMLA01 1 Component COMPA01 2 Component COMPA02 4 Component COMPA03 2 Component COMPA04 2 Component COMPA05 2 Kit 536177A03R00 1 Kit 536177A06R00 1 Kit 536177A09R00 1 Kit 536177A12R00 1 Kit 536177A15R00 1 Kit 536177A18R00 1 Kit 536177A21R00 1 Kit 536177A24R00 1 Kit 536177A27R00 1 Kit 536177A30R00 1 Kit 536177A33R00 1 Kit 536177A36R00 1 **CONF 004 No Material Set **CONF ALL B. CONCURRENT REQUIREMENTS None C. REASON (1) History During a routine maintenance on A300-600 aircraft, operators have reported separate instances of cracks in the Frame feet fittings, connecting the Frame lower positions to the centre wing box (air conditioning bay). Since this time, AIRBUS has carried out a sampling inspection program on both aircraft types (A300 and A300-600). During this sampling program, twenty three A300-600 aircraft were inspected and cracks were found on the lower Frame fittings of Frame 44 to Frame 46 (LH and RH) on twenty two of the inspected aircraft. The aircraft with the findings have accumulated between 8000 and 21000 Flight Cycles (FC) and the lengths of the cracks varied between 12 mm and 18 mm (0.472 in. and 0.709 in.).

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 5 5

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# @A300-600 SERVICE BULLETIN Service Bulletin No. A300-53-6111 was created in order to treat the affected areas by repetitive inspection and also repair in case of crack finding. Repaired Frames were no longer inspected up to aircraft Limit of Validity (LoV). Further to new findings on repaired Frame feet, a new detailed Finite Element Model (FEM) study was performed. Outcomes of this study led Airbus to review the inspection program. (2) Objective/Action The aim of the Service Bulletin, depending of the accomplishment of Service Bulletin No. A300-53-6111, is to perform a Detailed Inspection (DET) of the lower Frame feet fittings between Frame 41 and Frame 46 for the entire fleet. In case of crack finding, two options are possible: - The cracked Frame foot is replaced by an identical new one and the Inspection Service Bulletin (ISB) No. A300-53-6177 is still applicable. - All Frame feet are replaced by new optimized parts as per Modification Service Bulletin No. A300-53-6176 (Mod. No. 13721S22901). In this case, no further inspection is necessary. Any findings (including Nil findings) are to be reported to AIRBUS. Service Bulletin No. A300-53-6111 is therefore cancelled and superseded by this new ISB. In addition to this new inspection program, Airbus designed new Frame feet. Their installation is proposed through a dedicated modification Service Bulletin No. A300-53-6176. Accomplishment of Modification Service Bulletin No. A300-53-6176 cancels the requirements of this ISB. (3) Advantages Accomplishment of this ISB will allow early detection of cracks in order to avoid possible occurrence of crack propagation which can lead to costly and time-consuming repairs. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 536177-832-801-001: Detailed Inspection of the Frame foot (1) Do a Detailed Inspection of the Frame Foot at FR41 on LH Side (2) Do a Detailed Inspection of the Frame Foot at FR41 on RH Side (3) Do a Detailed Inspection of the Frame Foot at FR42 on LH Side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 6 5

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# @A300-600 SERVICE BULLETIN (4) Do a Detailed Inspection of the Frame Foot at FR42 on RH Side (5) Do a Detailed Inspection of the Frame Foot at FR43 on LH Side (6) Do a Detailed Inspection of the Frame Foot at FR43 on RH Side (7) Do a Detailed Inspection of the Frame Foot at FR44 on LH Side (8) Do a Detailed Inspection of the Frame Foot at FR44 on RH Side (9) Do a Detailed Inspection of the Frame Foot at FR45 on LH Side (10) Do a Detailed Inspection of the Frame Foot at FR45 on RH Side (11) Do a Detailed Inspection of the Frame Foot at FR46 on LH Side (12) Do a Detailed Inspection of the Frame Foot at FR46 on RH Side Task 536177-833-801-001: Repair (1) Depending on Inspection results, if necessary, remove the Fasteners from FR41, LH side (2) Depending on Inspection results, remove the Gussets from FR41, LH side (3) Depending on Inspection results, remove the Frame Foot from FR41, LH side (4) Depending on Inspection results, install an identical Frame Foot at FR41, LH side (5) Depending on Inspection results, if removed, install the Fasteners at FR41, LH side (6) Depending on Inspection results, if necessary, remove the Fasteners from FR41, RH side (7) Depending on Inspection results, remove the Gussets from FR41, RH side (8) Depending on Inspection results, remove the Frame Foot from FR41, RH side (9) Depending on Inspection results, install an identical Frame Foot at FR41, RH side (10) Depending on Inspection results, if removed, install the Fasteners at FR41, RH side (11) Depending on Inspection results, if necessary, remove the Fasteners from FR42, LH side (12) Depending on Inspection results, remove the Gussets from FR42, LH side (13) Depending on Inspection results, remove the Frame Foot from FR42, LH side (14) Depending on Inspection results, install an identical Frame Foot at FR42, LH side (15) Depending on Inspection results, if removed, install the Fasteners at FR42, LH side (16) Depending on Inspection results, if necessary, remove the Fasteners from FR42, DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 7 5

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# @A300-600 SERVICE BULLETIN
RH side (17) Depending on Inspection results, remove the Gussets from FR42, RH side (18) Depending on Inspection results, remove the Frame Foot from FR42, RH side (19) Depending on Inspection results, install an identical Frame Foot at FR42, RH side (20) Depending on Inspection results, if removed, install the Fasteners at FR42, RH side (21) Depending on Inspection results, if necessary, remove the Fasteners from FR43, LH side (22) Depending on Inspection results, remove the Gussets from FR43, LH side (23) Depending on Inspection results, remove the Frame Foot from FR43, LH side (24) Depending on Inspection results, install an identical Frame Foot at FR43, LH side (25) Depending on Inspection results, if removed, install the Fasteners at FR43, LH side (26) Depending on Inspection results, if necessary, remove the Fasteners from FR43, RH side (27) Depending on Inspection results, remove the Gussets from FR43, RH side (28) Depending on Inspection results, remove the Frame Foot from FR43, RH side (29) Depending on Inspection results, install an identical Frame Foot at FR43, RH side (30) Depending on Inspection results, if removed, install the Fasteners at FR43, RH side (31) Depending on Inspection results, if necessary, remove the Fasteners from FR44, LH side (32) Depending on Inspection results, remove the Gussets from FR44, LH side (33) Depending on Inspection results, remove the Frame Foot from FR44, LH side (34) Depending on Inspection results, install an identical Frame Foot at FR44, LH side (35) Depending on Inspection results, if removed, install the Fasteners at FR44, LH side (36) Depending on Inspection results, if necessary, remove the Fasteners from FR44, RH side (37) Depending on Inspection results, remove the Gussets from FR44, RH side (38) Depending on Inspection results, remove the Frame Foot from FR44, RH side (39) Depending on Inspection results, install an identical Frame Foot at FR44, RH side (40) Depending on Inspection results, if removed, install the Fasteners at FR44, RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 8 5

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# @A300-600 SERVICE BULLETIN (41) Depending on Inspection results, if necessary, remove the Fasteners from FR45, LH side (42) Depending on Inspection results, remove the Gussets from FR45, LH side (43) Depending on Inspection results, remove the Frame Foot from FR45, LH side (44) Depending on Inspection results, install an identical Frame Foot at FR45, LH side (45) Depending on Inspection results, if removed, install the Fasteners at FR45, LH side (46) Depending on Inspection results, if necessary, remove the Fasteners from FR45, RH side (47) Depending on Inspection results, remove the Gussets from FR45, RH side (48) Depending on Inspection results, remove the Frame Foot from FR45, RH side (49) Depending on Inspection results, install an identical Frame Foot at FR45, RH side (50) Depending on Inspection results, install the Fasteners at FR45, RH side (51) Depending on Inspection results, if necessary, remove the Fasteners from FR46, LH side (52) Depending on Inspection results, remove the Gussets from FR46, LH side (53) Depending on Inspection results, remove the Frame Foot from FR46, LH side (54) Depending on Inspection results, install an identical Frame Foot at FR46, LH side (55) Depending on Inspection results, if removed, install the Fasteners at FR46, LH side (56) Depending on Inspection results, if necessary, remove the Fasteners from FR46, RH side (57) Depending on Inspection results, remove the Gussets from FR46, RH side (58) Depending on Inspection results, remove the Frame Foot from FR46, RH side (59) Depending on Inspection results, install an identical Frame Foot at FR46, RH side (60) Depending on Inspection results, install the Fasteners at FR46, RH side **CONF 002 Task 536177-832-801-001: Detailed Inspection of the Frame foot (1) Do a Detailed Inspection of the Frame Foot at FR41 on LH Side (2) Do a Detailed Inspection of the Frame Foot at FR41 on RH Side (3) Do a Detailed Inspection of the Frame Foot at FR42 on LH Side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 9 5

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# @A300-600 SERVICE BULLETIN (4) Do a Detailed Inspection of the Frame Foot at FR42 on RH Side (5) Do a Detailed Inspection of the Frame Foot at FR43 on LH Side (6) Do a Detailed Inspection of the Frame Foot at FR43 on RH Side (7) Do a Detailed Inspection of the Frame Foot at FR44 on LH Side (8) Do a Detailed Inspection of the Frame Foot at FR44 on RH Side (9) Do a Detailed Inspection of the Frame Foot at FR45 on LH Side (10) Do a Detailed Inspection of the Frame Foot at FR45 on RH Side (11) Do a Detailed Inspection of the Frame Foot at FR46 on LH Side (12) Do a Detailed Inspection of the Frame Foot at FR46 on RH Side Task 536177-833-801-001: Repair (1) Depending on Inspection results, if necessary, remove the Fasteners from FR41, LH side (2) Depending on Inspection results, remove the Gussets from FR41, LH side (3) Depending on Inspection results, remove the Frame Foot from FR41, LH side (4) Depending on Inspection results, install an identical Frame Foot at FR41, LH side (5) Depending on Inspection results, if removed, install the Fasteners at FR41, LH side (6) Depending on Inspection results, if necessary, remove the Fasteners from FR41, RH side (7) Depending on Inspection results, remove the Gussets from FR41, RH side (8) Depending on Inspection results, remove the Frame Foot from FR41, RH side (9) Depending on Inspection results, install an identical Frame Foot at FR41, RH side (10) Depending on Inspection results, if removed, install the Fasteners at FR41, RH side (11) Depending on Inspection results, if necessary, remove the Fasteners from FR42, LH side (12) Depending on Inspection results, remove the Gussets from FR42, LH side (13) Depending on Inspection results, remove the Frame Foot from FR42, LH side (14) Depending on Inspection results, install an identical Frame Foot at FR42, LH side (15) Depending on Inspection results, if removed, install the Fasteners at FR42, LH side (16) Depending on Inspection results, if necessary, remove the Fasteners from FR42, DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 10 5

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# @A300-600 SERVICE BULLETIN
RH side (17) Depending on Inspection results, remove the Gussets from FR42, RH side (18) Depending on Inspection results, remove the Frame Foot from FR42, RH side (19) Depending on Inspection results, install an identical Frame Foot at FR42, RH side (20) Depending on Inspection results, if removed, install the Fasteners at FR42, RH side (21) Depending on Inspection results, if necessary, remove the Fasteners from FR43, LH side (22) Depending on Inspection results, remove the Gussets from FR43, LH side (23) Depending on Inspection results, remove the Frame Foot from FR43, LH side (24) Depending on Inspection results, install an identical Frame Foot at FR43, LH side (25) Depending on Inspection results, if removed, install the Fasteners at FR43, LH side (26) Depending on Inspection results, if necessary, remove the Fasteners from FR43, RH side (27) Depending on Inspection results, remove the Gussets from FR43, RH side (28) Depending on Inspection results, remove the Frame Foot from FR43, RH side (29) Depending on Inspection results, install an identical Frame Foot at FR43, RH side (30) Depending on Inspection results, if removed, install the Fasteners at FR43, RH side (31) Depending on Inspection results, if necessary, remove the Fasteners from FR44, LH side (32) Depending on Inspection results, remove the Gussets from FR44, LH side (33) Depending on Inspection results, remove the Frame Foot from FR44, LH side (34) Depending on Inspection results, install an identical Frame Foot at FR44, LH side (35) Depending on Inspection results, if removed, install the Fasteners at FR44, LH side (36) Depending on Inspection results, if necessary, remove the Fasteners from FR44, RH side (37) Depending on Inspection results, remove the Gussets from FR44, RH side (38) Depending on Inspection results, remove the Frame Foot from FR44, RH side (39) Depending on Inspection results, install an identical Frame Foot at FR44, RH side (40) Depending on Inspection results, if removed, install the Fasteners at FR44, RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 11 5

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# @A300-600 SERVICE BULLETIN (41) Depending on Inspection results, if necessary, remove the Fasteners from FR45, LH side (42) Depending on Inspection results, remove the Gussets from FR45, LH side (43) Depending on Inspection results, remove the Frame Foot from FR45, LH side (44) Depending on Inspection results, install an identical Frame Foot at FR45, LH side (45) Depending on Inspection results, if removed, install the Fasteners at FR45, LH side (46) Depending on Inspection results, if necessary, remove the Fasteners from FR45, RH side (47) Depending on Inspection results, remove the Gussets from FR45, RH side (48) Depending on Inspection results, remove the Frame Foot from FR45, RH side (49) Depending on Inspection results, install an identical Frame Foot at FR45, RH side (50) Depending on Inspection results, install the Fasteners at FR45, RH side (51) Depending on Inspection results, if necessary, remove the Fasteners from FR46, LH side (52) Depending on Inspection results, remove the Gussets from FR46, LH side (53) Depending on Inspection results, remove the Frame Foot from FR46, LH side (54) Depending on Inspection results, install an identical Frame Foot at FR46, LH side (55) Depending on Inspection results, if removed, install the Fasteners at FR46, LH side (56) Depending on Inspection results, if necessary, remove the Fasteners from FR46, RH side (57) Depending on Inspection results, remove the Gussets from FR46, RH side (58) Depending on Inspection results, remove the Frame Foot from FR46, RH side (59) Depending on Inspection results, install an identical Frame Foot at FR46, RH side (60) Depending on Inspection results, install the Fasteners at FR46, RH side **CONF 003 Task 536177-832-801-001: Detailed Inspection of the Frame foot (1) Do a Detailed Inspection of the Frame Foot at FR41 on LH Side (2) Do a Detailed Inspection of the Frame Foot at FR41 on RH Side (3) Do a Detailed Inspection of the Frame Foot at FR42 on LH Side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 12 5

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# @A300-600 SERVICE BULLETIN (4) Do a Detailed Inspection of the Frame Foot at FR42 on RH Side (5) Do a Detailed Inspection of the Frame Foot at FR43 on LH Side (6) Do a Detailed Inspection of the Frame Foot at FR43 on RH Side (7) Do a Detailed Inspection of the Frame Foot at FR44 on LH Side (8) Do a Detailed Inspection of the Frame Foot at FR44 on RH Side (9) Do a Detailed Inspection of the Frame Foot at FR45 on LH Side (10) Do a Detailed Inspection of the Frame Foot at FR45 on RH Side (11) Do a Detailed Inspection of the Frame Foot at FR46 on LH Side (12) Do a Detailed Inspection of the Frame Foot at FR46 on RH Side Task 536177-833-801-001: Repair (1) Depending on Inspection results, if necessary, remove the Fasteners from FR41, LH side (2) Depending on Inspection results, remove the Gussets from FR41, LH side (3) Depending on Inspection results, remove the Frame Foot from FR41, LH side (4) Depending on Inspection results, install an identical Frame Foot at FR41, LH side (5) Depending on Inspection results, if removed, install the Fasteners at FR41, LH side (6) Depending on Inspection results, if necessary, remove the Fasteners from FR41, RH side (7) Depending on Inspection results, remove the Gussets from FR41, RH side (8) Depending on Inspection results, remove the Frame Foot from FR41, RH side (9) Depending on Inspection results, install an identical Frame Foot at FR41, RH side (10) Depending on Inspection results, if removed, install the Fasteners at FR41, RH side (11) Depending on Inspection results, if necessary, remove the Fasteners from FR42, LH side (12) Depending on Inspection results, remove the Gussets from FR42, LH side (13) Depending on Inspection results, remove the Frame Foot from FR42, LH side (14) Depending on Inspection results, install an identical Frame Foot at FR42, LH side (15) Depending on Inspection results, if removed, install the Fasteners at FR42, LH side (16) Depending on Inspection results, if necessary, remove the Fasteners from FR42, DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 13 5

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# @A300-600 SERVICE BULLETIN
RH side (17) Depending on Inspection results, remove the Gussets from FR42, RH side (18) Depending on Inspection results, remove the Frame Foot from FR42, RH side (19) Depending on Inspection results, install an identical Frame Foot at FR42, RH side (20) Depending on Inspection results, if removed, install the Fasteners at FR42, RH side (21) Depending on Inspection results, if necessary, remove the Fasteners from FR43, LH side (22) Depending on Inspection results, remove the Gussets from FR43, LH side (23) Depending on Inspection results, remove the Frame Foot from FR43, LH side (24) Depending on Inspection results, install an identical Frame Foot at FR43, LH side (25) Depending on Inspection results, if removed, install the Fasteners at FR43, LH side (26) Depending on Inspection results, if necessary, remove the Fasteners from FR43, RH side (27) Depending on Inspection results, remove the Gussets from FR43, RH side (28) Depending on Inspection results, remove the Frame Foot from FR43, RH side (29) Depending on Inspection results, install an identical Frame Foot at FR43, RH side (30) Depending on Inspection results, if removed, install the Fasteners at FR43, RH side (31) Depending on Inspection results, if necessary, remove the Fasteners from FR44, LH side (32) Depending on Inspection results, remove the Gussets from FR44, LH side (33) Depending on Inspection results, remove the Frame Foot from FR44, LH side (34) Depending on Inspection results, install an identical Frame Foot at FR44, LH side (35) Depending on Inspection results, if removed, install the Fasteners at FR44, LH side (36) Depending on Inspection results, if necessary, remove the Fasteners from FR44, RH side (37) Depending on Inspection results, remove the Gussets from FR44, RH side (38) Depending on Inspection results, remove the Frame Foot from FR44, RH side (39) Depending on Inspection results, install an identical Frame Foot at FR44, RH side (40) Depending on Inspection results, if removed, install the Fasteners at FR44, RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 14 5

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# @A300-600 SERVICE BULLETIN (41) Depending on Inspection results, if necessary, remove the Fasteners from FR45, LH side (42) Depending on Inspection results, remove the Gussets from FR45, LH side (43) Depending on Inspection results, remove the Frame Foot from FR45, LH side (44) Depending on Inspection results, install an identical Frame Foot at FR45, LH side (45) Depending on Inspection results, if removed, install the Fasteners at FR45, LH side (46) Depending on Inspection results, if necessary, remove the Fasteners from FR45, RH side (47) Depending on Inspection results, remove the Gussets from FR45, RH side (48) Depending on Inspection results, remove the Frame Foot from FR45, RH side (49) Depending on Inspection results, install an identical Frame Foot at FR45, RH side (50) Depending on Inspection results, install the Fasteners at FR45, RH side (51) Depending on Inspection results, if necessary, remove the Fasteners from FR46, LH side (52) Depending on Inspection results, remove the Gussets from FR46, LH side (53) Depending on Inspection results, remove the Frame Foot from FR46, LH side (54) Depending on Inspection results, install an identical Frame Foot at FR46, LH side (55) Depending on Inspection results, if removed, install the Fasteners at FR46, LH side (56) Depending on Inspection results, if necessary, remove the Fasteners from FR46, RH side (57) Depending on Inspection results, remove the Gussets from FR46, RH side (58) Depending on Inspection results, remove the Frame Foot from FR46, RH side (59) Depending on Inspection results, install an identical Frame Foot at FR46, RH side (60) Depending on Inspection results, install the Fasteners at FR46, RH side **CONF 004 Task 536177-839-801-001: Contact and Report to AIRBUS (1) Contact and Report to AIRBUS

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 15 5

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# @A300-600 SERVICE BULLETIN
**CONF ALL E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale 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 intervals given but reference should be made to the AD for confirmation of the mandated accomplishment timescale.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 16 5

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# @A300-600 SERVICE BULLETIN Table 1, Config. 001 - Detailed Inspection of the Frame foot Compliance time (Whichever occurs later) Condition Action Threshold (Whichever occurs first) Grace period (Whichever occurs first) Repetitive interval (Whichever occurs first) Frame foot not inspected as per Service Bulletin No. A300-53-6111 - For aircraft (A/C) with Average Flight Time (AFT) higher than 1.5 hours: 5000 Flight Cycles (FC) / 10800 Flight Hours (FH) - For A/C with

AFT lower or equal to 1.5 hours: 5400 FC / 8100 FH 1000 FC from issuance of revision 04 of Service Bulletin No. A300-53-6111 None All Frame feet

Frame foot inspected as per Service Bulletin No. A300-53-6111 with nil finding and thus not repaired Do a detailed inspection of the area 1 and the area 2 of the Frame foot in accordance with TASK 536177-832-801 001

- For A/C with AFT higher than 1.5 hours: 3200 FC / 7000 FH from last inspection as per Service Bulletin No. A300-53-6111 - For A/C with

AFT lower or equal to 1.5 hours: 3500 FC / 5300 FH from last inspection as per Service Bulletin No. A300-53-6111 None None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 17 5

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# @A300-600 SERVICE BULLETIN Table 1, Config. 001 - Detailed Inspection of the Frame foot Compliance time (Whichever occurs later) Condition Action Threshold (Whichever occurs first) Grace period (Whichever occurs first) Repetitive interval (Whichever occurs first) Apply Service Bulletin No. A300-53-6176 See NOTE (**) And Before next flight None None

Send inspection report to AIRBUS And 1 month from inspection date None None

No further action None None None OR Replace the cracked Frame foot by a new identical one in accordance with TASK 536177-833-801 001 And Before next flight None None

Send inspection report to AIRBUS And 1 month from inspection date None None Crack found in area 1 or area 2 See NOTE (*)

Repeat the inspection of the replaced Frame foot in accordance with TASK 536177-832-801 001 - For A/C with AFT higher than 1.5 hours: 5000 FC / 10800 FH from Frame foot replacement - For A/C with

AFT lower or equal to 1.5 hours: 5400 FC / 8100 FH from Frame foot replacement None - For A/C with AFT higher than 1.5 hours: 3200 FC / 7000 FH from Frame foot replacement - For A/C with

AFT lower or equal to 1.5 hours: 3500 FC / 5300 FH from Frame foot replacement

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 18 5

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# @A300-600 SERVICE BULLETIN Table 1, Config. 001 - Detailed Inspection of the Frame foot Compliance time (Whichever occurs later) Condition Action Threshold (Whichever occurs first) Grace period (Whichever occurs first) Repetitive interval (Whichever occurs first) Apply Service Bulletin No. A300-53-6176 See NOTE (**) And Before next flight None None

Send inspection report to AIRBUS And 1 month from inspection date None None

No further action None None None OR Send inspection report to AIRBUS And 1 month from inspection date None None No crack found in area 1 nor in area 2

Repeat the inspection of the Frame foot in accordance with TASK 536177-832-801 001 None None - For A/C with AFT higher than 1.5 hours: 3200 FC / 7000 FH - For A/C with

AFT lower or equal to 1.5 hours: 3500 FC / 5300 FH NOTE (*): If a crack is longer than 30 mm (1.181 in.), inform AIRBUS and send the affected Frame foot for laboratory investigation NOTE (**): The accomplishment of the Service Bulletin No. A300-53-6176 consists in replacing all the Frame feet (between Frame 41 and Frame 46, LH and RH sides) of the aircraft with optimized Frame feet.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 19 5

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# @A300-600 SERVICE BULLETIN Table 2, Config. 002 - Detailed Inspection of the Frame foot Compliance time (Whichever occurs later) Condition Action Threshold (Whichever occurs first) Grace period (Whichever occurs first) Repetitive interval (Whichever occurs first)

All Frame feet Do a detailed inspection of the area 1 and the area 2 of the Frame foot in accordance with TASK 536177-832-801 001 - For aircraft (A/C) with AFT higher than 1.5 hours: 3200 FC / 7000 FH from Frame foot repair embodiment - For A/C with AFT

lower or equal to 1.5 hours: 3500 FC / 5300 FH from Frame foot repair embodiment 1000 FC from issuance of Service Bulletin No. A300-53-6177 None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 20 5

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# @A300-600 SERVICE BULLETIN Table 2, Config. 002 - Detailed Inspection of the Frame foot Compliance time (Whichever occurs later) Condition Action Threshold (Whichever occurs first) Grace period (Whichever occurs first) Repetitive interval (Whichever occurs first)
Apply Service Bulletin No. A300-53-6176 See NOTE (**) And Before next flight None None

Send inspection report to AIRBUS And 1 month from inspection date None None
No further action None None None OR Replace the cracked Frame foot by a new identical one and do the cutting-out in accordance with TASK 536177-833-801 001 And Before next flight None None

Send inspection report to AIRBUS And 1 month from inspection date None None Crack found in area 1 or area 2 See NOTE (*)

Repeat the inspection of the replaced Frame foot in accordance with TASK 536177-832-801 001 - For A/C with AFT higher than 1.5 hours: 5000 FC / 10800 FH from Frame foot replacement - For A/C with AFT

lower or equal to 1.5 hours: 5400 FC / 8100 FH from Frame foot replacement None - For A/C with AFT higher than 1.5 hours: 3200 FC / 7000 FH from Frame foot replacement - For A/C with AFT

lower or equal to 1.5 hours: 3500 FC / 5300 FH from Frame foot replacement

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 21 5

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# @A300-600 SERVICE BULLETIN Table 2, Config. 002 - Detailed Inspection of the Frame foot Compliance time (Whichever occurs later) Condition Action Threshold (Whichever occurs first) Grace period (Whichever occurs first) Repetitive interval (Whichever occurs first)
Apply Service Bulletin No. A300-53-6176 See NOTE (**) And Before next flight None None

Send inspection report to AIRBUS And 1 month from inspection date None None
No further action None None None OR Send inspection report to AIRBUS And 1 month from inspection date None None No crack found in area 1 nor in area 2

Repeat the inspection of the Frame foot in accordance with TASK 536177-832-801 001 None None - For A/C with AFT higher than 1.5 hours: 3200 FC / 7000 FH - For A/C with AFT

lower or equal to 1.5 hours: 3500 FC / 5300 FH NOTE (*): If a crack is longer than 30 mm (1.181 in.), inform AIRBUS and send the affected Frame foot for laboratory investigation NOTE (**): The accomplishment of the Service Bulletin No. A300-53-6176 consists in replacing all the Frame feet (between Frame 41 and Frame 46, LH and RH sides) of the aircraft with optimized Frame feet.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 22 5

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# @A300-600 SERVICE BULLETIN Table 3, Config. 003 - Detailed Inspection of the Frame foot Compliance time (Whichever occurs later) Condition Action Threshold (Whichever occurs first) Grace period (Whichever occurs first) Repetitive interval (Whichever occurs first)

All Frame feet Do a detailed inspection of the area 2 of the Frame foot in accordance with TASK 536177-832-801 001 - For aircraft (A/C) with AFT higher than 1.5 hours: 3200 FC / 7000 FH from Frame foot repair embodiment - For A/C with AFT

lower or equal to 1.5 hours: 3500 FC / 5300 FH from Frame foot repair embodiment 1000 FC from issuance of Service Bulletin No. A300-53-6177 None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 23 5

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# @A300-600 SERVICE BULLETIN Table 3, Config. 003 - Detailed Inspection of the Frame foot Compliance time (Whichever occurs later) Condition Action Threshold (Whichever occurs first) Grace period (Whichever occurs first) Repetitive interval (Whichever occurs first)
Apply Service Bulletin No. A300-53-6176 See NOTE (**) And Before next flight None None

Send inspection report to AIRBUS And 1 month from inspection date None None
No further action None None None OR Replace the cracked Frame foot by a new identical one and do the cutting-out in accordance with TASK 536177-833-801 001 And Before next flight None None

Send inspection report to AIRBUS And 1 month from inspection date None None Crack found in area 2 See NOTE (*)

Repeat the inspection of the replaced Frame foot, in accordance with TASK 536177-832-801 001 - For A/C with AFT higher than 1.5 hours: 5000 FC / 10800 FH from Frame foot replacement - For A/C with AFT

lower or equal to 1.5 hours: 5400 FC / 8100 FH from Frame foot replacement None - For A/C with AFT higher than 1.5 hours: 3200 FC / 7000 FH from Frame foot replacement - For A/C with AFT

lower or equal to 1.5 hours: 3500 FC / 5300 FH from Frame foot replacement

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 24 5

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# @A300-600 SERVICE BULLETIN Table 3, Config. 003 - Detailed Inspection of the Frame foot Compliance time (Whichever occurs later) Condition Action Threshold (Whichever occurs first) Grace period (Whichever occurs first) Repetitive interval (Whichever occurs first)
Apply Service Bulletin No. A300-53-6176 See NOTE (**) And Before next flight None None

Send inspection report to AIRBUS And 1 month from inspection date None None
No further action None None None OR Send inspection report to AIRBUS And 1 month from inspection date None None No crack found in area 2

Repeat the inspection of the Frame foot in accordance with TASK 536177-832-801 001 None None - For A/C with AFT higher than 1.5 hours: 3200 FC / 7000 FH - For A/C with AFT

lower or equal to 1.5 hours: 3500 FC / 5300 FH NOTE (*): If a crack is longer than 30 mm (1.181 in.), inform AIRBUS and send the affected Frame foot for laboratory investigation NOTE (**): The accomplishment of the Service Bulletin No. A300-53-6176 consists in replacing all the Frame feet (between Frame 41 and Frame 46, LH and RH sides) of the aircraft with optimized Frame feet. Table 4, Config. 004 - Contact and Report to AIRBUS Compliance time (Whichever occurs later) Condition Action Threshold (Whichever occurs first) Grace period (Whichever occurs first) Repetitive interval (Whichever occurs first)

All Frame feet Contact and report to AIRBUS in accordance with TASK 536177-839-801 001 6 months from this Service Bulletin issuance None None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 25 5

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# @A300-600 SERVICE BULLETIN
F. APPROVAL The technical content of this document is approved under the authority of Design Organisation Approval No. EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. **CONF 001 Task 536177-832-801-001: Detailed Inspection of the Frame foot Get Access 1.00 On Aircraft Do a Detailed Inspection of the Frame Foot at FR41 on LH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR41 on RH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR42 on LH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR42 on RH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR43 on LH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR43 on RH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR44 on LH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR44 on RH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR45 on LH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR45 on RH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR46 on LH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR46 on RH Side 0.50 Close-Up 1.00 TOTAL MANHOURS 8.00 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 26 5

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# @A300-600 SERVICE BULLETIN Task 536177-832-801-001: Detailed Inspection of the Frame foot ELAPSED TIME (HOURS) 2.50 Task 536177-833-801-001: Repair Get Access 12.00 On Aircraft Depending on Inspection results, if necessary, remove the Fasteners from FR41, LH side 4.00 Depending on Inspection results, remove the Gussets from FR41, LH side 1.00 Depending on Inspection results, remove the Frame Foot from FR41, LH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR41, LH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR41, LH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR41, RH side 4.00 Depending on Inspection results, remove the Gussets from FR41, RH side 1.00 Depending on Inspection results, remove the Frame Foot from FR41, RH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR41, RH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR41, RH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR42, LH side 4.00 Depending on Inspection results, remove the Gussets from FR42, LH side 1.00 Depending on Inspection results, remove the Frame Foot from FR42, LH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR42, LH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR42, LH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR42, RH side 4.00 Depending on Inspection results, remove the Gussets from FR42, RH side 1.00 Depending on Inspection results, remove the Frame Foot from FR42, RH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR42, RH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR42, RH side 6.00

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 27 5

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# @A300-600 SERVICE BULLETIN Task 536177-833-801-001: Repair Depending on Inspection results, if necessary, remove the Fasteners from FR43, LH side 4.00 Depending on Inspection results, remove the Gussets from FR43, LH side 1.00 Depending on Inspection results, remove the Frame Foot from FR43, LH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR43, LH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR43, LH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR43, RH side 4.00 Depending on Inspection results, remove the Gussets from FR43, RH side 1.00 Depending on Inspection results, remove the Frame Foot from FR43, RH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR43, RH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR43, RH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR44, LH side 4.00 Depending on Inspection results, remove the Gussets from FR44, LH side 1.00 Depending on Inspection results, remove the Frame Foot from FR44, LH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR44, LH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR44, LH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR44, RH side 4.00 Depending on Inspection results, remove the Gussets from FR44, RH side 1.00 Depending on Inspection results, remove the Frame Foot from FR44, RH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR44, RH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR44, RH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR45, LH side 4.00 Depending on Inspection results, remove the Gussets from FR45, LH side 1.00 Depending on Inspection results, remove the Frame Foot from FR45, LH side 16.00
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 28 5

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

# @A300-600 SERVICE BULLETIN Task 536177-833-801-001: Repair Depending on Inspection results, install an identical Frame Foot at FR45, LH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR45, LH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR45, RH side 4.00 Depending on Inspection results, remove the Gussets from FR45, RH side 1.00 Depending on Inspection results, remove the Frame Foot from FR45, RH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR45, RH side 16.00 Depending on Inspection results, install the Fasteners at FR45, RH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR46, LH side 4.00 Depending on Inspection results, remove the Gussets from FR46, LH side 1.00 Depending on Inspection results, remove the Frame Foot from FR46, LH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR46, LH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR46, LH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR46, RH side 4.00 Depending on Inspection results, remove the Gussets from FR46, RH side 1.00 Depending on Inspection results, remove the Frame Foot from FR46, RH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR46, RH side 16.00 Depending on Inspection results, install the Fasteners at FR46, RH side 6.00 Close-Up 13.00 TOTAL MANHOURS 541.00 ELAPSED TIME (HOURS) 42.00 NOTE : For an explanation of the manhours and elapsed time, refer to the Gantt Chart, Fig. A-FAAAA given in Appendix 01 - Elapsed Time Assumptions . NOTE : The minimum manhours necessary to accomplish this Service Bulletin are those for the Inspection. Depending on the inspection result, additional manhours can apply.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 29 5

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

# @A300-600 SERVICE BULLETIN
**CONF 002 Task 536177-832-801-001: Detailed Inspection of the Frame foot Get Access 1.00 On Aircraft Do a Detailed Inspection of the Frame Foot at FR41 on LH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR41 on RH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR42 on LH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR42 on RH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR43 on LH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR43 on RH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR44 on LH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR44 on RH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR45 on LH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR45 on RH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR46 on LH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR46 on RH Side 0.50 Close-Up 1.00 TOTAL MANHOURS 8.00 ELAPSED TIME (HOURS) 2.50 Task 536177-833-801-001: Repair Get Access 12.00 On Aircraft Depending on Inspection results, if necessary, remove the Fasteners from FR41, LH side 4.00 Depending on Inspection results, remove the Gussets from FR41, LH side 1.00 Depending on Inspection results, remove the Frame Foot from FR41, LH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR41, LH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR41, LH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR41, RH side 4.00
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 30 5

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

# @A300-600 SERVICE BULLETIN Task 536177-833-801-001: Repair Depending on Inspection results, remove the Gussets from FR41, RH side 1.00 Depending on Inspection results, remove the Frame Foot from FR41, RH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR41, RH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR41, RH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR42, LH side 4.00 Depending on Inspection results, remove the Gussets from FR42, LH side 1.00 Depending on Inspection results, remove the Frame Foot from FR42, LH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR42, LH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR42, LH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR42, RH side 4.00 Depending on Inspection results, remove the Gussets from FR42, RH side 1.00 Depending on Inspection results, remove the Frame Foot from FR42, RH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR42, RH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR42, RH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR43, LH side 4.00 Depending on Inspection results, remove the Gussets from FR43, LH side 1.00 Depending on Inspection results, remove the Frame Foot from FR43, LH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR43, LH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR43, LH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR43, RH side 4.00 Depending on Inspection results, remove the Gussets from FR43, RH side 1.00 Depending on Inspection results, remove the Frame Foot from FR43, RH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR43, RH side 16.00
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 31 5

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

# @A300-600 SERVICE BULLETIN Task 536177-833-801-001: Repair Depending on Inspection results, if removed, install the Fasteners at FR43, RH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR44, LH side 4.00 Depending on Inspection results, remove the Gussets from FR44, LH side 1.00 Depending on Inspection results, remove the Frame Foot from FR44, LH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR44, LH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR44, LH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR44, RH side 4.00 Depending on Inspection results, remove the Gussets from FR44, RH side 1.00 Depending on Inspection results, remove the Frame Foot from FR44, RH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR44, RH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR44, RH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR45, LH side 4.00 Depending on Inspection results, remove the Gussets from FR45, LH side 1.00 Depending on Inspection results, remove the Frame Foot from FR45, LH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR45, LH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR45, LH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR45, RH side 4.00 Depending on Inspection results, remove the Gussets from FR45, RH side 1.00 Depending on Inspection results, remove the Frame Foot from FR45, RH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR45, RH side 16.00 Depending on Inspection results, install the Fasteners at FR45, RH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR46, LH side 4.00 Depending on Inspection results, remove the Gussets from FR46, LH side 1.00
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 32 5

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

# @A300-600 SERVICE BULLETIN Task 536177-833-801-001: Repair Depending on Inspection results, remove the Frame Foot from FR46, LH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR46, LH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR46, LH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR46, RH side 4.00 Depending on Inspection results, remove the Gussets from FR46, RH side 1.00 Depending on Inspection results, remove the Frame Foot from FR46, RH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR46, RH side 16.00 Depending on Inspection results, install the Fasteners at FR46, RH side 6.00 Close-Up 13.00 TOTAL MANHOURS 541.00 ELAPSED TIME (HOURS) 42.00 NOTE : For an explanation of the manhours and elapsed time, refer to the Gantt Chart, Fig. A-FAAAA given in Appendix 01 - Elapsed Time Assumptions . NOTE : The minimum manhours necessary to accomplish this Service Bulletin are those for the Inspection. Depending on the inspection result, additional manhours can apply. **CONF 003 Task 536177-832-801-001: Detailed Inspection of the Frame foot Get Access 1.00 On Aircraft Do a Detailed Inspection of the Frame Foot at FR41 on LH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR41 on RH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR42 on LH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR42 on RH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR43 on LH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR43 on RH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR44 on LH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR44 on RH Side 0.50 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 33 5

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

# @A300-600 SERVICE BULLETIN Task 536177-832-801-001: Detailed Inspection of the Frame foot Do a Detailed Inspection of the Frame Foot at FR45 on LH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR45 on RH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR46 on LH Side 0.50 Do a Detailed Inspection of the Frame Foot at FR46 on RH Side 0.50 Close-Up 1.00 TOTAL MANHOURS 8.00 ELAPSED TIME (HOURS) 2.50 Task 536177-833-801-001: Repair Get Access 12.00 On Aircraft Depending on Inspection results, if necessary, remove the Fasteners from FR41, LH side 4.00 Depending on Inspection results, remove the Gussets from FR41, LH side 1.00 Depending on Inspection results, remove the Frame Foot from FR41, LH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR41, LH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR41, LH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR41, RH side 4.00 Depending on Inspection results, remove the Gussets from FR41, RH side 1.00 Depending on Inspection results, remove the Frame Foot from FR41, RH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR41, RH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR41, RH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR42, LH side 4.00 Depending on Inspection results, remove the Gussets from FR42, LH side 1.00 Depending on Inspection results, remove the Frame Foot from FR42, LH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR42, LH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR42, LH side 6.00

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 34 5

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

# @A300-600 SERVICE BULLETIN Task 536177-833-801-001: Repair Depending on Inspection results, if necessary, remove the Fasteners from FR42, RH side 4.00 Depending on Inspection results, remove the Gussets from FR42, RH side 1.00 Depending on Inspection results, remove the Frame Foot from FR42, RH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR42, RH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR42, RH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR43, LH side 4.00 Depending on Inspection results, remove the Gussets from FR43, LH side 1.00 Depending on Inspection results, remove the Frame Foot from FR43, LH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR43, LH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR43, LH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR43, RH side 4.00 Depending on Inspection results, remove the Gussets from FR43, RH side 1.00 Depending on Inspection results, remove the Frame Foot from FR43, RH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR43, RH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR43, RH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR44, LH side 4.00 Depending on Inspection results, remove the Gussets from FR44, LH side 1.00 Depending on Inspection results, remove the Frame Foot from FR44, LH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR44, LH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR44, LH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR44, RH side 4.00 Depending on Inspection results, remove the Gussets from FR44, RH side 1.00 Depending on Inspection results, remove the Frame Foot from FR44, RH side 16.00
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 35 5

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

# @A300-600 SERVICE BULLETIN Task 536177-833-801-001: Repair Depending on Inspection results, install an identical Frame Foot at FR44, RH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR44, RH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR45, LH side 4.00 Depending on Inspection results, remove the Gussets from FR45, LH side 1.00 Depending on Inspection results, remove the Frame Foot from FR45, LH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR45, LH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR45, LH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR45, RH side 4.00 Depending on Inspection results, remove the Gussets from FR45, RH side 1.00 Depending on Inspection results, remove the Frame Foot from FR45, RH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR45, RH side 16.00 Depending on Inspection results, install the Fasteners at FR45, RH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR46, LH side 4.00 Depending on Inspection results, remove the Gussets from FR46, LH side 1.00 Depending on Inspection results, remove the Frame Foot from FR46, LH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR46, LH side 16.00 Depending on Inspection results, if removed, install the Fasteners at FR46, LH side 6.00 Depending on Inspection results, if necessary, remove the Fasteners from FR46, RH side 4.00 Depending on Inspection results, remove the Gussets from FR46, RH side 1.00 Depending on Inspection results, remove the Frame Foot from FR46, RH side 16.00 Depending on Inspection results, install an identical Frame Foot at FR46, RH side 16.00 Depending on Inspection results, install the Fasteners at FR46, RH side 6.00 Close-Up 13.00 TOTAL MANHOURS 541.00 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 36 5

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

# @A300-600 SERVICE BULLETIN Task 536177-833-801-001: Repair ELAPSED TIME (HOURS) 42.00 NOTE : For an explanation of the manhours and elapsed time, refer to the Gantt Chart, Fig. A-FAAAA given in Appendix 01 - Elapsed Time Assumptions . NOTE : The minimum manhours necessary to accomplish this Service Bulletin are those for the Inspection. Depending on the inspection result, additional manhours can apply. **CONF 004 Task 536177-839-801-001: Contact and Report to AIRBUS On Aircraft Contact and Report to AIRBUS 0.50 TOTAL MANHOURS 0.50 ELAPSED TIME (HOURS) 0.50 **CONF ALL H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00 06-41-53 20-21-12 20-28-11 24-00-00 28-00-00 28-10-00 28-11-00 28-11-29 28-13-21 28-25-00 32-12-11 Consumable Material List (CML) Drawing R53810322 R53810323 R53810329 R53810330 R53810331 R53810332 Elec. Std. Practices Manual (ESPM) 20-51-20 20-55-00 Service Bulletin (SB) A300-53-6111 A300-53-6176 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 51-40-40
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 37 5

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

# @A300-600 SERVICE BULLETIN
**CONF 002 Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00 06-41-53 20-21-12 20-28-11 24-00-00 28-00-00 28-10-00 28-11-00 28-11-29 28-13-21 28-25-00 32-12-11 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-51-20 20-55-00 Service Bulletin (SB) A300-53-6111 A300-53-6176 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 51-40-40 **CONF 003 Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00 06-41-53 20-21-12 20-28-11 24-00-00 28-00-00 28-10-00 28-11-00 28-11-29 28-13-21 28-25-00 32-12-11 Consumable Material List (CML) Drawing R53810322 R53810323 R53810329 R53810330 R53810331 R53810332 Elec. Std. Practices Manual (ESPM) 20-51-20 20-55-00 Service Bulletin (SB) A300-53-6111 A300-53-6176 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 51-40-40 **CONF 004 Elec. Std. Practices Manual (ESPM) 20-55-00 **CONF ALL K. PUBLICATION AFFECTED

Maintenance Planning Document (MPD) 531541-01-1 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 38 5

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

# @A300-600 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses AIRBUS Material, Logistics and Suppliers do not stock standard hardware as competitive multiple suppliers ensure access to minimum prices. AIRBUS recommends Customers with aircraft shown in the effectivity of this Service Bulletin to send a purchase order to KLX Aerospace Solutions. The address is: Component COMPA01 Component COMPA02 Component COMPA03 Component COMPA04 Component COMPA05 KLX Aerospace Solutions. 10000 NW 15th Terrace Miami FL 33172 USA Tel EMEA: +49 (0) 40 822 285 31500 Tel US: +1 305 925 2600 Tel ASIA: +1 310 900 1300 Fax EMEA: +49 (0) 40 822 285 31010 Fax US: +1 305 507 7191 Fax ASIA: +1 310 819 1200 SITA: MIAMMCR E-Mail: AOGdesk@klx.com internet: http://www.KLXaerospace.com or, alternatively any other source on the open market. 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:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 39 5

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

# @A300-600 SERVICE BULLETIN
Kit 536177A01R00 Kit 536177A02R00 Kit 536177A03R00 Kit 536177A04R00 Kit 536177A05R00 Kit 536177A06R00 Kit 536177A07R00 Kit 536177A08R00 Kit 536177A09R00 Kit 536177A10R00 Kit 536177A11R00 Kit 536177A12R00 Kit 536177A13R00 Kit 536177A14R00 Kit 536177A15R00 Kit 536177A16R00 Kit 536177A17R00 Kit 536177A18R00 Kit 536177A19R00 Kit 536177A20R00 Kit 536177A21R00 Kit 536177A22R00 Kit 536177A23R00 Kit 536177A24R00 Kit 536177A25R00 Kit 536177A26R00 Kit 536177A27R00 Kit 536177A28R00 Kit 536177A29R00 Kit 536177A30R00 Kit 536177A31R00 Kit 536177A32R00 Kit 536177A33R00 Kit 536177A34R00 Kit 536177A35R00 Kit 536177A36R00 AIRBUS Material, Logistics and Suppliers Weg beim Jaeger 150 D-22335 HAMBURG GERMANY For ordering by internet: http://spares.airbus.com For ordering by fax: +49 40 50 76 2590 For ordering by E-mail: airbus.kit@airbus.com

(2) Price and Availability

Kit 536177A01R00 Cost 7,400.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 40 5

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

# @A300-600 SERVICE BULLETIN
Kit 536177A02R00 Cost 7,600.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A03R00 Cost 8,100.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A04R00 Cost 8,100.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A05R00 Cost 8,200.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A06R00 Cost 8,900.00 USD Availability 180 calendar days from receipt of order

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 41 5

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

# @A300-600 SERVICE BULLETIN The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A07R00 Cost 7,000.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A08R00 Cost 7,100.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A09R00 Cost 7,600.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A10R00 Cost 6,600.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 42 5

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

# @A300-600 SERVICE BULLETIN
Kit 536177A11R00 Cost 6,700.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A12R00 Cost 7,300.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A13R00 Cost 7,200.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A14R00 Cost 7,300.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A15R00 Cost 7,900.00 USD Availability 180 calendar days from receipt of order

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 43 5

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

# @A300-600 SERVICE BULLETIN The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A16R00 Cost 8,200.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A17R00 Cost 8,200.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A18R00 Cost 8,700.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A19R00 Cost 7,400.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 44 5

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# @A300-600 SERVICE BULLETIN
Kit 536177A20R00 Cost 7,600.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A21R00 Cost 8,100.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A22R00 Cost 8,100.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A23R00 Cost 8,200.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A24R00 Cost 9,000.00 USD Availability 180 calendar days from receipt of order

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 45 5

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

# @A300-600 SERVICE BULLETIN The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A25R00 Cost 7,000.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A26R00 Cost 7,100.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A27R00 Cost 7,600.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A28R00 Cost 6,600.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 46 5

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# @A300-600 SERVICE BULLETIN
Kit 536177A29R00 Cost 6,700.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A30R00 Cost 7,300.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A31R00 Cost 7,200.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A32R00 Cost 7,300.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A33R00 Cost 7,900.00 USD Availability 180 calendar days from receipt of order

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 47 5

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

# @A300-600 SERVICE BULLETIN The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A34R00 Cost 8,100.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A35R00 Cost 8,200.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 536177A36R00 Cost 8,700.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Component COMPA01 Operator supplied standard hardware parts required to accomplish this Service Bulletin, are to be supplied from the operator’s stock. Component COMPA02 Operator supplied standard hardware parts required to accomplish this Service Bulletin, are to be supplied from the operator’s stock. Component COMPA03 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 48 5

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# @A300-600 SERVICE BULLETIN Operator supplied standard hardware parts required to accomplish this Service Bulletin, are to be supplied from the operator’s stock. Component COMPA04 Operator supplied standard hardware parts required to accomplish this Service Bulletin, are to be supplied from the operator’s stock. Component COMPA05 Operator supplied standard hardware parts required to accomplish this Service Bulletin, are to be supplied from the operator’s stock. B. INDUSTRY SUPPORT INFORMATION AIRBUS will not provide industry support for accomplishment of this Service Bulletin. C. LIST OF COMPONENTS Kit 536177A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 15 SCREW 9 ASNA2529-3 36 NUT 10 EN6115V3A6 9 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 4 SCREW 16 ASNA2529-5 4 NUT 17 EN6115V3A5 10 SCREW 18 EN6115V3A4 2 SCREW 19 ASNA2050DXJ4020 2 RIVET 21 ASNA2529-4 2 NUT 26 EN6114V6X14 2 SCREW 30 EN6114V4X8 1 SCREW 31 EN6114V4X10 1 SCREW 56 NSA5057-6 4 NUT 100 A5711112920095 1 FOOT 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. Kit 536177A02R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 15 SCREW DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 49 5

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 9 ASNA2529-3 36 NUT 10 EN6115V3A6 9 SCREW 11 EN6114V6Y14 4 SCREW 12 ASNA2529-6 4 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 4 SCREW 16 ASNA2529-5 4 NUT 17 EN6115V3A5 10 SCREW 18 EN6115V3A4 2 SCREW 19 ASNA2050DXJ4020 2 RIVET 20 EN6114V4Y9 1 SCREW 21 ASNA2529-4 2 NUT 22 EN6114V4Y10 1 SCREW 56 NSA5057-6 4 NUT 100 A5711112920095 1 FOOT 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. Kit 536177A03R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 9 ASNA2529-3 36 NUT 12 ASNA2529-6 2 NUT 14 NAS1726-5E 2 NUT 16 ASNA2529-5 4 NUT 19 ASNA2050DXJ4020 2 RIVET 21 ASNA2529-4 2 NUT 23 EN6115V3X5 15 SCREW 24 EN6115V3X7 6 SCREW 25 EN6115V3X6 13 SCREW 26 EN6114V6X14 2 SCREW 27 ASNA2001V5-8X 2 SCREW 28 EN6114V5X8 4 SCREW 29 EN6115V3X4 2 SCREW 30 EN6114V4X8 1 SCREW 31 EN6114V4X10 1 SCREW 56 NSA5057-6 4 NUT 100 A5711112920095 1 FOOT 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. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 50 5

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# @A300-600 SERVICE BULLETIN
Kit 536177A04R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 1 SCREW 9 ASNA2529-3 53 NUT 10 EN6115V3A6 11 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 8 SCREW 16 ASNA2529-5 8 NUT 17 EN6115V3A5 10 SCREW 18 EN6115V3A4 4 SCREW 19 ASNA2050DXJ4020 4 RIVET 21 ASNA2529-4 2 NUT 30 EN6114V4X8 1 SCREW 31 EN6114V4X10 1 SCREW 32 EN6115V3A8 14 SCREW 33 EN6115V3A9 11 SCREW 35 EN6114V6X13 2 SCREW 56 NSA5057-6 4 NUT 102 A5711113020095 1 FOOT 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. Kit 536177A05R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 1 SCREW 9 ASNA2529-3 53 NUT 10 EN6115V3A6 11 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 8 SCREW 16 ASNA2529-5 8 NUT 17 EN6115V3A5 10 SCREW 18 EN6115V3A4 4 SCREW 19 ASNA2050DXJ4020 4 RIVET 20 EN6114V4Y9 1 SCREW 21 ASNA2529-4 2 NUT 22 EN6114V4Y10 1 SCREW 32 EN6115V3A8 14 SCREW 33 EN6115V3A9 11 SCREW DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 51 5

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 34 EN6114V6Y13 2 SCREW 56 NSA5057-6 4 NUT 102 A5711113020095 1 FOOT 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. Kit 536177A06R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 9 ASNA2529-3 48 NUT 12 ASNA2529-6 2 NUT 14 NAS1726-5E 2 NUT 16 ASNA2529-5 8 NUT 19 ASNA2050DXJ4020 4 RIVET 21 ASNA2529-4 2 NUT 23 EN6115V3X5 15 SCREW 24 EN6115V3X7 5 SCREW 25 EN6115V3X6 24 SCREW 27 ASNA2001V5-8X 2 SCREW 28 EN6114V5X8 8 SCREW 29 EN6115V3X4 4 SCREW 30 EN6114V4X8 1 SCREW 31 EN6114V4X10 1 SCREW 35 EN6114V6X13 2 SCREW 56 NSA5057-6 4 NUT 102 A5711113020095 1 FOOT 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. Kit 536177A07R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 7 SCREW 9 ASNA2529-3 39 NUT 10 EN6115V3A6 10 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 4 SCREW 16 ASNA2529-5 5 NUT DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 52 5

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 17 EN6115V3A5 9 SCREW 19 ASNA2050DXJ4020 2 RIVET 21 ASNA2529-4 1 NUT 26 EN6114V6X14 2 SCREW 30 EN6114V4X8 1 SCREW 32 EN6115V3A8 11 SCREW 33 EN6115V3A9 1 SCREW 36 EN6115V3A3 5 SCREW 41 EN6114V5X10 1 SCREW 56 NSA5057-6 4 NUT 104 A5711113120095 1 FOOT 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. Kit 536177A08R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 7 SCREW 9 ASNA2529-3 39 NUT 10 EN6115V3A6 10 SCREW 11 EN6114V6Y14 2 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 4 SCREW 16 ASNA2529-5 5 NUT 17 EN6115V3A5 9 SCREW 19 ASNA2050DXJ4020 2 RIVET 20 EN6114V4Y9 1 SCREW 21 ASNA2529-4 1 NUT 32 EN6115V3A8 11 SCREW 33 EN6115V3A9 1 SCREW 36 EN6115V3A3 5 SCREW 37 EN6114V5Y10 1 SCREW 56 NSA5057-6 4 NUT 104 A5711113120095 1 FOOT 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.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 53 5

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# @A300-600 SERVICE BULLETIN
Kit 536177A09R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 9 ASNA2529-3 39 NUT 12 ASNA2529-6 2 NUT 14 NAS1726-5E 2 NUT 16 ASNA2529-5 5 NUT 19 ASNA2050DXJ4020 2 RIVET 21 ASNA2529-4 1 NUT 23 EN6115V3X5 9 SCREW 24 EN6115V3X7 4 SCREW 25 EN6115V3X6 11 SCREW 26 EN6114V6X14 2 SCREW 27 ASNA2001V5-8X 2 SCREW 28 EN6114V5X8 4 SCREW 30 EN6114V4X8 1 SCREW 39 EN6115V3X9 3 SCREW 40 EN6115V3X8 11 SCREW 41 EN6114V5X10 1 SCREW 56 NSA5057-6 4 NUT 104 A5711113120095 1 FOOT 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. Kit 536177A10R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 11 SCREW 9 ASNA2529-3 35 NUT 10 EN6115V3A6 12 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 2 SCREW 16 ASNA2529-5 4 NUT 17 EN6115V3A5 9 SCREW 18 EN6115V3A4 2 SCREW 19 ASNA2050DXJ4020 2 RIVET 26 EN6114V6X14 2 SCREW 28 EN6114V5X8 1 SCREW 36 EN6115V3A3 1 SCREW 41 EN6114V5X10 1 SCREW 56 NSA5057-6 4 NUT 106 A5711113220095 1 FOOT DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 54 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. Kit 536177A11R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 11 SCREW 9 ASNA2529-3 35 NUT 10 EN6115V3A6 12 SCREW 11 EN6114V6Y14 2 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 2 SCREW 16 ASNA2529-5 4 NUT 17 EN6115V3A5 9 SCREW 18 EN6115V3A4 2 SCREW 19 ASNA2050DXJ4020 2 RIVET 36 EN6115V3A3 1 SCREW 37 EN6114V5Y10 2 SCREW 56 NSA5057-6 4 NUT 106 A5711113220095 1 FOOT 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. Kit 536177A12R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 9 ASNA2529-3 35 NUT 12 ASNA2529-6 2 NUT 14 NAS1726-5E 2 NUT 16 ASNA2529-5 4 NUT 19 ASNA2050DXJ4020 2 RIVET 23 EN6115V3X5 10 SCREW 24 EN6115V3X7 11 SCREW 25 EN6115V3X6 12 SCREW 26 EN6114V6X14 2 SCREW 27 ASNA2001V5-8X 2 SCREW 28 EN6114V5X8 3 SCREW 29 EN6115V3X4 2 SCREW 41 EN6114V5X10 1 SCREW 56 NSA5057-6 4 NUT 106 A5711113220095 1 FOOT DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 55 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. Kit 536177A13R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 4 SCREW 9 ASNA2529-3 48 NUT 10 EN6115V3A6 7 SCREW 12 ASNA2529-6 2 NUT 16 ASNA2529-5 2 NUT 17 EN6115V3A5 3 SCREW 19 ASNA2050DXJ4020 4 RIVET 26 EN6114V6X14 2 SCREW 28 EN6114V5X8 1 SCREW 32 EN6115V3A8 7 SCREW 33 EN6115V3A9 17 SCREW 41 EN6114V5X10 1 SCREW 42 EN6114V3A6 1 SCREW 43 EN6115V3A10 2 SCREW 44 EN6115V3A11 7 SCREW 45 ASNA2001V6-8Y 2 SCREW 46 NAS1726-6E 2 NUT 56 NSA5057-6 4 NUT 76 NSA5057-7 4 NUT 108 A5711113320095 1 FOOT 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. Kit 536177A14R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 4 SCREW 9 ASNA2529-3 48 NUT 10 EN6115V3A6 7 SCREW 11 EN6114V6Y14 2 SCREW 12 ASNA2529-6 2 NUT 16 ASNA2529-5 2 NUT 17 EN6115V3A5 3 SCREW 19 ASNA2050DXJ4020 4 RIVET 32 EN6115V3A8 7 SCREW 33 EN6115V3A9 17 SCREW 37 EN6114V5Y10 2 SCREW DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 56 5

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 42 EN6114V3A6 1 SCREW 43 EN6115V3A10 2 SCREW 44 EN6115V3A11 7 SCREW 45 ASNA2001V6-8Y 2 SCREW 46 NAS1726-6E 2 NUT 56 NSA5057-6 4 NUT 76 NSA5057-7 4 NUT 108 A5711113320095 1 FOOT 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. Kit 536177A15R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 9 ASNA2529-3 48 NUT 12 ASNA2529-6 2 NUT 16 ASNA2529-5 2 NUT 19 ASNA2050DXJ4020 4 RIVET 23 EN6115V3X5 8 SCREW 24 EN6115V3X7 7 SCREW 25 EN6115V3X6 18 SCREW 26 EN6114V6X14 2 SCREW 28 EN6114V5X8 1 SCREW 39 EN6115V3X9 4 SCREW 40 EN6115V3X8 10 SCREW 41 EN6114V5X10 1 SCREW 46 NAS1726-6E 2 NUT 47 EN6114V3X6 1 SCREW 48 ASNA2001V6-8X 2 SCREW 56 NSA5057-6 4 NUT 76 NSA5057-7 4 NUT 108 A5711113320095 1 FOOT 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. Kit 536177A16R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 3 SCREW 9 ASNA2529-3 43 NUT DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 57 5

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 10 EN6115V3A6 11 SCREW 12 ASNA2529-6 3 NUT 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 6 SCREW 16 ASNA2529-5 7 NUT 17 EN6115V3A5 7 SCREW 18 EN6115V3A4 2 SCREW 19 ASNA2050DXJ4020 2 RIVET 26 EN6114V6X14 1 SCREW 33 EN6115V3A9 9 SCREW 43 EN6115V3A10 5 SCREW 44 EN6115V3A11 6 SCREW 50 ASNA2001V5-12Y 2 SCREW 52 EN6114V6X17 2 SCREW 54 EN6114V5X12 1 SCREW 56 NSA5057-6 4 NUT 76 NSA5057-7 4 NUT 110 A5711113420095 1 FOOT 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. Kit 536177A17R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 3 SCREW 9 ASNA2529-3 43 NUT 10 EN6115V3A6 11 SCREW 11 EN6114V6Y14 1 SCREW 12 ASNA2529-6 3 NUT 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 6 SCREW 16 ASNA2529-5 7 NUT 17 EN6115V3A5 7 SCREW 18 EN6115V3A4 2 SCREW 19 ASNA2050DXJ4020 2 RIVET 33 EN6115V3A9 9 SCREW 43 EN6115V3A10 5 SCREW 44 EN6115V3A11 6 SCREW 49 EN6114V6Y17 2 SCREW 50 ASNA2001V5-12Y 2 SCREW 51 EN6114V5Y12 1 SCREW 56 NSA5057-6 4 NUT 76 NSA5057-7 4 NUT DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 58 5

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 110 A5711113420095 1 FOOT 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. Kit 536177A18R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 9 ASNA2529-3 43 NUT 12 ASNA2529-6 3 NUT 14 NAS1726-5E 2 NUT 16 ASNA2529-5 7 NUT 19 ASNA2050DXJ4020 2 RIVET 23 EN6115V3X5 12 SCREW 24 EN6115V3X7 10 SCREW 25 EN6115V3X6 19 SCREW 26 EN6114V6X14 1 SCREW 28 EN6114V5X8 6 SCREW 29 EN6115V3X4 2 SCREW 52 EN6114V6X17 2 SCREW 53 ASNA2001V5-12X 2 SCREW 54 EN6114V5X12 1 SCREW 56 NSA5057-6 4 NUT 76 NSA5057-7 4 NUT 110 A5711113420095 1 FOOT 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. Kit 536177A19R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 15 SCREW 9 ASNA2529-3 36 NUT 10 EN6115V3A6 9 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 4 SCREW 16 ASNA2529-5 4 NUT 17 EN6115V3A5 10 SCREW 18 EN6115V3A4 2 SCREW DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 59 5

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 19 ASNA2050DXJ4020 2 RIVET 21 ASNA2529-4 2 NUT 26 EN6114V6X14 2 SCREW 30 EN6114V4X8 1 SCREW 31 EN6114V4X10 1 SCREW 56 NSA5057-6 4 NUT 101 A5711112920195 1 FOOT 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. Kit 536177A20R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 15 SCREW 9 ASNA2529-3 36 NUT 10 EN6115V3A6 9 SCREW 11 EN6114V6Y14 4 SCREW 12 ASNA2529-6 4 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 4 SCREW 16 ASNA2529-5 4 NUT 17 EN6115V3A5 10 SCREW 18 EN6115V3A4 2 SCREW 19 ASNA2050DXJ4020 2 RIVET 20 EN6114V4Y9 1 SCREW 21 ASNA2529-4 2 NUT 22 EN6114V4Y10 1 SCREW 56 NSA5057-6 4 NUT 101 A5711112920195 1 FOOT 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. Kit 536177A21R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 9 ASNA2529-3 36 NUT 12 ASNA2529-6 2 NUT 14 NAS1726-5E 2 NUT 16 ASNA2529-5 4 NUT DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 60 5

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 19 ASNA2050DXJ4020 2 RIVET 21 ASNA2529-4 2 NUT 23 EN6115V3X5 15 SCREW 24 EN6115V3X7 6 SCREW 25 EN6115V3X6 13 SCREW 26 EN6114V6X14 2 SCREW 27 ASNA2001V5-8X 2 SCREW 28 EN6114V5X8 4 SCREW 29 EN6115V3X4 2 SCREW 30 EN6114V4X8 1 SCREW 31 EN6114V4X10 1 SCREW 56 NSA5057-6 4 NUT 101 A5711112920195 1 FOOT 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. Kit 536177A22R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 1 SCREW 9 ASNA2529-3 53 NUT 10 EN6115V3A6 11 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 8 SCREW 16 ASNA2529-5 8 NUT 17 EN6115V3A5 10 SCREW 18 EN6115V3A4 4 SCREW 19 ASNA2050DXJ4020 4 RIVET 21 ASNA2529-4 2 NUT 30 EN6114V4X8 1 SCREW 31 EN6114V4X10 1 SCREW 32 EN6115V3A8 14 SCREW 33 EN6115V3A9 11 SCREW 35 EN6114V6X13 2 SCREW 56 NSA5057-6 4 NUT 103 A5711113020195 1 FOOT 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. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 61 5

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# @A300-600 SERVICE BULLETIN
Kit 536177A23R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 1 SCREW 9 ASNA2529-3 53 NUT 10 EN6115V3A6 11 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 8 SCREW 16 ASNA2529-5 8 NUT 17 EN6115V3A5 10 SCREW 18 EN6115V3A4 4 SCREW 19 ASNA2050DXJ4020 4 RIVET 20 EN6114V4Y9 1 SCREW 21 ASNA2529-4 2 NUT 22 EN6114V4Y10 1 SCREW 32 EN6115V3A8 14 SCREW 33 EN6115V3A9 11 SCREW 34 EN6114V6Y13 2 SCREW 56 NSA5057-6 4 NUT 103 A5711113020195 1 FOOT 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. Kit 536177A24R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 9 ASNA2529-3 48 NUT 12 ASNA2529-6 2 NUT 14 NAS1726-5E 2 NUT 16 ASNA2529-5 8 NUT 19 ASNA2050DXJ4020 4 RIVET 21 ASNA2529-4 2 NUT 23 EN6115V3X15 5 SCREW 23 EN6115V3X5 10 SCREW 24 EN6115V3X7 5 SCREW 25 EN6115V3X6 24 SCREW 27 ASNA2001V5-8X 2 SCREW 28 EN6114V5X8 8 SCREW 29 EN6115V3X4 4 SCREW 30 EN6114V4X8 1 SCREW 31 EN6114V4X10 1 SCREW 35 EN6114V6X13 2 SCREW DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 62 5

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 56 NSA5057-6 4 NUT 103 A5711113020195 1 FOOT 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. Kit 536177A25R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 7 SCREW 9 ASNA2529-3 39 NUT 10 EN6115V3A6 10 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 4 SCREW 16 ASNA2529-5 5 NUT 17 EN6115V3A5 9 SCREW 19 ASNA2050DXJ4020 2 RIVET 21 ASNA2529-4 1 NUT 26 EN6114V6X14 2 SCREW 30 EN6114V4X8 1 SCREW 32 EN6115V3A8 11 SCREW 33 EN6115V3A9 1 SCREW 36 EN6115V3A3 5 SCREW 41 EN6114V5X10 1 SCREW 56 NSA5057-6 4 NUT 105 A5711113120195 1 FOOT 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. Kit 536177A26R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 7 SCREW 9 ASNA2529-3 39 NUT 10 EN6115V3A6 10 SCREW 11 EN6114V6Y14 2 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 63 5

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 15 EN6114V5Y8 4 SCREW 16 ASNA2529-5 5 NUT 17 EN6115V3A5 9 SCREW 19 ASNA2050DXJ4020 2 RIVET 20 EN6114V4Y9 1 SCREW 21 ASNA2529-4 1 NUT 32 EN6115V3A8 11 SCREW 33 EN6115V3A9 1 SCREW 36 EN6115V3A3 5 SCREW 37 EN6114V5Y10 1 SCREW 56 NSA5057-6 4 NUT 105 A5711113120195 1 FOOT 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. Kit 536177A27R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 9 ASNA2529-3 39 NUT 12 ASNA2529-6 2 NUT 14 NAS1726-5E 2 NUT 16 ASNA2529-5 5 NUT 19 ASNA2050DXJ4020 2 RIVET 21 ASNA2529-4 1 NUT 23 EN6115V3X5 9 SCREW 24 EN6115V3X7 4 SCREW 25 EN6115V3X6 11 SCREW 26 EN6114V6X14 2 SCREW 27 ASNA2001V5-8X 2 SCREW 28 EN6114V5X8 4 SCREW 30 EN6114V4X8 1 SCREW 39 EN6115V3X9 3 SCREW 40 EN6115V3X8 11 SCREW 41 EN6114V5X10 1 SCREW 56 NSA5057-6 4 NUT 105 A5711113120195 1 FOOT 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.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 64 5

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# @A300-600 SERVICE BULLETIN
Kit 536177A28R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 11 SCREW 9 ASNA2529-3 35 NUT 10 EN6115V3A6 12 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 2 SCREW 16 ASNA2529-5 4 NUT 17 EN6115V3A5 9 SCREW 18 EN6115V3A4 2 SCREW 19 ASNA2050DXJ4020 2 RIVET 26 EN6114V6X14 2 SCREW 28 EN6114V5X8 1 SCREW 36 EN6115V3A3 1 SCREW 41 EN6114V5X10 1 SCREW 56 NSA5057-6 4 NUT 107 A5711113220195 1 FOOT 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. Kit 536177A29R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 11 SCREW 9 ASNA2529-3 35 NUT 10 EN6115V3A6 12 SCREW 11 EN6114V6Y14 2 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 2 SCREW 16 ASNA2529-5 4 NUT 17 EN6115V3A5 9 SCREW 18 EN6115V3A4 2 SCREW 19 ASNA2050DXJ4020 2 RIVET 36 EN6115V3A3 1 SCREW 37 EN6114V5Y10 2 SCREW 56 NSA5057-6 4 NUT 107 A5711113220195 1 FOOT

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 65 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. Kit 536177A30R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 9 ASNA2529-3 35 NUT 12 ASNA2529-6 2 NUT 14 NAS1726-5E 2 NUT 16 ASNA2529-5 4 NUT 19 ASNA2050DXJ4020 2 RIVET 23 EN6115V3X5 10 SCREW 24 EN6115V3X7 11 SCREW 25 EN6115V3X6 12 SCREW 26 EN6114V6X14 2 SCREW 27 ASNA2001V5-8X 2 SCREW 28 EN6114V5X8 3 SCREW 29 EN6115V3X4 2 SCREW 41 EN6114V5X10 1 SCREW 56 NSA5057-6 4 NUT 107 A5711113220195 1 FOOT 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. Kit 536177A31R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 4 SCREW 9 ASNA2529-3 48 NUT 10 EN6115V3A6 5 SCREW 12 ASNA2529-6 2 NUT 16 ASNA2529-5 2 NUT 17 EN6115V3A5 5 SCREW 19 ASNA2050DXJ4020 4 RIVET 26 EN6114V6X14 2 SCREW 28 EN6114V5X8 1 SCREW 32 EN6115V3A8 7 SCREW 33 EN6115V3A9 17 SCREW 41 EN6114V5X10 1 SCREW 42 EN6114V3A6 1 SCREW 43 EN6115V3A10 2 SCREW 44 EN6115V3A11 7 SCREW 45 ASNA2001V6-8Y 2 SCREW DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 66 5

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 46 NAS1726-6E 2 NUT 56 NSA5057-6 4 NUT 76 NSA5057-7 4 NUT 109 A5711113320195 1 FOOT 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. Kit 536177A32R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 4 SCREW 9 ASNA2529-3 48 NUT 10 EN6115V3A6 5 SCREW 11 EN6114V6Y14 2 SCREW 12 ASNA2529-6 2 NUT 16 ASNA2529-5 2 NUT 17 EN6115V3A5 5 SCREW 19 ASNA2050DXJ4020 4 RIVET 32 EN6115V3A8 7 SCREW 33 EN6115V3A9 17 SCREW 37 EN6114V5Y10 2 SCREW 42 EN6114V3A6 1 SCREW 43 EN6115V3A10 2 SCREW 44 EN6115V3A11 7 SCREW 45 ASNA2001V6-8Y 2 SCREW 46 NAS1726-6E 2 NUT 56 NSA5057-6 4 NUT 76 NSA5057-7 4 NUT 109 A5711113320195 1 FOOT 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. Kit 536177A33R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 9 ASNA2529-3 48 NUT 12 ASNA2529-6 2 NUT 16 ASNA2529-5 2 NUT 19 ASNA2050DXJ4020 4 RIVET 23 EN6115V3X5 10 SCREW DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 67 5

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 24 EN6115V3X7 7 SCREW 25 EN6115V3X6 16 SCREW 26 EN6114V6X14 2 SCREW 28 EN6114V5X8 1 SCREW 39 EN6115V3X9 4 SCREW 40 EN6115V3X8 10 SCREW 41 EN6114V5X10 1 SCREW 46 NAS1726-6E 2 NUT 47 EN6114V3X6 1 SCREW 48 ASNA2001V6-8X 2 SCREW 56 NSA5057-6 4 NUT 76 NSA5057-7 4 NUT 109 A5711113320195 1 FOOT 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. Kit 536177A34R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 3 SCREW 9 ASNA2529-3 43 NUT 10 EN6115V3A6 8 SCREW 12 ASNA2529-6 3 NUT 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 6 SCREW 16 ASNA2529-5 7 NUT 17 EN6115V3A5 7 SCREW 18 EN6115V3A4 2 SCREW 19 ASNA2050DXJ4020 2 RIVET 26 EN6114V6X14 1 SCREW 33 EN6115V3A9 9 SCREW 43 EN6115V3A10 5 SCREW 44 EN6115V3A11 6 SCREW 50 ASNA2001V5-12Y 2 SCREW 52 EN6114V6X17 2 SCREW 54 EN6114V5X12 1 SCREW 56 NSA5057-6 4 NUT 76 NSA5057-7 4 NUT 111 A5711113420195 1 FOOT 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. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 68 5

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# @A300-600 SERVICE BULLETIN
Kit 536177A35R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115V3A7 3 SCREW 9 ASNA2529-3 43 NUT 10 EN6115V3A6 8 SCREW 11 EN6114V6Y14 1 SCREW 12 ASNA2529-6 3 NUT 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 6 SCREW 16 ASNA2529-5 7 NUT 17 EN6115V3A5 7 SCREW 18 EN6115V3A4 2 SCREW 19 ASNA2050DXJ4020 2 RIVET 33 EN6115V3A9 9 SCREW 43 EN6115V3A10 5 SCREW 44 EN6115V3A11 6 SCREW 49 EN6114V6Y17 2 SCREW 50 ASNA2001V5-12Y 2 SCREW 51 EN6114V5Y12 1 SCREW 56 NSA5057-6 4 NUT 76 NSA5057-7 4 NUT 111 A5711113420195 1 FOOT 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. Kit 536177A36R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 9 ASNA2529-3 43 NUT 12 ASNA2529-6 3 NUT 14 NAS1726-5E 2 NUT 16 ASNA2529-5 7 NUT 19 ASNA2050DXJ4020 2 RIVET 23 EN6115V3X5 12 SCREW 24 EN6115V3X7 10 SCREW 25 EN6115V3X6 19 SCREW 26 EN6114V6X14 1 SCREW 28 EN6114V5X8 6 SCREW 29 EN6115V3X4 2 SCREW 52 EN6114V6X17 2 SCREW 53 ASNA2001V5-12X 2 SCREW 54 EN6114V5X12 1 SCREW 56 NSA5057-6 4 NUT DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 69 5

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 76 NSA5057-7 4 NUT 111 A5711113420195 1 FOOT 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. D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required Non Aqueous Cleaner - General 08BAA9 As required (2) Components Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 9 ASNA2529-3 32 NUT 90 ASNA2019-56-25 32 RIVET 91 EN6114V3X5 32 SCREW 92 EN6080D6X-32 20 RIVET 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 : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required.
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 70 5

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# @A300-600 SERVICE BULLETIN Component COMPA02 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 9 ASNA2529-3 24 NUT 90 ASNA2019-56-25 24 RIVET 91 EN6114V3X5 24 SCREW 92 EN6080D6X-32 16 RIVET 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 : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Component COMPA03 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 9 ASNA2529-3 24 NUT 47 EN6114V3X6 24 SCREW 90 ASNA2019-56-25 24 RIVET 92 EN6080D6X-32 16 RIVET 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 : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Component COMPA04 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 9 ASNA2529-3 32 NUT 47 EN6114V3X6 32 SCREW 90 ASNA2019-56-25 32 RIVET 92 EN6080D6X-32 20 RIVET

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 71 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 : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Component COMPA05 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 9 ASNA2529-3 24 NUT 47 EN6114V3X6 16 SCREW 90 ASNA2019-56-25 24 RIVET 91 EN6114V3X5 8 SCREW 92 EN6080D6X-32 16 RIVET 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 : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 72 5

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# @A300-600 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 536177-832-801-001 - Detailed Inspection of the Frame foot 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. NOTE : The accomplishment instructions of this Service Bulletin include procedures given in other documents or in other sections of the Service Bulletin. When the words "refer to" are used and the operator has a procedure accepted by the local authority he belongs to, the accepted alternative procedure can be used. When the words "in accordance with" are used then the given procedure must be followed. NOTE : The access and close-up instructions, not comprising return to service tests, in this Service Bulletin do not constitute or affect the technical intent of the Service Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or close-up steps to add flexibility to their maintenance operations as long as the technical intent of the Service Bulletin is met within the set parameters. NOTE : Manual titles given in the accomplishment instructions are referred to by acronyms. Refer to paragraph 1.J., References, for the definition of acronyms. NOTE : The purpose of flow charts is to supplement the information given in the Procedure and Compliance paragraphs and not to serve as the primary source for tasks or compliance times given in this Service Bulletin. NOTE : This Service Bulletin is classified mandatory or expected to be classified mandatory by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from those given in the Service Bulletin, as long as the RC paragraphs can be done and the aircraft can be put back into a serviceable condition.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 73 5

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# @A300-600 SERVICE BULLETIN
Task Associated Data **CONF 001 Zone 147 148 Access Door 147BZ Manpower TOTAL MANHOURS 8.00 ELAPSED TIME (HOURS) 2.50 **CONF 002 Zone 147 148 Access Door 147AZ 147BZ Manpower TOTAL MANHOURS 8.00 ELAPSED TIME (HOURS) 2.50 **CONF 003 Zone 147 148 Access Door 147BZ Manpower TOTAL MANHOURS 8.00 ELAPSED TIME (HOURS) 2.50 **CONF 004 None **CONF ALL A. GENERAL **CONF 001 (1) Subtask 536177-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 74 5

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# @A300-600 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-00, Page Block 001 Consumable Material List (CML) (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001. (d) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Material List (CML). (2) Subtask 536177-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 002 (1) Subtask 536177-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-00, Page Block 001 Consumable Material List (CML) (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001. (d) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Material List (CML). (2) Subtask 536177-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 75 5

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# @A300-600 SERVICE BULLETIN
**CONF 003 (1) Subtask 536177-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-00, Page Block 001 Consumable Material List (CML) (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001. (d) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Material List (CML). (2) Subtask 536177-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 004 None **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 536177-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001 24-00-00, Page Block 301 32-12-11, Page Block 301 NOTE : The items given in this note shall be considered as the basic Aircraft configuration before you start a maintenance task: DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 76 5

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# @A300-600 SERVICE BULLETIN - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear) - Engine shut down, thrust reversers closed and locked - Aircraft in clean configuration - Parking brake applied - Aircraft electrical network de-energized - Hydraulic systems depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position (a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (b) Open the Main Landing Gear (MLG) door, refer to AMM 32-12-11, Page Block 301. (c) Put an access platform in position at zone 140. (d) Open the access door 147BZ, refer to AMM 06-41-53, Page Block 001. **CONF 002 (1) Subtask 536177-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001 24-00-00, Page Block 301 32-12-11, Page Block 301 NOTE : The items given in this note shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear) - Engine shut down, thrust reversers closed and locked - Aircraft in clean configuration - Parking brake applied - Aircraft electrical network de-energized DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 77 5

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# @A300-600 SERVICE BULLETIN - Hydraulic systems depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position (a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (b) Open the Main Landing Gear (MLG) door, refer to AMM 32-12-11, Page Block 301. (c) Put an access platform in position at zone 140. (d) Open the access door 147BZ, refer to AMM 06-41-53, Page Block 001. **CONF 003 (1) Subtask 536177-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001 24-00-00, Page Block 301 32-12-11, Page Block 301 NOTE : The items given in this note shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear) - Engine shut down, thrust reversers closed and locked - Aircraft in clean configuration - Parking brake applied - Aircraft electrical network de-energized - Hydraulic systems depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position (a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 78 5

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# @A300-600 SERVICE BULLETIN (b) Open the Main Landing Gear (MLG) door, refer to AMM 32-12-11, Page Block 301. (c) Put an access platform in position at zone 140. (d) Open the access door 147BZ, refer to AMM 06-41-53, Page Block 001. **CONF 004 None **CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 536177-832-001-001 - Do a Detailed Inspection of the Frame Foot at FR41 on LH Side Work Zones and Access Panels Zone Access/Work location 147 Access Door 147BZ Work location Frame 41 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required
References Drawing R53810329 Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FFAAA Flow Chart for Frame 41 on LH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 79 5

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# @A300-600 SERVICE BULLETIN
References Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 41 on LH side. Refer to Fig. A-FFAAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 02 and Fig. A-FBAAA Sheet 08 1 The Frame have never been inspected as per Service Bulletin No. A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111 or never be repaired as per R53810329:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 41 on LH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 41 on LH side, at the interval given in the table 2 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. <2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 80 5

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# @A300-600 SERVICE BULLETIN <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 41 on LH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 41 on LH side, at the threshold given in the table 2 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (2) Subtask 536177-832-002-001 - Do a Detailed Inspection of the Frame Foot at FR41 on RH Side Work Zones and Access Panels Zone Access/Work location 148 Access Door 147BZ Work location Frame 41 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required
References Drawing R53810329 Service Bulletin (SB) A300-53-6111 A300-53-6176

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 81 5

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# @A300-600 SERVICE BULLETIN
References Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 Fig. A-FFBAA Flow Chart for Frame 41 on RH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 41 on RH side. Refer to Fig. A-FFBAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 02 and Fig. A-FBAAA Sheet 08 1 The Frame have never been inspected as per Service Bulletin No. A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111 or never be repaired as per R53810329:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 41 on RH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 41 on RH side, at the interval given in the table 2 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 82 5

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# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 41 on RH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 41 on RH side, at the threshold given in the table 2 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (3) Subtask 536177-832-003-001 - Do a Detailed Inspection of the Frame Foot at FR42 on LH Side Work Zones and Access Panels Zone Access/Work location 147 Access Door 147BZ Work location Frame 42 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 83 5

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# @A300-600 SERVICE BULLETIN
References Drawing R53810330 Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 Fig. A-FFCAA Flow Chart for Frame 42 on LH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 42 on LH side. Refer to Fig. A-FFCAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 03 and Fig. A-FBAAA Sheet 08 1 The Frame have never been inspected as per Service Bulletin No. A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111 or never be repaired as per R53810330:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 42 on LH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 42 on LH side, at the interval given in the table 2 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 84 5

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# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 42 on LH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 42 on LH side, at the threshold given in the table 2 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (4) Subtask 536177-832-004-001 - Do a Detailed Inspection of the Frame Foot at FR42 on RH Side Work Zones and Access Panels Zone Access/Work location 148 Access Door 147BZ Work location Frame 42 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 85 5

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# @A300-600 SERVICE BULLETIN
References Drawing R53810330 Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FFDAA Flow Chart for Frame 42 on RH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 42 on RH side. Refer to Fig. A-FFDAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 03 and Fig. A-FBAAA Sheet 08 1 The Frame have never been inspected as per Service Bulletin No. A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111 or never be repaired as per R53810330:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 42 on RH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 42 on RH side, at the interval given in the table 2 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 86 5

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# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 42 on RH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 42 on RH side, at the threshold given in the table 2 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (5) Subtask 536177-832-005-001 - Do a Detailed Inspection of the Frame Foot at FR43 on LH Side Work Zones and Access Panels Zone Access/Work location 147 Access Door 147BZ Work location Frame 43 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 87 5

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# @A300-600 SERVICE BULLETIN
References Drawing R53810331 Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 Fig. A-FFEAA Flow Chart for Frame 43 on LH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 43 on LH side. Refer to Fig. A-FFEAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet 08 1 The Frame have never been inspected as per Service Bulletin No. A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111 or never be repaired as per R53810331.
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 43 on LH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 43 on LH side, at the interval given in the table 2 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 88 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 43 on LH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 43 on LH side, at the threshold given in the table 2 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (6) Subtask 536177-832-006-001 - Do a Detailed Inspection of the Frame Foot at FR43 on RH Side Work Zones and Access Panels Zone Access/Work location 148 Access Door 147BZ Work location Frame 43 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 89 5

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

# @A300-600 SERVICE BULLETIN
References Drawing R53810331 Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 Fig. A-FFFAA Flow Chart for Frame 43 on RH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 43 on RH side. Refer to Fig. A-FFFAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet 08 1 The Frame have never been inspected as per Service Bulletin No. A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111 or never be repaired as per R53810331:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 43 on RH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 43 on RH side, at the interval given in the table 2 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 90 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 43 on RH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 43 on RH side, at the threshold given in the table 2 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (7) Subtask 536177-832-007-001 - Do a Detailed Inspection of the Frame Foot at FR44 on LH Side Work Zones and Access Panels Zone Access/Work location 147 Access Door 147BZ Work location Frame 44 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 91 5

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

# @A300-600 SERVICE BULLETIN
References Drawing R53810332 Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 Fig. A-FFGAA Flow Chart for Frame 44 on LH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 44 on LH side. Refer to Fig. A-FFGAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 05 and Fig. A-FBAAA Sheet 08 1 The Frame have never been inspected as per Service Bulletin No. A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111 or never be repaired as per R53810332:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 44 on LH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 44 on LH side, at the interval given in the table 2 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 92 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 44 on LH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 44 on LH side, at the threshold given in the table 2 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (8) Subtask 536177-832-008-001 - Do a Detailed Inspection of the Frame Foot at FR44 on RH Side Work Zones and Access Panels Zone Access/Work location 148 Access Door 147BZ Work location Frame 44 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 93 5

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

# @A300-600 SERVICE BULLETIN
References Drawing R53810332 Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 Fig. A-FFHAA Flow Chart for Frame 44 on RH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 44 on RH side. Refer to Fig. A-FFHAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 05 and Fig. A-FBAAA Sheet 08 1 The Frame have never been inspected as per Service Bulletin No. A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111 or never be repaired as per R53810332:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 44 on RH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 44 on RH side, at the interval given in the table 2 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 94 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 44 on RH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 44 on RH side, at the threshold given in the table 2 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (9) Subtask 536177-832-009-001 - Do a Detailed Inspection of the Frame Foot at FR45 on LH Side Work Zones and Access Panels Zone Access/Work location 147 Access Door 147BZ Work location Frame 45 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 95 5

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

# @A300-600 SERVICE BULLETIN
References Drawing R53810322 Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FFIAA Flow Chart for Frame 45 on LH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 45 on LH side. Refer to Fig. A-FFIAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 06 and Fig. A-FBAAA Sheet 08 1 The Frame have never been inspected as per Service Bulletin No. A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111 or never be repaired as per R53810322:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 45 on LH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 45 on LH side, at the interval given in the table 2 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 96 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 45 on LH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 45 on LH side, at the threshold given in the table 2 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (10) Subtask 536177-832-010-001 - Do a Detailed Inspection of the Frame Foot at FR45 on RH Side Work Zones and Access Panels Zone Access/Work location 148 Access Door 147BZ Work location Frame 45 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 97 5

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

# @A300-600 SERVICE BULLETIN
References Drawing R53810322 Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FFJAA Flow Chart for Frame 45 on RH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 45 on RH side. Refer to Fig. A-FFJAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 06 and Fig. A-FBAAA Sheet 08 1 The Frame have never been inspected as per Service Bulletin No. A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111 or never be repaired as per R53810322:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 45 on RH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 45 on RH side, at the interval given in the table 2 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 98 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 45 on RH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 45 on RH side, at the threshold given in the table 2 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (11) Subtask 536177-832-011-001 - Do a Detailed Inspection of the Frame Foot at FR46 on LH Side Work Zones and Access Panels Zone Access/Work location 147 Access Door 147BZ Work location Frame 46 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 99 5

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

# @A300-600 SERVICE BULLETIN
References Drawing R53810323 Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 Fig. A-FFKAA Flow Chart for Frame 46 on LH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 46 on LH side. Refer to Fig. A-FFKAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 07 and Fig. A-FBAAA Sheet 08 1 The Frame have never been inspected as per Service Bulletin No. A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111 or never be repaired as per R53810323:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 46 on LH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 46 on LH side, at the interval given in the table 2 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 100 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 46 on LH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 46 on LH side, at the threshold given in the table 2 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (12) Subtask 536177-832-012-001 - Do a Detailed Inspection of the Frame Foot at FR46 on RH Side Work Zones and Access Panels Zone Access/Work location 148 Access Door 147BZ Work location Frame 46 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 101 5

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

# @A300-600 SERVICE BULLETIN
References Drawing R53810323 Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 Fig. A-FFLAA Flow Chart for Frame 46 on RH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 46 on RH side. Refer to Fig. A-FFLAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 07 and Fig. A-FBAAA Sheet 08 1 The Frame have never been inspected as per Service Bulletin No. A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111 or never be repaired as per R53810323:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 46 on RH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 46 on RH side, at the interval given in the table 2 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 102 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 46 on RH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 46 on RH side, at the threshold given in the table 2 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. **CONF 002 (1) Subtask 536177-832-001-002 - Do a Detailed Inspection of the Frame Foot at FR41 on LH Side Work Zones and Access Panels Zone Access/Work location 147 Access Door 147BZ Work location Frame 41 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 103 5

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

# @A300-600 SERVICE BULLETIN
References Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FFAAA Flow Chart for Frame 41 on LH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 41 on LH side. Refer to Fig. A-FFAAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 02 and Fig. A-FBAAA Sheet 08 1 The Frame have been preventively repaired as per Service Bulletin No. A300-53-6111:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 41 on LH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 41 on LH side, at the interval given in the table 3 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action.
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 104 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 41 on LH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 41 on LH side, at the threshold given in the table 3 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (2) Subtask 536177-832-002-002 - Do a Detailed Inspection of the Frame Foot at FR41 on RH Side Work Zones and Access Panels Zone Access/Work location 148 Access Door 147BZ Work location Frame 41 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 105 5

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

# @A300-600 SERVICE BULLETIN
References Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FFBAA Flow Chart for Frame 41 on RH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 41 on RH side. Refer to Fig. A-FFBAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 02 and Fig. A-FBAAA Sheet 08 1 The Frame have been preventively repaired as per Service Bulletin No. A300-53-6111:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 41 on RH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 41 on RH side, at the interval given in the table 3 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action.
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 106 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 41 on RH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 41 on RH side, at the threshold given in the table 3 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (3) Subtask 536177-832-003-002 - Do a Detailed Inspection of the Frame Foot at FR42 on LH Side Work Zones and Access Panels Zone Access/Work location 147 Access Door 147BZ Work location Frame 42 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 107 5

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

# @A300-600 SERVICE BULLETIN
References Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FFCAA Flow Chart for Frame 42 on LH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 42 on LH side. Refer to Fig. A-FFCAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 03 and Fig. A-FBAAA Sheet 08 1 The Frame have been preventively repaired as per Service Bulletin No. A300-53-6111:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 42 on LH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 42 on LH side, at the interval given in the table 3 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action.
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 108 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 42 on LH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 42 on LH side, at the threshold given in the table 3 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (4) Subtask 536177-832-004-002 - Do a Detailed Inspection of the Frame Foot at FR42 on RH Side Work Zones and Access Panels Zone Access/Work location 148 Access Door 147BZ Work location Frame 42 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 109 5

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

# @A300-600 SERVICE BULLETIN
References Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 Fig. A-FFDAA Flow Chart for Frame 42 on RH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 42 on RH side. Refer to Fig. A-FFDAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 03 and Fig. A-FBAAA Sheet 08 1 The Frame have been preventively repaired as per Service Bulletin No. A300-53-6111:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 42 on RH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 42 on RH side, at the interval given in the table 3 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action.
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 110 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 42 on RH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 42 on RH side, at the threshold given in the table 3 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (5) Subtask 536177-832-005-002 - Do a Detailed Inspection of the Frame Foot at FR43 on LH Side Work Zones and Access Panels Zone Access/Work location 147 Access Door 147BZ Work location Frame 43 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 111 5

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

# @A300-600 SERVICE BULLETIN
References Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FFEAA Flow Chart for Frame 43 on LH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 43 on LH side. Refer to Fig. A-FFEAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet 08 1 The Frame have been preventively repaired as per Service Bulletin No. A300-53-6111:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 43 on LH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 43 on LH side, at the interval given in the table 3 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action.
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 112 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 43 on LH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 43 on LH side, at the threshold given in the table 3 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (6) Subtask 536177-832-006-002 - Do a Detailed Inspection of the Frame Foot at FR43 on RH Side Work Zones and Access Panels Zone Access/Work location 148 Access Door 147BZ Work location Frame 43 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 113 5

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

# @A300-600 SERVICE BULLETIN
References Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FFFAA Flow Chart for Frame 43 on RH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 43 on RH side. Refer to Fig. A-FFFAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet 08 1 The Frame have been preventively repaired as per Service Bulletin No. A300-53-6111:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 43 on RH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 43 on RH side, at the interval given in the table 3 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action.
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 114 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 43 on RH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 43 on RH side, at the threshold given in the table 3 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (7) Subtask 536177-832-007-002 - Do a Detailed Inspection of the Frame Foot at FR44 on LH Side Work Zones and Access Panels Zone Access/Work location 147 Access Door 147BZ Work location Frame 44 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 115 5

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

# @A300-600 SERVICE BULLETIN
References Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FFGAA Flow Chart for Frame 44 on LH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 44 on LH side. Refer to Fig. A-FFGAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 05 and Fig. A-FBAAA Sheet 08 1 The Frame have been preventively repaired as per Service Bulletin No. A300-53-6111:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 44 on LH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 44 on LH side, at the interval given in the table 3 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action.
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 116 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 44 on LH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 44 on LH side, at the threshold given in the table 3 planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (8) Subtask 536177-832-008-002 - Do a Detailed Inspection of the Frame Foot at FR44 on RH Side Work Zones and Access Panels Zone Access/Work location 148 Access Door 147BZ Work location Frame 44 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 117 5

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

# @A300-600 SERVICE BULLETIN
References Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FFHAA Flow Chart for Frame 44 on RH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 44 on RH side. Refer to Fig. A-FFHAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 05 and Fig. A-FBAAA Sheet 08 1 The Frame have been preventively repaired as per Service Bulletin No. A300-53-6111:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 44 on RH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 44 on RH side, at the interval given in the table 3 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action.
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 118 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 44 on RH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 44 on RH side, at the threshold given in the table 3 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (9) Subtask 536177-832-009-002 - Do a Detailed Inspection of the Frame Foot at FR45 on LH Side Work Zones and Access Panels Zone Access/Work location 147 Access Door 147BZ Work location Frame 45 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 119 5

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

# @A300-600 SERVICE BULLETIN
References Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FFIAA Flow Chart for Frame 45 on LH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 45 on LH side. Refer to Fig. A-FFIAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 06 and Fig. A-FBAAA Sheet 08 1 The Frame have been preventively repaired as per Service Bulletin No. A300-53-6111:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 45 on LH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 45 on LH side, at the interval given in the table 3 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action.
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 120 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 45 on LH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 45 on LH side, at the threshold given in the table 3 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (10) Subtask 536177-832-010-002 - Do a Detailed Inspection of the Frame Foot at FR45 on RH Side Work Zones and Access Panels Zone Access/Work location 148 Access Door 147AZ Work location Frame 45 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 121 5

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

# @A300-600 SERVICE BULLETIN
References Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FFJAA Flow Chart for Frame 45 on RH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 45 on RH side. Refer to Fig. A-FFJAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 06 and Fig. A-FBAAA Sheet 08 1 The Frame have been preventively repaired as per Service Bulletin No. A300-53-6111:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 45 on RH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 45 on RH side, at the interval given in the table 3 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action.
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 122 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 45 on RH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 45 on RH side, at the threshold given in the table 3 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (11) Subtask 536177-832-011-002 - Do a Detailed Inspection of the Frame Foot at FR46 on LH Side Work Zones and Access Panels Zone Access/Work location 147 Access Door 147BZ Work location Frame 46 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 123 5

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

# @A300-600 SERVICE BULLETIN
References Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 Fig. A-FFKAA Flow Chart for Frame 46 on LH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 46 on LH side. Refer to Fig. A-FFKAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 07 and Fig. A-FBAAA Sheet 08 1 The Frame have been preventively repaired as per Service Bulletin No. A300-53-6111:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 46 on LH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 46 on LH side, at the interval given in the table 3 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action.
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 124 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 46 on LH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 46 on LH side, at the threshold given in the table 3 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (12) Subtask 536177-832-012-002 - Do a Detailed Inspection of the Frame Foot at FR46 on RH Side Work Zones and Access Panels Zone Access/Work location 148 Access Door 147BZ Work location Frame 46 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 125 5

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

# @A300-600 SERVICE BULLETIN
References Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 Fig. A-FFLAA Flow Chart for Frame 46 on RH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 46 on RH side. Refer to Fig. A-FFLAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 07 and Fig. A-FBAAA Sheet 08 1 The Frame have been preventively repaired as per Service Bulletin No. A300-53-6111:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 1 and the area 2 of Frame foot at Frame 46 on RH side. <1> If crack is not found in area 1 or area 2: <a> Repeat the inspection of the Frame foot at Frame 46 on RH side, at the interval given in the table 3 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action.
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 126 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 1 or area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 46 on RH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 46 on RH side, at the threshold given in the table 3 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. **CONF 003 (1) Subtask 536177-832-001-003 - Do a Detailed Inspection of the Frame Foot at FR41 on LH Side Work Zones and Access Panels Zone Access/Work location 147 Access Door 147BZ Work location Frame 41 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 127 5

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

# @A300-600 SERVICE BULLETIN
References Drawing R53810329 Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FFAAA Flow Chart for Frame 41 on LH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 41 on LH side. Refer to Fig. A-FFAAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 02 and Fig. A-FBAAA Sheet 08 1 The Frame have been repaired in area 1 as per Service Bulletin No. A300-53-6111 or R53810329:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 2 of Frame foot at Frame 41 on LH side. <1> If crack is not found in area 2: <a> Repeat the inspection of the Frame foot at Frame 41 on LH side, at the interval given in the table 4 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 128 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 41 on LH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 41 on LH side, at the threshold given in the table 4 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (2) Subtask 536177-832-002-003 - Do a Detailed Inspection of the Frame Foot at FR41 on RH Side Work Zones and Access Panels Zone Access/Work location 148 Access Door 147BZ Work location Frame 41 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 129 5

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

# @A300-600 SERVICE BULLETIN
References Drawing R53810329 Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FFBAA Flow Chart for Frame 41 on RH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 41 on RH side. Refer to Fig. A-FFBAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 02 and Fig. A-FBAAA Sheet 08 1 The Frame have been repaired in area 1 as per Service Bulletin No. A300-53-6111 or R53810329:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 2 of Frame foot at Frame 41 on RH side. <1> If crack is not found in area 2: <a> Repeat the inspection of the Frame foot at Frame 41 on RH side, at the interval given in the table 4 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 130 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 41 on RH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 41 on RH side, at the threshold given in the table 4 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (3) Subtask 536177-832-003-003 - Do a Detailed Inspection of the Frame Foot at FR42 on LH Side Work Zones and Access Panels Zone Access/Work location 147 Access Door 147BZ Work location Frame 42 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 131 5

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# @A300-600 SERVICE BULLETIN
References Drawing R53810330 Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FFCAA Flow Chart for Frame 42 on LH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 42 on LH side. Refer to Fig. A-FFCAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 03 and Fig. A-FBAAA Sheet 08 1 The Frame have been repaired in area 1 as per Service Bulletin No. A300-53-6111 or R53810330:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 2 of Frame foot at Frame 42 on LH side. <1> If crack is not found in area 2: <a> Repeat the inspection of the Frame foot at Frame 42 on LH side, at the interval given in the table 4 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 132 5

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# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 42 on LH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 42 on LH side, at the threshold given in the table 4 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (4) Subtask 536177-832-004-003 - Do a Detailed Inspection of the Frame Foot at FR42 on RH Side Work Zones and Access Panels Zone Access/Work location 148 Access Door 147BZ Work location Frame 42 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 133 5

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# @A300-600 SERVICE BULLETIN
References Drawing R53810330 Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 Fig. A-FFDAA Flow Chart for Frame 42 on RH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 42 on RH side. Refer to Fig. A-FFDAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 03 and Fig. A-FBAAA Sheet 08 1 The Frame have been repaired in area 1 as per Service Bulletin No. A300-53-6111 or R53810330:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 2 of Frame foot at Frame 42 on RH side. <1> If crack is not found in area 2: <a> Repeat the inspection of the Frame foot at Frame 42 on RH side, at the interval given in the table 4 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 134 5

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# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 42 on RH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 42 on RH side, at the threshold given in the table 4 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (5) Subtask 536177-832-005-003 - Do a Detailed Inspection of the Frame Foot at FR43 on LH Side Work Zones and Access Panels Zone Access/Work location 147 Access Door 147BZ Work location Frame 43 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 135 5

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# @A300-600 SERVICE BULLETIN
References Drawing R53810331 Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FFEAA Flow Chart for Frame 43 on LH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 43 on LH side. Refer to Fig. A-FFEAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet 08 1 The Frame have been repaired in area 1 as per Service Bulletin No. A300-53-6111 or R53810331:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 2 of Frame foot at Frame 43 on LH side. <1> If crack is not found in area 2: <a> Repeat the inspection of the Frame foot at Frame 43 on LH side, at the interval given in the table 4 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 136 5

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# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 43 on LH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 43 on LH side, at the threshold given in the table 4 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (6) Subtask 536177-832-006-003 - Do a Detailed Inspection of the Frame Foot at FR43 on RH Side Work Zones and Access Panels Zone Access/Work location 148 Access Door 147BZ Work location Frame 43 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 137 5

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# @A300-600 SERVICE BULLETIN
References Drawing R53810331 Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FFFAA Flow Chart for Frame 43 on RH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 43 on RH side. Refer to Fig. A-FFFAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet 08 1 The Frame have been repaired in area 1 as per Service Bulletin No. A300-53-6111 or R53810331:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 2 of Frame foot at Frame 43 on RH side. <1> If crack is not found in area 2: <a> Repeat the inspection of the Frame foot at Frame 43 on RH side, at the interval given in the table 4 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 138 5

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# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 43 on RH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 43 on RH side, at the threshold given in the table 4 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (7) Subtask 536177-832-007-003 - Do a Detailed Inspection of the Frame Foot at FR44 on LH Side Work Zones and Access Panels Zone Access/Work location 147 Access Door 147BZ Work location Frame 44 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 139 5

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

# @A300-600 SERVICE BULLETIN
References Drawing R53810332 Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FFGAA Flow Chart for Frame 44 on LH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 44 on LH side. Refer to Fig. A-FFGAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 05 and Fig. A-FBAAA Sheet 08 1 The Frame have been repaired in area 1 as per Service Bulletin No. A300-53-6111 or R53810332:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 2 of Frame foot at Frame 44 on LH side. <1> If crack is not found in area 2: <a> Repeat the inspection of the Frame foot at Frame 44 on LH side, at the interval given in the table 4 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 140 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 44 on LH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 44 on LH side, at the threshold given in the table 4 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (8) Subtask 536177-832-008-003 - Do a Detailed Inspection of the Frame Foot at FR44 on RH Side Work Zones and Access Panels Zone Access/Work location 148 Access Door 147BZ Work location Frame 44 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 141 5

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

# @A300-600 SERVICE BULLETIN
References Drawing R53810332 Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FFHAA Flow Chart for Frame 44 on RH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 44 on RH side. Refer to Fig. A-FFHAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 05 and Fig. A-FBAAA Sheet 08 1 The Frame have been repaired in area 1 as per Service Bulletin No. A300-53-6111 or R53810332:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 2 of Frame foot at Frame 44 on RH side. <1> If crack is not found in area 2: <a> Repeat the inspection of the Frame foot at Frame 44 on RH side, at the interval given in the table 4 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 142 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 44 on RH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 44 on RH side, at the threshold given in the table 4 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (9) Subtask 536177-832-009-003 - Do a Detailed Inspection of the Frame Foot at FR45 on LH Side Work Zones and Access Panels Zone Access/Work location 148 Access Door 147BZ Work location Frame 45 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 143 5

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

# @A300-600 SERVICE BULLETIN
References Drawing R53810322 Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FFIAA Flow Chart for Frame 45 on LH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 45 on LH side. Refer to Fig. A-FFIAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 06 and Fig. A-FBAAA Sheet 08 1 The Frame have been repaired in area 1 as per Service Bulletin No. A300-53-6111 or R53810322:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 2 of Frame foot at Frame 45 on LH side. <1> If crack is not found in area 2: <a> Repeat the inspection of the Frame foot at Frame 45 on LH side, at the interval given in the table 4 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 144 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 45 on LH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 45 on LH side, at the threshold given in the table 4 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (10) Subtask 536177-832-010-003 - Do a Detailed Inspection of the Frame Foot at FR45 on RH Side Work Zones and Access Panels Zone Access/Work location 148 Access Door 147BZ Work location Frame 45 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 145 5

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

# @A300-600 SERVICE BULLETIN
References Drawing R53810322 Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FFJAA Flow Chart for Frame 45 on RH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 45 on RH side. Refer to Fig. A-FFJAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 06 and Fig. A-FBAAA Sheet 08 1 The Frame have been repaired in area 1 as per Service Bulletin No. A300-53-6111 or R53810322:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 2 of Frame foot at Frame 45 on RH side. <1> If crack is not found in area 2: <a> Repeat the inspection of the Frame foot at Frame 45 on RH side, at the interval given in the table 4 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 146 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 45 on RH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 45 on RH side, at the threshold given in the table 4 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (11) Subtask 536177-832-011-003 - Do a Detailed Inspection of the Frame Foot at FR46 on LH Side Work Zones and Access Panels Zone Access/Work location 147 Access Door 147BZ Work location Frame 46 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 147 5

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

# @A300-600 SERVICE BULLETIN
References Drawing R53810323 Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 Fig. A-FFKAA Flow Chart for Frame 46 on LH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 46 on LH side. Refer to Fig. A-FFKAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 07 and Fig. A-FBAAA Sheet 08 1 The Frame have been repaired in area 1 as per Service Bulletin No. A300-53-6111 or R53810323:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 2 of Frame foot at Frame 46 on LH side. <1> If crack is not found in area 2: <a> Repeat the inspection of the Frame foot at Frame 46 on LH side, at the interval given in the table 4 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 148 5

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

# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 46 on LH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 46 on LH side, at the threshold given in the table 4 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. (12) Subtask 536177-832-012-003 - Do a Detailed Inspection of the Frame Foot at FR46 on RH Side Work Zones and Access Panels Zone Access/Work location 148 Access Door 147BZ Work location Frame 46 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 149 5

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

# @A300-600 SERVICE BULLETIN
References Drawing R53810323 Service Bulletin (SB) A300-53-6111 A300-53-6176 Fig. A-FBAAA Inspection areas Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Fig. A-FFLAA Flow Chart for Frame 46 on RH side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FRAAA Inspection report Sheet 01 Sheet 02 (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): Do a detailed inspection of the Frame foot at Frame 46 on RH side. Refer to Fig. A-FFLAA Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 07 and Fig. A-FBAAA Sheet 08 1 The Frame have been repaired in area 1 as per Service Bulletin No. A300-53-6111 or R53810323:
a Clean the inspected areas with: Non Aqueous Cleaner - General 08BAA9 As required
b Do a detailed inspection of the area 2 of Frame foot at Frame 46 on RH side. <1> If crack is not found in area 2: <a> Repeat the inspection of the Frame foot at Frame 46 on RH side, at the interval given in the table 4 of the planning information paragraph E.(2). OR <b> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 150 5

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# @A300-600 SERVICE BULLETIN
<2> If crack is found in area 2: NOTE : If crack is higher than 30 mm (1.181 in.): - Inform AIRBUS and send the affected Frame foot for laboratory investigation. - Perform the following steps. <a> Apply Service Bulletin No. A300-53-6176 before next flight. and No further action. OR <b> Replace the cracked Frame foot at Frame 46 on RH side before next flight, in accordance with TASK 536177-833-801 001 Repair . and Repeat the inspection of the replaced Frame foot at Frame 46 on RH side, at the threshold given in the table 4 of the planning information paragraph E.(2). (b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA

. **CONF 004 None **CONF ALL D. TEST **CONF 001 None **CONF 002 None **CONF 003 None **CONF 004 None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 151 5

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# @A300-600 SERVICE BULLETIN
**CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 536177-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001 32-12-11, Page Block 301 NOTE : If you intend to accomplish an associated Repair Task during the same layover period, the subsequent Close-up procedure is not necessary. (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Close the access door 147BZ, refer to AMM 06-41-53, Page Block 001. (c) Remove the access platform(s). (d) Close the MLG door, refer to AMM 32-12-11, Page Block 301. (e) Put the aircraft back to its initial configuration. **CONF 002 (1) Subtask 536177-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001 32-12-11, Page Block 301 NOTE : If you intend to accomplish an associated Repair Task during the same layover period, the subsequent Close-up procedure is not necessary. (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Close the access door 147BZ, refer to AMM 06-41-53, Page Block 001. (c) Remove the access platform(s). (d) Close the MLG door, refer to AMM 32-12-11, Page Block 301. (e) Put the aircraft back to its initial configuration. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 152 5

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# @A300-600 SERVICE BULLETIN
**CONF 003 (1) Subtask 536177-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001 32-12-11, Page Block 301 NOTE : If you intend to accomplish an associated Repair Task during the same layover period, the subsequent Close-up procedure is not necessary. (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Close the access door 147BZ, refer to AMM 06-41-53, Page Block 001. (c) Remove the access platform(s). (d) Close the MLG door, refer to AMM 32-12-11, Page Block 301. (e) Put the aircraft back to its initial configuration. **CONF 004 None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 153 5

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# @A300-600 SERVICE BULLETIN

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DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 154 5

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# @A300-600 SERVICE BULLETIN Task 536177-833-801-001 - Repair **CONF ALL WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : THIS PROCEDURE USES A FUEL SYSTEM ITEM THAT IS IN A CATEGORY KNOWN AS A CRITICAL DESIGN CONFIGURATION CONTROL LIMITATION (CDCCL). CDCCL IDENTIFIES AN ITEM THAT CAN BE THE SOURCE OF A POSSIBLE FUEL TANK IGNITION. YOU MUST KEEP ALL CDCCL ITEMS IN THE APPROVED CONFIGURATION. DAMAGE, WEAR OR CHANGES TO A CDCCL ITEM CAN CAUSE A POSSIBLE FUEL TANK EXPLOSION. MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY INSTALLED ON THE LANDING GEAR. THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING GEAR. MAKE SURE THAT YOU HAVE THE CORRECT FIRE FIGHTING EQUIPMENT AVAILABLE. ISOLATE ALL THE AIRCRAFT ELECTRICAL CIRCUITS. UNWANTED ELECTRICAL POWER CAN BE DANGEROUS. 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. TheRE IS CONTAMINATION REFER TO ESPM 20-55-00. CAUTION : DO NOT REPLACE TWO CONSECUTIVE FRAME FEET AT THE SAME TIME. REPLACE THE FRAME FEET AT FR41 AND/OR FR43 AND/OR FR45 FIRST, THEN REPLACE THE FRAME FEET AT FR42 AND/OR FR44 AND/OR FR46. NOTE : The accomplishment instructions of this Service Bulletin include procedures given in other documents or in other sections of the Service Bulletin. When the words "refer to" are used and the operator has a procedure accepted by the local authority he belongs to, the accepted alternative procedure can be used. When the words "in accordance with" are used then the given procedure must be followed. NOTE : The access and close-up instructions, not comprising return to service tests, in this Service Bulletin do not constitute or affect the technical intent of the Service DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 155 5

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# @A300-600 SERVICE BULLETIN Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or close-up steps to add flexibility to their maintenance operations as long as the technical intent of the Service Bulletin is met within the set parameters. NOTE : Manual titles given in the accomplishment instructions are referred to by acronyms. Refer to paragraph 1.J., References, for the definition of acronyms. NOTE : This Service Bulletin is classified mandatory or expected to be classified mandatory by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from those given in the Service Bulletin, as long as the RC paragraphs can be done and the aircraft can be put back into a serviceable condition. Task Associated Data **CONF 001 Zone 140 Manpower TOTAL MANHOURS 541.00 ELAPSED TIME (HOURS) 42.00 **CONF 002 Zone 140 Manpower TOTAL MANHOURS 541.00 ELAPSED TIME (HOURS) 42.00 **CONF 003 Zone 140 Manpower TOTAL MANHOURS 541.00 ELAPSED TIME (HOURS) 42.00 **CONF 004 None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 156 5

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# @A300-600 SERVICE BULLETIN
**CONF ALL A. GENERAL **CONF 001 (1) Subtask 536177-910-003-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-00, Page Block 001 20-21-12, Page Block 001 20-28-11, Page Block 001 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-51-20 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 51-40-40 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001. (d) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Material List (CML). (e) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page Block 001. (f) Remove and install fasteners in accordance with SRM 51-40-20. (g) Apply sealant in accordance with SRM 51-24-00. (h) Obtain fastener hole diameters and drill data in accordance with SRM 51-40-40. (i) Obtain alternative and substitute fastener data in accordance with SRM 51-40-30. (j) If alternative and substitute fasteners have to be used, you must make sure that the associated nut/collar are compatible in accordance with SRM 51-40-00 "Mating Part" column.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 157 5

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# @A300-600 SERVICE BULLETIN (k) 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. (l) Put all the retained hardware in identified plastic bags and attach the bags to the related unit. (m) For the electrical bonding, refer to ESPM 20-51-20 and AMM 20-28-11, Page Block 001. (2) Subtask 536177-839-002-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 002 (1) Subtask 536177-910-003-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-00, Page Block 001 20-21-12, Page Block 001 20-28-11, Page Block 001 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-51-20 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 51-40-40 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001. (d) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Material List (CML). (e) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page Block 001. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 158 5

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# @A300-600 SERVICE BULLETIN (f) Remove and install fasteners in accordance with SRM 51-40-20. (g) Apply sealant in accordance with SRM 51-24-00. (h) Obtain fastener hole diameters and drill data in accordance with SRM 51-40-40. (i) Obtain alternative and substitute fastener data in accordance with SRM 51-40-30. (j) If alternative and substitute fasteners have to be used, you must make sure that the associated nut/collar are compatible in accordance with SRM 51-40-00 "Mating Part" column. (k) 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. (l) Put all the retained hardware in identified plastic bags and attach the bags to the related unit. (m) For the electrical bonding, refer to ESPM 20-51-20 and AMM 20-28-11, Page Block 001. (2) Subtask 536177-839-002-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 003 (1) Subtask 536177-910-003-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-00, Page Block 001 20-21-12, Page Block 001 20-28-11, Page Block 001 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-51-20 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 51-40-40 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 159 5

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# @A300-600 SERVICE BULLETIN (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001. (d) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Material List (CML). (e) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page Block 001. (f) Remove and install fasteners in accordance with SRM 51-40-20. (g) Apply sealant in accordance with SRM 51-24-00. (h) Obtain fastener hole diameters and drill data in accordance with SRM 51-40-40. (i) Obtain alternative and substitute fastener data in accordance with SRM 51-40-30. (j) If alternative and substitute fasteners have to be used, you must make sure that the associated nut/collar are compatible in accordance with SRM 51-40-00 "Mating Part" column. (k) 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. (l) Put all the retained hardware in identified plastic bags and attach the bags to the related unit. (m) For the electrical bonding, refer to ESPM 20-51-20 and AMM 20-28-11, Page Block 001. (2) Subtask 536177-839-002-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 004 None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 160 5

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# @A300-600 SERVICE BULLETIN
**CONF ALL B. PREPARATION **CONF 001 (1) Subtask 536177-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001 24-00-00, Page Block 301 28-00-00, Page Block 301 28-10-00, Page Block 301 28-11-29, Page Block 401 28-13-21, Page Block 401 28-25-00, Page Block 301 32-12-11, Page Block 301 WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY INSTALLED ON THE LANDING GEAR. DO NOT CONNECT GROUND POWER OR SWITCH ON ANY AIRCRAFT ELECTRICAL SYSTEM UNTIL THE FUEL TANKS have been COMPLETELY DRAINED AND VENTED. MAKE CERTAIN THAT FIRE EQUIPMENT IS AVAILABLE AND ADEQUATE. OBEY THE FUEL SERVICING SAFETY INSTRUCTIONS. NOTE : If you intend to accomplish this Repair Task during the same layover period as the associated Inspection, the subsequent Preparation procedure is not necessary, except the defueling and the degassing of the center tank, the openning of the access doors 147AZ and 148AZ and the removal of the vapor seal. NOTE : The items given in this note shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear) - Engine shut down, thrust reversers closed and locked - Aircraft in clean configuration - Parking brake applied - Aircraft electrical network de-energized DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 161 5

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# @A300-600 SERVICE BULLETIN - Hydraulic systems depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position (a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (b) Open the Main Landing Gear (MLG) door, refer to AMM 32-12-11, Page Block 301. (c) Put an access platform in position at zone 140. (d) Open the access door 147BZ, refer to AMM 06-41-53, Page Block 001. (e) Defuel the center fuel tank, refer to AMM 28-25-00, Page Block 301. (f) Degas and ventilate the center fuel tank, refer to AMM 28-00-00, Page Block 301 and refer to AMM 28-10-00, Page Block 301. (g) Open the access doors 147AZ and 148AZ, refer to AMM 28-11-29, Page Block 401. (h) Remove the vapor seal to get access to the Frame foot fittings to be replaced, refer to AMM 28-13-21, Page Block 401. **CONF 002 (1) Subtask 536177-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001 24-00-00, Page Block 301 28-00-00, Page Block 301 28-10-00, Page Block 301 28-11-29, Page Block 401 28-13-21, Page Block 401 28-25-00, Page Block 301 32-12-11, Page Block 301

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 162 5

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# @A300-600 SERVICE BULLETIN
WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY INSTALLED ON THE LANDING GEAR. DO NOT CONNECT GROUND POWER OR SWITCH ON ANY AIRCRAFT ELECTRICAL SYSTEM UNTIL THE FUEL TANKS have been COMPLETELY DRAINED AND VENTED. MAKE CERTAIN THAT FIRE EQUIPMENT IS AVAILABLE AND ADEQUATE. OBEY THE FUEL SERVICING SAFETY INSTRUCTIONS. NOTE : If you intend to accomplish this Repair Task during the same layover period as the associated Inspection, the subsequent Preparation procedure is not necessary, except the defueling and the degassing of the center tank, the openning of the access doors 147AZ and 148AZ and the removal of the vapor seal. NOTE : The items given in this note shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear) - Engine shut down, thrust reversers closed and locked - Aircraft in clean configuration - Parking brake applied - Aircraft electrical network de-energized - Hydraulic systems depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position (a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (b) Open the Main Landing Gear (MLG) door, refer to AMM 32-12-11, Page Block 301. (c) Put an access platform in position at zone 140. (d) Open the access door 147BZ, refer to AMM 06-41-53, Page Block 001. (e) Defuel the center fuel tank, refer to AMM 28-25-00, Page Block 301. (f) Degas and ventilate the center fuel tank, refer to AMM 28-00-00, Page Block 301 and refer to AMM 28-10-00, Page Block 301. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 163 5

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# @A300-600 SERVICE BULLETIN (g) Open the access doors 147AZ and 148AZ, refer to AMM 28-11-29, Page Block 401. (h) Remove the vapor seal to get access to the Frame foot fittings to be replaced, refer to AMM 28-13-21, Page Block 401. **CONF 003 (1) Subtask 536177-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001 24-00-00, Page Block 301 28-00-00, Page Block 301 28-10-00, Page Block 301 28-11-29, Page Block 401 28-13-21, Page Block 401 28-25-00, Page Block 301 32-12-11, Page Block 301 WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY INSTALLED ON THE LANDING GEAR. DO NOT CONNECT GROUND POWER OR SWITCH ON ANY AIRCRAFT ELECTRICAL SYSTEM UNTIL THE FUEL TANKS have been COMPLETELY DRAINED AND VENTED. MAKE CERTAIN THAT FIRE EQUIPMENT IS AVAILABLE AND ADEQUATE. OBEY THE FUEL SERVICING SAFETY INSTRUCTIONS. NOTE : If you intend to accomplish this Repair Task during the same layover period as the associated Inspection, the subsequent Preparation procedure is not necessary, except the defueling and the degassing of the center tank, the openning of the access doors 147AZ and 148AZ and the removal of the vapor seal. NOTE : The items given in this note shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear) - Engine shut down, thrust reversers closed and locked - Aircraft in clean configuration - Parking brake applied DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 164 5

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# @A300-600 SERVICE BULLETIN - Aircraft electrical network de-energized - Hydraulic systems depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position (a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (b) Open the Main Landing Gear (MLG) door, refer to AMM 32-12-11, Page Block 301. (c) Put an access platform in position at zone 140. (d) Open the access door 147BZ, refer to AMM 06-41-53, Page Block 001. (e) Defuel the center fuel tank, refer to AMM 28-25-00, Page Block 301. (f) Degas and ventilate the center fuel tank, refer to AMM 28-00-00, Page Block 301 and refer to AMM 28-10-00, Page Block 301. (g) Open the access doors 147AZ and 148AZ, refer to AMM 28-11-29, Page Block 401. (h) Remove the vapor seal to get access to the Frame foot fittings to be replaced, refer to AMM 28-13-21, Page Block 401. **CONF 004 None **CONF ALL C. PROCEDURE CAUTION : DO NOT REPLACE TWO CONSECUTIVE FRAME FEET AT THE SAME TIME. REPLACE THE FRAME FEET AT FR41 AND/OR FR43 AND/OR FR45 FIRST, THEN REPLACE THE FRAME FEET AT FR42 AND/OR FR44 AND/OR FR46. **CONF 001 (1) Subtask 536177-831-001-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR41, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 165 5

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# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 41, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 20 Rivet Item (19) Discard And: 32 Rivet Item (5) Discard or 32 Bolt Item (3) Discard 32 Nut Item (4) Discard

(2) Subtask 536177-831-002-001 - Depending on Inspection results, remove the Gussets from FR41, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME
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# @A300-600 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-40-20 Fig. A-FLAAA Removal/Installation of the Gussets at FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 41, LH side. Refer to Fig. A-FLAAA In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (120) Retain 1 Gusset Item (122) Retain attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

(3) Subtask 536177-831-003-003 - Depending on Inspection results, remove the Frame Foot from FR41, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FCAAC Replacement of the Frame foot FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Remove the Frame foot from Frame 41, LH side. Refer to Fig. A-FCAAC In accordance with SRM 51-40-20 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 167 5

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# @A300-600 SERVICE BULLETIN
1 Remove: 1 Frame foot Item (100) Discard 1 Stiffener Item (58) Retain 1 Splice Item (60) Retain 4 Screw Item (55) Retain 4 Nut Item (56) Discard 33 Screw Item (3) Discard 33 Nut Item (4) Discard 2 Rivet Item (19) Discard And: 11 Rivet Item (5) Discard or 11 Rivet Item (6) Discard 11 Bush Item (7) Discard

(4) Subtask 536177-831-004-003 - Depending on Inspection results, install an identical Frame Foot at FR41, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A03R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 36 NUT 12 ASNA2529-6 2 NUT 14 NAS1726-5E 2 NUT 16 ASNA2529-5 4 NUT DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 168 5

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 19 ASNA2050DXJ4020 2 RIVET 21 ASNA2529-4 2 NUT 23 EN6115V3X5 15 SCREW 24 EN6115V3X7 6 SCREW 25 EN6115V3X6 13 SCREW 26 EN6114V6X14 2 SCREW 27 ASNA2001V5-8X 2 SCREW 28 EN6114V5X8 4 SCREW 29 EN6115V3X4 2 SCREW 30 EN6114V4X8 1 SCREW 31 EN6114V4X10 1 SCREW 56 NSA5057-6 4 NUT 100 A5711112920095 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FCAAC Replacement of the Frame foot FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Fig. A-FLAAA Removal/Installation of the Gussets at FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FCAAC In accordance with SRM 51-40-40

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# @A300-600 SERVICE BULLETIN
1 Put all the parts in position as shown on Fig. A-FCAAC

. 1 Frame foot A5711112920095 Item 100 1 Stiffener Item (58) Retained at removal 1 Splice Item (60) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FCAAC Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H1 to H23 and H26 to H31 to the diameter given on Fig. A-FCAAC Sheet 03 and Fig. A-FCAAC Sheet 04

. 3 Drill the holes of the stiffener H45 and H46 to the diameter given on Fig. AFCAAC Sheet 05

. 4 Drill the holes of the splice H32 to H44 to the diameter given on Fig. AFCAAC Sheet 06

. (b) Install the fasteners. Refer to Fig. A-FCAAC In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H1 to H23 and H26 to H31: Refer to Fig. A-FCAAC Sheet 03 to Fig. A-FCAAC Sheet 05 5 Screw EN6115V3X5 Item 23 5 Screw EN6115V3X7 Item 24 13 Screw EN6115V3X6 Item 25 2 Screw ASNA2001V5-8X Item 27 4 Screw EN6114V5X8 Item 28 23 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 170 5

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# @A300-600 SERVICE BULLETIN
4 Nut ASNA2529-5 Item 16 NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FCAAC Sheet 02 4 Screw Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H45 and H46: Refer to Fig. A-FCAAC Sheet 05 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the splice H32 to H44: Refer to Fig. A-FCAAC Sheet 06 10 Screw EN6115V3X5 Item 23 1 Screw EN6115V3X7 Item 24 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 171 5

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# @A300-600 SERVICE BULLETIN
2 Screw EN6115V3X4 Item 29 13 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (c) Install the Gussets at Frame 41, LH side. Refer to Fig. A-FLAAA In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FLAAA Sheet 02 and Fig. AFLAAA Sheet 03

. 1 Gusset Item (120) Retained at removal 1 Gusset Item (122) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H24 and H25 to the diameter given on Fig. A-FLAAA Sheet 03

. 3 Drill holes H47 and H48 to the diameter given on Fig. A-FLAAA Sheet 03

. 4 Install: 1 Gusset Item (120) Retained at removal

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 172 5

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# @A300-600 SERVICE BULLETIN 1 Gusset Item (122) Retained at removal 2 Screw EN6114V6X14 Item 26 1 Screw EN6114V4X8 Item 30 1 Screw EN6114V4X10 Item 31 2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-4 Item 21

(5) Subtask 536177-831-005-001 - Depending on Inspection results, if removed, install the Fasteners at FR41, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 32 NUT 90 ASNA2019-56-25 32 RIVET 91 EN6114V3X5 32 SCREW 92 EN6080D6X-32 20 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 173 5

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

# @A300-600 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 41, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 20 Rivet EN6080D6X-32 Item 92 And: 32 Rivet ASNA2019-56-25 Item 90 or 32 Screw EN6114V3X5 Item 91 32 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(6) Subtask 536177-831-006-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR41, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 174 5

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# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 41, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 20 Rivet Item (19) Discard And: 32 Rivet Item (5) Discard or 32 Bolt Item (3) Discard 32 Nut Item (4) Discard

(7) Subtask 536177-831-007-001 - Depending on Inspection results, remove the Gussets from FR41, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 175 5

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# @A300-600 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-40-20 Fig. A-FLAAA Removal/Installation of the Gussets at FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 41, RH side. Refer to Fig. A-FLAAA In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (121) Retain 1 Gusset Item (123) Retain attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

(8) Subtask 536177-831-008-003 - Depending on Inspection results, remove the Frame Foot from FR41, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FCAAC Replacement of the Frame foot FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Remove the Frame foot from Frame 41, RH side. Refer to Fig. A-FCAAC In accordance with SRM 51-40-20 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 176 5

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# @A300-600 SERVICE BULLETIN
1 Remove: 1 Frame foot Item (101) Discard 1 Stiffener Item (57) Retain 1 Splice Item (59) Retain 4 Screw Item (55) Retain 4 Nut Item (56) Discard 33 Screw Item (3) Discard 33 Nut Item (4) Discard 2 Rivet Item (19) Discard And:: 11 Rivet Item (5) Discard or 11 Rivet Item (6) Discard 11 Bush Item (7) Discard

(9) Subtask 536177-831-009-003 - Depending on Inspection results, install an identical Frame Foot at FR41, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A21R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 36 NUT 12 ASNA2529-6 2 NUT 14 NAS1726-5E 2 NUT 16 ASNA2529-5 4 NUT DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 177 5

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

# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 19 ASNA2050DXJ4020 2 RIVET 21 ASNA2529-4 2 NUT 23 EN6115V3X5 15 SCREW 24 EN6115V3X7 6 SCREW 25 EN6115V3X6 13 SCREW 26 EN6114V6X14 2 SCREW 27 ASNA2001V5-8X 2 SCREW 28 EN6114V5X8 4 SCREW 29 EN6115V3X4 2 SCREW 30 EN6114V4X8 1 SCREW 31 EN6114V4X10 1 SCREW 56 NSA5057-6 4 NUT 101 A5711112920195 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FCAAC Replacement of the Frame foot FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Fig. A-FLAAA Removal/Installation of the Gussets at FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FCAAC In accordance with SRM 51-40-40

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 178 5

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

# @A300-600 SERVICE BULLETIN
1 Put all the parts in position as shown on Fig. A-FCAAC

. 1 Frame foot A5711112920195 Item 101 1 Stiffener Item (57) Retained at removal 1 Splice Item (59) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FCAAC Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H1 to H23 and H26 to H31 to the diameter given on Fig. A-FCAAC Sheet 03 and Fig. A-FCAAC Sheet 04

. 3 Drill the holes of the stiffener H45 and H46 to the diameter given on Fig. AFCAAC Sheet 05

. 4 Drill the holes of the splice H32 to H44 to the diameter given on Fig. AFCAAC Sheet 06

. (b) Install the fasteners. Refer to Fig. A-FCAAC In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H1 to H23 and H26 to H31: Refer to Fig. A-FCAAC Sheet 03 to Fig. A-FCAAC Sheet 05 5 Screw EN6115V3X5 Item 23 5 Screw EN6115V3X7 Item 24 13 Screw EN6115V3X6 Item 25 2 Screw ASNA2001V5-8X Item 27 4 Screw EN6114V5X8 Item 28 23 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 179 5

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# @A300-600 SERVICE BULLETIN
4 Nut ASNA2529-5 Item 16 NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FCAAC Sheet 02 4 Screw Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H45 and H46: Refer to Fig. A-FCAAC Sheet 05 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the splice H32 to H44: Refer to Fig. A-FCAAC Sheet 06 10 Screw EN6115V3X5 Item 23 1 Screw EN6115V3X7 Item 24 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 180 5

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# @A300-600 SERVICE BULLETIN
2 Screw EN6115V3X4 Item 29 13 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (c) Install the Gussets at Frame 41, LH side. Refer to Fig. A-FLAAA In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FLAAA Sheet 02 and Fig. AFLAAA Sheet 03

. 1 Gusset Item (121) Retained at removal 1 Gusset Item (123) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H24 and H25 to the diameter given on Fig. A-FLAAA Sheet 03

. 3 Drill holes H47 and H48 to the diameter given on Fig. A-FLAAA Sheet 03

. 4 Install: 1 Gusset Item (121) Retained at removal

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 181 5

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# @A300-600 SERVICE BULLETIN 1 Gusset Item (123) Retained at removal 2 Screw EN6114V6X14 Item 26 1 Screw EN6114V4X8 Item 30 1 Screw EN6114V4X10 Item 31 2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-4 Item 21

(10) Subtask 536177-831-010-001 - Depending on Inspection results, if removed, install the Fasteners at FR41, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 32 NUT 90 ASNA2019-56-25 32 RIVET 91 EN6114V3X5 32 SCREW 92 EN6080D6X-32 20 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 182 5

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

# @A300-600 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 41, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 20 Rivet EN6080D6X-32 Item 92 And: 32 Rivet ASNA2019-56-25 Item 90 or 32 Screw EN6114V3X5 Item 91 32 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(11) Subtask 536177-831-011-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR42, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 183 5

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# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 42, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard 24 Nut Item (4) Discard

(12) Subtask 536177-831-012-001 - Depending on Inspection results, remove the Gussets from FR42, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 184 5

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

# @A300-600 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-40-20 Fig. A-FNAAA Removal/Installation of the Gussets at FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 42, LH side. Refer to Fig. A-FNAAA In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (124) Retain 1 Gusset Item (126) Retain attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

(13) Subtask 536177-831-013-003 - Depending on Inspection results, remove the Frame Foot from FR42, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FDAAC Replacement of the Frame foot FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Remove the Frame foot from Frame 42, LH side. Refer to Fig. A-FDAAC In accordance with SRM 51-40-20 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 185 5

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# @A300-600 SERVICE BULLETIN
1 Remove: 1 Frame foot Item (102) Discard 1 Stiffener Item (58) Retain 1 Stiffener Item (68) Retain 1 Splice Item (66) Retain 4 Screw Item (55) Retain 4 Nut Item (56) Discard 42 Screw Item (3) Discard 42 Nut Item (4) Discard 6 Rivet Item (19) Discard And: 16 Rivet Item (5) Discard or 16 Rivet Item (6) Discard 16 Bush Item (7) Discard

(14) Subtask 536177-831-014-003 - Depending on Inspection results, install an identical Frame Foot at FR42, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A06R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 48 NUT 12 ASNA2529-6 2 NUT DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 186 5

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 14 NAS1726-5E 2 NUT 16 ASNA2529-5 8 NUT 19 ASNA2050DXJ4020 4 RIVET 21 ASNA2529-4 2 NUT 23 EN6115V3X5 15 SCREW 24 EN6115V3X7 5 SCREW 25 EN6115V3X6 24 SCREW 27 ASNA2001V5-8X 2 SCREW 28 EN6114V5X8 8 SCREW 29 EN6115V3X4 4 SCREW 30 EN6114V4X8 1 SCREW 31 EN6114V4X10 1 SCREW 35 EN6114V6X13 2 SCREW 56 NSA5057-6 4 NUT 102 A5711113020095 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FDAAC Replacement of the Frame foot FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Fig. A-FNAAA Removal/Installation of the Gussets at FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Fig. A-FDAAC In accordance with SRM 51-40-40 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 187 5

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

# @A300-600 SERVICE BULLETIN
1 Put all the parts in position as shown on Fig. A-FDAAC

. 1 Frame foot A5711113020095 Item 102 1 Stiffener Item (58) Retained at removal 1 Stiffener Item (68) Retained at removal 1 Splice Item (66) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FDAAC Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H51 to H78, H83 to H90 and H93 to H102 to the diameter given on Fig. A-FDAAC Sheet 03 to Fig. A-FDAAC Sheet 05

. 3 Drill the holes of the stiffener at STGR 36 H79 and H80 to the diameter given on Fig. A-FDAAC Sheet 05

. NOTE : Use the existing holes of the stringers. 4 Drill the holes of the stiffener at STGR 37 H81, H82, H103 and H104 to the diameter given on Fig. A-FDAAC Sheet 06

. 5 Drill the holes of the splice H105 to H117 to the diameter given on Fig. AFDAAC Sheet 06

. 6 Do the spotfacing of holes H107 to H113 to the dimensions given on Fig. AFDAAC Sheet 06

. (b) Install the fasteners. Fig. A-FDAAC In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H51 to H78, H83 to H90 and H93 to H102: Refer to Fig. A-FDAAC Sheet 03 to Fig. A-FDAAC Sheet 05 5 Screw EN6115V3X5 Item 23 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 188 5

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

# @A300-600 SERVICE BULLETIN
4 Screw EN6115V3X7 Item 24 24 Screw EN6115V3X6 Item 25 2 Screw ASNA2001V5-8X Item 27 8 Screw EN6114V5X8 Item 28 33 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 8 Nut ASNA2529-5 Item 16 NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FDAAC Sheet 02 4 Screw Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffeners at STGR 36 H79 and H80: Refer to Fig. A-FDAAC Sheet 05 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 189 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the stiffener at STGR 37 H81, H82, H103 and H104: Refer to Fig. A-FDAAC Sheet 06 2 Screw EN6115V3X4 Item 29 2 Nut ASNA2529-3 Item 9 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Install the fasteners of the splice H105 to H117: Refer to Fig. A-FDAAC Sheet 06 10 Screw EN6115V3X5 Item 23 1 Screw EN6115V3X7 Item 24 2 Screw EN6115V3X4 Item 29 13 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

6 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 190 5

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# @A300-600 SERVICE BULLETIN (c) Install the Gussets at Frame 42, LH side. Refer to Fig. A-FNAAA In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FNAAA

. 1 Gusset Item (124) Retained at removal 1 Gusset Item (126) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H91 and H92 to the diameter given on Fig. A-FNAAA Sheet 03

. 3 Drill holes H118 and H119 to the diameter given on Fig. A-FNAAA Sheet 03

. 4 Install: 1 Gusset Item (124) Retained at removal 1 Gusset Item (126) Retained at removal 1 Screw EN6114V4X8 Item 30 1 Screw EN6114V4X10 Item 31 2 Screw EN6114V6X13 Item 35 2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-4 Item 21

(15) Subtask 536177-831-015-001 - Depending on Inspection results, if removed, install the Fasteners at FR42, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 191 5

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

# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 90 ASNA2019-56-25 24 RIVET 91 EN6114V3X5 24 SCREW 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 42, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 192 5

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

# @A300-600 SERVICE BULLETIN
1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 24 Rivet ASNA2019-56-25 Item 90 or 24 Screw EN6114V3X5 Item 91 24 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(16) Subtask 536177-831-016-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR42, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 42, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 193 5

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

# @A300-600 SERVICE BULLETIN
And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard 24 Nut Item (4) Discard

(17) Subtask 536177-831-017-001 - Depending on Inspection results, remove the Gussets from FR42, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FNAAA Removal/Installation of the Gussets at FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 42, RH side. Refer to Fig. A-FNAAA In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (125) Retain 1 Gusset Item (127) Retain attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 194 5

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

# @A300-600 SERVICE BULLETIN (18) Subtask 536177-831-018-003 - Depending on Inspection results, remove the Frame Foot from FR42, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FDAAC Replacement of the Frame foot FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Remove the Frame foot from Frame 42, RH side. Refer to Fig. A-FDAAC In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (103) Discard 1 Stiffener Item (57) Retain 1 Stiffener Item (69) Retain 1 Splice Item (67) Retain 4 Screw Item (55) Retain 4 Nut Item (56) Discard 42 Screw Item (3) Discard 42 Nut Item (4) Discard 6 Rivet Item (19) Discard And: DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 195 5

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

# @A300-600 SERVICE BULLETIN 16 Rivet Item (5) Discard or 16 Rivet Item (6) Discard 16 Bush Item (7) Discard

(19) Subtask 536177-831-019-003 - Depending on Inspection results, install an identical Frame Foot at FR42, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A24R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 48 NUT 12 ASNA2529-6 2 NUT 14 NAS1726-5E 2 NUT 16 ASNA2529-5 8 NUT 19 ASNA2050DXJ4020 4 RIVET 21 ASNA2529-4 2 NUT 23 EN6115V3X15 5 SCREW 23 EN6115V3X5 10 SCREW 24 EN6115V3X7 5 SCREW 25 EN6115V3X6 24 SCREW 27 ASNA2001V5-8X 2 SCREW 28 EN6114V5X8 8 SCREW 29 EN6115V3X4 4 SCREW 30 EN6114V4X8 1 SCREW 31 EN6114V4X10 1 SCREW 35 EN6114V6X13 2 SCREW 56 NSA5057-6 4 NUT 103 A5711113020195 1 FOOT

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 196 5

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

# @A300-600 SERVICE BULLETIN
Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FDAAC Replacement of the Frame foot FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Fig. A-FNAAA Removal/Installation of the Gussets at FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Fig. A-FDAAC In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FDAAC

. 1 Frame foot A5711113020195 Item 103 1 Stiffener Item (57) Retained at removal 1 Stiffener Item (69) Retained at removal 1 Splice Item (67) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FDAAC Sheet 03

. NOTE : Between parts apply:
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 197 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H51 to H78, H83 to H90 and H93 to H102 to the diameter given on Fig. A-FDAAC Sheet 03 to Fig. A-FDAAC Sheet 05

. 3 Drill the holes of the stiffener at STGR 36 H79 and H80 to the diameter given on Fig. A-FDAAC Sheet 05

. NOTE : Use the existing holes of the stringers. 4 Drill the holes of the stiffener at STGR 37 H81, H82, H103 and H104 to the diameter given on Fig. A-FDAAC Sheet 06

. 5 Drill the holes of the splice H105 to H117 to the diameter given on Fig. AFDAAC Sheet 06

. 6 Do the spotfacing of holes H107 to H113 to the dimensions given on Fig. AFDAAC Sheet 06

. (b) Install the fasteners. Fig. A-FDAAC In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H51 to H78, H83 to H90 and H93 to H102: Refer to Fig. A-FDAAC Sheet 03 to Fig. A-FDAAC Sheet 05 5 Screw EN6115V3X15 Item 23 4 Screw EN6115V3X7 Item 24 24 Screw EN6115V3X6 Item 25 2 Screw ASNA2001V5-8X Item 27 8 Screw EN6114V5X8 Item 28 33 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 8 Nut ASNA2529-5 Item 16 NOTE : Protect the fasteners head and nuts with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 198 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FDAAC Sheet 02 4 Screw Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffeners at STGR 36 H79 and H80: Refer to Fig. A-FDAAC Sheet 05 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the stiffener at STGR 37 H81, H82, H103 and H104: Refer to Fig. A-FDAAC Sheet 06 2 Screw EN6115V3X4 Item 29 2 Nut ASNA2529-3 Item 9 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 199 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Install the fasteners of the splice H105 to H117: Refer to Fig. A-FDAAC Sheet 06 10 Screw EN6115V3X5 Item 23 1 Screw EN6115V3X7 Item 24 2 Screw EN6115V3X4 Item 29 13 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

6 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (c) Install the Gussets at Frame 42, LH side. Refer to Fig. A-FNAAA In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FNAAA

. 1 Gusset Item (125) Retained at removal

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 200 5

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

# @A300-600 SERVICE BULLETIN 1 Gusset Item (127) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H91 and H92 to the diameter given on Fig. A-FNAAA Sheet 03

. 3 Drill holes H118 and H119 to the diameter given on Fig. A-FNAAA Sheet 03

. 4 Install: 1 Gusset Item (125) Retained at removal 1 Gusset Item (127) Retained at removal 1 Screw EN6114V4X8 Item 30 1 Screw EN6114V4X10 Item 31 2 Screw EN6114V6X13 Item 35 2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-4 Item 21

(20) Subtask 536177-831-020-001 - Depending on Inspection results, if removed, install the Fasteners at FR42, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 90 ASNA2019-56-25 24 RIVET DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 201 5

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 91 EN6114V3X5 24 SCREW 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 42, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 24 Rivet ASNA2019-56-25 Item 90 or 24 Screw EN6114V3X5 Item 91 24 Nut ASNA2529-3 Item 9 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 202 5

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

# @A300-600 SERVICE BULLETIN
NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(21) Subtask 536177-831-021-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR43, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 43, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard 24 Nut Item (4) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 203 5

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# @A300-600 SERVICE BULLETIN (22) Subtask 536177-831-022-001 - Depending on Inspection results, remove the Gussets from FR43, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FPAAA Removal/Installation of the Gussets at FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 43, LH side. Refer to Fig. A-FPAAA In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (128) Retain 1 Gusset Item (130) Retain attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

(23) Subtask 536177-831-023-003 - Depending on Inspection results, remove the Frame Foot from FR43, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 204 5

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# @A300-600 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-40-20 Fig. A-FEAAC Replacement of the Frame foot FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Remove the Frame foot from Frame 43, LH side. Refer to Fig. A-FEAAC In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (104) Discard 1 Stiffener Item (58) Retain 1 Splice Item (72) Retain 4 Bolt Item (55) Retain 4 Nut Item (56) Discard 34 Screw Item (3) Discard 34 Nut Item (4) Discard 2 Rivet Item (19) Discard And: 13 Rivet Item (5) Discard or 13 Rivet Item (6) Discard 13 Bush Item (7) Discard

(24) Subtask 536177-831-024-003 - Depending on Inspection results, install an identical Frame Foot at FR43, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 205 5

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

# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A09R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 39 NUT 12 ASNA2529-6 2 NUT 14 NAS1726-5E 2 NUT 16 ASNA2529-5 5 NUT 19 ASNA2050DXJ4020 2 RIVET 21 ASNA2529-4 1 NUT 23 EN6115V3X5 9 SCREW 24 EN6115V3X7 4 SCREW 25 EN6115V3X6 11 SCREW 26 EN6114V6X14 2 SCREW 27 ASNA2001V5-8X 2 SCREW 28 EN6114V5X8 4 SCREW 30 EN6114V4X8 1 SCREW 39 EN6115V3X9 3 SCREW 40 EN6115V3X8 11 SCREW 41 EN6114V5X10 1 SCREW 56 NSA5057-6 4 NUT 104 A5711113120095 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 206 5

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# @A300-600 SERVICE BULLETIN
References Fig. A-FEAAC Replacement of the Frame foot FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Fig. A-FPAAA Removal/Installation of the Gussets at FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FEAAC In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FEAAC

. 1 Frame foot A5711113120095 Item 104 1 Stiffener Item (58) Retained at removal 1 Splice Item (72) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FEAAC Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H121 to H136, H140 to H149 and H152 to H157 to the diameter given on Fig. A-FEAAC Sheet 03 to Fig. A-FEAAC Sheet 05

. 3 Drill the holes of the stiffener H168 and H169 to the diameter given on Fig. AFEAAC Sheet 05

. 4 Drill the holes of the splice H137 to H139 and H158 to H167 to the diameter given on Fig. A-FEAAC Sheet 06

. (b) Install the fasteners. Fig. A-FEAAC In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 207 5

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

# @A300-600 SERVICE BULLETIN
1 Install the fasteners of the Frame foot H121 to H136, H140 to H149 and H152 to H157: Refer to Fig. A-FEAAC Sheet 03 to Fig. A-FEAAC Sheet 05 5 Screw EN6115V3X5 Item 23 2 Screw EN6115V3X7 Item 24 11 Screw EN6115V3X6 Item 25 2 Screw ASNA2001V5-8X Item 27 4 Screw EN6114V5X8 Item 28 2 Screw EN6115V3X9 Item 39 5 Screw EN6115V3X8 Item 40 26 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 4 Nut ASNA2529-5 Item 16 NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FEAAC Sheet 04 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 208 5

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# @A300-600 SERVICE BULLETIN
3 Install the fasteners of the stiffener at STGR 36 H168 and H169: Refer to Fig. A-FEAAC Sheet 05 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the splice H137 to H139 and H158 to H167: Refer to Fig. A-FEAAC Sheet 06 4 Screw EN6115V3X5 Item 23 2 Screw EN6115V3X7 Item 24 1 Screw EN6115V3X9 Item 39 6 Screw EN6115V3X8 Item 40 13 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (c) Install the Gussets at Frame 43, LH side. Refer to Fig. A-FPAAA In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 209 5

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

# @A300-600 SERVICE BULLETIN Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FPAAA Sheet 02 and Fig. AFPAAA Sheet 03

. 1 Gusset Item (128) Retained at removal 1 Gusset Item (130) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H150 and H151 to the diameter given on Fig. A-FPAAA Sheet 03

. 3 Drill holes H170 and H171 to the diameter given on Fig. A-FPAAA Sheet 03

. 4 Install: 1 Gusset Item (128) Retained at removal 1 Gusset Item (130) Retained at removal 2 Screw EN6114V6X14 Item 26 1 Screw EN6114V4X8 Item 30 1 Screw EN6114V5X10 Item 41 2 Nut ASNA2529-6 Item 12 1 Nut ASNA2529-5 Item 16 1 Nut ASNA2529-4 Item 21

(25) Subtask 536177-831-025-001 - Depending on Inspection results, if removed, install the Fasteners at FR43, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 210 5

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

# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 47 EN6114V3X6 24 SCREW 90 ASNA2019-56-25 24 RIVET 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 43, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 211 5

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

# @A300-600 SERVICE BULLETIN
1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 24 Rivet ASNA2019-56-25 Item 90 or 24 Screw EN6114V3X6 Item 47 24 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(26) Subtask 536177-831-026-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR43, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 43, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 212 5

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

# @A300-600 SERVICE BULLETIN
And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard 24 Nut Item (4) Discard

(27) Subtask 536177-831-027-001 - Depending on Inspection results, remove the Gussets from FR43, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FPAAA Removal/Installation of the Gussets at FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 43, RH side. Refer to Fig. A-FPAAA In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (129) Retain 1 Gusset Item (131) Retain attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 213 5

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

# @A300-600 SERVICE BULLETIN (28) Subtask 536177-831-028-003 - Depending on Inspection results, remove the Frame Foot from FR43, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FEAAC Replacement of the Frame foot FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Remove the Frame foot from Frame 43, RH side. Refer to Fig. A-FEAAC In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (105) Discard 1 Stiffener Item (57) Retain 1 Splice Item (71) Retain 4 Bolt Item (55) Retain 4 Nut Item (56) Discard 34 Screw Item (3) Discard 34 Nut Item (4) Discard 2 Rivet Item (19) Discard And: 13 Rivet Item (5) Discard or DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 214 5

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

# @A300-600 SERVICE BULLETIN 13 Rivet Item (6) Discard 13 Bush Item (7) Discard

(29) Subtask 536177-831-029-003 - Depending on Inspection results, install an identical Frame Foot at FR43, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A27R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 39 NUT 12 ASNA2529-6 2 NUT 14 NAS1726-5E 2 NUT 16 ASNA2529-5 5 NUT 19 ASNA2050DXJ4020 2 RIVET 21 ASNA2529-4 1 NUT 23 EN6115V3X5 9 SCREW 24 EN6115V3X7 4 SCREW 25 EN6115V3X6 11 SCREW 26 EN6114V6X14 2 SCREW 27 ASNA2001V5-8X 2 SCREW 28 EN6114V5X8 4 SCREW 30 EN6114V4X8 1 SCREW 39 EN6115V3X9 3 SCREW 40 EN6115V3X8 11 SCREW 41 EN6114V5X10 1 SCREW 56 NSA5057-6 4 NUT 105 A5711113120195 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 215 5

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

# @A300-600 SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FEAAC Replacement of the Frame foot FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Fig. A-FPAAA Removal/Installation of the Gussets at FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FEAAC In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FEAAC

. 1 Frame foot A5711113120195 Item 105 1 Stiffener Item (57) Retained at removal 1 Splice Item (71) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FEAAC Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H121 to H136, H140 to H149 and H152 to H157 to the diameter given on Fig. A-FEAAC Sheet 03 to Fig. A-FEAAC Sheet 05

. 3 Drill the holes of the stiffener H168 and H169 to the diameter given on Fig. AFEAAC Sheet 05

. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 216 5

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# @A300-600 SERVICE BULLETIN
4 Drill the holes of the splice H137 to H139 and H158 to H167 to the diameter given on Fig. A-FEAAC Sheet 06

. (b) Install the fasteners. Fig. A-FEAAC In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H121 to H136, H140 to H149 and H152 to H157: Refer to Fig. A-FEAAC Sheet 03 to Fig. A-FEAAC Sheet 05 5 Screw EN6115V3X5 Item 23 2 Screw EN6115V3X7 Item 24 11 Screw EN6115V3X6 Item 25 2 Screw ASNA2001V5-8X Item 27 4 Screw EN6114V5X8 Item 28 2 Screw EN6115V3X9 Item 39 5 Screw EN6115V3X8 Item 40 26 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 4 Nut ASNA2529-5 Item 16 NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FEAAC Sheet 04 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with:
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 217 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H168 and H169: Refer to Fig. A-FEAAC Sheet 05 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the splice H137 to H139 and H158 to H167: Refer to Fig. A-FEAAC Sheet 06 4 Screw EN6115V3X5 Item 23 2 Screw EN6115V3X7 Item 24 1 Screw EN6115V3X9 Item 39 6 Screw EN6115V3X8 Item 40 13 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 218 5

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# @A300-600 SERVICE BULLETIN
5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (c) Install the Gussets at Frame 43, LH side. Refer to Fig. A-FPAAA In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FPAAA Sheet 02 and Fig. AFPAAA Sheet 03

. 1 Gusset Item (129) Retained at removal 1 Gusset Item (131) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H150 and H151 to the diameter given on Fig. A-FPAAA Sheet 03

. 3 Drill holes H170 and H171 to the diameter given on Fig. A-FPAAA Sheet 03

. 4 Install: 1 Gusset Item (129) Retained at removal 1 Gusset Item (131) Retained at removal 2 Screw EN6114V6X14 Item 26 1 Screw EN6114V4X8 Item 30 1 Screw EN6114V5X10 Item 41 2 Nut ASNA2529-6 Item 12 1 Nut ASNA2529-5 Item 16 1 Nut ASNA2529-4 Item 21
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 219 5

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

# @A300-600 SERVICE BULLETIN (30) Subtask 536177-831-030-001 - Depending on Inspection results, if removed, install the Fasteners at FR43, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 47 EN6114V3X6 24 SCREW 90 ASNA2019-56-25 24 RIVET 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 220 5

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

# @A300-600 SERVICE BULLETIN (a) If removed, install the fasteners at Frame 43, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 24 Rivet ASNA2019-56-25 Item 90 or 24 Screw EN6114V3X6 Item 47 24 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(31) Subtask 536177-831-031-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR44, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 221 5

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# @A300-600 SERVICE BULLETIN (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 44, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard 24 Nut Item (4) Discard

(32) Subtask 536177-831-032-001 - Depending on Inspection results, remove the Gussets from FR44, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FQAAA Removal/Installation of the Gussets at FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 44, LH side. Refer to Fig. A-FQAAA In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (132) Retain 1 Gusset Item (134) Retain
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 222 5

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

# @A300-600 SERVICE BULLETIN
attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

(33) Subtask 536177-831-033-003 - Depending on Inspection results, remove the Frame Foot from FR44, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FGAAC Replacement of the Frame foot FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Remove the Frame foot from Frame 44, LH side. Refer to Fig. A-FGAAC In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (106) Discard 1 Stiffener Item (58) Retain 1 Splice Item (74) Retain 4 Bolt Item (55) Retain 4 Nut Item (56) Discard 29 Screw Item (3) Discard 29 Nut Item (4) Discard
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 223 5

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

# @A300-600 SERVICE BULLETIN 2 Rivet Item (19) Discard And: 12 Rivet Item (5) Discard or 12 Rivet Item (6) Discard 12 Bush Item (7) Discard

(34) Subtask 536177-831-034-003 - Depending on Inspection results, install an identical Frame Foot at FR44, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A12R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 35 NUT 12 ASNA2529-6 2 NUT 14 NAS1726-5E 2 NUT 16 ASNA2529-5 4 NUT 19 ASNA2050DXJ4020 2 RIVET 23 EN6115V3X5 10 SCREW 24 EN6115V3X7 11 SCREW 25 EN6115V3X6 12 SCREW 26 EN6114V6X14 2 SCREW 27 ASNA2001V5-8X 2 SCREW 28 EN6114V5X8 3 SCREW 29 EN6115V3X4 2 SCREW 41 EN6114V5X10 1 SCREW 56 NSA5057-6 4 NUT 106 A5711113220095 1 FOOT

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 224 5

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

# @A300-600 SERVICE BULLETIN
Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FQAAA Removal/Installation of the Gussets at FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Fig. A-FGAAC Replacement of the Frame foot FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Install and drill all the parts. Refer to Fig. A-FGAAC In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FGAAC

. 1 Frame foot A5711113220095 Item 106 1 Stiffener Item (58) Retained at removal 1 Splice Item (74) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FGAAC Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 225 5

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

# @A300-600 SERVICE BULLETIN
2 Drill the holes of the Frame foot H180 to H202 and H205 to H208 to the diameter given on Fig. A-FGAAC Sheet 03 to Fig. A-FGAAC Sheet 05

. 3 Drill the holes of the stiffener H221 and H222 to the diameter given on Fig. AFGAAC Sheet 03

. 4 Drill the holes of the splice H209 to H220 to the diameter given on Fig. AFGAAC Sheet 06

. (b) Install the fasteners. Refer to Fig. A-FGAAC In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H180 to H202 and H205 to H208: Refer to Fig. A-FGAAC Sheet 03 to Fig. A-FGAAC Sheet 05 1 Screw EN6115V3X5 Item 23 10 Screw EN6115V3X7 Item 24 12 Screw EN6115V3X6 Item 25 2 Screw ASNA2001V5-8X Item 27 2 Screw EN6114V5X8 Item 28 23 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 2 Nut ASNA2529-5 Item 16 NOTE : For holes H205 to H208, adjust the shims as shown on Fig. AFGAAC Sheet 05

. NOTE : Wet install the fasteners except for holes H203 and H204 with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 226 5

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# @A300-600 SERVICE BULLETIN
2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FGAAC Sheet 02 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H221 and H222: Refer to Fig. A-FGAAC Sheet 03 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the splice H209 to H220: Refer to Fig. A-FGAAC Sheet 06 1 Screw EN6115V3X7 Item 24 9 Screw EN6115V3X5 Item 23 2 Screw EN6115V3X4 Item 29 12 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 227 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (c) Install the Gussets at Frame 44, LH side. Refer to Fig. A-FQAAA In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FQAAA

. 1 Gusset Item (132) Retained at removal 1 Gusset Item (134) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H203 and H204 to the diameter given on Fig. A-FQAAA Sheet 03

. 3 Drill holes H223 and H224 to the diameter given on Fig. A-FQAAA Sheet 03

. 4 Install: 1 Gusset Item (132) Retained at removal 1 Gusset Item (134) Retained at removal 2 Screw EN6114V6X14 Item 26 1 Screw EN6114V5X8 Item 28 1 Screw EN6114V5X10 Item 41 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 228 5

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# @A300-600 SERVICE BULLETIN
2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-5 Item 16

(35) Subtask 536177-831-035-001 - Depending on Inspection results, if removed, install the Fasteners at FR44, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 90 ASNA2019-56-25 24 RIVET 91 EN6114V3X5 24 SCREW 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 229 5

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

# @A300-600 SERVICE BULLETIN
References Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 44, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 24 Rivet ASNA2019-56-25 Item 90 or 24 Screw EN6114V3X5 Item 91 24 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(36) Subtask 536177-831-036-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR44, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 230 5

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

# @A300-600 SERVICE BULLETIN
References Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 44, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard 24 Nut Item (4) Discard

(37) Subtask 536177-831-037-001 - Depending on Inspection results, remove the Gussets from FR44, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FQAAA Removal/Installation of the Gussets at FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 44, RH side. Refer to Fig. A-FQAAA DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 231 5

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

# @A300-600 SERVICE BULLETIN
In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (133) Retain 1 Gusset Item (135) Retain attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

(38) Subtask 536177-831-038-003 - Depending on Inspection results, remove the Frame Foot from FR44, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FGAAC Replacement of the Frame foot FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Remove the Frame foot from Frame 44, RH side. Refer to Fig. A-FGAAC In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (107) Discard 1 Stiffener Item (57) Retain 1 Splice Item (75) Retain 4 Bolt Item (55) Retain DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 232 5

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

# @A300-600 SERVICE BULLETIN 4 Nut Item (56) Discard 29 Screw Item (3) Discard 29 Nut Item (4) Discard 2 Rivet Item (19) Discard And: 12 Rivet Item (5) Discard or 12 Rivet Item (6) Discard 12 Bush Item (7) Discard

(39) Subtask 536177-831-039-003 - Depending on Inspection results, install an identical Frame Foot at FR44, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A30R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 35 NUT 12 ASNA2529-6 2 NUT 14 NAS1726-5E 2 NUT 16 ASNA2529-5 4 NUT 19 ASNA2050DXJ4020 2 RIVET 23 EN6115V3X5 10 SCREW 24 EN6115V3X7 11 SCREW 25 EN6115V3X6 12 SCREW 26 EN6114V6X14 2 SCREW 27 ASNA2001V5-8X 2 SCREW 28 EN6114V5X8 3 SCREW 29 EN6115V3X4 2 SCREW 41 EN6114V5X10 1 SCREW DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 233 5

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 56 NSA5057-6 4 NUT 107 A5711113220195 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FGAAC Replacement of the Frame foot FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Fig. A-FQAAA Removal/Installation of the Gussets at FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FGAAC In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FGAAC

. 1 Frame foot A5711113220195 Item 107 1 Stiffener Item (57) Retained at removal 1 Splice Item (75) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FGAAC Sheet 03

. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 234 5

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# @A300-600 SERVICE BULLETIN
NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H180 to H202 and H205 to H208 to the diameter given on Fig. A-FGAAC Sheet 03 to Fig. A-FGAAC Sheet 05

. 3 Drill the holes of the stiffener H221 and H222 to the diameter given on Fig. AFGAAC Sheet 03

. 4 Drill the holes of the splice H209 to H220 to the diameter given on Fig. AFGAAC Sheet 06

. (b) Install the fasteners. Refer to Fig. A-FGAAC In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H180 to H202 and H205 to H208: Refer to Fig. A-FGAAC Sheet 03 to Fig. A-FGAAC Sheet 05 1 Screw EN6115V3X5 Item 23 10 Screw EN6115V3X7 Item 24 12 Screw EN6115V3X6 Item 25 2 Screw ASNA2001V5-8X Item 27 2 Screw EN6114V5X8 Item 28 23 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 2 Nut ASNA2529-5 Item 16 NOTE : For holes H205 to H208, adjust the shims as shown on Fig. AFGAAC Sheet 05

. NOTE : Wet install the fasteners except for holes H203 and H204 with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with:
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 235 5

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# @A300-600 SERVICE BULLETIN Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FGAAC Sheet 02 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H221 and H222: Refer to Fig. A-FGAAC Sheet 03 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the splice H209 to H220: Refer to Fig. A-FGAAC Sheet 06 1 Screw EN6115V3X7 Item 24 9 Screw EN6115V3X5 Item 23 2 Screw EN6115V3X4 Item 29 12 Nut ASNA2529-3 Item 9 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 236 5

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# @A300-600 SERVICE BULLETIN
NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (c) Install the Gussets at Frame 44, LH side. Refer to Fig. A-FQAAA In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FQAAA

. 1 Gusset Item (133) Retained at removal 1 Gusset Item (135) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H203 and H204 to the diameter given on Fig. A-FQAAA Sheet 03

. 3 Drill holes H223 and H224 to the diameter given on Fig. A-FQAAA Sheet 03

. 4 Install: 1 Gusset Item (133) Retained at removal 1 Gusset Item (135) Retained at removal 2 Screw EN6114V6X14 Item 26 1 Screw EN6114V5X8 Item 28 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 237 5

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# @A300-600 SERVICE BULLETIN
1 Screw EN6114V5X10 Item 41 2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-5 Item 16

(40) Subtask 536177-831-040-001 - Depending on Inspection results, if removed, install the Fasteners at FR44, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 90 ASNA2019-56-25 24 RIVET 91 EN6114V3X5 24 SCREW 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 238 5

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# @A300-600 SERVICE BULLETIN
References Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 44, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 24 Rivet ASNA2019-56-25 Item 90 or 24 Screw EN6114V3X5 Item 91 24 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(41) Subtask 536177-831-041-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR45, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 239 5

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# @A300-600 SERVICE BULLETIN
References Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 45, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 20 Rivet Item (19) Discard And: 32 Rivet Item (5) Discard or 32 Bolt Item (3) Discard 32 Nut Item (4) Discard

(42) Subtask 536177-831-042-001 - Depending on Inspection results, remove the Gussets from FR45, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FTAAA Removal/Installation of the Gussets at FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 45, LH side. Refer to Fig. A-FTAAA DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 240 5

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# @A300-600 SERVICE BULLETIN
In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (136) Retain 1 Gusset Item (138) Retain attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

(43) Subtask 536177-831-043-003 - Depending on Inspection results, remove the Frame Foot from FR45, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FJAAC Replacement of the Frame foot FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Remove the Frame foot from Frame 45, LH side. Refer to Fig. A-FJAAC In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (108) Discard 2 Stiffener Item (58) Retain 1 Splice Item (72) Retain 4 Rivet Item (19) Discard DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 241 5

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# @A300-600 SERVICE BULLETIN 29 Screw Item (3) Discard 29 Nut Item (4) Discard And: 4 Screw Item (55) Retain 4 Nut Item (56) Discard or 4 Nut Item (76) Discard And 23 Rivet Item (5) Discard or 23 Screw Item (93) Discard 23 Nut Item (94) Discard And if installed, remove: 1 Bracket Item (79) Retain

(44) Subtask 536177-831-044-003 - Depending on Inspection results, install an identical Frame Foot at FR45, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 145 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A15R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 48 NUT 12 ASNA2529-6 2 NUT 16 ASNA2529-5 2 NUT 19 ASNA2050DXJ4020 4 RIVET 23 EN6115V3X5 8 SCREW DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 242 5

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 24 EN6115V3X7 7 SCREW 25 EN6115V3X6 18 SCREW 26 EN6114V6X14 2 SCREW 28 EN6114V5X8 1 SCREW 39 EN6115V3X9 4 SCREW 40 EN6115V3X8 10 SCREW 41 EN6114V5X10 1 SCREW 46 NAS1726-6E 2 NUT 47 EN6114V3X6 1 SCREW 48 ASNA2001V6-8X 2 SCREW 56 NSA5057-6 4 NUT 76 NSA5057-7 4 NUT 108 A5711113320095 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FJAAC Replacement of the Frame foot FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Fig. A-FTAAA Removal/Installation of the Gussets at FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FJAAC In accordance with SRM 51-40-40

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 243 5

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# @A300-600 SERVICE BULLETIN
1 Put all the parts in position as shown on Fig. A-FJAAC

. 1 Frame foot A5711113320095 Item 108 2 Stiffener Item (58) Retained at removal 1 Splice Item (72) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FJAAC Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H231 to H254, H257 to H266 and H271 to H272 to the diameter given on Fig. A-FJAAC Sheet 03 to Fig. A-FJAAC Sheet 05

. 3 Drill the holes of the stiffener at STGR 36 H255 and H256 to the diameter given on Fig. A-FJAAC Sheet 03

. 4 Drill the holes of the stiffener at STGR 37 H267 and H268 to the diameter given on Fig. A-FJAAC Sheet 05

. NOTE : Use the existing holes of the stringers. 5 Drill the holes of the splice H273 to H285 to the diameter given on Fig. AFJAAC Sheet 06

. (b) Install the fasteners. Fig. A-FJAAC In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H231 to H254, H257 to H266 and H271 to H272: Refer to Fig. A-FJAAC Sheet 03 to Fig. A-FJAAC Sheet 05 6 Screw EN6115V3X5 Item 23 5 Screw EN6115V3X7 Item 24 16 Screw EN6115V3X6 Item 25
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 244 5

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# @A300-600 SERVICE BULLETIN
3 Screw EN6115V3X9 Item 39 4 Screw EN6115V3X8 Item 40 1 Screw EN6114V3X6 Item 47 2 Screw ASNA2001V6-8X Item 48 35 Nut ASNA2529-3 Item 9 2 Nut NAS1726-6E Item 46 NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FJAAC Sheet 02 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 or 4 Nut NSA5057-7 Item 76 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H255 and H256: Refer to Fig. A-FJAAC Sheet 03 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 245 5

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

# @A300-600 SERVICE BULLETIN
NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the stiffener at STGR 37 H267 and H268: Refer to Fig. A-FJAAC Sheet 05 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Install the fasteners of the splice H273 to H285: Refer to Fig. A-FJAAC Sheet 06 2 Screw EN6115V3X7 Item 24 2 Screw EN6115V3X5 Item 23 1 Screw EN6115V3X9 Item 39 6 Screw EN6115V3X8 Item 40 13 Nut ASNA2529-3 Item 9 2 Screw EN6115V3X6 Item 25 And if removed, install: 1 Bracket Item (79) Retained at removal NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 246 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

6 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (c) Install the Gussets at Frame 45, LH side. Refer to Fig. A-FTAAA In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FTAAA

. 1 Gusset Item (136) Retained at removal 1 Gusset Item (138) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H269 and H270 to the diameter given on Fig. A-FTAAA Sheet 03

. 3 Drill holes H286 and H287 to the diameter given on Fig. A-FTAAA Sheet 03

. 4 Install: 1 Gusset Item (136) Retained at removal 1 Gusset Item (138) Retained at removal 2 Screw EN6114V6X14 Item 26 1 Screw EN6114V5X8 Item 28 1 Screw EN6114V5X10 Item 41 2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-5 Item 16 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 247 5

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# @A300-600 SERVICE BULLETIN (45) Subtask 536177-831-045-001 - Depending on Inspection results, if removed, install the Fasteners at FR45, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 32 NUT 47 EN6114V3X6 32 SCREW 90 ASNA2019-56-25 32 RIVET 92 EN6080D6X-32 20 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 248 5

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

# @A300-600 SERVICE BULLETIN (a) If removed, install the fasteners at Frame 45, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 20 Rivet EN6080D6X-32 Item 92 And: 32 Rivet ASNA2019-56-25 Item 90 or 32 Screw EN6114V3X6 Item 47 32 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(46) Subtask 536177-831-046-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR45, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 249 5

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

# @A300-600 SERVICE BULLETIN (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 45, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 20 Rivet Item (19) Discard And: 32 Rivet Item (5) Discard or 32 Bolt Item (3) Discard 32 Nut Item (4) Discard

(47) Subtask 536177-831-047-001 - Depending on Inspection results, remove the Gussets from FR45, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FTAAA Removal/Installation of the Gussets at FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 45, RH side. Refer to Fig. A-FTAAA In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (137) Retain 1 Gusset Item (139) Retain
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 250 5

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# @A300-600 SERVICE BULLETIN
attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

(48) Subtask 536177-831-048-003 - Depending on Inspection results, remove the Frame Foot from FR45, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FJAAC Replacement of the Frame foot FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Remove the Frame foot from Frame 45, RH side. Refer to Fig. A-FJAAC In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (109) Discard 2 Stiffener Item (57) Retain 1 Splice Item (71) Retain 4 Rivet Item (19) Discard 29 Screw Item (3) Discard 29 Nut Item (4) Discard And:
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 251 5

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# @A300-600 SERVICE BULLETIN 4 Screw Item (55) Retain 4 Nut Item (56) Discard or 4 Nut Item (76) Discard And: 23 Rivet Item (5) Discard or 23 Screw Item (93) Discard 23 Nut Item (94) Discard

(49) Subtask 536177-831-049-003 - Depending on Inspection results, install an identical Frame Foot at FR45, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A33R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 48 NUT 12 ASNA2529-6 2 NUT 16 ASNA2529-5 2 NUT 19 ASNA2050DXJ4020 4 RIVET 23 EN6115V3X5 10 SCREW 24 EN6115V3X7 7 SCREW 25 EN6115V3X6 16 SCREW 26 EN6114V6X14 2 SCREW 28 EN6114V5X8 1 SCREW 39 EN6115V3X9 4 SCREW 40 EN6115V3X8 10 SCREW 41 EN6114V5X10 1 SCREW 46 NAS1726-6E 2 NUT 47 EN6114V3X6 1 SCREW DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 252 5

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 48 ASNA2001V6-8X 2 SCREW 56 NSA5057-6 4 NUT 76 NSA5057-7 4 NUT 109 A5711113320195 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FJAAC Replacement of the Frame foot FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Fig. A-FTAAA Removal/Installation of the Gussets at FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FJAAC In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FJAAC

. 1 Frame foot A5711113320195 Item 109 2 Stiffener Item (57) Retained at removal 1 Splice Item (71) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 253 5

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

# @A300-600 SERVICE BULLETIN
A-FJAAC Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H231 to H254, H257 to H266 and H271 to H272 to the diameter given on Fig. A-FJAAC Sheet 03 to Fig. A-FJAAC Sheet 05

. 3 Drill the holes of the stiffener at STGR 36 H255 and H256 to the diameter given on Fig. A-FJAAC Sheet 03

. 4 Drill the holes of the stiffener at STGR 37 H267 and H268 to the diameter given on Fig. A-FJAAC Sheet 05

. NOTE : Use the existing holes of the stringers. 5 Drill the holes of the splice H273 to H285 to the diameter given on Fig. AFJAAC Sheet 06

. (b) Install the fasteners. Fig. A-FJAAC In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H231 to H254, H257 to H266 and H271 to H272: Refer to Fig. A-FJAAC Sheet 03 to Fig. A-FJAAC Sheet 05 6 Screw EN6115V3X5 Item 23 5 Screw EN6115V3X7 Item 24 16 Screw EN6115V3X6 Item 25 3 Screw EN6115V3X9 Item 39 4 Screw EN6115V3X8 Item 40 1 Screw EN6114V3X6 Item 47 2 Screw ASNA2001V6-8X Item 48 35 Nut ASNA2529-3 Item 9 2 Nut NAS1726-6E Item 46 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 254 5

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

# @A300-600 SERVICE BULLETIN
NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FJAAC Sheet 02 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 or 4 Nut NSA5057-7 Item 76 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H255 and H256: Refer to Fig. A-FJAAC Sheet 03 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the stiffener at STGR 37 H267 and H268: Refer to Fig. A-FJAAC Sheet 05 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 255 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Install the fasteners of the splice H273 to H285: Refer to Fig. A-FJAAC Sheet 06 2 Screw EN6115V3X7 Item 24 4 Screw EN6115V3X5 Item 23 1 Screw EN6115V3X9 Item 39 6 Screw EN6115V3X8 Item 40 13 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

6 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (c) Install the Gussets at Frame 45, LH side. Refer to Fig. A-FTAAA In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FTAAA

. 1 Gusset Item (137) Retained at removal DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 256 5

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

# @A300-600 SERVICE BULLETIN 1 Gusset Item (139) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H269 and H270 to the diameter given on Fig. A-FTAAA Sheet 03

. 3 Drill holes H286 and H287 to the diameter given on Fig. A-FTAAA Sheet 03

. 4 Install: 1 Gusset Item (137) Retained at removal 1 Gusset Item (139) Retained at removal 2 Screw EN6114V6X14 Item 26 1 Screw EN6114V5X8 Item 28 1 Screw EN6114V5X10 Item 41 2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-5 Item 16

(50) Subtask 536177-831-050-001 - Depending on Inspection results, install the Fasteners at FR45, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 32 NUT 47 EN6114V3X6 32 SCREW DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 257 5

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

# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 90 ASNA2019-56-25 32 RIVET 92 EN6080D6X-32 20 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 45, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 20 Rivet EN6080D6X-32 Item 92 And: 32 Rivet ASNA2019-56-25 Item 90 or 32 Screw EN6114V3X6 Item 47 32 Nut ASNA2529-3 Item 9 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 258 5

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

# @A300-600 SERVICE BULLETIN
NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(51) Subtask 536177-831-051-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR46, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 46, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard 24 Nut Item (4) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 259 5

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

# @A300-600 SERVICE BULLETIN (52) Subtask 536177-831-052-001 - Depending on Inspection results, remove the Gussets from FR46, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FUAAA Removal/Installation of the Gussets at FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 46, LH side. Refer to Fig. A-FUAAA In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (140) Retain 1 Gusset Item (142) Retain attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

(53) Subtask 536177-831-053-003 - Depending on Inspection results, remove the Frame Foot from FR46, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 260 5

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

# @A300-600 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-40-20 Fig. A-FKAAC Replacement of the Frame foot FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Remove the Frame foot from Frame 46, LH side. Refer to Fig. A-FKAAC In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (110) Discard 1 Stiffener Item (58) Retain 1 Splice Item (82) Retain 2 Rivet Item (19) Discard 37 Screw Item (3) Discard 37 Nut Item (4) Discard And: 4 Screw Item (55) Retain 4 Nut Item (56) Discard or 4 Nut Item (76) Discard And: 16 Rivet Item (5) Discard or 16 Screw Item (93) Discard 16 Nut Item (94) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 261 5

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

# @A300-600 SERVICE BULLETIN (54) Subtask 536177-831-054-003 - Depending on Inspection results, install an identical Frame Foot at FR46, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 16.00 Minimum number of person 1 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A18R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 43 NUT 12 ASNA2529-6 3 NUT 14 NAS1726-5E 2 NUT 16 ASNA2529-5 7 NUT 19 ASNA2050DXJ4020 2 RIVET 23 EN6115V3X5 12 SCREW 24 EN6115V3X7 10 SCREW 25 EN6115V3X6 19 SCREW 26 EN6114V6X14 1 SCREW 28 EN6114V5X8 6 SCREW 29 EN6115V3X4 2 SCREW 52 EN6114V6X17 2 SCREW 53 ASNA2001V5-12X 2 SCREW 54 EN6114V5X12 1 SCREW 56 NSA5057-6 4 NUT 76 NSA5057-7 4 NUT 110 A5711113420095 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 262 5

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

# @A300-600 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FKAAC Replacement of the Frame foot FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Fig. A-FUAAA Removal/Installation of the Gussets at FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FKAAC In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FKAAC

. 1 Frame foot A5711113420095 Item 110 1 Stiffener Item (58) Retained at removal 1 Splice Item (82) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FKAAC Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H300 to H313, H316 to H331 and H334 to H341 to H313 and H316 to H341 to the diameter given on Fig. A-FKAAC Sheet 03 to Fig. A-FKAAC Sheet 05

. 3 Drill the holes of the stiffener H314 and H315 to the diameter given on Fig. AFKAAC Sheet 05

. 4 Drill the holes of the splice H342 to H354 to the diameter given on Fig. AFKAAC Sheet 06

. (b) Install the fasteners. Fig. A-FKAAC DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 263 5

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

# @A300-600 SERVICE BULLETIN In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H300 to H313, H316 to H331 and H334 to H341 to H313 and H316 to H341: Refer to Fig. A-FKAAC Sheet 03 to Fig. A-FKAAC Sheet 05 5 Screw EN6115V3X5 Item 23 9 Screw EN6115V3X7 Item 24 16 Screw EN6115V3X6 Item 25 6 Screw EN6114V5X8 Item 28 2 Screw ASNA2001V5-12X Item 53 30 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 6 Nut ASNA2529-5 Item 16 NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FKAAC Sheet 02 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 or 4 Nut NSA5057-7 Item 76 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 264 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 37 H314 and H315: Refer to Fig. A-FKAAC Sheet 05 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the splice H342 to H354: Refer to Fig. A-FKAAC Sheet 06 7 Screw EN6115V3X5 Item 23 1 Screw EN6115V3X7 Item 24 3 Screw EN6115V3X6 Item 25 2 Screw EN6115V3X4 Item 29 13 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 265 5

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

# @A300-600 SERVICE BULLETIN (c) Install the Gussets at Frame 46, LH side. Refer to Fig. A-FUAAA In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FUAAA

. 1 Gusset Item (140) Retained at removal 1 Gusset Item (142) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H332 and H333 to the diameter given on Fig. A-FUAAA Sheet 03

. 3 Drill holes H355 and H356 to the diameter given on Fig. A-FUAAA Sheet 03

. 4 Install: 1 Gusset Item (140) Retained at removal 1 Gusset Item (142) Retained at removal 1 Screw EN6114V6X14 Item 26 2 Screw EN6114V6X17 Item 52 1 Screw EN6114V5X12 Item 54 3 Nut ASNA2529-6 Item 12 1 Nut ASNA2529-5 Item 16

(55) Subtask 536177-831-055-001 - Depending on Inspection results, if removed, install the Fasteners at FR46, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 266 5

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

# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA05 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 47 EN6114V3X6 16 SCREW 90 ASNA2019-56-25 24 RIVET 91 EN6114V3X5 8 SCREW 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 46, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 267 5

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

# @A300-600 SERVICE BULLETIN Refer to AMM 20-21-12, Page Block 001 1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 16 Rivet ASNA2019-56-25 Item 90 or 16 Screw EN6114V3X6 Item 47 16 Nut ASNA2529-3 Item 9 And: 8 Rivet ASNA2019-56-25 Item 90 or 8 Screw EN6114V3X5 Item 91 8 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(56) Subtask 536177-831-056-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR46, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 268 5

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

# @A300-600 SERVICE BULLETIN
References Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 46, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard 24 Nut Item (4) Discard

(57) Subtask 536177-831-057-001 - Depending on Inspection results, remove the Gussets from FR46, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FUAAA Removal/Installation of the Gussets at FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 46, RH side. Refer to Fig. A-FUAAA DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 269 5

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

# @A300-600 SERVICE BULLETIN
In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (141) Retain 1 Gusset Item (143) Retain attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

(58) Subtask 536177-831-058-003 - Depending on Inspection results, remove the Frame Foot from FR46, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FKAAC Replacement of the Frame foot FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Remove the Frame foot from Frame 46, RH side. Refer to Fig. A-FKAAC In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (111) Discard 1 Stiffener Item (57) Retain 1 Splice Item (83) Retain 2 Rivet Item (19) Discard DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 270 5

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

# @A300-600 SERVICE BULLETIN 37 Screw Item (3) Discard 37 Nut Item (4) Discard And: 4 Screw Item (55) Retain 4 Nut Item (56) Discard or 4 Nut Item (76) Discard And: 16 Rivet Item (5) Discard or 16 Screw Item (93) Discard 16 Nut Item (94) Discard

(59) Subtask 536177-831-059-003 - Depending on Inspection results, install an identical Frame Foot at FR46, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A36R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 43 NUT 12 ASNA2529-6 3 NUT 14 NAS1726-5E 2 NUT 16 ASNA2529-5 7 NUT 19 ASNA2050DXJ4020 2 RIVET 23 EN6115V3X5 12 SCREW 24 EN6115V3X7 10 SCREW 25 EN6115V3X6 19 SCREW DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 271 5

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 26 EN6114V6X14 1 SCREW 28 EN6114V5X8 6 SCREW 29 EN6115V3X4 2 SCREW 52 EN6114V6X17 2 SCREW 53 ASNA2001V5-12X 2 SCREW 54 EN6114V5X12 1 SCREW 56 NSA5057-6 4 NUT 76 NSA5057-7 4 NUT 111 A5711113420195 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FKAAC Replacement of the Frame foot FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Fig. A-FUAAA Removal/Installation of the Gussets at FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FKAAC In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FKAAC

. 1 Frame foot A5711113420195 Item 111 1 Stiffener Item (57) Retained at removal DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 272 5

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

# @A300-600 SERVICE BULLETIN 1 Splice Item (83) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FKAAC Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H300 to H313, H316 to H331 and H334 to H341 to H313 and H316 to H341 to the diameter given on Fig. A-FKAAC Sheet 03 to Fig. A-FKAAC Sheet 05

. 3 Drill the holes of the stiffener H314 and H315 to the diameter given on Fig. AFKAAC Sheet 05

. 4 Drill the holes of the splice H342 to H354 to the diameter given on Fig. AFKAAC Sheet 06

. (b) Install the fasteners. Fig. A-FKAAC In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H300 to H313, H316 to H331 and H334 to H341 to H313 and H316 to H341: Refer to Fig. A-FKAAC Sheet 03 to Fig. A-FKAAC Sheet 05 5 Screw EN6115V3X5 Item 23 9 Screw EN6115V3X7 Item 24 16 Screw EN6115V3X6 Item 25 6 Screw EN6114V5X8 Item 28 2 Screw ASNA2001V5-12X Item 53 30 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 6 Nut ASNA2529-5 Item 16 NOTE : Protect the fasteners head and nuts with:
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 273 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FKAAC Sheet 02 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 or 4 Nut NSA5057-7 Item 76 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 37 H314 and H315: Refer to Fig. A-FKAAC Sheet 05 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the splice H342 to H354: Refer to Fig. A-FKAAC Sheet 06 7 Screw EN6115V3X5 Item 23 1 Screw EN6115V3X7 Item 24
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 274 5

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# @A300-600 SERVICE BULLETIN
3 Screw EN6115V3X6 Item 25 2 Screw EN6115V3X4 Item 29 13 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (c) Install the Gussets at Frame 46, LH side. Refer to Fig. A-FUAAA In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FUAAA

. 1 Gusset Item (141) Retained at removal 1 Gusset Item (143) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H332 and H333 to the diameter given on Fig. A-FUAAA Sheet 03

. 3 Drill holes H355 and H356 to the diameter given on Fig. A-FUAAA Sheet 03

. 4 Install: 1 Gusset Item (141) Retained at removal DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 275 5

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# @A300-600 SERVICE BULLETIN 1 Gusset Item (143) Retained at removal 1 Screw EN6114V6X14 Item 26 2 Screw EN6114V6X17 Item 52 1 Screw EN6114V5X12 Item 54 3 Nut ASNA2529-6 Item 12 1 Nut ASNA2529-5 Item 16

(60) Subtask 536177-831-060-001 - Depending on Inspection results, install the Fasteners at FR46, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA05 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 47 EN6114V3X6 16 SCREW 90 ASNA2019-56-25 24 RIVET 91 EN6114V3X5 8 SCREW 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 276 5

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# @A300-600 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 46, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 16 Rivet ASNA2019-56-25 Item 90 or 16 Screw EN6114V3X6 Item 47 16 Nut ASNA2529-3 Item 9 And: 8 Rivet ASNA2019-56-25 Item 90 or 8 Screw EN6114V3X5 Item 91 8 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 277 5

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# @A300-600 SERVICE BULLETIN
**CONF 002 (1) Subtask 536177-831-001-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR41, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 41, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 20 Rivet Item (19) Discard And: 32 Rivet Item (5) Discard or 32 Bolt Item (3) Discard 32 Nut Item (4) Discard

(2) Subtask 536177-831-002-002 - Depending on Inspection results, remove the Gussets from FR41, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 278 5

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

# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FLAAB Removal/Installation of the Gussets at FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 41, LH side. Refer to Fig. A-FLAAB In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (120) Retain 1 Gusset Item (122) Retain attached with: 2 Pin Item (1) Discard 2 Collar Item (2) Discard 2 Screw Item (3) Discard 2 Nut Item (4) Discard

(3) Subtask 536177-831-003-002 - Depending on Inspection results, remove the Frame Foot from FR41, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 279 5

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# @A300-600 SERVICE BULLETIN
References Fig. A-FCAAB Replacement of the Frame foot FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Remove the Frame foot from Frame 41, LH side. Refer to Fig. A-FCAAB In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (100) Discard 1 Stiffener Item (58) Retain 1 Splice Item (60) Retain 1 Shim Item (61) Retain 4 Screw Item (55) Retain 4 Nut Item (56) Discard 42 Pin Item (1) Discard 42 Collar Item (2) Discard 2 Screw Item (3) Discard 2 Nut Item (4) Discard 2 Rivet Item (5) Discard

(4) Subtask 536177-831-004-002 - Depending on Inspection results, install an identical Frame Foot at FR41, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 280 5

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

# @A300-600 SERVICE BULLETIN Material necessary to do the job Kit 536177A02R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 15 SCREW 9 ASNA2529-3 36 NUT 10 EN6115V3A6 9 SCREW 11 EN6114V6Y14 4 SCREW 12 ASNA2529-6 4 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 4 SCREW 16 ASNA2529-5 4 NUT 17 EN6115V3A5 10 SCREW 18 EN6115V3A4 2 SCREW 19 ASNA2050DXJ4020 2 RIVET 20 EN6114V4Y9 1 SCREW 21 ASNA2529-4 2 NUT 22 EN6114V4Y10 1 SCREW 56 NSA5057-6 4 NUT 100 A5711112920095 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FCAAB Replacement of the Frame foot FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 281 5

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

# @A300-600 SERVICE BULLETIN
References Fig. A-FLAAB Removal/Installation of the Gussets at FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FCAAB In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FCAAB

. 1 Frame foot A5711112920095 Item 100 1 Stiffener Item (58) Retained at removal 1 Splice Item (60) Retained at removal 1 Shim Item (61) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FCAAB Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H1 to H23 and H26 to H31 to the diameter given on Fig. A-FCAAB Sheet 03 and Fig. A-FCAAB Sheet 04

. 3 Drill the holes of the stiffener H45 and H46 to the diameter given on Fig. AFCAAB Sheet 04

. 4 Drill the holes of the splice H32 to H44 to the diameter given on Fig. A-FCAAB Sheet 05

. (b) Cut-out the Frame foot Item 100 as shown on Fig. A-FCAAB Sheet 03

. Protect the cut-out with: Wash Primer - Structure 04CMA2 As required
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 282 5

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# @A300-600 SERVICE BULLETIN (c) Install the fasteners. Refer to Fig. A-FCAAB In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H1 to H31: Refer to Fig. A-FCAAB Sheet 03 and Fig. A-FCAAB Sheet 04 14 Screw EN6115V3A7 Item 8 9 Screw EN6115V3A6 Item 10 2 Screw EN6114V6Y14 Item 11 2 Screw ASNA2001V5-8Y Item 13 4 Screw EN6114V5Y8 Item 15 23 Nut ASNA2529-3 Item 9 2 Nut ASNA2529-6 Item 12 2 Nut NAS1726-5E Item 14 4 Nut ASNA2529-5 Item 16 NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FCAAB Sheet 02 4 Screw Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with:
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 283 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H45 and H46: Refer to Fig. A-FCAAB Sheet 04 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the splice H32 to H44: Refer to Fig. A-FCAAB Sheet 05 1 Screw EN6115V3A7 Item 8 10 Screw EN6115V3A5 Item 17 2 Screw EN6115V3A4 Item 18 13 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (d) Install the Gussets at Frame 41, LH side. Refer to Fig. A-FLAAB DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 284 5

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

# @A300-600 SERVICE BULLETIN In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FLAAB Sheet 02 and Fig. AFLAAB Sheet 03

. 1 Gusset Item (120) Retained at removal 1 Gusset Item (122) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H24 and H25 to the diameter given on Fig. A-FLAAB Sheet 03

. 3 Drill holes H47 and H48 to the diameter given on Fig. A-FLAAB Sheet 03

. 4 Install: 1 Gusset Item (120) Retained at removal 1 Gusset Item (122) Retained at removal 2 Screw EN6114V6Y14 Item 11 1 Screw EN6114V4Y9 Item 20 1 Screw EN6114V4Y10 Item 22 2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-4 Item 21

(5) Subtask 536177-831-005-001 - Depending on Inspection results, if removed, install the Fasteners at FR41, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 285 5

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

# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 32 NUT 90 ASNA2019-56-25 32 RIVET 91 EN6114V3X5 32 SCREW 92 EN6080D6X-32 20 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 41, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 286 5

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# @A300-600 SERVICE BULLETIN
1 Install: 20 Rivet EN6080D6X-32 Item 92 And: 32 Rivet ASNA2019-56-25 Item 90 or 32 Screw EN6114V3X5 Item 91 32 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(6) Subtask 536177-831-006-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR41, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 41, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 20 Rivet Item (19) Discard DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 287 5

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# @A300-600 SERVICE BULLETIN
And: 32 Rivet Item (5) Discard or 32 Bolt Item (3) Discard 32 Nut Item (4) Discard

(7) Subtask 536177-831-007-002 - Depending on Inspection results, remove the Gussets from FR41, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FLAAB Removal/Installation of the Gussets at FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 41, RH side. Refer to Fig. A-FLAAB In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (121) Retain 1 Gusset Item (123) Retain attached with: 2 Pin Item (1) Discard 2 Collar Item (2) Discard 2 Screw Item (3) Discard 2 Nut Item (4) Discard
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 288 5

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

# @A300-600 SERVICE BULLETIN (8) Subtask 536177-831-008-002 - Depending on Inspection results, remove the Frame Foot from FR41, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FCAAB Replacement of the Frame foot FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Remove the Frame foot from Frame 41, RH side. Refer to Fig. A-FCAAB In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (101) Discard 1 Stiffener Item (57) Retain 1 Splice Item (59) Retain 1 Shim Item (61) Retain 4 Screw Item (55) Retain 4 Nut Item (56) Discard 42 Pin Item (1) Discard 42 Collar Item (2) Discard 2 Screw Item (3) Discard 2 Nut Item (4) Discard
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 289 5

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

# @A300-600 SERVICE BULLETIN 2 Rivet Item (5) Discard

(9) Subtask 536177-831-009-002 - Depending on Inspection results, install an identical Frame Foot at FR41, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A20R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 15 SCREW 9 ASNA2529-3 36 NUT 10 EN6115V3A6 9 SCREW 11 EN6114V6Y14 4 SCREW 12 ASNA2529-6 4 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 4 SCREW 16 ASNA2529-5 4 NUT 17 EN6115V3A5 10 SCREW 18 EN6115V3A4 2 SCREW 19 ASNA2050DXJ4020 2 RIVET 20 EN6114V4Y9 1 SCREW 21 ASNA2529-4 2 NUT 22 EN6114V4Y10 1 SCREW 56 NSA5057-6 4 NUT 101 A5711112920195 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 290 5

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

# @A300-600 SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FCAAB Replacement of the Frame foot FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FLAAB Removal/Installation of the Gussets at FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FCAAB In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FCAAB

. 1 Frame foot A5711112920195 Item 101 1 Stiffener Item (57) Retained at removal 1 Splice Item (59) Retained at removal 1 Shim Item (61) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FCAAB Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H1 to H23 and H26 to H31 to the diameter given on Fig. A-FCAAB Sheet 03 and Fig. A-FCAAB Sheet 04

.
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 291 5

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# @A300-600 SERVICE BULLETIN
3 Drill the holes of the stiffener H45 and H46 to the diameter given on Fig. AFCAAB Sheet 04

. 4 Drill the holes of the splice H32 to H44 to the diameter given on Fig. A-FCAAB Sheet 05

. (b) Cut-out the Frame foot Item 100 as shown on Fig. A-FCAAB Sheet 03

. Protect the cut-out with: Wash Primer - Structure 04CMA2 As required
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

(c) Install the fasteners. Refer to Fig. A-FCAAB In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H1 to H31: Refer to Fig. A-FCAAB Sheet 03 and Fig. A-FCAAB Sheet 04 14 Screw EN6115V3A7 Item 8 9 Screw EN6115V3A6 Item 10 2 Screw EN6114V6Y14 Item 11 2 Screw ASNA2001V5-8Y Item 13 4 Screw EN6114V5Y8 Item 15 23 Nut ASNA2529-3 Item 9 2 Nut ASNA2529-6 Item 12 2 Nut NAS1726-5E Item 14 4 Nut ASNA2529-5 Item 16 NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 292 5

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

# @A300-600 SERVICE BULLETIN
2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FCAAB Sheet 02 4 Screw Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H45 and H46: Refer to Fig. A-FCAAB Sheet 04 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the splice H32 to H44: Refer to Fig. A-FCAAB Sheet 05 1 Screw EN6115V3A7 Item 8 10 Screw EN6115V3A5 Item 17 2 Screw EN6115V3A4 Item 18 13 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 293 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (d) Install the Gussets at Frame 41, LH side. Refer to Fig. A-FLAAB In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FLAAB Sheet 02 and Fig. AFLAAB Sheet 03

. 1 Gusset Item (121) Retained at removal 1 Gusset Item (123) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H24 and H25 to the diameter given on Fig. A-FLAAB Sheet 03

. 3 Drill holes H47 and H48 to the diameter given on Fig. A-FLAAB Sheet 03

. 4 Install: 1 Gusset Item (121) Retained at removal 1 Gusset Item (123) Retained at removal 2 Screw EN6114V6Y14 Item 11 1 Screw EN6114V4Y9 Item 20 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 294 5

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# @A300-600 SERVICE BULLETIN
1 Screw EN6114V4Y10 Item 22 2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-4 Item 21

(10) Subtask 536177-831-010-001 - Depending on Inspection results, if removed, install the Fasteners at FR41, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 32 NUT 90 ASNA2019-56-25 32 RIVET 91 EN6114V3X5 32 SCREW 92 EN6080D6X-32 20 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 295 5

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

# @A300-600 SERVICE BULLETIN
References Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 41, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 20 Rivet EN6080D6X-32 Item 92 And: 32 Rivet ASNA2019-56-25 Item 90 or 32 Screw EN6114V3X5 Item 91 32 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(11) Subtask 536177-831-011-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR42, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 296 5

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

# @A300-600 SERVICE BULLETIN
References Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 42, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard 24 Nut Item (4) Discard

(12) Subtask 536177-831-012-002 - Depending on Inspection results, remove the Gussets from FR42, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FNAAB Removal/Installation of the Gussets at FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 42, LH side. Refer to Fig. A-FNAAB DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 297 5

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

# @A300-600 SERVICE BULLETIN
In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (124) Retain 1 Gusset Item (126) Retain attached with: 2 Pin Item (1) Discard 2 Collar Item (2) Discard 2 Screw Item (3) Discard 2 Nut Item (4) Discard

(13) Subtask 536177-831-013-002 - Depending on Inspection results, remove the Frame Foot from FR42, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FDAAB Replacement of the Frame foot FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Remove the Frame foot from Frame 42, LH side. Refer to Fig. A-FDAAB In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (102) Discard 1 Doubler Item (62) Retain DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 298 5

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

# @A300-600 SERVICE BULLETIN 1 Shim Item (63) Retain 1 Shim Item (64) Retain 1 Shim Item (65) Retain 1 Stiffener Item (58) Retain 1 Stiffener Item (68) Retain 1 Splice Item (66) Retain 4 Screw Item (55) Retain 4 Nut Item (56) Discard 46 Pin Item (1) Discard 46 Collar Item (2) Discard 15 Screw Item (3) Discard 15 Nut Item (4) Discard 6 Rivet Item (5) Discard

(14) Subtask 536177-831-014-002 - Depending on Inspection results, install an identical Frame Foot at FR42, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A05R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 1 SCREW 9 ASNA2529-3 53 NUT 10 EN6115V3A6 11 SCREW 12 ASNA2529-6 2 NUT DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 299 5

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

# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 8 SCREW 16 ASNA2529-5 8 NUT 17 EN6115V3A5 10 SCREW 18 EN6115V3A4 4 SCREW 19 ASNA2050DXJ4020 4 RIVET 20 EN6114V4Y9 1 SCREW 21 ASNA2529-4 2 NUT 22 EN6114V4Y10 1 SCREW 32 EN6115V3A8 14 SCREW 33 EN6115V3A9 11 SCREW 34 EN6114V6Y13 2 SCREW 56 NSA5057-6 4 NUT 102 A5711113020095 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FDAAB Replacement of the Frame foot FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FNAAB Removal/Installation of the Gussets at FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FDAAB DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 300 5

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

# @A300-600 SERVICE BULLETIN
In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FDAAB 1 Frame foot A5711113020095 Item 102 1 Doubler Item (62) Retained at removal 1 Shim Item (63) Retained at removal 1 Shim Item (64) Retained at removal 1 Shim Item (65) Retained at removal 1 Splice Item (66) Retained at removal 1 Stiffener Item (58) Retained at removal 1 Stiffener Item (68) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FDAAB Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H51 to H78, H83 to H90 and H93 to H102 to the diameter given on Fig. A-FDAAB Sheet 03 to Fig. A-FDAAB Sheet 05

. 3 Drill the holes of the stiffener at STGR 37 H81, H82, H103 and H104 to the diameter given on Fig. A-FDAAB Sheet 05

. 4 Drill the holes of the splice H105 to H117 to the diameter given on Fig. AFDAAB Sheet 05

. (b) Cut-out the Frame foot Item 102 as shown on Fig. A-FDAAB Sheet 03

. Protect the cut-out with: Wash Primer - Structure 04CMA2 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 301 5

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

# @A300-600 SERVICE BULLETIN
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

(c) Install the fasteners. Refer to Fig. A-FDAAB In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H51 to H78, H83 to H90 and H93 to H102: Refer to Fig. A-FDAAB Sheet 03 and Fig. A-FDAAB Sheet 04 11 Screw EN6115V3A6 Item 10 2 Screw ASNA2001V5-8Y Item 13 8 Screw EN6114V5Y8 Item 15 14 Screw EN6115V3A8 Item 32 11 Screw EN6115V3A9 Item 33 36 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 8 Nut ASNA2529-5 Item 16 NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FDAAB Sheet 02 4 Screw Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 302 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H79 and H80: Refer to Fig. A-FDAAB Sheet 04 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the stiffener at STGR 37 H81, H82, H103 and H104: Refer to Fig. A-FDAAB Sheet 05 2 Screw EN6115V3A4 Item 18 2 Nut ASNA2529-3 Item 9 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Install the fasteners of the splice H105 to H117: Refer to Fig. A-FDAAB Sheet 05 1 Screw EN6115V3A7 Item 8 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 303 5

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

# @A300-600 SERVICE BULLETIN
10 Screw EN6115V3A5 Item 17 2 Screw EN6115V3A4 Item 18 15 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

6 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (d) Install the Gussets at Frame 42, LH side. Refer to Fig. A-FNAAB In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FNAAB

. 1 Gusset Item (124) Retained at removal 1 Gusset Item (126) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H91 and H92 to the diameter given on Fig. A-FNAAB Sheet 03

. 3 Drill holes H118 and H119 to the diameter given on Fig. A-FNAAB Sheet 03

. 4 Install: 1 Gusset Item (124) Retained at removal DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 304 5

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

# @A300-600 SERVICE BULLETIN 1 Gusset Item (126) Retained at removal 1 Screw EN6114V4Y9 Item 20 1 Screw EN6114V4Y10 Item 22 2 Screw EN6114V6Y13 Item 34 2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-4 Item 21

(15) Subtask 536177-831-015-001 - Depending on Inspection results, if removed, install the Fasteners at FR42, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 90 ASNA2019-56-25 24 RIVET 91 EN6114V3X5 24 SCREW 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 305 5

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

# @A300-600 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 42, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 24 Rivet ASNA2019-56-25 Item 90 or 24 Screw EN6114V3X5 Item 91 24 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(16) Subtask 536177-831-016-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR42, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 306 5

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

# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 42, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard 24 Nut Item (4) Discard

(17) Subtask 536177-831-017-002 - Depending on Inspection results, remove the Gussets from FR42, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 307 5

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

# @A300-600 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-40-20 Fig. A-FNAAB Removal/Installation of the Gussets at FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 42, RH side. Refer to Fig. A-FNAAB In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (125) Retain 1 Gusset Item (127) Retain attached with: 2 Pin Item (1) Discard 2 Collar Item (2) Discard 2 Screw Item (3) Discard 2 Nut Item (4) Discard

(18) Subtask 536177-831-018-002 - Depending on Inspection results, remove the Frame Foot from FR42, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FDAAB Replacement of the Frame foot FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 308 5

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

# @A300-600 SERVICE BULLETIN (a) Remove the Frame foot from Frame 42, RH side. Refer to Fig. A-FDAAB In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (103) Discard 1 Doubler Item (62) Retain 1 Shim Item (63) Retain 1 Shim Item (64) Retain 1 Shim Item (65) Retain 1 Stiffener Item (57) Retain 1 Stiffener Item (69) Retain 1 Splice Item (67) Retain 4 Screw Item (55) Retain 4 Nut Item (56) Discard 46 Pin Item (1) Discard 46 Collar Item (2) Discard 15 Screw Item (3) Discard 15 Nut Item (4) Discard 6 Rivet Item (5) Discard

(19) Subtask 536177-831-019-002 - Depending on Inspection results, install an identical Frame Foot at FR42, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 309 5

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

# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A23R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 1 SCREW 9 ASNA2529-3 53 NUT 10 EN6115V3A6 11 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 8 SCREW 16 ASNA2529-5 8 NUT 17 EN6115V3A5 10 SCREW 18 EN6115V3A4 4 SCREW 19 ASNA2050DXJ4020 4 RIVET 20 EN6114V4Y9 1 SCREW 21 ASNA2529-4 2 NUT 22 EN6114V4Y10 1 SCREW 32 EN6115V3A8 14 SCREW 33 EN6115V3A9 11 SCREW 34 EN6114V6Y13 2 SCREW 56 NSA5057-6 4 NUT 103 A5711113020195 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 310 5

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

# @A300-600 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FDAAB Replacement of the Frame foot FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FNAAB Removal/Installation of the Gussets at FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FDAAB In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FDAAB 1 Frame foot A5711113020195 Item 103 1 Doubler Item (62) Retained at removal 1 Shim Item (63) Retained at removal 1 Shim Item (64) Retained at removal 1 Shim Item (65) Retained at removal 1 Splice Item (67) Retained at removal 1 Stiffener Item (57) Retained at removal 1 Stiffener Item (69) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FDAAB Sheet 03

. NOTE : Between parts apply:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 311 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H51 to H78, H83 to H90 and H93 to H102 to the diameter given on Fig. A-FDAAB Sheet 03 to Fig. A-FDAAB Sheet 05

. 3 Drill the holes of the stiffener at STGR 37 H81, H82, H103 and H104 to the diameter given on Fig. A-FDAAB Sheet 05

. 4 Drill the holes of the splice H105 to H117 to the diameter given on Fig. AFDAAB Sheet 05

. (b) Cut-out the Frame foot Item 102 as shown on Fig. A-FDAAB Sheet 03

. Protect the cut-out with: Wash Primer - Structure 04CMA2 As required
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

(c) Install the fasteners. Refer to Fig. A-FDAAB In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 11 Screw EN6115V3A6 Item 10 2 Screw ASNA2001V5-8Y Item 13 8 Screw EN6114V5Y8 Item 15 14 Screw EN6115V3A8 Item 32 11 Screw EN6115V3A9 Item 33 36 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 8 Nut ASNA2529-5 Item 16 1 Install the fasteners of the Frame foot H51 to H78, H83 to H90 and H93 to H102: Refer to Fig. A-FDAAB Sheet 03 and Fig. A-FDAAB Sheet 04 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 312 5

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

# @A300-600 SERVICE BULLETIN
NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FDAAB Sheet 02 4 Screw Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H79 and H80: Refer to Fig. A-FDAAB Sheet 04 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the stiffener at STGR 37 H81, H82, H103 and H104: Refer to Fig. A-FDAAB Sheet 05 2 Screw EN6115V3A4 Item 18 2 Nut ASNA2529-3 Item 9 2 Rivet ASNA2050DXJ4020 Item 19 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 313 5

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

# @A300-600 SERVICE BULLETIN
NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Install the fasteners of the splice H105 to H117: Refer to Fig. A-FDAAB Sheet 05 1 Screw EN6115V3A7 Item 8 10 Screw EN6115V3A5 Item 17 2 Screw EN6115V3A4 Item 18 15 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

6 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (d) Install the Gussets at Frame 42, LH side. Refer to Fig. A-FNAAB In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FNAAB

. 1 Gusset Item (125) Retained at removal DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 314 5

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

# @A300-600 SERVICE BULLETIN 1 Gusset Item (127) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H91 and H92 to the diameter given on Fig. A-FNAAB Sheet 02

. 3 Drill holes H118 and H119 to the diameter given on Fig. A-FNAAB Sheet 03

. 4 Install: 1 Gusset Item (125) Retained at removal 1 Gusset Item (127) Retained at removal 1 Screw EN6114V4Y9 Item 20 1 Screw EN6114V4Y10 Item 22 2 Screw EN6114V6Y13 Item 34 2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-4 Item 21

(20) Subtask 536177-831-020-001 - Depending on Inspection results, if removed, install the Fasteners at FR42, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 90 ASNA2019-56-25 24 RIVET DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 315 5

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 91 EN6114V3X5 24 SCREW 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 42, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 24 Rivet ASNA2019-56-25 Item 90 or 24 Screw EN6114V3X5 Item 91 24 Nut ASNA2529-3 Item 9 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 316 5

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# @A300-600 SERVICE BULLETIN
NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(21) Subtask 536177-831-021-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR43, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 43, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard 24 Nut Item (4) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 317 5

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

# @A300-600 SERVICE BULLETIN (22) Subtask 536177-831-022-002 - Depending on Inspection results, remove the Gussets from FR43, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FPAAB Removal/Installation of the Gussets at FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 43, LH side. Refer to Fig. A-FPAAB In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (128) Retain 1 Gusset Item (130) Retain attached with: 2 Pin Item (1) Discard 2 Collar Item (2) Discard 2 Screw Item (3) Discard 2 Nut Item (4) Discard

(23) Subtask 536177-831-023-002 - Depending on Inspection results, remove the Frame Foot from FR43, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 318 5

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# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FEAAB Replacement of the Frame foot FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Remove the Frame foot from Frame 43, LH side. Refer to Fig. A-FEAAB In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (104) Discard 1 Stiffener Item (58) Retain 1 Shim Item (70) Retain 1 Splice Item (72) Retain 4 Bolt Item (55) Retain 4 Nut Item (56) Discard 45 Pin Item (1) Discard 45 Collar Item (2) Discard 2 Bolt Item (3) Discard 2 Nut Item (4) Discard 2 Rivet Item (5) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 319 5

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

# @A300-600 SERVICE BULLETIN (24) Subtask 536177-831-024-002 - Depending on Inspection results, install an identical Frame Foot at FR43, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A08R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 7 SCREW 9 ASNA2529-3 39 NUT 10 EN6115V3A6 10 SCREW 11 EN6114V6Y14 2 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 4 SCREW 16 ASNA2529-5 5 NUT 17 EN6115V3A5 9 SCREW 19 ASNA2050DXJ4020 2 RIVET 20 EN6114V4Y9 1 SCREW 21 ASNA2529-4 1 NUT 32 EN6115V3A8 11 SCREW 33 EN6115V3A9 1 SCREW 36 EN6115V3A3 5 SCREW 37 EN6114V5Y10 1 SCREW 56 NSA5057-6 4 NUT 104 A5711113120095 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 320 5

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

# @A300-600 SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FEAAB Replacement of the Frame foot FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FPAAB Removal/Installation of the Gussets at FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FEAAB In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FEAAB

. 1 Frame foot A5711113120095 Item 104 1 Stiffener Item (58) Retained at removal 1 Shim Item (70) Retained at removal 1 Splice Item (72) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FEAAB Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H121 to H136, H140 to H149 and H152 to H157 to the diameter given on Fig. A-FEAAB Sheet 03 and Fig. A-FEAAB Sheet 04

. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 321 5

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

# @A300-600 SERVICE BULLETIN
3 Drill the holes of the stiffener H168 and H169 to the diameter given on Fig. AFEAAB Sheet 04

. 4 Drill the holes of the splice H137 to H139 and H158 to H167 to the diameter given on Fig. A-FEAAB Sheet 04

. (b) Cut-out the Frame foot Item 104 as shown on Fig. A-FEAAB Sheet 03

. Protect the cut-out with: Wash Primer - Structure 04CMA2 As required
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

(c) Install the fasteners. Refer to Fig. A-FEAAB In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H121 to H136, H140 to H149 and H152 to H157: Refer to Fig. A-FEAAB Sheet 03 and Fig. A-FEAAB Sheet 04 5 Screw EN6115V3A7 Item 8 10 Screw EN6115V3A6 Item 10 2 Screw ASNA2001V5-8Y Item 13 4 Screw EN6114V5Y8 Item 15 5 Screw EN6115V3A5 Item 17 5 Screw EN6115V3A8 Item 32 5 Screw EN6115V3A3 Item 36 26 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 4 Nut ASNA2529-5 Item 16 NOTE : Wet install the fasteners with: DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 322 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FEAAB Sheet 02 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H168 and H169: Refer to Fig. A-FEAAB Sheet 04 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the splice H137 to H139 and H158 to H167: Refer to Fig. A-FEAAB Sheet 05 2 Screw EN6115V3A7 Item 8 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 323 5

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# @A300-600 SERVICE BULLETIN
4 Screw EN6115V3A5 Item 17 6 Screw EN6115V3A8 Item 32 1 Screw EN6115V3A9 Item 33 13 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (d) Install the Gussets at Frame 43, LH side. Refer to Fig. A-FPAAB In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FPAAB Sheet 02 and Fig. AFPAAB Sheet 03

. 1 Gusset Item (128) Retained at removal 1 Gusset Item (130) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H150 and H151 to the diameter given on Fig. A-FPAAB Sheet 03

. 3 Drill holes H170 and H171 to the diameter given on Fig. A-FPAAB Sheet 03

.
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 324 5

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

# @A300-600 SERVICE BULLETIN
4 Install: 1 Gusset Item (128) Retained at removal 1 Gusset Item (130) Retained at removal 2 Screw EN6114V6Y14 Item 11 1 Screw EN6114V4Y9 Item 20 1 Screw EN6114V5Y10 Item 37 2 Nut ASNA2529-6 Item 12 1 Nut ASNA2529-5 Item 16 1 Nut ASNA2529-4 Item 21

(25) Subtask 536177-831-025-001 - Depending on Inspection results, if removed, install the Fasteners at FR43, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 47 EN6114V3X6 24 SCREW 90 ASNA2019-56-25 24 RIVET 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 325 5

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

# @A300-600 SERVICE BULLETIN
Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 43, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 24 Rivet ASNA2019-56-25 Item 90 or 24 Screw EN6114V3X6 Item 47 24 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 326 5

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

# @A300-600 SERVICE BULLETIN (26) Subtask 536177-831-026-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR43, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 43, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard 24 Nut Item (4) Discard

(27) Subtask 536177-831-027-002 - Depending on Inspection results, remove the Gussets from FR43, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 327 5

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

# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FPAAB Removal/Installation of the Gussets at FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 43, RH side. Refer to Fig. A-FPAAB In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (129) Retain 1 Gusset Item (131) Retain attached with: 2 Pin Item (1) Discard 2 Collar Item (2) Discard 2 Screw Item (3) Discard 2 Nut Item (4) Discard

(28) Subtask 536177-831-028-002 - Depending on Inspection results, remove the Frame Foot from FR43, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 328 5

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

# @A300-600 SERVICE BULLETIN
References Fig. A-FEAAB Replacement of the Frame foot FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Remove the Frame foot from Frame 43, RH side. Refer to Fig. A-FEAAB In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (105) Discard 1 Stiffener Item (57) Retain 1 Shim Item (70) Retain 1 Splice Item (71) Retain 4 Bolt Item (55) Retain 4 Nut Item (56) Discard 45 Pin Item (1) Discard 45 Collar Item (2) Discard 2 Bolt Item (3) Discard 2 Nut Item (4) Discard 2 Rivet Item (5) Discard

(29) Subtask 536177-831-029-002 - Depending on Inspection results, install an identical Frame Foot at FR43, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 329 5

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

# @A300-600 SERVICE BULLETIN Material necessary to do the job Kit 536177A26R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 7 SCREW 9 ASNA2529-3 39 NUT 10 EN6115V3A6 10 SCREW 11 EN6114V6Y14 2 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 4 SCREW 16 ASNA2529-5 5 NUT 17 EN6115V3A5 9 SCREW 19 ASNA2050DXJ4020 2 RIVET 20 EN6114V4Y9 1 SCREW 21 ASNA2529-4 1 NUT 32 EN6115V3A8 11 SCREW 33 EN6115V3A9 1 SCREW 36 EN6115V3A3 5 SCREW 37 EN6114V5Y10 1 SCREW 56 NSA5057-6 4 NUT 105 A5711113120195 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 330 5

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# @A300-600 SERVICE BULLETIN
References Fig. A-FEAAB Replacement of the Frame foot FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FPAAB Removal/Installation of the Gussets at FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FEAAB In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FEAAB

. 1 Frame foot A5711113120195 Item 105 1 Stiffener Item (57) Retained at removal 1 Shim Item (70) Retained at removal 1 Splice Item (71) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FEAAB Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H121 to H136, H140 to H149 and H152 to H157 to the diameter given on Fig. A-FEAAB Sheet 03 and Fig. A-FEAAB Sheet 04

. 3 Drill the holes of the stiffener H168 and H169 to the diameter given on Fig. AFEAAB Sheet 04

. 4 Drill the holes of the splice H137 to H139 and H158 to H167 to the diameter given on Fig. A-FEAAB Sheet 04

. (b) Cut-out the Frame foot Item 104 as shown on Fig. A-FEAAB Sheet 03

. Protect the cut-out with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 331 5

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

# @A300-600 SERVICE BULLETIN
Wash Primer - Structure 04CMA2 As required
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

(c) Install the fasteners. Refer to Fig. A-FEAAB In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H121 to H136, H140 to H149 and H152 to H157: Refer to Fig. A-FEAAB Sheet 03 and Fig. A-FEAAB Sheet 04 5 Screw EN6115V3A7 Item 8 10 Screw EN6115V3A6 Item 10 2 Screw ASNA2001V5-8Y Item 13 4 Screw EN6114V5Y8 Item 15 5 Screw EN6115V3A5 Item 17 5 Screw EN6115V3A8 Item 32 5 Screw EN6115V3A3 Item 36 26 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 4 Nut ASNA2529-5 Item 16 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 332 5

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

# @A300-600 SERVICE BULLETIN
2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FEAAB Sheet 02 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H168 and H169: Refer to Fig. A-FEAAB Sheet 04 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the splice H137 to H139 and H158 to H167: Refer to Fig. A-FEAAB Sheet 05 2 Screw EN6115V3A7 Item 8 4 Screw EN6115V3A5 Item 17 6 Screw EN6115V3A8 Item 32 1 Screw EN6115V3A9 Item 33 13 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 333 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (d) Install the Gussets at Frame 43, LH side. Refer to Fig. A-FPAAB In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FPAAB Sheet 02 and Fig. AFPAAB Sheet 03

. 1 Gusset Item (129) Retained at removal 1 Gusset Item (131) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H150 and H151 to the diameter given on Fig. A-FPAAB Sheet 02

. 3 Drill holes H170 and H171 to the diameter given on Fig. A-FPAAB Sheet 03

. 4 Install: 1 Gusset Item (129) Retained at removal 1 Gusset Item (131) Retained at removal 2 Screw EN6114V6Y14 Item 11 1 Screw EN6114V4Y9 Item 20 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 334 5

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

# @A300-600 SERVICE BULLETIN
1 Screw EN6114V5Y10 Item 37 2 Nut ASNA2529-6 Item 12 1 Nut ASNA2529-5 Item 16 1 Nut ASNA2529-4 Item 21

(30) Subtask 536177-831-030-001 - Depending on Inspection results, if removed, install the Fasteners at FR43, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 47 EN6114V3X6 24 SCREW 90 ASNA2019-56-25 24 RIVET 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 335 5

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

# @A300-600 SERVICE BULLETIN
References Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 43, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 24 Rivet ASNA2019-56-25 Item 90 or 24 Screw EN6114V3X6 Item 47 24 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(31) Subtask 536177-831-031-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR44, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 336 5

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

# @A300-600 SERVICE BULLETIN
References Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 44, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard 24 Nut Item (4) Discard

(32) Subtask 536177-831-032-002 - Depending on Inspection results, remove the Gussets from FR44, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FQAAB Removal/Installation of the Gussets at FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 44, LH side. Refer to Fig. A-FQAAB DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 337 5

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

# @A300-600 SERVICE BULLETIN
In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (132) Retain 1 Gusset Item (134) Retain attached with: 2 Pin Item (1) Discard 2 Collar Item (2) Discard 2 Screw Item (3) Discard 2 Nut Item (4) Discard

(33) Subtask 536177-831-033-002 - Depending on Inspection results, remove the Frame Foot from FR44, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FGAAB Replacement of the Frame foot FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Remove the Frame foot from Frame 44, LH side. Refer to Fig. A-FGAAB In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (106) Discard 1 Stiffener Item (58) Retain
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 338 5

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

# @A300-600 SERVICE BULLETIN 1 Splice Item (74) Retain 1 Shim Item (73) Retain 4 Bolt Item (55) Retain 4 Nut Item (56) Discard 39 Pin Item (1) Discard 39 Collar Item (2) Discard 2 Bolt Item (3) Discard 2 Nut Item (4) Discard 2 Rivet Item (5) Discard

(34) Subtask 536177-831-034-002 - Depending on Inspection results, install an identical Frame Foot at FR44, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A11R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 11 SCREW 9 ASNA2529-3 35 NUT 10 EN6115V3A6 12 SCREW 11 EN6114V6Y14 2 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 2 SCREW 16 ASNA2529-5 4 NUT 17 EN6115V3A5 9 SCREW 18 EN6115V3A4 2 SCREW 19 ASNA2050DXJ4020 2 RIVET DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 339 5

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

# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 36 EN6115V3A3 1 SCREW 37 EN6114V5Y10 2 SCREW 56 NSA5057-6 4 NUT 106 A5711113220095 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FQAAB Removal/Installation of the Gussets at FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Fig. A-FGAAB Replacement of the Frame foot FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Install and drill all the parts. Refer to Fig. A-FGAAB In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FGAAB

. 1 Frame foot A5711113220095 Item 106 1 Stiffener Item (58) Retained at removal 1 Splice Item (74) Retained at removal DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 340 5

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

# @A300-600 SERVICE BULLETIN 1 Shim Item (73) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FGAAB Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H180 to H202 and H205 to H208 to the diameter given on Fig. A-FGAAB Sheet 03 and Fig. A-FGAAB Sheet 04

. 3 Drill the holes of the stiffener H221 and H222 to the diameter given on Fig. AFGAAB Sheet 03

. 4 Drill the holes of the splice H209 to H220 to the diameter given on Fig. AFGAAB Sheet 05

. (b) Cut-out the Frame foot Item 106 as shown on Fig. A-FGAAB Sheet 03

. Protect the cut-out with: Wash Primer - Structure 04CMA2 As required
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

(c) Install the fasteners. Refer to Fig. A-FGAAB In accordance with SRM 51-40-00, SRM 51-40-20, and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H180 to H202 and H205 to H208: Refer to Fig. A-FGAAB Sheet 03 and Fig. A-FGAAB Sheet 04 10 Screw EN6115V3A7 Item 8 12 Screw EN6115V3A6 Item 10 2 Screw ASNA2001V5-8Y Item 13 2 Screw EN6114V5Y8 Item 15
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 341 5

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

# @A300-600 SERVICE BULLETIN
1 Screw EN6115V3A3 Item 36 23 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 2 Nut ASNA2529-5 Item 16 NOTE : For holes H205 to H208, adjust the shims as shown on Fig. AFGAAB Sheet 04

. NOTE : Wet install the fasteners except for holes H203 and H204 with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FGAAB Sheet 02 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H221 and H222: Refer to Fig. A-FGAAB Sheet 03 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 342 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the splice H209 to H220: Refer to Fig. A-FGAAB Sheet 05 1 Screw EN6115V3A7 Item 8 9 Screw EN6115V3A5 Item 17 2 Screw EN6115V3A4 Item 18 12 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (d) Install the Gussets at Frame 44, LH side. Refer to Fig. A-FQAAB In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FQAAB

. 1 Gusset Item (132) Retained at removal 1 Gusset Item (134) Retained at removal DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 343 5

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

# @A300-600 SERVICE BULLETIN
NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H203 and H204 to the diameter given on Fig. A-FQAAB Sheet 03

. 3 Drill holes H223 and H224 to the diameter given on Fig. A-FQAAB Sheet 03

. 4 Install: 1 Gusset Item (132) Retained at removal 1 Gusset Item (134) Retained at removal 2 Screw EN6114V5Y10 Item 37 2 Screw EN6114V6Y14 Item 11 2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-5 Item 16

(35) Subtask 536177-831-035-001 - Depending on Inspection results, if removed, install the Fasteners at FR44, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 90 ASNA2019-56-25 24 RIVET 91 EN6114V3X5 24 SCREW 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 344 5

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

# @A300-600 SERVICE BULLETIN
NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 44, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 24 Rivet ASNA2019-56-25 Item 90 or 24 Screw EN6114V3X5 Item 91 24 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 345 5

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

# @A300-600 SERVICE BULLETIN (36) Subtask 536177-831-036-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR44, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 44, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard 24 Nut Item (4) Discard

(37) Subtask 536177-831-037-002 - Depending on Inspection results, remove the Gussets from FR44, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 346 5

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

# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FQAAB Removal/Installation of the Gussets at FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 44, RH side. Refer to Fig. A-FQAAB In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (133) Retain 1 Gusset Item (135) Retain attached with: 2 Pin Item (1) Discard 2 Collar Item (2) Discard 2 Screw Item (3) Discard 2 Nut Item (4) Discard

(38) Subtask 536177-831-038-002 - Depending on Inspection results, remove the Frame Foot from FR44, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 347 5

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

# @A300-600 SERVICE BULLETIN
References Fig. A-FGAAB Replacement of the Frame foot FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Remove the Frame foot from Frame 44, RH side. Refer to Fig. A-FGAAB In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (107) Discard 1 Stiffener Item (57) Retain 1 Splice Item (75) Retain 1 Shim Item (73) Retain 4 Bolt Item (55) Retain 4 Nut Item (56) Discard 39 Pin Item (1) Discard 39 Collar Item (2) Discard 2 Bolt Item (3) Discard 2 Nut Item (4) Discard 2 Rivet Item (5) Discard

(39) Subtask 536177-831-039-002 - Depending on Inspection results, install an identical Frame Foot at FR44, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 348 5

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

# @A300-600 SERVICE BULLETIN Material necessary to do the job Kit 536177A29R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 11 SCREW 9 ASNA2529-3 35 NUT 10 EN6115V3A6 12 SCREW 11 EN6114V6Y14 2 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 2 SCREW 16 ASNA2529-5 4 NUT 17 EN6115V3A5 9 SCREW 18 EN6115V3A4 2 SCREW 19 ASNA2050DXJ4020 2 RIVET 36 EN6115V3A3 1 SCREW 37 EN6114V5Y10 2 SCREW 56 NSA5057-6 4 NUT 107 A5711113220195 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FGAAB Replacement of the Frame foot FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 349 5

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

# @A300-600 SERVICE BULLETIN
References Fig. A-FQAAB Removal/Installation of the Gussets at FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FGAAB In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FGAAB

. 1 Frame foot A5711113220195 Item 107 1 Stiffener Item (57) Retained at removal 1 Splice Item (75) Retained at removal 1 Shim Item (73) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FGAAB Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H180 to H202 and H205 to H208 to the diameter given on Fig. A-FGAAB Sheet 03 and Fig. A-FGAAB Sheet 04

. 3 Drill the holes of the stiffener H221 and H222 to the diameter given on Fig. AFGAAB Sheet 03

. 4 Drill the holes of the splice H209 to H220 to the diameter given on Fig. AFGAAB Sheet 05

. (b) Cut-out the Frame foot Item 106 as shown on Fig. A-FGAAB Sheet 03

. Protect the cut-out with: Wash Primer - Structure 04CMA2 As required
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 350 5

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

# @A300-600 SERVICE BULLETIN (c) Install the fasteners. Refer to Fig. A-FGAAB In accordance with SRM 51-40-00, SRM 51-40-20, and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H180 to H202 and H205 to H208: Refer to Fig. A-FGAAB Sheet 03 and Fig. A-FGAAB Sheet 04 10 Screw EN6115V3A7 Item 8 12 Screw EN6115V3A6 Item 10 2 Screw ASNA2001V5-8Y Item 13 2 Screw EN6114V5Y8 Item 15 1 Screw EN6115V3A3 Item 36 23 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 2 Nut ASNA2529-5 Item 16 NOTE : For holes H205 to H208, adjust the shims as shown on Fig. AFGAAB Sheet 04

. NOTE : Wet install the fasteners except for holes H203 and H204 with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FGAAB Sheet 02 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with: DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 351 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H221 and H222: Refer to Fig. A-FGAAB Sheet 03 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the splice H209 to H220: Refer to Fig. A-FGAAB Sheet 05 1 Screw EN6115V3A7 Item 8 9 Screw EN6115V3A5 Item 17 2 Screw EN6115V3A4 Item 18 12 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 352 5

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

# @A300-600 SERVICE BULLETIN
5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (d) Install the Gussets at Frame 44, LH side. Refer to Fig. A-FQAAB In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FQAAB

. 1 Gusset Item (133) Retained at removal 1 Gusset Item (135) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H203 and H204 to the diameter given on Fig. A-FQAAB Sheet 03

. 3 Drill holes H223 and H224 to the diameter given on Fig. A-FQAAB Sheet 03

. 4 Install: 1 Gusset Item (133) Retained at removal 1 Gusset Item (135) Retained at removal 2 Screw EN6114V5Y10 Item 37 2 Screw EN6114V6Y14 Item 11 2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-5 Item 16

(40) Subtask 536177-831-040-001 - Depending on Inspection results, if removed, install the Fasteners at FR44, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 353 5

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

# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 90 ASNA2019-56-25 24 RIVET 91 EN6114V3X5 24 SCREW 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 44, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 354 5

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

# @A300-600 SERVICE BULLETIN
1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 24 Rivet ASNA2019-56-25 Item 90 or 24 Screw EN6114V3X5 Item 91 24 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(41) Subtask 536177-831-041-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR45, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 45, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 20 Rivet Item (19) Discard DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 355 5

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

# @A300-600 SERVICE BULLETIN
And: 32 Rivet Item (5) Discard or 32 Bolt Item (3) Discard 32 Nut Item (4) Discard

(42) Subtask 536177-831-042-002 - Depending on Inspection results, remove the Gussets from FR45, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FTAAB Removal/Installation of the Gussets at FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 45, LH side. Refer to Fig. A-FTAAB In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (136) Retain 1 Gusset Item (138) Retain attached with: 2 Pin Item (1) Discard 2 Collar Item (2) Discard 2 Screw Item (3) Discard 2 Nut Item (4) Discard
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 356 5

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

# @A300-600 SERVICE BULLETIN (43) Subtask 536177-831-043-002 - Depending on Inspection results, remove the Frame Foot from FR45, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FJAAB Replacement of the Frame foot FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Remove the Frame foot from Frame 45, LH side. Refer to Fig. A-FJAAB In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (108) Discard 2 Stiffener Item (58) Retain 1 Splice Item (72) Retain 1 Doubler Item (77) Retain 1 Shim Item (78) Retain 36 Pin Item (1) Discard 36 Collar Item (2) Discard 4 Rivet Item (19) Discard 15 Screw Item (3) Discard 15 Nut Item (4) Discard DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 357 5

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# @A300-600 SERVICE BULLETIN
And: 4 Screw Item (55) Retain 4 Nut Item (56) Discard or 4 Nut Item (76) Discard And: 1 Rivet Item (5) Discard or 1 Screw Item (93) Discard 1 Nut Item (94) Discard And if installed, remove: 1 Bracket Item (79) Retain

(44) Subtask 536177-831-044-002 - Depending on Inspection results, install an identical Frame Foot at FR45, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 145 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A14R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 4 SCREW 9 ASNA2529-3 48 NUT 10 EN6115V3A6 7 SCREW 11 EN6114V6Y14 2 SCREW 12 ASNA2529-6 2 NUT 16 ASNA2529-5 2 NUT 17 EN6115V3A5 3 SCREW 19 ASNA2050DXJ4020 4 RIVET 32 EN6115V3A8 7 SCREW DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 358 5

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 33 EN6115V3A9 17 SCREW 37 EN6114V5Y10 2 SCREW 42 EN6114V3A6 1 SCREW 43 EN6115V3A10 2 SCREW 44 EN6115V3A11 7 SCREW 45 ASNA2001V6-8Y 2 SCREW 46 NAS1726-6E 2 NUT 56 NSA5057-6 4 NUT 76 NSA5057-7 4 NUT 108 A5711113320095 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FJAAB Replacement of the Frame foot FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Fig. A-FTAAB Removal/Installation of the Gussets at FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FJAAB In accordance with SRM 51-40-40

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 359 5

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# @A300-600 SERVICE BULLETIN
1 Put all the parts in position as shown on Fig. A-FJAAB

. 1 Frame foot A5711113320095 Item 108 2 Stiffener Item (58) Retained at removal 1 Splice Item (72) Retained at removal 1 Doubler Item (77) Retained at removal 1 Shim Item (78) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FJAAB Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H231 to H254, H257 to H266 and H271 to H272 to the diameter given on Fig. A-FJAAB Sheet 03 to Fig. A-FJAAB Sheet 05

. 3 Drill the holes of the stiffener at STGR 36 H255 and H256 to the diameter given on Fig. A-FJAAB Sheet 03

. 4 Drill the holes of the stiffener at STGR 37 H267 and H268 to the diameter given on Fig. A-FJAAB Sheet 05

. 5 Drill the holes of the splice H273 to H285 to the diameter given on Fig. AFJAAB Sheet 06

. (b) Cut-out the Frame foot Item 108 as shown on Fig. A-FJAAB Sheet 03

. Protect the cut-out with: Wash Primer - Structure 04CMA2 As required
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

(c) Install the fasteners. Refer to Fig. A-FJAAB DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 360 5

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

# @A300-600 SERVICE BULLETIN In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H231 to H254, H257 to H266 and H271 to H272: Refer to Fig. A-FJAAB Sheet 03 to Fig. A-FJAAB Sheet 05 2 Screw EN6115V3A7 Item 8 5 Screw EN6115V3A6 Item 10 1 Screw EN6115V3A5 Item 17 1 Screw EN6115V3A8 Item 32 16 Screw EN6115V3A9 Item 33 1 Screw EN6114V3A6 Item 42 2 Screw EN6115V3A10 Item 43 7 Screw EN6115V3A11 Item 44 2 Screw ASNA2001V6-8Y Item 45 35 Nut ASNA2529-3 Item 9 2 Nut NAS1726-6E Item 46 NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FJAAB Sheet 02 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 or 4 Nut NSA5057-7 Item 76 NOTE : Wet install the fasteners with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 361 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H255 and H256: Refer to Fig. A-FJAAB Sheet 03 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the stiffener at STGR 37 H267 and H268: Refer to Fig. A-FJAAB Sheet 06 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Install the fasteners of the splice H273 to H285: Refer to Fig. A-FJAAB Sheet 06 2 Screw EN6115V3A7 Item 8 2 Screw EN6115V3A5 Item 17 6 Screw EN6115V3A8 Item 32 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 362 5

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# @A300-600 SERVICE BULLETIN
1 Screw EN6115V3A9 Item 33 13 Nut ASNA2529-3 Item 9 2 Screw EN6115V3A6 Item 10 And if removed, install: 1 Bracket Item (79) Retained at removal NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

6 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (d) Install the Gussets at Frame 45, LH side. Refer to Fig. A-FTAAB In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FTAAB

. 1 Gusset Item (136) Retained at removal 1 Gusset Item (138) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H269 and H270 to the diameter given on Fig. A-FTAAB Sheet 02

. 3 Drill holes H286 and H287 to the diameter given on Fig. A-FTAAB Sheet 03

. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 363 5

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# @A300-600 SERVICE BULLETIN
4 Install: 1 Gusset Item (136) Retained at removal 1 Gusset Item (138) Retained at removal 2 Screw EN6114V6Y14 Item 11 2 Screw EN6114V5Y10 Item 37 2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-5 Item 16

(45) Subtask 536177-831-045-001 - Depending on Inspection results, if removed, install the Fasteners at FR45, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 32 NUT 47 EN6114V3X6 32 SCREW 90 ASNA2019-56-25 32 RIVET 92 EN6080D6X-32 20 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 364 5

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

# @A300-600 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 45, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 20 Rivet EN6080D6X-32 Item 92 And: 32 Rivet ASNA2019-56-25 Item 90 or 32 Screw EN6114V3X6 Item 47 32 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(46) Subtask 536177-831-046-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR45, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 365 5

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

# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 45, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 20 Rivet Item (19) Discard And: 32 Rivet Item (5) Discard or 32 Bolt Item (3) Discard 32 Nut Item (4) Discard

(47) Subtask 536177-831-047-002 - Depending on Inspection results, remove the Gussets from FR45, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 366 5

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

# @A300-600 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-40-20 Fig. A-FTAAB Removal/Installation of the Gussets at FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 45, RH side. Refer to Fig. A-FTAAB In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (137) Retain 1 Gusset Item (139) Retain attached with: 2 Pin Item (1) Discard 2 Collar Item (2) Discard 2 Screw Item (3) Discard 2 Nut Item (4) Discard

(48) Subtask 536177-831-048-002 - Depending on Inspection results, remove the Frame Foot from FR45, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FJAAB Replacement of the Frame foot FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 367 5

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

# @A300-600 SERVICE BULLETIN (a) Remove the Frame foot from Frame 45, RH side. Refer to Fig. A-FJAAB In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (109) Discard 2 Stiffener Item (57) Retain 1 Splice Item (71) Retain 1 Doubler Item (77) Retain 1 Shim Item (78) Retain 36 Pin Item (1) Discard 36 Collar Item (2) Discard 4 Rivet Item (19) Discard 15 Screw Item (3) Discard 15 Nut Item (4) Discard And: 4 Screw Item (55) Retain 4 Nut Item (56) Discard or 4 Nut Item (76) Discard And: 1 Rivet Item (5) Discard or 1 Screw Item (93) Discard 1 Nut Item (94) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 368 5

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

# @A300-600 SERVICE BULLETIN (49) Subtask 536177-831-049-002 - Depending on Inspection results, install an identical Frame Foot at FR45, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A32R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 4 SCREW 9 ASNA2529-3 48 NUT 10 EN6115V3A6 5 SCREW 11 EN6114V6Y14 2 SCREW 12 ASNA2529-6 2 NUT 16 ASNA2529-5 2 NUT 17 EN6115V3A5 5 SCREW 19 ASNA2050DXJ4020 4 RIVET 32 EN6115V3A8 7 SCREW 33 EN6115V3A9 17 SCREW 37 EN6114V5Y10 2 SCREW 42 EN6114V3A6 1 SCREW 43 EN6115V3A10 2 SCREW 44 EN6115V3A11 7 SCREW 45 ASNA2001V6-8Y 2 SCREW 46 NAS1726-6E 2 NUT 56 NSA5057-6 4 NUT 76 NSA5057-7 4 NUT 109 A5711113320195 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 369 5

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

# @A300-600 SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FJAAB Replacement of the Frame foot FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Fig. A-FTAAB Removal/Installation of the Gussets at FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FJAAB In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FJAAB

. 1 Frame foot A5711113320195 Item 109 2 Stiffener Item (57) Retained at removal 1 Splice Item (71) Retained at removal 1 Doubler Item (77) Retained at removal 1 Shim Item (78) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FJAAB Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 370 5

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

# @A300-600 SERVICE BULLETIN
2 Drill the holes of the Frame foot H231 to H254, H257 to H266 and H271 to H272 to the diameter given on Fig. A-FJAAB Sheet 03 to Fig. A-FJAAB Sheet 05

. 3 Drill the holes of the stiffener at STGR 36 H255 and H256 to the diameter given on Fig. A-FJAAB Sheet 03

. 4 Drill the holes of the stiffener at STGR 37 H267 and H268 to the diameter given on Fig. A-FJAAB Sheet 05

. 5 Drill the holes of the splice H273 to H285 to the diameter given on Fig. AFJAAB Sheet 06

. (b) Cut-out the Frame foot Item 108 as shown on Fig. A-FJAAB Sheet 03

. Protect the cut-out with: Wash Primer - Structure 04CMA2 As required
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

(c) Install the fasteners. Refer to Fig. A-FJAAB In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H231 to H254, H257 to H266 and H271 to H272: Refer to Fig. A-FJAAB Sheet 03 to Fig. A-FJAAB Sheet 05 2 Screw EN6115V3A7 Item 8 5 Screw EN6115V3A6 Item 10 1 Screw EN6115V3A5 Item 17 1 Screw EN6115V3A8 Item 32 16 Screw EN6115V3A9 Item 33 1 Screw EN6114V3A6 Item 42 2 Screw EN6115V3A10 Item 43 7 Screw EN6115V3A11 Item 44 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 371 5

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

# @A300-600 SERVICE BULLETIN
2 Screw ASNA2001V6-8Y Item 45 35 Nut ASNA2529-3 Item 9 2 Nut NAS1726-6E Item 46 NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FJAAB Sheet 02 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 or 4 Nut NSA5057-7 Item 76 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H255 and H256: Refer to Fig. A-FJAAB Sheet 03 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 372 5

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

# @A300-600 SERVICE BULLETIN
4 Install the fasteners of the stiffener at STGR 37 H267 and H268: Refer to Fig. A-FJAAB Sheet 06 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Install the fasteners of the splice H273 to H285: Refer to Fig. A-FJAAB Sheet 06 2 Screw EN6115V3A7 Item 8 4 Screw EN6115V3A5 Item 17 6 Screw EN6115V3A8 Item 32 1 Screw EN6115V3A9 Item 33 13 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

6 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (d) Install the Gussets at Frame 45, LH side. Refer to Fig. A-FTAAB In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 373 5

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

# @A300-600 SERVICE BULLETIN Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FTAAB

. 1 Gusset Item (137) Retained at removal 1 Gusset Item (139) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H269 and H270 to the diameter given on Fig. A-FTAAB Sheet 03

. 3 Drill holes H286 and H287 to the diameter given on Fig. A-FTAAB Sheet 03

. 4 Install: 1 Gusset Item (137) Retained at removal 1 Gusset Item (139) Retained at removal 2 Screw EN6114V6Y14 Item 11 2 Screw EN6114V5Y10 Item 37 2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-5 Item 16

(50) Subtask 536177-831-050-001 - Depending on Inspection results, install the Fasteners at FR45, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 374 5

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

# @A300-600 SERVICE BULLETIN Material necessary to do the job Component COMPA04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 32 NUT 47 EN6114V3X6 32 SCREW 90 ASNA2019-56-25 32 RIVET 92 EN6080D6X-32 20 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 45, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 20 Rivet EN6080D6X-32 Item 92 And: 32 Rivet ASNA2019-56-25 Item 90 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 375 5

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

# @A300-600 SERVICE BULLETIN

or 32 Screw EN6114V3X6 Item 47 32 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(51) Subtask 536177-831-051-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR46, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 46, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 376 5

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

# @A300-600 SERVICE BULLETIN 24 Nut Item (4) Discard

(52) Subtask 536177-831-052-002 - Depending on Inspection results, remove the Gussets from FR46, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FUAAB Removal/Installation of the Gussets at FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 46, LH side. Refer to Fig. A-FUAAB In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (140) Retain 1 Gusset Item (142) Retain attached with: 2 Pin Item (1) Discard 2 Collar Item (2) Discard 2 Screw Item (3) Discard 2 Nut Item (4) Discard

(53) Subtask 536177-831-053-002 - Depending on Inspection results, remove the Frame Foot from FR46, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 377 5

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

# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FKAAB Replacement of the Frame foot FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Remove the Frame foot from Frame 46, LH side. Refer to Fig. A-FKAAB In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (110) Discard 1 Stiffener Item (58) Retain 1 Doubler Item (80) Retain 1 Shim Item (81) Retain 1 Splice Item (82) Retain 40 Pin Item (1) Discard 40 Collar Item (2) Discard 2 Rivet Item (19) Discard 13 Screw Item (3) Discard 13 Nut Item (4) Discard And: 4 Screw Item (55) Retain 4 Nut Item (56) Discard or DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 378 5

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

# @A300-600 SERVICE BULLETIN 4 Nut Item (76) Discard

(54) Subtask 536177-831-054-002 - Depending on Inspection results, install an identical Frame Foot at FR46, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 16.00 Minimum number of person 1 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A17R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 3 SCREW 9 ASNA2529-3 43 NUT 10 EN6115V3A6 11 SCREW 11 EN6114V6Y14 1 SCREW 12 ASNA2529-6 3 NUT 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 6 SCREW 16 ASNA2529-5 7 NUT 17 EN6115V3A5 7 SCREW 18 EN6115V3A4 2 SCREW 19 ASNA2050DXJ4020 2 RIVET 33 EN6115V3A9 9 SCREW 43 EN6115V3A10 5 SCREW 44 EN6115V3A11 6 SCREW 49 EN6114V6Y17 2 SCREW 50 ASNA2001V5-12Y 2 SCREW 51 EN6114V5Y12 1 SCREW 56 NSA5057-6 4 NUT 76 NSA5057-7 4 NUT 110 A5711113420095 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 379 5

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

# @A300-600 SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FKAAB Replacement of the Frame foot FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FUAAB Removal/Installation of the Gussets at FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FKAAB In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FKAAB

. 1 Frame foot A5711113420095 Item 110 1 Stiffener Item (58) Retained at removal 1 Doubler Item (80) Retained at removal 1 Shim Item (81) Retained at removal 1 Splice Item (82) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FKAAB Sheet 03

. NOTE : Between parts apply: DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 380 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H300 to H313, H316 to H331 and H334 to H341 to the diameter given on Fig. A-FKAAB Sheet 03 and Fig. A-FKAAB Sheet 04

. 3 Drill the holes of the stiffener H314 and H315 to the diameter given on Fig. AFKAAB Sheet 04

. 4 Drill the holes of the splice H342 to H354 to the diameter given on Fig. AFKAAB Sheet 05

. (b) Cut-out the Frame foot Item 110 as shown on Fig. A-FKAAB Sheet 03

. Protect the cut-out with: Wash Primer - Structure 04CMA2 As required
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

(c) Install the fasteners. Refer to Fig. A-FKAAB In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H300 to H313, H316 to H331 and H334 to H341 to H313 and H316 to H341: Refer to Fig. A-FKAAB Sheet 03 and Fig. A-FKAAB Sheet 04 2 Screw EN6115V3A7 Item 8 8 Screw EN6115V3A6 Item 10 6 Screw EN6114V5Y8 Item 15 9 Screw EN6115V3A9 Item 33 5 Screw EN6115V3A10 Item 43 6 Screw EN6115V3A11 Item 44 2 Screw ASNA2001V5-12Y Item 50 30 Nut ASNA2529-3 Item 9 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 381 5

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

# @A300-600 SERVICE BULLETIN
2 Nut NAS1726-5E Item 14 6 Nut ASNA2529-5 Item 16 NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FKAAB Sheet 02 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 or 4 Nut NSA5057-7 Item 76 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 37 H314 and H315: Refer to Fig. A-FKAAB Sheet 04 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 382 5

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

# @A300-600 SERVICE BULLETIN
4 Install the fasteners of the splice H342 to H354: Refer to Fig. A-FKAAB Sheet 05 1 Screw EN6115V3A7 Item 8 3 Screw EN6115V3A6 Item 10 7 Screw EN6115V3A5 Item 17 2 Screw EN6115V3A4 Item 18 13 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (d) Install the Gussets at Frame 46, LH side. Refer to Fig. A-FUAAB In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FUAAB

. 1 Gusset Item (140) Retained at removal 1 Gusset Item (142) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset.
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 383 5

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

# @A300-600 SERVICE BULLETIN
2 Drill holes H332 and H333 to the diameter given on Fig. A-FUAAB Sheet 02

. 3 Drill holes H355 and H356 to the diameter given on Fig. A-FUAAB Sheet 03

. 4 Install: 1 Gusset Item (140) Retained at removal 1 Gusset Item (142) Retained at removal 1 Screw EN6114V6Y14 Item 11 2 Screw EN6114V6Y17 Item 49 1 Screw EN6114V5Y12 Item 51 3 Nut ASNA2529-6 Item 12 1 Nut ASNA2529-5 Item 16

(55) Subtask 536177-831-055-001 - Depending on Inspection results, if removed, install the Fasteners at FR46, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA05 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 47 EN6114V3X6 16 SCREW 90 ASNA2019-56-25 24 RIVET 91 EN6114V3X5 8 SCREW 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 384 5

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

# @A300-600 SERVICE BULLETIN
Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 46, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 16 Rivet ASNA2019-56-25 Item 90 or 16 Screw EN6114V3X6 Item 47 16 Nut ASNA2529-3 Item 9 And: 8 Rivet ASNA2019-56-25 Item 90 or 8 Screw EN6114V3X5 Item 91 8 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 385 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(56) Subtask 536177-831-056-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR46, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 46, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard 24 Nut Item (4) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 386 5

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

# @A300-600 SERVICE BULLETIN (57) Subtask 536177-831-057-002 - Depending on Inspection results, remove the Gussets from FR46, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FUAAB Removal/Installation of the Gussets at FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 46, RH side. Refer to Fig. A-FUAAB In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (141) Retain 1 Gusset Item (143) Retain attached with: 2 Pin Item (1) Discard 2 Collar Item (2) Discard 2 Screw Item (3) Discard 2 Nut Item (4) Discard

(58) Subtask 536177-831-058-002 - Depending on Inspection results, remove the Frame Foot from FR46, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 387 5

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

# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FKAAB Replacement of the Frame foot FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Remove the Frame foot from Frame 46, RH side. Refer to Fig. A-FKAAB In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (111) Discard 1 Stiffener Item (57) Retain 1 Doubler Item (80) Retain 1 Shim Item (81) Retain 1 Splice Item (83) Retain 40 Pin Item (1) Discard 40 Collar Item (2) Discard 2 Rivet Item (19) Discard 13 Screw Item (3) Discard 13 Nut Item (4) Discard And: 4 Screw Item (55) Retain 4 Nut Item (56) Discard or DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 388 5

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

# @A300-600 SERVICE BULLETIN 4 Nut Item (76) Discard

(59) Subtask 536177-831-059-002 - Depending on Inspection results, install an identical Frame Foot at FR46, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A35R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 3 SCREW 9 ASNA2529-3 43 NUT 10 EN6115V3A6 8 SCREW 11 EN6114V6Y14 1 SCREW 12 ASNA2529-6 3 NUT 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 6 SCREW 16 ASNA2529-5 7 NUT 17 EN6115V3A5 7 SCREW 18 EN6115V3A4 2 SCREW 19 ASNA2050DXJ4020 2 RIVET 33 EN6115V3A9 9 SCREW 43 EN6115V3A10 5 SCREW 44 EN6115V3A11 6 SCREW 49 EN6114V6Y17 2 SCREW 50 ASNA2001V5-12Y 2 SCREW 51 EN6114V5Y12 1 SCREW 56 NSA5057-6 4 NUT 76 NSA5057-7 4 NUT 111 A5711113420195 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 389 5

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

# @A300-600 SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FKAAB Replacement of the Frame foot FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FUAAB Removal/Installation of the Gussets at FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FKAAB In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FKAAB

. 1 Frame foot A5711113420195 Item 111 1 Stiffener Item (57) Retained at removal 1 Doubler Item (80) Retained at removal 1 Shim Item (81) Retained at removal 1 Splice Item (83) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FKAAB Sheet 03

. NOTE : Between parts apply: DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 390 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H300 to H313, H316 to H331 and H334 to H341 to the diameter given on Fig. A-FKAAB Sheet 03 and Fig. A-FKAAB Sheet 04

. 3 Drill the holes of the stiffener H314 and H315 to the diameter given on Fig. AFKAAB Sheet 04

. 4 Drill the holes of the splice H342 to H354 to the diameter given on Fig. AFKAAB Sheet 05

. (b) Cut-out the Frame foot Item 110 as shown on Fig. A-FKAAB Sheet 03

. Protect the cut-out with: Wash Primer - Structure 04CMA2 As required
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

(c) Install the fasteners. Refer to Fig. A-FKAAB In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H300 to H313, H316 to H331 and H334 to H341 to H313 and H316 to H341: Refer to Fig. A-FKAAB Sheet 03 and Fig. A-FKAAB Sheet 04 2 Screw EN6115V3A7 Item 8 5 Screw EN6115V3A6 Item 10 6 Screw EN6114V5Y8 Item 15 9 Screw EN6115V3A9 Item 33 5 Screw EN6115V3A10 Item 43 6 Screw EN6115V3A11 Item 44 2 Screw ASNA2001V5-12Y Item 50 30 Nut ASNA2529-3 Item 9 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 391 5

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

# @A300-600 SERVICE BULLETIN
2 Nut NAS1726-5E Item 14 6 Nut ASNA2529-5 Item 16 NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FKAAB Sheet 02 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 or 4 Nut NSA5057-7 Item 76 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 37 H314 and H315: Refer to Fig. A-FKAAB Sheet 04 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 392 5

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

# @A300-600 SERVICE BULLETIN
4 Install the fasteners of the splice H342 to H354: Refer to Fig. A-FKAAB Sheet 05 1 Screw EN6115V3A7 Item 8 3 Screw EN6115V3A6 Item 10 7 Screw EN6115V3A5 Item 17 2 Screw EN6115V3A4 Item 18 13 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (d) Install the Gussets at Frame 46, LH side. Refer to Fig. A-FUAAB In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FUAAB

. 1 Gusset Item (141) Retained at removal 1 Gusset Item (143) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset.
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 393 5

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

# @A300-600 SERVICE BULLETIN
2 Drill holes H332 and H333 to the diameter given on Fig. A-FUAAB Sheet 03

. 3 Drill holes H355 and H356 to the diameter given on Fig. A-FUAAB Sheet 03

. 4 Install: 1 Gusset Item (141) Retained at removal 1 Gusset Item (143) Retained at removal 1 Screw EN6114V6Y14 Item 11 2 Screw EN6114V6Y17 Item 49 1 Screw EN6114V5Y12 Item 51 3 Nut ASNA2529-6 Item 12 1 Nut ASNA2529-5 Item 16

(60) Subtask 536177-831-060-001 - Depending on Inspection results, install the Fasteners at FR46, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA05 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 47 EN6114V3X6 16 SCREW 90 ASNA2019-56-25 24 RIVET 91 EN6114V3X5 8 SCREW 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 394 5

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

# @A300-600 SERVICE BULLETIN
Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 46, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 16 Rivet ASNA2019-56-25 Item 90 or 16 Screw EN6114V3X6 Item 47 16 Nut ASNA2529-3 Item 9 And: 8 Rivet ASNA2019-56-25 Item 90 or 8 Screw EN6114V3X5 Item 91 8 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 395 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

**CONF 003 (1) Subtask 536177-831-001-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR41, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 41, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 20 Rivet Item (19) Discard And: 32 Rivet Item (5) Discard or 32 Bolt Item (3) Discard 32 Nut Item (4) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 396 5

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

# @A300-600 SERVICE BULLETIN (2) Subtask 536177-831-002-001 - Depending on Inspection results, remove the Gussets from FR41, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FLAAA Removal/Installation of the Gussets at FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 41, LH side. Refer to Fig. A-FLAAA In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (120) Retain 1 Gusset Item (122) Retain attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

(3) Subtask 536177-831-003-001 - Depending on Inspection results, remove the Frame Foot from FR41, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 397 5

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

# @A300-600 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-40-20 Fig. A-FCAAA Replacement of the Frame foot FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Remove the Frame foot from Frame 41, LH side. Refer to Fig. A-FCAAA In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (100) Discard 1 Stiffener Item (58) Retain 1 Splice Item (60) Retain 1 Shim Item (61) Retain 4 Screw Item (55) Retain 4 Nut Item (56) Discard 14 Pin Item (1) Discard 14 Collar Item (2) Discard 30 Screw Item (3) Discard 30 Nut Item (4) Discard 2 Rivet Item (5) Discard

(4) Subtask 536177-831-004-001 - Depending on Inspection results, install an identical Frame Foot at FR41, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 398 5

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

# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 15 SCREW 9 ASNA2529-3 36 NUT 10 EN6115V3A6 9 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 4 SCREW 16 ASNA2529-5 4 NUT 17 EN6115V3A5 10 SCREW 18 EN6115V3A4 2 SCREW 19 ASNA2050DXJ4020 2 RIVET 21 ASNA2529-4 2 NUT 26 EN6114V6X14 2 SCREW 30 EN6114V4X8 1 SCREW 31 EN6114V4X10 1 SCREW 56 NSA5057-6 4 NUT 100 A5711112920095 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 399 5

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

# @A300-600 SERVICE BULLETIN
References Fig. A-FCAAA Replacement of the Frame foot FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FLAAA Removal/Installation of the Gussets at FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FCAAA In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FCAAA

. 1 Frame foot A5711112920095 Item 100 1 Stiffener Item (58) Retained at removal 1 Splice Item (60) Retained at removal 1 Shim Item (61) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FCAAA Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H1 to H23 and H26 to H31 to the diameter given on Fig. A-FCAAA Sheet 03 and Fig. A-FCAAA Sheet 04

. 3 Drill the holes of the stiffener H45 and H46 to the diameter given on Fig. AFCAAA Sheet 04

. 4 Drill the holes of the splice H32 to H44 to the diameter given on Fig. A-FCAAA Sheet 05

. (b) Cut-out the Frame foot Item 100 as shown on Fig. A-FCAAA Sheet 03

. Protect the cut-out with: Wash Primer - Structure 04CMA2 As required
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 400 5

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# @A300-600 SERVICE BULLETIN
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

(c) Install the fasteners. Refer to Fig. A-FCAAA In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H1 to H23 and H26 to H31: Refer to Fig. A-FCAAA Sheet 03 and Fig. A-FCAAA Sheet 04 14 Screw EN6115V3A7 Item 8 9 Screw EN6115V3A6 Item 10 2 Screw ASNA2001V5-8Y Item 13 4 Screw EN6114V5Y8 Item 15 23 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 4 Nut ASNA2529-5 Item 16 NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FCAAA Sheet 02 4 Screw Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 401 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H45 and H46: Refer to Fig. A-FCAAA Sheet 04 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the splice H32 to H44: Refer to Fig. A-FCAAA Sheet 05 1 Screw EN6115V3A7 Item 8 10 Screw EN6115V3A5 Item 17 2 Screw EN6115V3A4 Item 18 13 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (d) Install the Gussets at Frame 41, LH side. Refer to Fig. A-FLAAA DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 402 5

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

# @A300-600 SERVICE BULLETIN In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FLAAA Sheet 02 and Fig. AFLAAA Sheet 03

. 1 Gusset Item (120) Retained at removal 1 Gusset Item (122) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H24 and H25 to the diameter given on Fig. A-FLAAA Sheet 03

. 3 Drill holes H47 and H48 to the diameter given on Fig. A-FLAAA Sheet 03

. 4 Install: 1 Gusset Item (120) Retained at removal 1 Gusset Item (122) Retained at removal 2 Screw EN6114V6X14 Item 26 1 Screw EN6114V4X8 Item 30 1 Screw EN6114V4X10 Item 31 2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-4 Item 21

(5) Subtask 536177-831-005-001 - Depending on Inspection results, if removed, install the Fasteners at FR41, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 403 5

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

# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 32 NUT 90 ASNA2019-56-25 32 RIVET 91 EN6114V3X5 32 SCREW 92 EN6080D6X-32 20 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 41, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 404 5

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# @A300-600 SERVICE BULLETIN
1 Install: 20 Rivet EN6080D6X-32 Item 92 And: 32 Rivet ASNA2019-56-25 Item 90 or 32 Screw EN6114V3X5 Item 91 32 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(6) Subtask 536177-831-006-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR41, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 41, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 20 Rivet Item (19) Discard DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 405 5

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# @A300-600 SERVICE BULLETIN
And: 32 Rivet Item (5) Discard or 32 Bolt Item (3) Discard 32 Nut Item (4) Discard

(7) Subtask 536177-831-007-001 - Depending on Inspection results, remove the Gussets from FR41, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FLAAA Removal/Installation of the Gussets at FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 41, RH side. Refer to Fig. A-FLAAA In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (121) Retain 1 Gusset Item (123) Retain attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 406 5

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

# @A300-600 SERVICE BULLETIN (8) Subtask 536177-831-008-001 - Depending on Inspection results, remove the Frame Foot from FR41, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FCAAA Replacement of the Frame foot FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Remove the Frame foot from Frame 41, RH side. Refer to Fig. A-FCAAA In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (101) Discard 1 Stiffener Item (57) Retain 1 Splice Item (59) Retain 1 Shim Item (61) Retain 4 Screw Item (55) Retain 4 Nut Item (56) Discard 14 Pin Item (1) Discard 14 Collar Item (2) Discard 30 Screw Item (3) Discard 30 Nut Item (4) Discard
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 407 5

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

# @A300-600 SERVICE BULLETIN 2 Rivet Item (5) Discard

(9) Subtask 536177-831-009-001 - Depending on Inspection results, install an identical Frame Foot at FR41, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A19R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 15 SCREW 9 ASNA2529-3 36 NUT 10 EN6115V3A6 9 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 4 SCREW 16 ASNA2529-5 4 NUT 17 EN6115V3A5 10 SCREW 18 EN6115V3A4 2 SCREW 19 ASNA2050DXJ4020 2 RIVET 21 ASNA2529-4 2 NUT 26 EN6114V6X14 2 SCREW 30 EN6114V4X8 1 SCREW 31 EN6114V4X10 1 SCREW 56 NSA5057-6 4 NUT 101 A5711112920195 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 408 5

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# @A300-600 SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FCAAA Replacement of the Frame foot FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FLAAA Removal/Installation of the Gussets at FR41, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FCAAA In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FCAAA

. 1 Frame foot A5711112920195 Item 101 1 Stiffener Item (57) Retained at removal 1 Splice Item (59) Retained at removal 1 Shim Item (61) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FCAAA Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H1 to H23 and H26 to H31 to the diameter given on Fig. A-FCAAA Sheet 03 and Fig. A-FCAAA Sheet 04

.
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 409 5

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# @A300-600 SERVICE BULLETIN
3 Drill the holes of the stiffener H45 and H46 to the diameter given on Fig. AFCAAA Sheet 04

. 4 Drill the holes of the splice H32 to H44 to the diameter given on Fig. A-FCAAA Sheet 05

. (b) Cut-out the Frame foot Item 100 as shown on Fig. A-FCAAA Sheet 03

. Protect the cut-out with: Wash Primer - Structure 04CMA2 As required
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

(c) Install the fasteners. Refer to Fig. A-FCAAA In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H1 to H23 and H26 to H31: Refer to Fig. A-FCAAA Sheet 03 and Fig. A-FCAAA Sheet 04 14 Screw EN6115V3A7 Item 8 9 Screw EN6115V3A6 Item 10 2 Screw ASNA2001V5-8Y Item 13 4 Screw EN6114V5Y8 Item 15 23 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 4 Nut ASNA2529-5 Item 16 NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FCAAA Sheet 02 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 410 5

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

# @A300-600 SERVICE BULLETIN 4 Screw Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H45 and H46: Refer to Fig. A-FCAAA Sheet 04 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the splice H32 to H44: Refer to Fig. A-FCAAA Sheet 05 1 Screw EN6115V3A7 Item 8 10 Screw EN6115V3A5 Item 17 2 Screw EN6115V3A4 Item 18 13 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 411 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (d) Install the Gussets at Frame 41, LH side. Refer to Fig. A-FLAAA In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FLAAA Sheet 02 and Fig. AFLAAA Sheet 03

. 1 Gusset Item (121) Retained at removal 1 Gusset Item (123) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H24 and H25 to the diameter given on Fig. A-FLAAA Sheet 03

. 3 Drill holes H47 and H48 to the diameter given on Fig. A-FLAAA Sheet 03

. 4 Install: 1 Gusset Item (121) Retained at removal 1 Gusset Item (123) Retained at removal 2 Screw EN6114V6X14 Item 26 1 Screw EN6114V4X8 Item 30 1 Screw EN6114V4X10 Item 31 2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-4 Item 21 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 412 5

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

# @A300-600 SERVICE BULLETIN (10) Subtask 536177-831-010-001 - Depending on Inspection results, if removed, install the Fasteners at FR41, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 41 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 32 NUT 90 ASNA2019-56-25 32 RIVET 91 EN6114V3X5 32 SCREW 92 EN6080D6X-32 20 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 413 5

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

# @A300-600 SERVICE BULLETIN (a) If removed, install the fasteners at Frame 41, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 20 Rivet EN6080D6X-32 Item 92 And: 32 Rivet ASNA2019-56-25 Item 90 or 32 Screw EN6114V3X5 Item 91 32 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(11) Subtask 536177-831-011-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR42, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 414 5

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

# @A300-600 SERVICE BULLETIN (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 42, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard 24 Nut Item (4) Discard

(12) Subtask 536177-831-012-001 - Depending on Inspection results, remove the Gussets from FR42, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FNAAA Removal/Installation of the Gussets at FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 42, LH side. Refer to Fig. A-FNAAA In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (124) Retain 1 Gusset Item (126) Retain
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 415 5

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# @A300-600 SERVICE BULLETIN
attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

(13) Subtask 536177-831-013-001 - Depending on Inspection results, remove the Frame Foot from FR42, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FDAAA Replacement of the Frame foot FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Remove the Frame foot from Frame 42, LH side. Refer to Fig. A-FDAAA In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (102) Discard 1 Doubler Item (62) Retain 1 Shim Item (63) Retain 1 Shim Item (64) Retain 1 Shim Item (65) Retain 1 Stiffener Item (58) Retain 1 Stiffener Item (68) Retain 1 Splice Item (66) Retain DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 416 5

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# @A300-600 SERVICE BULLETIN 4 Screw Item (55) Retain 4 Nut Item (56) Discard 28 Pin Item (1) Discard 28 Collar Item (2) Discard 31 Screw Item (3) Discard 31 Nut Item (4) Discard 6 Rivet Item (5) Discard

(14) Subtask 536177-831-014-001 - Depending on Inspection results, install an identical Frame Foot at FR42, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A04R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 1 SCREW 9 ASNA2529-3 53 NUT 10 EN6115V3A6 11 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 8 SCREW 16 ASNA2529-5 8 NUT 17 EN6115V3A5 10 SCREW 18 EN6115V3A4 4 SCREW 19 ASNA2050DXJ4020 4 RIVET 21 ASNA2529-4 2 NUT 30 EN6114V4X8 1 SCREW 31 EN6114V4X10 1 SCREW 32 EN6115V3A8 14 SCREW 33 EN6115V3A9 11 SCREW DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 417 5

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

# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 35 EN6114V6X13 2 SCREW 56 NSA5057-6 4 NUT 102 A5711113020095 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FDAAA Replacement of the Frame foot FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FNAAA Removal/Installation of the Gussets at FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FDAAA In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FDAAA 1 Frame foot A5711113020095 Item 102 1 Doubler Item (62) Retained at removal 1 Shim Item (63) Retained at removal
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 418 5

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

# @A300-600 SERVICE BULLETIN 1 Shim Item (64) Retained at removal 1 Shim Item (65) Retained at removal 1 Splice Item (66) Retained at removal 1 Stiffener Item (58) Retained at removal 1 Stiffener Item (68) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FDAAA Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H51 to H78, H83 to H90 and H93 to H102 to the diameter given on Fig. A-FDAAA Sheet 03 to Fig. A-FDAAA Sheet 05

. 3 Drill the holes of the stiffener at STGR 37 H81, H82, H103 and H104 to the diameter given on Fig. A-FDAAA Sheet 05

. 4 Drill the holes of the splice H105 to H117 to the diameter given on Fig. AFDAAA Sheet 05

. (b) Cut-out the Frame foot Item 102 as shown on Fig. A-FDAAA Sheet 03

. Protect the cut-out with: Wash Primer - Structure 04CMA2 As required
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

(c) Install the fasteners. Refer to Fig. A-FDAAA In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 419 5

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

# @A300-600 SERVICE BULLETIN
11 Screw EN6115V3A6 Item 10 2 Screw ASNA2001V5-8Y Item 13 8 Screw EN6114V5Y8 Item 15 14 Screw EN6115V3A8 Item 32 11 Screw EN6115V3A9 Item 33 36 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 8 Nut ASNA2529-5 Item 16 1 Install the fasteners of the Frame foot H51 to H78, H83 to H90 and H93 to H102: Refer to Fig. A-FDAAA Sheet 03 and Fig. A-FDAAA Sheet 04 NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FDAAA Sheet 02 4 Screw Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H79 and H80: Refer to Fig. A-FDAAA Sheet 04 2 Rivet ASNA2050DXJ4020 Item 19 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 420 5

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

# @A300-600 SERVICE BULLETIN
NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the stiffener at STGR 37 H81, H82, H103 and H104: Refer to Fig. A-FDAAA Sheet 05 2 Screw EN6115V3A4 Item 18 2 Nut ASNA2529-3 Item 9 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Install the fasteners of the splice H105 to H117: Refer to Fig. A-FDAAA Sheet 05 1 Screw EN6115V3A7 Item 8 10 Screw EN6115V3A5 Item 17 2 Screw EN6115V3A4 Item 18 15 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with:
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 421 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

6 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (d) Install the Gussets at Frame 42, LH side. Refer to Fig. A-FNAAA In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FNAAA

. 1 Gusset Item (124) Retained at removal 1 Gusset Item (126) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H91 and H92 to the diameter given on Fig. A-FNAAA Sheet 03

. 3 Drill holes H118 and H119 to the diameter given on Fig. A-FNAAA Sheet 03

. 4 Install: 1 Gusset Item (124) Retained at removal 1 Gusset Item (126) Retained at removal 1 Screw EN6114V4X8 Item 30 1 Screw EN6114V4X10 Item 31 2 Screw EN6114V6X13 Item 35 2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-4 Item 21 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 422 5

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

# @A300-600 SERVICE BULLETIN (15) Subtask 536177-831-015-001 - Depending on Inspection results, if removed, install the Fasteners at FR42, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 90 ASNA2019-56-25 24 RIVET 91 EN6114V3X5 24 SCREW 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 423 5

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

# @A300-600 SERVICE BULLETIN (a) If removed, install the fasteners at Frame 42, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 24 Rivet ASNA2019-56-25 Item 90 or 24 Screw EN6114V3X5 Item 91 24 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(16) Subtask 536177-831-016-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR42, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 424 5

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

# @A300-600 SERVICE BULLETIN (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 42, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard 24 Nut Item (4) Discard

(17) Subtask 536177-831-017-001 - Depending on Inspection results, remove the Gussets from FR42, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FNAAA Removal/Installation of the Gussets at FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 42, RH side. Refer to Fig. A-FNAAA In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (125) Retain 1 Gusset Item (127) Retain
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 425 5

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

# @A300-600 SERVICE BULLETIN
attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

(18) Subtask 536177-831-018-001 - Depending on Inspection results, remove the Frame Foot from FR42, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FDAAA Replacement of the Frame foot FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Remove the Frame foot from Frame 42, RH side. Refer to Fig. A-FDAAA In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (103) Discard 1 Doubler Item (62) Retain 1 Shim Item (63) Retain 1 Shim Item (64) Retain 1 Shim Item (65) Retain 1 Stiffener Item (57) Retain 1 Stiffener Item (69) Retain 1 Splice Item (67) Retain DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 426 5

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# @A300-600 SERVICE BULLETIN 4 Screw Item (55) Retain 4 Nut Item (56) Discard 28 Pin Item (1) Discard 28 Collar Item (2) Discard 31 Screw Item (3) Discard 31 Nut Item (4) Discard 6 Rivet Item (5) Discard

(19) Subtask 536177-831-019-001 - Depending on Inspection results, install an identical Frame Foot at FR42, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A22R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 1 SCREW 9 ASNA2529-3 53 NUT 10 EN6115V3A6 11 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 8 SCREW 16 ASNA2529-5 8 NUT 17 EN6115V3A5 10 SCREW 18 EN6115V3A4 4 SCREW 19 ASNA2050DXJ4020 4 RIVET 21 ASNA2529-4 2 NUT 30 EN6114V4X8 1 SCREW 31 EN6114V4X10 1 SCREW 32 EN6115V3A8 14 SCREW 33 EN6115V3A9 11 SCREW DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 427 5

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

# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 35 EN6114V6X13 2 SCREW 56 NSA5057-6 4 NUT 103 A5711113020195 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FDAAA Replacement of the Frame foot FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FNAAA Removal/Installation of the Gussets at FR42, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FDAAA In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FDAAA 1 Frame foot A5711113020195 Item 103 1 Doubler Item (62) Retained at removal 1 Shim Item (63) Retained at removal
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 428 5

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

# @A300-600 SERVICE BULLETIN 1 Shim Item (64) Retained at removal 1 Shim Item (65) Retained at removal 1 Splice Item (67) Retained at removal 1 Stiffener Item (57) Retained at removal 1 Stiffener Item (69) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FDAAA Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H51 to H78, H83 to H90 and H93 to H102 to the diameter given on Fig. A-FDAAA Sheet 03 to Fig. A-FDAAA Sheet 05

. 3 Drill the holes of the stiffener at STGR 37 H81, H82, H103 and H104 to the diameter given on Fig. A-FDAAA Sheet 05

. 4 Drill the holes of the splice H105 to H117 to the diameter given on Fig. AFDAAA Sheet 05

. (b) Cut-out the Frame foot Item 102 as shown on Fig. A-FDAAA Sheet 03

. Protect the cut-out with: Wash Primer - Structure 04CMA2 As required
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

(c) Install the fasteners. Refer to Fig. A-FDAAA In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 429 5

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

# @A300-600 SERVICE BULLETIN
11 Screw EN6115V3A6 Item 10 2 Screw ASNA2001V5-8Y Item 13 8 Screw EN6114V5Y8 Item 15 14 Screw EN6115V3A8 Item 32 11 Screw EN6115V3A9 Item 33 36 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 8 Nut ASNA2529-5 Item 16 1 Install the fasteners of the Frame foot H51 to H78, H83 to H90 and H93 to H102: Refer to Fig. A-FDAAA Sheet 03 and Fig. A-FDAAA Sheet 04 NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FDAAA Sheet 02 4 Screw Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H79 and H80: Refer to Fig. A-FDAAA Sheet 04 2 Rivet ASNA2050DXJ4020 Item 19 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 430 5

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

# @A300-600 SERVICE BULLETIN
NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the stiffener at STGR 37 H81, H82, H103 and H104: Refer to Fig. A-FDAAA Sheet 05 2 Screw EN6115V3A4 Item 18 2 Nut ASNA2529-3 Item 9 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Install the fasteners of the splice H105 to H117: Refer to Fig. A-FDAAA Sheet 05 1 Screw EN6115V3A7 Item 8 10 Screw EN6115V3A5 Item 17 2 Screw EN6115V3A4 Item 18 15 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with:
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 431 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

6 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (d) Install the Gussets at Frame 42, LH side. Refer to Fig. A-FNAAA In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FNAAA

. 1 Gusset Item (125) Retained at removal 1 Gusset Item (127) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H91 and H92 to the diameter given on Fig. A-FNAAA Sheet 03

. 3 Drill holes H118 and H119 to the diameter given on Fig. A-FNAAA Sheet 03

. 4 Install: 1 Gusset Item (125) Retained at removal 1 Gusset Item (127) Retained at removal 1 Screw EN6114V4X8 Item 30 1 Screw EN6114V4X10 Item 31 2 Screw EN6114V6X13 Item 35 2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-4 Item 21 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 432 5

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

# @A300-600 SERVICE BULLETIN (20) Subtask 536177-831-020-001 - Depending on Inspection results, if removed, install the Fasteners at FR42, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 42 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 90 ASNA2019-56-25 24 RIVET 91 EN6114V3X5 24 SCREW 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 433 5

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

# @A300-600 SERVICE BULLETIN (a) If removed, install the fasteners at Frame 42, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 24 Rivet ASNA2019-56-25 Item 90 or 24 Screw EN6114V3X5 Item 91 24 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(21) Subtask 536177-831-021-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR43, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 434 5

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

# @A300-600 SERVICE BULLETIN (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 43, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard 24 Nut Item (4) Discard

(22) Subtask 536177-831-022-001 - Depending on Inspection results, remove the Gussets from FR43, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FPAAA Removal/Installation of the Gussets at FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 43, LH side. Refer to Fig. A-FPAAA In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (128) Retain 1 Gusset Item (130) Retain
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 435 5

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

# @A300-600 SERVICE BULLETIN
attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

(23) Subtask 536177-831-023-001 - Depending on Inspection results, remove the Frame Foot from FR43, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FEAAA Replacement of the Frame foot FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Remove the Frame foot from Frame 43, LH side. Refer to Fig. A-FEAAA In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (104) Discard 1 Stiffener Item (58) Retain 1 Shim Item (70) Retain 1 Splice Item (72) Retain 4 Bolt Item (55) Retain 4 Nut Item (56) Discard 16 Pin Item (1) Discard 16 Collar Item (2) Discard DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 436 5

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

# @A300-600 SERVICE BULLETIN 31 Bolt Item (3) Discard 31 Nut Item (4) Discard 2 Rivet Item (5) Discard

(24) Subtask 536177-831-024-001 - Depending on Inspection results, install an identical Frame Foot at FR43, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A07R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 7 SCREW 9 ASNA2529-3 39 NUT 10 EN6115V3A6 10 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 4 SCREW 16 ASNA2529-5 5 NUT 17 EN6115V3A5 9 SCREW 19 ASNA2050DXJ4020 2 RIVET 21 ASNA2529-4 1 NUT 26 EN6114V6X14 2 SCREW 30 EN6114V4X8 1 SCREW 32 EN6115V3A8 11 SCREW 33 EN6115V3A9 1 SCREW 36 EN6115V3A3 5 SCREW 41 EN6114V5X10 1 SCREW 56 NSA5057-6 4 NUT 104 A5711113120095 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 437 5

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

# @A300-600 SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FEAAA Replacement of the Frame foot FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FPAAA Removal/Installation of the Gussets at FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FEAAA In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FEAAA

. 1 Frame foot A5711113120095 Item 104 1 Stiffener Item (58) Retained at removal 1 Shim Item (70) Retained at removal 1 Splice Item (72) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FEAAA Sheet 03

. NOTE : Between parts apply:
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 438 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H121 to H136, H140 to H149 and H152 to H157 to the diameter given on Fig. A-FEAAA Sheet 03 and Fig. A-FEAAA Sheet 04

. 3 Drill the holes of the stiffener H168 and H169 to the diameter given on Fig. AFEAAA Sheet 04

. 4 Drill the holes of the splice H137 to H139 and H158 to H167 to the diameter given on Fig. A-FEAAA Sheet 04

. (b) Cut-out the Frame foot Item 104 as shown on Fig. A-FEAAA Sheet 03

. Protect the cut-out with: Wash Primer - Structure 04CMA2 As required
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

(c) Install the fasteners. Refer to Fig. A-FEAAA In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H121 to H136, H140 to H149 and H152 to H157: Refer to Fig. A-FEAAA Sheet 03 and Fig. A-FEAAA Sheet 04 5 Screw EN6115V3A7 Item 8 10 Screw EN6115V3A6 Item 10 2 Screw ASNA2001V5-8Y Item 13 4 Screw EN6114V5Y8 Item 15 5 Screw EN6115V3A5 Item 17 5 Screw EN6115V3A8 Item 32 5 Screw EN6115V3A3 Item 36 26 Nut ASNA2529-3 Item 9 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 439 5

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

# @A300-600 SERVICE BULLETIN
2 Nut NAS1726-5E Item 14 4 Nut ASNA2529-5 Item 16 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FEAAA Sheet 02 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H168 and H169: Refer to Fig. A-FEAAA Sheet 04 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 440 5

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

# @A300-600 SERVICE BULLETIN
4 Install the fasteners of the splice H137 to H139 and H158 to H167: Refer to Fig. A-FEAAA Sheet 05 2 Screw EN6115V3A7 Item 8 4 Screw EN6115V3A5 Item 17 6 Screw EN6115V3A8 Item 32 1 Screw EN6115V3A9 Item 33 13 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (d) Install the Gussets at Frame 43, LH side. Refer to Fig. A-FPAAA In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FPAAA Sheet 02 and Fig. AFPAAA Sheet 03

. 1 Gusset Item (128) Retained at removal 1 Gusset Item (130) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 441 5

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

# @A300-600 SERVICE BULLETIN
2 Drill holes H150 and H151 to the diameter given on Fig. A-FPAAA Sheet 03

. 3 Drill holes H170 and H171 to the diameter given on Fig. A-FPAAA Sheet 03

. 4 Install: 1 Gusset Item (128) Retained at removal 1 Gusset Item (130) Retained at removal 2 Screw EN6114V6X14 Item 26 1 Screw EN6114V4X8 Item 30 1 Screw EN6114V5X10 Item 41 2 Nut ASNA2529-6 Item 12 1 Nut ASNA2529-5 Item 16 1 Nut ASNA2529-4 Item 21

(25) Subtask 536177-831-025-001 - Depending on Inspection results, if removed, install the Fasteners at FR43, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 47 EN6114V3X6 24 SCREW 90 ASNA2019-56-25 24 RIVET 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel.
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 442 5

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

# @A300-600 SERVICE BULLETIN
NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 43, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 24 Rivet ASNA2019-56-25 Item 90 or 24 Screw EN6114V3X6 Item 47 24 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 443 5

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

# @A300-600 SERVICE BULLETIN (26) Subtask 536177-831-026-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR43, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 43, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard 24 Nut Item (4) Discard

(27) Subtask 536177-831-027-001 - Depending on Inspection results, remove the Gussets from FR43, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 444 5

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

# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FPAAA Removal/Installation of the Gussets at FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 43, RH side. Refer to Fig. A-FPAAA In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (129) Retain 1 Gusset Item (131) Retain attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

(28) Subtask 536177-831-028-001 - Depending on Inspection results, remove the Frame Foot from FR43, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FEAAA Replacement of the Frame foot FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 445 5

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

# @A300-600 SERVICE BULLETIN (a) Remove the Frame foot from Frame 43, RH side. Refer to Fig. A-FEAAA In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (105) Discard 1 Stiffener Item (57) Retain 1 Shim Item (70) Retain 1 Splice Item (71) Retain 4 Bolt Item (55) Retain 4 Nut Item (56) Discard 16 Pin Item (1) Discard 16 Collar Item (2) Discard 31 Bolt Item (3) Discard 31 Nut Item (4) Discard 2 Rivet Item (5) Discard

(29) Subtask 536177-831-029-001 - Depending on Inspection results, install an identical Frame Foot at FR43, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A25R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 7 SCREW DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 446 5

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

# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 39 NUT 10 EN6115V3A6 10 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 4 SCREW 16 ASNA2529-5 5 NUT 17 EN6115V3A5 9 SCREW 19 ASNA2050DXJ4020 2 RIVET 21 ASNA2529-4 1 NUT 26 EN6114V6X14 2 SCREW 30 EN6114V4X8 1 SCREW 32 EN6115V3A8 11 SCREW 33 EN6115V3A9 1 SCREW 36 EN6115V3A3 5 SCREW 41 EN6114V5X10 1 SCREW 56 NSA5057-6 4 NUT 105 A5711113120195 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FEAAA Replacement of the Frame foot FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FPAAA Removal/Installation of the Gussets at FR43, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 447 5

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

# @A300-600 SERVICE BULLETIN (a) Install and drill all the parts. Refer to Fig. A-FEAAA In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FEAAA

. 1 Frame foot A5711113120195 Item 105 1 Stiffener Item (57) Retained at removal 1 Shim Item (70) Retained at removal 1 Splice Item (71) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FEAAA Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H121 to H136, H140 to H149 and H152 to H157 to the diameter given on Fig. A-FEAAA Sheet 03 and Fig. A-FEAAA Sheet 04

. 3 Drill the holes of the stiffener H168 and H169 to the diameter given on Fig. AFEAAA Sheet 04

. 4 Drill the holes of the splice H137 to H139 and H158 to H167 to the diameter given on Fig. A-FEAAA Sheet 04

. (b) Cut-out the Frame foot Item 104 as shown on Fig. A-FEAAA Sheet 03

. Protect the cut-out with: Wash Primer - Structure 04CMA2 As required
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

(c) Install the fasteners. Refer to Fig. A-FEAAA DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 448 5

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

# @A300-600 SERVICE BULLETIN In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H121 to H136, H140 to H149 and H152 to H157: Refer to Fig. A-FEAAA Sheet 03 and Fig. A-FEAAA Sheet 04 5 Screw EN6115V3A7 Item 8 10 Screw EN6115V3A6 Item 10 2 Screw ASNA2001V5-8Y Item 13 4 Screw EN6114V5Y8 Item 15 5 Screw EN6115V3A5 Item 17 5 Screw EN6115V3A8 Item 32 5 Screw EN6115V3A3 Item 36 26 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 4 Nut ASNA2529-5 Item 16 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FEAAA Sheet 02 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 449 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H168 and H169: Refer to Fig. A-FEAAA Sheet 04 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the splice H137 to H139 and H158 to H167: Refer to Fig. A-FEAAA Sheet 05 2 Screw EN6115V3A7 Item 8 4 Screw EN6115V3A5 Item 17 6 Screw EN6115V3A8 Item 32 1 Screw EN6115V3A9 Item 33 13 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 450 5

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

# @A300-600 SERVICE BULLETIN
5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (d) Install the Gussets at Frame 43, LH side. Refer to Fig. A-FPAAA In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FPAAA Sheet 02 and Fig. AFPAAA Sheet 03

. 1 Gusset Item (129) Retained at removal 1 Gusset Item (131) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H150 and H151 to the diameter given on Fig. A-FPAAA Sheet 03

. 3 Drill holes H170 and H171 to the diameter given on Fig. A-FPAAA Sheet 03

. 4 Install: 1 Gusset Item (129) Retained at removal 1 Gusset Item (131) Retained at removal 2 Screw EN6114V6X14 Item 26 1 Screw EN6114V4X8 Item 30 1 Screw EN6114V5X10 Item 41 2 Nut ASNA2529-6 Item 12 1 Nut ASNA2529-5 Item 16 1 Nut ASNA2529-4 Item 21
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 451 5

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

# @A300-600 SERVICE BULLETIN (30) Subtask 536177-831-030-001 - Depending on Inspection results, if removed, install the Fasteners at FR43, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 43 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 47 EN6114V3X6 24 SCREW 90 ASNA2019-56-25 24 RIVET 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 452 5

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

# @A300-600 SERVICE BULLETIN (a) If removed, install the fasteners at Frame 43, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 24 Rivet ASNA2019-56-25 Item 90 or 24 Screw EN6114V3X6 Item 47 24 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(31) Subtask 536177-831-031-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR44, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 453 5

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

# @A300-600 SERVICE BULLETIN (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 44, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard 24 Nut Item (4) Discard

(32) Subtask 536177-831-032-001 - Depending on Inspection results, remove the Gussets from FR44, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FQAAA Removal/Installation of the Gussets at FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 44, LH side. Refer to Fig. A-FQAAA In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (132) Retain 1 Gusset Item (134) Retain
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 454 5

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

# @A300-600 SERVICE BULLETIN
attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

(33) Subtask 536177-831-033-001 - Depending on Inspection results, remove the Frame Foot from FR44, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FGAAA Replacement of the Frame foot FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Remove the Frame foot from Frame 44, LH side. Refer to Fig. A-FGAAA In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (106) Discard 1 Stiffener Item (58) Retain 1 Splice Item (74) Retain 1 Shim Item (73) Retain 4 Bolt Item (55) Retain 4 Nut Item (56) Discard 15 Pin Item (1) Discard 15 Collar Item (2) Discard DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 455 5

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

# @A300-600 SERVICE BULLETIN 26 Bolt Item (3) Discard 26 Nut Item (4) Discard 2 Rivet Item (5) Discard

(34) Subtask 536177-831-034-001 - Depending on Inspection results, install an identical Frame Foot at FR44, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A10R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 11 SCREW 9 ASNA2529-3 35 NUT 10 EN6115V3A6 12 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 2 SCREW 16 ASNA2529-5 4 NUT 17 EN6115V3A5 9 SCREW 18 EN6115V3A4 2 SCREW 19 ASNA2050DXJ4020 2 RIVET 26 EN6114V6X14 2 SCREW 28 EN6114V5X8 1 SCREW 36 EN6115V3A3 1 SCREW 41 EN6114V5X10 1 SCREW 56 NSA5057-6 4 NUT 106 A5711113220095 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 456 5

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

# @A300-600 SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FQAAA Removal/Installation of the Gussets at FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Fig. A-FGAAA Replacement of the Frame foot FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Install and drill all the parts. Refer to Fig. A-FGAAA In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FGAAA

. 1 Frame foot A5711113220095 Item 106 1 Stiffener Item (58) Retained at removal 1 Splice Item (74) Retained at removal 1 Shim Item (73) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FGAAA Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 457 5

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

# @A300-600 SERVICE BULLETIN
2 Drill the holes of the Frame foot H180 to H202 and H205 to H208 to the diameter given on Fig. A-FGAAA Sheet 03 and Fig. A-FGAAA Sheet 04

. 3 Drill the holes of the stiffener H221 and H222 to the diameter given on Fig. AFGAAA Sheet 03

. 4 Drill the holes of the splice H209 to H220 to the diameter given on Fig. AFGAAA Sheet 05

. (b) Cut-out the Frame foot Item 106 as shown on Fig. A-FGAAA Sheet 03

. Protect the cut-out with: Wash Primer - Structure 04CMA2 As required
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

(c) Install the fasteners. Refer to Fig. A-FGAAA In accordance with SRM 51-40-00, SRM 51-40-20, and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H180 to H202 and H205 to H208: Refer to Fig. A-FGAAA Sheet 03 and Fig. A-FGAAA Sheet 04 10 Screw EN6115V3A7 Item 8 12 Screw EN6115V3A6 Item 10 2 Screw ASNA2001V5-8Y Item 13 2 Screw EN6114V5Y8 Item 15 1 Screw EN6115V3A3 Item 36 23 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 2 Nut ASNA2529-5 Item 16 NOTE : For holes H205 to H208, adjust the shims as shown on Fig. AFGAAA Sheet 04

. NOTE : Wet install the fasteners except for holes H203 and H204 with: DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 458 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FGAAA Sheet 02 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H221 and H222: Refer to Fig. A-FGAAA Sheet 03 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the splice H209 to H220: Refer to Fig. A-FGAAA Sheet 05 1 Screw EN6115V3A7 Item 8 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 459 5

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

# @A300-600 SERVICE BULLETIN
9 Screw EN6115V3A5 Item 17 2 Screw EN6115V3A4 Item 18 12 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (d) Install the Gussets at Frame 44, LH side. Refer to Fig. A-FQAAA In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FQAAA

. 1 Gusset Item (132) Retained at removal 1 Gusset Item (134) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H203 and H204 to the diameter given on Fig. A-FQAAA Sheet 03

. 3 Drill holes H223 and H224 to the diameter given on Fig. A-FQAAA Sheet 03

. 4 Install: 1 Gusset Item (132) Retained at removal
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 460 5

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

# @A300-600 SERVICE BULLETIN 1 Gusset Item (134) Retained at removal 2 Screw EN6114V6X14 Item 26 1 Screw EN6114V5X8 Item 28 1 Screw EN6114V5X10 Item 41 2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-5 Item 16

(35) Subtask 536177-831-035-001 - Depending on Inspection results, if removed, install the Fasteners at FR44, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 90 ASNA2019-56-25 24 RIVET 91 EN6114V3X5 24 SCREW 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 461 5

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

# @A300-600 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 44, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 24 Rivet ASNA2019-56-25 Item 90 or 24 Screw EN6114V3X5 Item 91 24 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(36) Subtask 536177-831-036-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR44, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 462 5

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

# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 44, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard 24 Nut Item (4) Discard

(37) Subtask 536177-831-037-001 - Depending on Inspection results, remove the Gussets from FR44, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 463 5

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

# @A300-600 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-40-20 Fig. A-FQAAA Removal/Installation of the Gussets at FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 44, RH side. Refer to Fig. A-FQAAA In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (133) Retain 1 Gusset Item (135) Retain attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

(38) Subtask 536177-831-038-001 - Depending on Inspection results, remove the Frame Foot from FR44, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FGAAA Replacement of the Frame foot FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Remove the Frame foot from Frame 44, RH side. Refer to Fig. A-FGAAA In accordance with SRM 51-40-20
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 464 5

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

# @A300-600 SERVICE BULLETIN
1 Remove: 1 Frame foot Item (107) Discard 1 Stiffener Item (57) Retain 1 Splice Item (75) Retain 1 Shim Item (73) Retain 4 Bolt Item (55) Retain 4 Nut Item (56) Discard 15 Pin Item (1) Discard 15 Collar Item (2) Discard 26 Bolt Item (3) Discard 26 Nut Item (4) Discard 2 Rivet Item (5) Discard

(39) Subtask 536177-831-039-001 - Depending on Inspection results, install an identical Frame Foot at FR44, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A28R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 11 SCREW 9 ASNA2529-3 35 NUT 10 EN6115V3A6 12 SCREW 12 ASNA2529-6 2 NUT 13 ASNA2001V5-8Y 2 SCREW 14 NAS1726-5E 2 NUT DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 465 5

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

# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 15 EN6114V5Y8 2 SCREW 16 ASNA2529-5 4 NUT 17 EN6115V3A5 9 SCREW 18 EN6115V3A4 2 SCREW 19 ASNA2050DXJ4020 2 RIVET 26 EN6114V6X14 2 SCREW 28 EN6114V5X8 1 SCREW 36 EN6115V3A3 1 SCREW 41 EN6114V5X10 1 SCREW 56 NSA5057-6 4 NUT 107 A5711113220195 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FGAAA Replacement of the Frame foot FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FQAAA Removal/Installation of the Gussets at FR44, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FGAAA In accordance with SRM 51-40-40

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 466 5

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

# @A300-600 SERVICE BULLETIN
1 Put all the parts in position as shown on Fig. A-FGAAA

. 1 Frame foot A5711113220195 Item 107 1 Stiffener Item (57) Retained at removal 1 Splice Item (75) Retained at removal 1 Shim Item (73) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FGAAA Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H180 to H202 and H205 to H208 to the diameter given on Fig. A-FGAAA Sheet 03 and Fig. A-FGAAA Sheet 04

. 3 Drill the holes of the stiffener H221 and H222 to the diameter given on Fig. AFGAAA Sheet 03

. 4 Drill the holes of the splice H209 to H220 to the diameter given on Fig. AFGAAA Sheet 05

. (b) Cut-out the Frame foot Item 106 as shown on Fig. A-FGAAA Sheet 03

. Protect the cut-out with: Wash Primer - Structure 04CMA2 As required
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

(c) Install the fasteners. Refer to Fig. A-FGAAA In accordance with SRM 51-40-00, SRM 51-40-20, and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H180 to H202 and H205 to H208: Refer to Fig. A-FGAAA Sheet 03 and Fig. A-FGAAA Sheet 04 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 467 5

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

# @A300-600 SERVICE BULLETIN
10 Screw EN6115V3A7 Item 8 12 Screw EN6115V3A6 Item 10 2 Screw ASNA2001V5-8Y Item 13 2 Screw EN6114V5Y8 Item 15 1 Screw EN6115V3A3 Item 36 23 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 2 Nut ASNA2529-5 Item 16 NOTE : For holes H205 to H208, adjust the shims as shown on Fig. AFGAAA Sheet 04

. NOTE : Wet install the fasteners except for holes H203 and H204 with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FGAAA Sheet 02 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 468 5

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

# @A300-600 SERVICE BULLETIN
3 Install the fasteners of the stiffener at STGR 36 H221 and H222: Refer to Fig. A-FGAAA Sheet 03 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the splice H209 to H220: Refer to Fig. A-FGAAA Sheet 05 1 Screw EN6115V3A7 Item 8 9 Screw EN6115V3A5 Item 17 2 Screw EN6115V3A4 Item 18 12 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (d) Install the Gussets at Frame 44, LH side. Refer to Fig. A-FQAAA In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 469 5

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

# @A300-600 SERVICE BULLETIN
1 Put the gussets in position as shown on Fig. A-FQAAA

. 1 Gusset Item (133) Retained at removal 1 Gusset Item (135) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H203 and H204 to the diameter given on Fig. A-FQAAA Sheet 03

. 3 Drill holes H223 and H224 to the diameter given on Fig. A-FQAAA Sheet 03

. 4 Install: 1 Gusset Item (133) Retained at removal 1 Gusset Item (135) Retained at removal 2 Screw EN6114V6X14 Item 26 1 Screw EN6114V5X8 Item 28 1 Screw EN6114V5X10 Item 41 2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-5 Item 16

(40) Subtask 536177-831-040-001 - Depending on Inspection results, if removed, install the Fasteners at FR44, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 44 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 470 5

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

# @A300-600 SERVICE BULLETIN Material necessary to do the job Component COMPA02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 90 ASNA2019-56-25 24 RIVET 91 EN6114V3X5 24 SCREW 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 44, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 24 Rivet ASNA2019-56-25 Item 90 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 471 5

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

# @A300-600 SERVICE BULLETIN

or 24 Screw EN6114V3X5 Item 91 24 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(41) Subtask 536177-831-041-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR45, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 45, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 20 Rivet Item (19) Discard And: 32 Rivet Item (5) Discard or 32 Bolt Item (3) Discard DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 472 5

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

# @A300-600 SERVICE BULLETIN 32 Nut Item (4) Discard

(42) Subtask 536177-831-042-001 - Depending on Inspection results, remove the Gussets from FR45, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FTAAA Removal/Installation of the Gussets at FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 45, LH side. Refer to Fig. A-FTAAA In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (136) Retain 1 Gusset Item (138) Retain attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

(43) Subtask 536177-831-043-001 - Depending on Inspection results, remove the Frame Foot from FR45, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 473 5

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

# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FJAAA Replacement of the Frame foot FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Remove the Frame foot from Frame 45, LH side. Refer to Fig. A-FJAAA In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (108) Discard 2 Stiffener Item (58) Retain 1 Splice Item (72) Retain 1 Doubler Item (77) Retain 1 Shim Item (78) Retain 23 Pin Item (1) Discard 23 Collar Item (2) Discard 4 Rivet Item (19) Discard 22 Screw Item (3) Discard 22 Nut Item (4) Discard And: 4 Screw Item (55) Retain 4 Nut Item (56) Discard or DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 474 5

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

# @A300-600 SERVICE BULLETIN 4 Nut Item (76) Discard And: 7 Rivet Item (5) Discard or 7 Screw Item (93) Discard 7 Nut Item (94) Discard And if installed, remove: 1 Bracket Item (79) Retain

(44) Subtask 536177-831-044-001 - Depending on Inspection results, install an identical Frame Foot at FR45, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 145 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A13R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 4 SCREW 9 ASNA2529-3 48 NUT 10 EN6115V3A6 7 SCREW 12 ASNA2529-6 2 NUT 16 ASNA2529-5 2 NUT 17 EN6115V3A5 3 SCREW 19 ASNA2050DXJ4020 4 RIVET 26 EN6114V6X14 2 SCREW 28 EN6114V5X8 1 SCREW 32 EN6115V3A8 7 SCREW 33 EN6115V3A9 17 SCREW 41 EN6114V5X10 1 SCREW 42 EN6114V3A6 1 SCREW 43 EN6115V3A10 2 SCREW 44 EN6115V3A11 7 SCREW 45 ASNA2001V6-8Y 2 SCREW DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 475 5

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

# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 46 NAS1726-6E 2 NUT 56 NSA5057-6 4 NUT 76 NSA5057-7 4 NUT 108 A5711113320095 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FJAAA Replacement of the Frame foot FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Fig. A-FTAAA Removal/Installation of the Gussets at FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FJAAA In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FJAAA

. 1 Frame foot A5711113320095 Item 108 2 Stiffener Item (58) Retained at removal

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 476 5

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

# @A300-600 SERVICE BULLETIN 1 Splice Item (72) Retained at removal 1 Doubler Item (77) Retained at removal 1 Shim Item (78) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FJAAA Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H231 to H254, H257 to H266 and H271 to H272 to the diameter given on Fig. A-FJAAA Sheet 03 to Fig. A-FJAAA Sheet 05

. 3 Drill the holes of the stiffener at STGR 36 H255 and H256 to the diameter given on Fig. A-FJAAA Sheet 03

. 4 Drill the holes of the stiffener at STGR 37 H267 and H268 to the diameter given on Fig. A-FJAAA Sheet 05

. 5 Drill the holes of the splice H273 to H285 to the diameter given on Fig. AFJAAA Sheet 06

. (b) Cut-out the Frame foot Item 108 as shown on Fig. A-FJAAA Sheet 03

. Protect the cut-out with: Wash Primer - Structure 04CMA2 As required
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

(c) Install the fasteners. Refer to Fig. A-FJAAA In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 477 5

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

# @A300-600 SERVICE BULLETIN
1 Install the fasteners of the Frame foot H231 to H254, H257 to H266 and H271 to H272: Refer to Fig. A-FJAAA Sheet 03 to Fig. A-FJAAA Sheet 05 2 Screw EN6115V3A7 Item 8 5 Screw EN6115V3A6 Item 10 1 Screw EN6115V3A5 Item 17 1 Screw EN6115V3A8 Item 32 16 Screw EN6115V3A9 Item 33 1 Screw EN6114V3A6 Item 42 2 Screw EN6115V3A10 Item 43 7 Screw EN6115V3A11 Item 44 2 Screw ASNA2001V6-8Y Item 45 35 Nut ASNA2529-3 Item 9 2 Nut NAS1726-6E Item 46 NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FJAAA Sheet 02 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 or 4 Nut NSA5057-7 Item 76 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 478 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H255 and H256: Refer to Fig. A-FJAAA Sheet 03 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the stiffener at STGR 37 H267 and H268: Refer to Fig. A-FJAAA Sheet 06 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Install the fasteners of the splice H273 to H285: Refer to Fig. A-FJAAA Sheet 06 2 Screw EN6115V3A7 Item 8 2 Screw EN6115V3A5 Item 17 6 Screw EN6115V3A8 Item 32 1 Screw EN6115V3A9 Item 33 13 Nut ASNA2529-3 Item 9
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 479 5

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

# @A300-600 SERVICE BULLETIN
2 Screw EN6115V3A6 Item 10 And if removed, install: 1 Bracket Item (79) Retained at removal NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

6 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (d) Install the Gussets at Frame 45, LH side. Refer to Fig. A-FTAAA In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FTAAA

. 1 Gusset Item (136) Retained at removal 1 Gusset Item (138) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H269 and H270 to the diameter given on Fig. A-FTAAA Sheet 03

. 3 Drill holes H286 and H287 to the diameter given on Fig. A-FTAAA Sheet 03

.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 480 5

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

# @A300-600 SERVICE BULLETIN
4 Install: 1 Gusset Item (136) Retained at removal 1 Gusset Item (138) Retained at removal 2 Screw EN6114V6X14 Item 26 1 Screw EN6114V5X8 Item 28 1 Screw EN6114V5X10 Item 41 2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-5 Item 16

(45) Subtask 536177-831-045-001 - Depending on Inspection results, if removed, install the Fasteners at FR45, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 32 NUT 47 EN6114V3X6 32 SCREW 90 ASNA2019-56-25 32 RIVET 92 EN6080D6X-32 20 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 481 5

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

# @A300-600 SERVICE BULLETIN
Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 45, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 20 Rivet EN6080D6X-32 Item 92 And: 32 Rivet ASNA2019-56-25 Item 90 or 32 Screw EN6114V3X6 Item 47 32 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 482 5

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

# @A300-600 SERVICE BULLETIN (46) Subtask 536177-831-046-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR45, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 45, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 20 Rivet Item (19) Discard And: 32 Rivet Item (5) Discard or 32 Bolt Item (3) Discard 32 Nut Item (4) Discard

(47) Subtask 536177-831-047-001 - Depending on Inspection results, remove the Gussets from FR45, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 483 5

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

# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FTAAA Removal/Installation of the Gussets at FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 45, RH side. Refer to Fig. A-FTAAA In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (137) Retain 1 Gusset Item (139) Retain attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

(48) Subtask 536177-831-048-001 - Depending on Inspection results, remove the Frame Foot from FR45, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 484 5

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

# @A300-600 SERVICE BULLETIN
References Fig. A-FJAAA Replacement of the Frame foot FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Remove the Frame foot from Frame 45, RH side. Refer to Fig. A-FJAAA In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (109) Discard 2 Stiffener Item (57) Retain 1 Splice Item (71) Retain 1 Doubler Item (77) Retain 1 Shim Item (78) Retain 23 Pin Item (1) Discard 23 Collar Item (2) Discard 4 Rivet Item (19) Discard 22 Screw Item (3) Discard 22 Nut Item (4) Discard And: 4 Screw Item (55) Retain 4 Nut Item (56) Discard or 4 Nut Item (76) Discard And: 7 Rivet Item (5) Discard or DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 485 5

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

# @A300-600 SERVICE BULLETIN 7 Screw Item (93) Discard 7 Nut Item (94) Discard

(49) Subtask 536177-831-049-001 - Depending on Inspection results, install an identical Frame Foot at FR45, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A31R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 4 SCREW 9 ASNA2529-3 48 NUT 10 EN6115V3A6 5 SCREW 12 ASNA2529-6 2 NUT 16 ASNA2529-5 2 NUT 17 EN6115V3A5 5 SCREW 19 ASNA2050DXJ4020 4 RIVET 26 EN6114V6X14 2 SCREW 28 EN6114V5X8 1 SCREW 32 EN6115V3A8 7 SCREW 33 EN6115V3A9 17 SCREW 41 EN6114V5X10 1 SCREW 42 EN6114V3A6 1 SCREW 43 EN6115V3A10 2 SCREW 44 EN6115V3A11 7 SCREW 45 ASNA2001V6-8Y 2 SCREW 46 NAS1726-6E 2 NUT 56 NSA5057-6 4 NUT 76 NSA5057-7 4 NUT 109 A5711113320195 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 486 5

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

# @A300-600 SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FJAAA Replacement of the Frame foot FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Fig. A-FTAAA Removal/Installation of the Gussets at FR45, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FJAAA In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FJAAA

. 1 Frame foot A5711113320195 Item 109 2 Stiffener Item (57) Retained at removal 1 Splice Item (71) Retained at removal 1 Doubler Item (77) Retained at removal 1 Shim Item (78) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 487 5

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

# @A300-600 SERVICE BULLETIN
A-FJAAA Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H231 to H254, H257 to H266 and H271 to H272 to the diameter given on Fig. A-FJAAA Sheet 03 to Fig. A-FJAAA Sheet 05

. 3 Drill the holes of the stiffener at STGR 36 H255 and H256 to the diameter given on Fig. A-FJAAA Sheet 03

. 4 Drill the holes of the stiffener at STGR 37 H267 and H268 to the diameter given on Fig. A-FJAAA Sheet 05

. 5 Drill the holes of the splice H273 to H285 to the diameter given on Fig. AFJAAA Sheet 06

. (b) Cut-out the Frame foot Item 108 as shown on Fig. A-FJAAA Sheet 03

. Protect the cut-out with: Wash Primer - Structure 04CMA2 As required
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

(c) Install the fasteners. Refer to Fig. A-FJAAA In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H231 to H254, H257 to H266 and H271 to H272: Refer to Fig. A-FJAAA Sheet 03 to Fig. A-FJAAA Sheet 05 2 Screw EN6115V3A7 Item 8 5 Screw EN6115V3A6 Item 10 1 Screw EN6115V3A5 Item 17 1 Screw EN6115V3A8 Item 32
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 488 5

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

# @A300-600 SERVICE BULLETIN
16 Screw EN6115V3A9 Item 33 1 Screw EN6114V3A6 Item 42 2 Screw EN6115V3A10 Item 43 7 Screw EN6115V3A11 Item 44 2 Screw ASNA2001V6-8Y Item 45 35 Nut ASNA2529-3 Item 9 2 Nut NAS1726-6E Item 46 NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FJAAA Sheet 02 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 or 4 Nut NSA5057-7 Item 76 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H255 and H256: Refer to Fig. A-FJAAA Sheet 03 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 489 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the stiffener at STGR 37 H267 and H268: Refer to Fig. A-FJAAA Sheet 06 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Install the fasteners of the splice H273 to H285: Refer to Fig. A-FJAAA Sheet 06 2 Screw EN6115V3A7 Item 8 4 Screw EN6115V3A5 Item 17 6 Screw EN6115V3A8 Item 32 1 Screw EN6115V3A9 Item 33 13 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 490 5

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

# @A300-600 SERVICE BULLETIN
6 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (d) Install the Gussets at Frame 45, LH side. Refer to Fig. A-FTAAA In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FTAAA

. 1 Gusset Item (137) Retained at removal 1 Gusset Item (139) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H269 and H270 to the diameter given on Fig. A-FTAAA Sheet 03

. 3 Drill holes H286 and H287 to the diameter given on Fig. A-FTAAA Sheet 03

. 4 Install: 1 Gusset Item (137) Retained at removal 1 Gusset Item (139) Retained at removal 2 Screw EN6114V6X14 Item 26 1 Screw EN6114V5X8 Item 28 1 Screw EN6114V5X10 Item 41 2 Nut ASNA2529-6 Item 12 2 Nut ASNA2529-5 Item 16

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 491 5

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

# @A300-600 SERVICE BULLETIN (50) Subtask 536177-831-050-001 - Depending on Inspection results, install the Fasteners at FR45, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 45 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 32 NUT 47 EN6114V3X6 32 SCREW 90 ASNA2019-56-25 32 RIVET 92 EN6080D6X-32 20 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 492 5

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

# @A300-600 SERVICE BULLETIN (a) If removed, install the fasteners at Frame 45, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 20 Rivet EN6080D6X-32 Item 92 And: 32 Rivet ASNA2019-56-25 Item 90 or 32 Screw EN6114V3X6 Item 47 32 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(51) Subtask 536177-831-051-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR46, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 493 5

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

# @A300-600 SERVICE BULLETIN (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 46, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard 24 Nut Item (4) Discard

(52) Subtask 536177-831-052-001 - Depending on Inspection results, remove the Gussets from FR46, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FUAAA Removal/Installation of the Gussets at FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 46, LH side. Refer to Fig. A-FUAAA In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (140) Retain 1 Gusset Item (142) Retain
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 494 5

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

# @A300-600 SERVICE BULLETIN
attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

(53) Subtask 536177-831-053-001 - Depending on Inspection results, remove the Frame Foot from FR46, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FKAAA Replacement of the Frame foot FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Remove the Frame foot from Frame 46, LH side. Refer to Fig. A-FKAAA In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (110) Discard 1 Stiffener Item (58) Retain 1 Doubler Item (80) Retain 1 Shim Item (81) Retain 1 Splice Item (82) Retain 20 Pin Item (1) Discard 20 Collar Item (2) Discard 2 Rivet Item (19) Discard DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 495 5

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

# @A300-600 SERVICE BULLETIN 28 Screw Item (3) Discard 28 Nut Item (4) Discard And: 4 Screw Item (55) Retain 4 Nut Item (56) Discard or 4 Nut Item (76) Discard And: 5 Rivet Item (5) Discard or 5 Screw Item (93) Discard 5 Nut Item (94) Discard

(54) Subtask 536177-831-054-001 - Depending on Inspection results, install an identical Frame Foot at FR46, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 16.00 Minimum number of person 1 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536177A16R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 3 SCREW 9 ASNA2529-3 43 NUT 10 EN6115V3A6 11 SCREW 12 ASNA2529-6 3 NUT 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 6 SCREW 16 ASNA2529-5 7 NUT 17 EN6115V3A5 7 SCREW DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 496 5

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

# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 18 EN6115V3A4 2 SCREW 19 ASNA2050DXJ4020 2 RIVET 26 EN6114V6X14 1 SCREW 33 EN6115V3A9 9 SCREW 43 EN6115V3A10 5 SCREW 44 EN6115V3A11 6 SCREW 50 ASNA2001V5-12Y 2 SCREW 52 EN6114V6X17 2 SCREW 54 EN6114V5X12 1 SCREW 56 NSA5057-6 4 NUT 76 NSA5057-7 4 NUT 110 A5711113420095 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40 Fig. A-FKAAA Replacement of the Frame foot FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FUAAA Removal/Installation of the Gussets at FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FKAAA In accordance with SRM 51-40-40
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 497 5

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

# @A300-600 SERVICE BULLETIN
1 Put all the parts in position as shown on Fig. A-FKAAA

. 1 Frame foot A5711113420095 Item 110 1 Stiffener Item (58) Retained at removal 1 Doubler Item (80) Retained at removal 1 Shim Item (81) Retained at removal 1 Splice Item (82) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FKAAA Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H300 to H313, H316 to H331 and H334 to H341 to the diameter given on Fig. A-FKAAA Sheet 03 and Fig. A-FKAAA Sheet 04

. 3 Drill the holes of the stiffener H314 and H315 to the diameter given on Fig. AFKAAA Sheet 04

. 4 Drill the holes of the splice H342 to H354 to the diameter given on Fig. AFKAAA Sheet 05

. (b) Cut-out the Frame foot Item 110 as shown on Fig. A-FKAAA Sheet 03

. Protect the cut-out with: Wash Primer - Structure 04CMA2 As required
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

(c) Install the fasteners. Refer to Fig. A-FKAAA In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 498 5

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

# @A300-600 SERVICE BULLETIN Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H300 to H313, H316 to H331 and H334 to H341 to H313 and H316 to H341: Refer to Fig. A-FKAAA Sheet 03 and Fig. A-FKAAA Sheet 04 2 Screw EN6115V3A7 Item 8 8 Screw EN6115V3A6 Item 10 6 Screw EN6114V5Y8 Item 15 9 Screw EN6115V3A9 Item 33 5 Screw EN6115V3A10 Item 43 6 Screw EN6115V3A11 Item 44 2 Screw ASNA2001V5-12Y Item 50 30 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 6 Nut ASNA2529-5 Item 16 NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FKAAA Sheet 02 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 or 4 Nut NSA5057-7 Item 76 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 499 5

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

# @A300-600 SERVICE BULLETIN Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 37 H314 and H315: Refer to Fig. A-FKAAA Sheet 04 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the splice H342 to H354: Refer to Fig. A-FKAAA Sheet 05 1 Screw EN6115V3A7 Item 8 3 Screw EN6115V3A6 Item 10 7 Screw EN6115V3A5 Item 17 2 Screw EN6115V3A4 Item 18 13 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 500 5

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

# @A300-600 SERVICE BULLETIN (d) Install the Gussets at Frame 46, LH side. Refer to Fig. A-FUAAA In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FUAAA

. 1 Gusset Item (140) Retained at removal 1 Gusset Item (142) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H332 and H333 to the diameter given on Fig. A-FUAAA Sheet 03

. 3 Drill holes H355 and H356 to the diameter given on Fig. A-FUAAA Sheet 03

. 4 Install: 1 Gusset Item (140) Retained at removal 1 Gusset Item (142) Retained at removal 1 Screw EN6114V6X14 Item 26 2 Screw EN6114V6X17 Item 52 1 Screw EN6114V5X12 Item 54 3 Nut ASNA2529-6 Item 12 1 Nut ASNA2529-5 Item 16

(55) Subtask 536177-831-055-001 - Depending on Inspection results, if removed, install the Fasteners at FR46, LH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 501 5

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

# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA05 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 47 EN6114V3X6 16 SCREW 90 ASNA2019-56-25 24 RIVET 91 EN6114V3X5 8 SCREW 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 46, LH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 502 5

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

# @A300-600 SERVICE BULLETIN Refer to AMM 20-21-12, Page Block 001 1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 16 Rivet ASNA2019-56-25 Item 90 or 16 Screw EN6114V3X6 Item 47 16 Nut ASNA2529-3 Item 9 And: 8 Rivet ASNA2019-56-25 Item 90 or 8 Screw EN6114V3X5 Item 91 8 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
(56) Subtask 536177-831-056-001 - Depending on Inspection results, if necessary, remove the Fasteners from FR46, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 503 5

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

# @A300-600 SERVICE BULLETIN
References Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If necessary, to ease the replacement of the Frame foot, remove fasteners from Frame 46, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20 1 Remove: 16 Rivet Item (19) Discard And: 24 Rivet Item (5) Discard or 24 Bolt Item (3) Discard 24 Nut Item (4) Discard

(57) Subtask 536177-831-057-001 - Depending on Inspection results, remove the Gussets from FR46, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FUAAA Removal/Installation of the Gussets at FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Remove the Gussets from Frame 46, RH side. Refer to Fig. A-FUAAA DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 504 5

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

# @A300-600 SERVICE BULLETIN
In accordance with SRM 51-40-20 1 Remove: 1 Gusset Item (141) Retain 1 Gusset Item (143) Retain attached with: 4 Screw Item (3) Discard 4 Nut Item (4) Discard

(58) Subtask 536177-831-058-001 - Depending on Inspection results, remove the Frame Foot from FR46, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-40-20 Fig. A-FKAAA Replacement of the Frame foot FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Remove the Frame foot from Frame 46, RH side. Refer to Fig. A-FKAAA In accordance with SRM 51-40-20 1 Remove: 1 Frame foot Item (111) Discard 1 Stiffener Item (57) Retain 1 Doubler Item (80) Retain 1 Shim Item (81) Retain
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 505 5

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

# @A300-600 SERVICE BULLETIN 1 Splice Item (83) Retain 20 Pin Item (1) Discard 20 Collar Item (2) Discard 2 Rivet Item (19) Discard 28 Screw Item (3) Discard 28 Nut Item (4) Discard And: 4 Screw Item (55) Retain 4 Nut Item (56) Discard or 4 Nut Item (76) Discard And: 5 Rivet Item (5) Discard or 5 Screw Item (93) Discard 5 Nut Item (94) Discard

(59) Subtask 536177-831-059-001 - Depending on Inspection results, install an identical Frame Foot at FR46, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 506 5

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

# @A300-600 SERVICE BULLETIN Material necessary to do the job Kit 536177A34R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115V3A7 3 SCREW 9 ASNA2529-3 43 NUT 10 EN6115V3A6 8 SCREW 12 ASNA2529-6 3 NUT 14 NAS1726-5E 2 NUT 15 EN6114V5Y8 6 SCREW 16 ASNA2529-5 7 NUT 17 EN6115V3A5 7 SCREW 18 EN6115V3A4 2 SCREW 19 ASNA2050DXJ4020 2 RIVET 26 EN6114V6X14 1 SCREW 33 EN6115V3A9 9 SCREW 43 EN6115V3A10 5 SCREW 44 EN6115V3A11 6 SCREW 50 ASNA2001V5-12Y 2 SCREW 52 EN6114V6X17 2 SCREW 54 EN6114V5X12 1 SCREW 56 NSA5057-6 4 NUT 76 NSA5057-7 4 NUT 111 A5711113420195 1 FOOT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polysulfide Sealant - General Purpose Brushable 06AAA1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 51-40-40

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 507 5

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

# @A300-600 SERVICE BULLETIN
References Fig. A-FKAAA Replacement of the Frame foot FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FUAAA Removal/Installation of the Gussets at FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 (a) Install and drill all the parts. Refer to Fig. A-FKAAA In accordance with SRM 51-40-40 1 Put all the parts in position as shown on Fig. A-FKAAA

. 1 Frame foot A5711113420195 Item 111 1 Stiffener Item (57) Retained at removal 1 Doubler Item (80) Retained at removal 1 Shim Item (81) Retained at removal 1 Splice Item (83) Retained at removal NOTE : If necessary, rework the upper and side surfaces of the Frame foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig. A-FKAAA Sheet 03

. NOTE : Between parts apply: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required

2 Drill the holes of the Frame foot H300 to H313, H316 to H331 and H334 to H341 to the diameter given on Fig. A-FKAAA Sheet 03 and Fig. A-FKAAA Sheet 04

. 3 Drill the holes of the stiffener H314 and H315 to the diameter given on Fig. AFKAAA Sheet 04

. 4 Drill the holes of the splice H342 to H354 to the diameter given on Fig. AFKAAA Sheet 05

.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 508 5

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

# @A300-600 SERVICE BULLETIN (b) Cut-out the Frame foot Item 110 as shown on Fig. A-FKAAA Sheet 03

. Protect the cut-out with: Wash Primer - Structure 04CMA2 As required
Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required

(c) Install the fasteners. Refer to Fig. A-FKAAA In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install the fasteners of the Frame foot H300 to H313, H316 to H331 and H334 to H341 to H313 and H316 to H341: Refer to Fig. A-FKAAA Sheet 03 and Fig. A-FKAAA Sheet 04 2 Screw EN6115V3A7 Item 8 5 Screw EN6115V3A6 Item 10 6 Screw EN6114V5Y8 Item 15 9 Screw EN6115V3A9 Item 33 5 Screw EN6115V3A10 Item 43 6 Screw EN6115V3A11 Item 44 2 Screw ASNA2001V5-12Y Item 50 30 Nut ASNA2529-3 Item 9 2 Nut NAS1726-5E Item 14 6 Nut ASNA2529-5 Item 16 NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 509 5

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

# @A300-600 SERVICE BULLETIN
2 Install the four upper fasteners of the Frame foot: Refer to Fig. A-FKAAA Sheet 02 4 Bolt Item (55) Retained at removal 4 Nut NSA5057-6 Item 56 or 4 Nut NSA5057-7 Item 76 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

3 Install the fasteners of the stiffener at STGR 37 H314 and H315: Refer to Fig. A-FKAAA Sheet 04 2 Rivet ASNA2050DXJ4020 Item 19 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

4 Install the fasteners of the splice H342 to H354: Refer to Fig. A-FKAAA Sheet 05 1 Screw EN6115V3A7 Item 8 3 Screw EN6115V3A6 Item 10 7 Screw EN6115V3A5 Item 17 2 Screw EN6115V3A4 Item 18 DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 510 5

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

# @A300-600 SERVICE BULLETIN
13 Nut ASNA2529-3 Item 9 NOTE : Wet install the fasteners with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

NOTE : Protect the fasteners head and nuts with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

5 Do a sealant bead around the parts with: Polysulfide Sealant - Fuel Tank Fillet 06ABB1 As required (d) Install the Gussets at Frame 46, LH side. Refer to Fig. A-FUAAA In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM 51-40-40 Refer to AMM 20-21-12, Page Block 001 1 Put the gussets in position as shown on Fig. A-FUAAA

. 1 Gusset Item (141) Retained at removal 1 Gusset Item (143) Retained at removal NOTE : Between the Frame foot and the aft gusset, the distance must be 2 times the thickness of the gusset. NOTE : Between the Frame foot and the FWD gusset, the distance must be 1.3 times the thickness of the gusset. 2 Drill holes H332 and H333 to the diameter given on Fig. A-FUAAA Sheet 03

. 3 Drill holes H355 and H356 to the diameter given on Fig. A-FUAAA Sheet 03

. 4 Install: 1 Gusset Item (141) Retained at removal 1 Gusset Item (143) Retained at removal
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 511 5

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

# @A300-600 SERVICE BULLETIN
1 Screw EN6114V6X14 Item 26 2 Screw EN6114V6X17 Item 52 1 Screw EN6114V5X12 Item 54 3 Nut ASNA2529-6 Item 12 1 Nut ASNA2529-5 Item 16

(60) Subtask 536177-831-060-001 - Depending on Inspection results, install the Fasteners at FR46, RH side Work Zones and Access Panels Zone Access/Work location 140 Work location Frame 46 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Component COMPA05 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2529-3 24 NUT 47 EN6114V3X6 16 SCREW 90 ASNA2019-56-25 24 RIVET 91 EN6114V3X5 8 SCREW 92 EN6080D6X-32 16 RIVET NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE : The components listed above are only necessary if crack is found on a Frame foot. The quantity of these items are to be ordered as required. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required
References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 512 5

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

# @A300-600 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20 51-40-30 Fig. A-FVAAA Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) If removed, install the fasteners at Frame 46, RH side. Refer to Fig. A-FVAAA In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM 51-40-30 Refer to AMM 20-21-12, Page Block 001 1 Install: 16 Rivet EN6080D6X-32 Item 92 And: 16 Rivet ASNA2019-56-25 Item 90 or 16 Screw EN6114V3X6 Item 47 16 Nut ASNA2529-3 Item 9 And: 8 Rivet ASNA2019-56-25 Item 90 or 8 Screw EN6114V3X5 Item 91 8 Nut ASNA2529-3 Item 9 NOTE : Protect the fasteners with: Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required

**CONF 004 None DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 513 5

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# @A300-600 SERVICE BULLETIN
**CONF ALL D. TEST **CONF 001 (1) Subtask 536177-700-003-001 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 28-11-29, Page Block 401 This Service Bulletin requires the accomplishment of the following Tests which are given in subtasks included in the topic Close-up. The manhours for the tests are included in the referenced Service Bulletin subtasks. - Remove the safety clip(s) and/or tag(s) and close/unlock the circuit breaker(s) as specified after the installation of the center tank manhole cover (147AZ and 148AZ), refer to AMM 28-11-29, Page Block 401. - Do the test procedure as specified after the installation of the center tank manhole cover (147AZ and 148AZ), refer to AMM 28-11-29, Page Block 401. **CONF 002 (1) Subtask 536177-700-003-001 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 28-11-29, Page Block 401 This Service Bulletin requires the accomplishment of the following Tests which are given in subtasks included in the topic Close-up. The manhours for the tests are included in the referenced Service Bulletin subtasks. - Remove the safety clip(s) and/or tag(s) and close/unlock the circuit breaker(s) as specified after the installation of the center tank manhole cover (147AZ and 148AZ), refer to AMM 28-11-29, Page Block 401. - Do the test procedure as specified after the installation of the center tank manhole cover (147AZ and 148AZ), refer to AMM 28-11-29, Page Block 401. **CONF 003 (1) Subtask 536177-700-003-001 - Testing Manpower Resources Skills NON SPECIFIC DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 514 5

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

# @A300-600 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) 28-11-29, Page Block 401 This Service Bulletin requires the accomplishment of the following Tests which are given in subtasks included in the topic Close-up. The manhours for the tests are included in the referenced Service Bulletin subtasks. - Remove the safety clip(s) and/or tag(s) and close/unlock the circuit breaker(s) as specified after the installation of the center tank manhole cover (147AZ and 148AZ), refer to AMM 28-11-29, Page Block 401. - Do the test procedure as specified after the installation of the center tank manhole cover (147AZ and 148AZ), refer to AMM 28-11-29, Page Block 401. **CONF 004 None **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 536177-942-003-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501 28-11-29, Page Block 401 28-13-21, Page Block 401 WARNING : MAKE CERTAIN THAT FIRE FIGHTING EQUIPMENT IS AVAILABLE AND ADEQUATE. OBEY THE FUEL SERVICING SAFETY INSTRUCTIONS. (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Close the access door 147BZ. (c) Close the access doors 147AZ and 148AZ, refer to AMM 28-11-29, Page Block 401. (d) Remove the access platform(s). (e) Install the vapor seals, refer to AMM 28-13-21, Page Block 401. (f) Refuel the center tank, refer to AMM 28-11-00, Page Block 501. DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 515 5

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

# @A300-600 SERVICE BULLETIN (g) Put the aircraft back to its initial configuration. **CONF 002 (1) Subtask 536177-942-003-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501 28-11-29, Page Block 401 28-13-21, Page Block 401 WARNING : MAKE CERTAIN THAT FIRE FIGHTING EQUIPMENT IS AVAILABLE AND ADEQUATE. OBEY THE FUEL SERVICING SAFETY INSTRUCTIONS. (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Close the access door 147BZ. (c) Close the access doors 147AZ and 148AZ, refer to AMM 28-11-29, Page Block 401. (d) Remove the access platform(s). (e) Install the vapor seals, refer to AMM 28-13-21, Page Block 401. (f) Refuel the center tank, refer to AMM 28-11-00, Page Block 501. (g) Put the aircraft back to its initial configuration. **CONF 003 (1) Subtask 536177-942-003-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501 28-11-29, Page Block 401 28-13-21, Page Block 401 WARNING : MAKE CERTAIN THAT FIRE FIGHTING EQUIPMENT IS AVAILABLE AND ADEQUATE. OBEY THE FUEL SERVICING SAFETY INSTRUCTIONS.
DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 516 5

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

# @A300-600 SERVICE BULLETIN (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Close the access door 147BZ. (c) Close the access doors 147AZ and 148AZ, refer to AMM 28-11-29, Page Block 401. (d) Remove the access platform(s). (e) Install the vapor seals, refer to AMM 28-13-21, Page Block 401. (f) Refuel the center tank, refer to AMM 28-11-00, Page Block 501. (g) Put the aircraft back to its initial configuration. **CONF 004 None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 517 5

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

# @A300-600 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 518 5

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

# @A300-600 SERVICE BULLETIN Task 536177-839-801-001 - Contact and Report to AIRBUS **CONF ALL Task Associated Data **CONF 001 None **CONF 002 None **CONF 003 None **CONF 004 Manpower TOTAL MANHOURS 0.50 ELAPSED TIME (HOURS) 0.50 **CONF ALL A. GENERAL **CONF 001 None **CONF 002 None **CONF 003 None **CONF 004 None **CONF ALL B. PREPARATION **CONF 001 None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 519 5

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# @A300-600 SERVICE BULLETIN
**CONF 002 None **CONF 003 None **CONF 004 None **CONF ALL C. PROCEDURE **CONF 001 None **CONF 002 None **CONF 003 None **CONF 004 (1) Subtask 536177-839-003-001 - Contact and Report to AIRBUS Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC NOTE : No physical work is required on aircraft. (a) At threshold given in the PLANNING INFORMATION Paragraph E.(2): 1 Verify that the Frame is covered by RDAS. 2 Contact and report to AIRBUS within 6 months from Service Bulletin issuance date.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 520 5

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# @A300-600 SERVICE BULLETIN
**CONF ALL D. TEST **CONF 001 None **CONF 002 None **CONF 003 None **CONF 004 None **CONF ALL E. CLOSE-UP **CONF 001 None **CONF 002 None **CONF 003 None **CONF 004 None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 521 5

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

# @A300-600 SERVICE BULLETIN

**CONF ALL



### B C F G D E K L H J M N A Z140

FR41 FR42 FR43 FR44 FR45 FR46



## A B C D E F G H J K L M N

D_SB_536177_5_BAAA_01_02 Figure A-FBAAA - Sheet 01 Inspection areas DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 522 5

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

# @A300-600 SERVICE BULLETIN

**CONF ALL

STGR35

LH SHOWN RH SYMMETRICAL VIEW LOOKING AFTERWARD FR41



## B

STGR35

LH SHOWN RH SYMMETRICAL VIEW LOOKING AFTERWARD FR41 CRACK



## C NOTE: AREA TO BE INSPECTED AREA 2 

### Q CRACK AREA 1 

### P

D_SB_536177_5_BAAA_02_00 Figure A-FBAAA - Sheet 02 Inspection areas DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 523 5

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

# @A300-600 SERVICE BULLETIN

**CONF ALL

CRACK

STGR36

STGR37

LH SHOWN RH SYMMETRICAL VIEW LOOKING AFTERWARD FR42



## E
NOTE: AREA TO BE INSPECTED CRACK

STGR36

STGR37

LH SHOWN RH SYMMETRICAL VIEW LOOKING AFTERWARD FR42



## D

AREA 2 AREA 1



### Q

P

D_SB_536177_5_BAAA_03_00 Figure A-FBAAA - Sheet 03 Inspection areas DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 524 5

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

# @A300-600 SERVICE BULLETIN

**CONF ALL

LH SHOWN RH SYMMETRICAL VIEW LOOKING AFTERWARD FR43

LH SHOWN RH SYMMETRICAL VIEW LOOKING AFTERWARD FR43 STGR36 CRACK

STGR36 

## G
NOTE: AREA TO BE INSPECTED 

## F

CRACK 

### P

Q AREA 2 AREA 1

D_SB_536177_5_BAAA_04_00 Figure A-FBAAA - Sheet 04 Inspection areas DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 525 5

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# @A300-600 SERVICE BULLETIN

**CONF ALL

STGR36

STGR37 CRACK

LH SHOWN RH SYMMETRICAL VIEW LOOKING AFTERWARD FR44



## H

STGR36

STGR37 CRACK

LH SHOWN RH SYMMETRICAL VIEW LOOKING AFTERWARD FR44



## J

NOTE: AREA TO BE INSPECTED AREA 1



### Q AREA 2 

### P

D_SB_536177_5_BAAA_05_00 Figure A-FBAAA - Sheet 05 Inspection areas DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 526 5

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

# @A300-600 SERVICE BULLETIN

**CONF ALL

CRACK

STGR37

LH SHOWN RH SYMMETRICAL VIEW LOOKING AFTERWARD FR45



## K

CRACK

STGR37

LH SHOWN RH SYMMETRICAL VIEW LOOKING AFTERWARD FR45



## L
NOTE: AREA TO BE INSPECTED 

### P

AREA 2 AREA 1



### Q

D_SB_536177_5_BAAA_06_00 Figure A-FBAAA - Sheet 06 Inspection areas DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 527 5

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# @A300-600 SERVICE BULLETIN

**CONF ALL

STGR37 CRACK

LH SHOWN RH SYMMETRICAL VIEW LOOKING AFTERWARD FR46

STGR37 CRACK

LH SHOWN RH SYMMETRICAL VIEW LOOKING AFTERWARD FR46



## N M

NOTE: AREA TO BE INSPECTED AREA 1



### Q P

AREA 2

D_SB_536177_5_BAAA_07_00 Figure A-FBAAA - Sheet 07 Inspection areas DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 528 5

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

# @A300-600 SERVICE BULLETIN

**CONF ALL

BASE FITTING

AREA 1

FWD 

## P

FWD 

## Q NOTE: AREA TO BE INSPECTED TYPICAL

TYPICAL
FOR REPAIRED FRAMES, THE NEW CRACKS ARE DETECTABLE IN THE FRAME FOOT FLANGE FIRST BASE FITTING AREA 2

D_SB_536177_5_BAAA_08_01 Figure A-FBAAA - Sheet 08 Inspection areas DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 529 5

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

# @A300-600 SERVICE BULLETIN

**CONF 003

FR40 

## A B FR41

FR47

FR41



## B Z140 

### A

C D F

C D F D_SB_536177_5_CAAA_01_00 Figure A-FCAAA - Sheet 01 Replacement of the Frame foot FR41, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 530 5

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

# @A300-600 SERVICE BULLETIN

**CONF 003

RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN



## A A F W D 

## C (55)

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H24 AND H25 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS 01 (56) 56

NOTE:



### A A

FR41 INBOARD

OUTBOARD

D_SB_536177_5_CAAA_02_01 Figure A-FCAAA - Sheet 02 Replacement of the Frame foot FR41, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 531 5

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

# @A300-600 SERVICE BULLETIN

**CONF 003



## D

RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN FR41 LH RH (100) (101)

H18

H14 H13 H12 H19

H10 H11 H23 H22 H21 H20 H15
H16
H17

H8 H6 H4 H2 H1
H3
H5
H7
H9
STGR35 

### E

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H24 AND H25 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS PROTECT THE CUT

Ü OUT AREA WITH MAT No 04CMA2 AND MAT. No 04EAC2 02 NOTE: FASTENERS NOT AFFECTED

HOLE SYMBOL ITEM P/N DESCRIPTION HOLE DIAMETER MIN MAX ASNA2529

Ü 3 (1) (2) NUT SCREW 5.552 mm (0.218 in) 5.512 mm (0.217 in) ASNA2529

Ü 3 (3) (4) NUT SCREW
ASNA2529

Ü 3 (3) (4) NUT SCREW N N F 8 9 10 9 10 9 EN6115V3A7 EN6115V3A6 EN6115V3A6 5.552 mm (0.218 in) 5.512 mm (0.217 in) 5.552 mm (0.218 in) 5.512 mm (0.217 in) HEAD ON THE VISIBLE SIDE N HEAD ON THE HIDDEN SIDE F 100 101

02 CUT

Ü OUT

01 INBOARD

OUTBOARD 04

04 04



### B

B C

C

REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) 04 DURING THE INSTALLATION OF THE NEW FRAME FOOT 

### C

C

D_SB_536177_5_CAAA_03_01 Figure A-FCAAA - Sheet 03 Replacement of the Frame foot FR41, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 532 5

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

# @A300-600 SERVICE BULLETIN

**CONF 003

FWD STGR35

(57) (58) RH LH 

## B B FR41 H46

H45

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H24 AND H25 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS 03 HOLE

SYMBOL ITEM P/N DESCRIPTION HOLE DIAMETER MIN MAX ASNA2529

Ü 6 (3) (4) NUT SCREW 9.925 mm (0.391 in) 9.886 mm (0.389 in) NAS1726

Ü 5E (3) (4) NUT SCREW
ASNA2529

Ü 5 (3) (4) NUT SCREW N N N 26 12 13 14 15 16 EN6114V6X14 ASNA2001V5

Ü 8Y

EN6114V5Y8 8.732 mm (0.344 in) 8.692 mm (0.342 in) HEAD ON THE VISIBLE SIDE N NOTE:

(5) RIVET N 19 ASNA2050DXJ4020 4.170 mm (0.164 in) 4.060 mm (0.160 in) 8.732 mm (0.344 in) 8.692 mm (0.342 in) 

## E 03

01

01 (100) (101) LH RH 100 101

H29 H28 H27 H26 H25 H24

H31 H30

05 05 FRAME FOOT



## C C

SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 27 mm 05 (1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in) FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in) TYPICAL SECTION ELECTRICAL BONDING

D_SB_536177_5_CAAA_04_01 Figure A-FCAAA - Sheet 04 Replacement of the Frame foot FR41, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 533 5

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

# @A300-600 SERVICE BULLETIN

**CONF 003

FWD (60) (59) LH RH FR41

STGR37 STGR36

H39 H38 H37 H36 H35 H34 H33 H32

H44 H43 H42 H41

FR41 RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN FR41

(59) (60)

(61)
RH LH 

## C C

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H24 AND H25 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS NOTE:

HOLE SYMBOL ITEM P/N DESCRIPTION HOLE DIAMETER MIN MAX ASNA2529

Ü 3 (3) (4) NUT SCREW 5.552 mm (0.218 in) 5.512 mm (0.217 in) ASNA2529

Ü 3 (3) (4) NUT SCREW
ASNA2529

Ü 3 (3) (4) NUT SCREW N N N 17 9 8 9 18 9 EN6115V3A5 EN6115V3A7 EN6115V3A4 5.552 mm (0.218 in) 5.512 mm (0.217 in) 5.552 mm (0.218 in) 5.512 mm (0.217 in) HEAD ON THE VISIBLE SIDE N 

### G H40

FASTENERS NOT AFFECTED 

### C C



## F G 01

01 H14
INBOARD

OUTBOARD

D_SB_536177_5_CAAA_05_00 Figure A-FCAAA - Sheet 05 Replacement of the Frame foot FR41, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 534 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

FR40 

## A B FR41

FR47

FR41



## B Z140 

### A

C D F

C D F D_SB_536177_5_CAAB_01_00 Figure A-FCAAB - Sheet 01 Replacement of the Frame foot FR41, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 535 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN



## A A F W D 

## C (55)

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H24 AND H25 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS 01 (56) 56

NOTE:



### A A

FR41 INBOARD

OUTBOARD

D_SB_536177_5_CAAB_02_01 Figure A-FCAAB - Sheet 02 Replacement of the Frame foot FR41, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 536 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002



## D

RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN FR41 LH RH (100) (101)

H18

H14 H13 H12 H19

H10 H11 H23 H22 H21 H20 H15
H16
H17

H8 H6 H4 H2 H1
H3
H5
H7
H9
STGR35 

### E

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H24 AND H25 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS PROTECT THE CUT

Ü OUT AREA WITH MAT No 04CMA2 AND MAT. No 04EAC2 02 NOTE: FASTENERS NOT AFFECTED

HOLE SYMBOL ITEM P/N DESCRIPTION HOLE DIAMETER MIN MAX HEAD ON THE VISIBLE SIDE N HEAD ON THE HIDDEN SIDE F 100 101

02 CUT

Ü OUT

01 INBOARD

OUTBOARD 04

04 04



### B

B C

C

REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) 04 DURING THE INSTALLATION OF THE NEW FRAME FOOT 

### C

C

ASNA2529

Ü 3 (1) (2) NUT SCREW 5.552 mm (0.218 in) 5.512 mm (0.217 in) ASNA2529

Ü 3 (1) (2) NUT SCREW
ASNA2529

Ü 3 (1) (2) NUT SCREW N N F 8 9 10 9 10 9 EN6115V3A7 EN6115V3A6 EN6115V3A6 5.552 mm (0.218 in) 5.512 mm (0.217 in) 5.552 mm (0.218 in) 5.512 mm (0.217 in)

D_SB_536177_5_CAAB_03_01 Figure A-FCAAB - Sheet 03 Replacement of the Frame foot FR41, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 537 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

FWD STGR35

(57) (58) RH LH 

## B B FR41 H46

H45

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H24 AND H25 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS 03 HOLE

SYMBOL ITEM P/N DESCRIPTION HOLE DIAMETER MIN MAX HEAD ON THE VISIBLE SIDE N NOTE: 

## E 03

01

01 (100) (101) LH RH 100 101

H29 H28 H27 H26 H25 H24

H31 H30

05 05 FRAME FOOT



## C C

SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 27 mm 05 (1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in) FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in) TYPICAL SECTION

ASNA2529

Ü 6 (1) (2) NUT SCREW 10.321 mm (0.406 in) 10.282 mm (0.405 in) NAS1726

Ü 5E (3) (4) NUT SCREW
ASNA2529

Ü 5 (1) (2) NUT SCREW N N N 11 12 13 14 15 16 EN6114V6Y14 ASNA2001V5

Ü 8Y

EN6114V5Y8 8.732 mm (0.344 in) 8.692 mm (0.342 in)
(5) RIVET N 19 ASNA2050DXJ4020 4.170 mm (0.164 in) 4.060 mm (0.160 in) 8.732 mm (0.344 in) 8.692 mm (0.342 in) ELECTRICAL BONDING

D_SB_536177_5_CAAB_04_01 Figure A-FCAAB - Sheet 04 Replacement of the Frame foot FR41, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 538 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

FWD (60) (59) LH RH FR41

STGR37 STGR36

H39 H38 H37 H36 H35 H34 H33 H32

H44 H43 H42 H41

FR41 RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN FR41

(59) (60) (61) RH LH 

## C C

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H24 AND H25 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS NOTE:

HOLE SYMBOL ITEM P/N DESCRIPTION HOLE DIAMETER MIN MAX ASNA2529

Ü 3 (1) (2) NUT SCREW 5.552 mm (0.218 in) 5.512 mm (0.217 in) ASNA2529

Ü 3 (1) (2) NUT SCREW
ASNA2529

Ü 3 (1) (2) NUT SCREW N N N 8 9 17 9 18 9 EN6115V3A7 EN6115V3A5 EN6115V3A4 5.552 mm (0.218 in) 5.512 mm (0.217 in) 5.552 mm (0.218 in) 5.512 mm (0.217 in) HEAD ON THE VISIBLE SIDE N 

### G H40

FASTENERS NOT AFFECTED 

### C C



## F G 01

01 H14

INBOARD

OUTBOARD

D_SB_536177_5_CAAB_05_00 Figure A-FCAAB - Sheet 05 Replacement of the Frame foot FR41, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 539 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

FR40 

## A B FR41

FR47

FR41



## B Z140 

### A

C F

C
F D

D

D_SB_536177_5_CAAC_01_00 Figure A-FCAAC - Sheet 01 Replacement of the Frame foot FR41, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 540 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN

F W D 

## C (55)

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H24 AND H25 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS 01 (56) 56

NOTE: 

### A A

FR41 INBOARD

OUTBOARD



## A A

D_SB_536177_5_CAAC_02_01 Figure A-FCAAC - Sheet 02 Replacement of the Frame foot FR41, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 541 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001



## D

RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN FR41 LH RH (100) (101)

H18

H14 H13 H12 H19

H10 H11 H23 H22 H21 H20 H15
H16
H17

H8 H6 H4 H2 H1
H3
H5
H7
H9
STGR35 

### E

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H24 AND H25 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS NOTE: FASTENERS NOT AFFECTED 100 101

01 INBOARD

OUTBOARD 03

03 03



### B

B C

C

REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) 03 DURING THE INSTALLATION OF THE NEW FRAME FOOT 

### C

C

D_SB_536177_5_CAAC_03_01

Figure A-FCAAC - Sheet 03 Replacement of the Frame foot FR41, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 542 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

5.113 mm (0.201 in)

5.113 mm (0.201 in) 5.152 mm (0.203 in)

5.152 mm (0.203 in) 9 23

9 24 NUT SCREW

NUT SCREW ASNA2529

Ü 3 EN6115V3X5

ASNA2529

Ü 3 EN6115V3X7 5.113 mm (0.201 in) 5.152 mm (0.203 in) 9 25 NUT SCREW ASNA2529

Ü 3 EN6115V3X6 5.113 mm (0.201 in) 5.152 mm (0.203 in) 9 23 NUT SCREW ASNA2529

Ü 3 EN6115V3X5 PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX

(7) (6)

(4) (3) N N (4) (3) (5) HOLE SYMBOL ITEM

N HEAD ON THE VISIBLE SIDE N HEAD ON THE HIDDEN SIDE F NOTE:

OR

5.113 mm (0.201 in) 5.152 mm (0.203 in) 9 24 NUT SCREW ASNA2529

Ü 3 EN6115V3X7 5.113 mm (0.201 in) 5.152 mm (0.203 in) 9 24 NUT SCREW ASNA2529

Ü 3 EN6115V3X7
(7) (6) (5) N OR

5.113 mm (0.201 in) 5.152 mm (0.203 in) 9 25 NUT SCREW ASNA2529

Ü 3 EN6115V3X6 5.113 mm (0.201 in) 5.152 mm (0.203 in) 9 25 NUT SCREW ASNA2529

Ü 3 EN6115V3X6
(7) (6) (5) N OR

5.113 mm (0.201 in) 5.152 mm (0.203 in) 9 25 NUT SCREW ASNA2529

Ü 3 EN6115V3X6 F (4) (3)

D_SB_536177_5_CAAC_04_00 Figure A-FCAAC - Sheet 04 Replacement of the Frame foot FR41, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 543 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

FWD STGR35

(57) (58) RH LH 

## B B FR41 H46

H45

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H24 AND H25 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS 02 HEAD ON THE VISIBLE SIDE

N NOTE: 

## E 02

01

01 (100) (101) LH RH 100 101

H29 H28 H27 H26 H25 H24

H31 H30

04 04 FRAME FOOT



## C C

SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 27 mm 04 (1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in) FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in) TYPICAL SECTION

9.886 mm (0.389 in) 9.925 mm (0.391 in) 12 26 NUT SCREW ASNA2529

Ü 6 EN6114V6X14 8.296 mm (0.327 in) 8.335 mm (0.328 in) 14 27 NUT SCREW NAS1726

Ü 5E ASNA2001V5

Ü 8X PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX
(4) (3) N N (4) (3) HOLE SYMBOL ITEM

8.296 mm (0.327 in) 8.335 mm (0.328 in) 16 28 NUT SCREW ASNA2529

Ü 5 EN6114V5X8 N (4) (3) 4.060 mm (0.160 in) 4.170 mm (0.164 in) 19 RIVET ASNA2050DXJ4020 (19) N ELECTRICAL BONDING

D_SB_536177_5_CAAC_05_01 Figure A-FCAAC - Sheet 05 Replacement of the Frame foot FR41, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 544 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

FWD (60) (59) LH RH FR41

STGR37 STGR36

H39 H38 H37 H36 H35 H34 H33 H32

H44 H43 H42 H41

FR41 RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN 

### G H40



## G F 01

01

FASTENERS NOT AFFECTED NOTE:

5.113 mm (0.201 in) 5.152 mm (0.203 in) 9 23 NUT SCREW ASNA2529

Ü 3 EN6115V3X5 5.113 mm (0.201 in) 5.152 mm (0.203 in) 9 24 NUT SCREW ASNA2529

Ü 3 EN6115V3X7 PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX (4) (3) N N (4) (3) HOLE SYMBOL ITEM

5.113 mm (0.201 in) 5.152 mm (0.203 in) 9 29 NUT SCREW ASNA2529

Ü 3 EN6115V3X4 N (4) (3) WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 01 EXCEPT FOR HOLES H24 AND H25 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS HEAD ON THE VISIBLE SIDE N INBOARD

OUTBOARD

D_SB_536177_5_CAAC_06_01 Figure A-FCAAC - Sheet 06 Replacement of the Frame foot FR41, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 545 5

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

# @A300-600 SERVICE BULLETIN

**CONF 003

FR42

FR47

FR40

FR42 

## A

B B Z140 

### A

C D F C D F

D_SB_536177_5_DAAA_01_00 Figure A-FDAAA - Sheet 01 Replacement of the Frame foot FR42, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 546 5

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

# @A300-600 SERVICE BULLETIN

**CONF 003

RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN



## A A F W D 

## C
(55)

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H91 AND H92 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS 01 (56) 56

NOTE: 

### A A

FR42 INBOARD

OUTBOARD

D_SB_536177_5_DAAA_02_01 Figure A-FDAAA - Sheet 02 Replacement of the Frame foot FR42, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 547 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.@A300-600SERVICE BULLETIN**CONF 003H90H68H69H70H71H72H75H76H77H78H67H66H65H64H62H61H63H74H73H60H89H88H87H86H85H83H52H53H54H55H56H57H59H58STGR36STGR37(62)(65)(63)(64)BBDFR42LH SHOWNRH SYMMETRICALVIEW LOOKING AFTCCNOTE:HEAD ON THE VISIBLE SIDEFASTENERS NOT AFFECTEDNNUTSCREWNUTSCREWASNA2529Ü3EN6115V3A6ASNA2529Ü3EN6115V3A6N(4)(3)109(3)(4)910HOLESYMBOLITEMPART NUMBERDESCRIPTIONHOLE DIAMETERMINMAXNUTSCREWASNA2529Ü3EN6115V3A9WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H91 AND H92PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1APPLY MAT No 06ABB1 BETWEEN PARTS0102PROTECT THE CUTÜOUT AREA WITH MAT No 04CMA2 AND MAT No 04EAC2NUTSCREWASNA2529Ü3EN6115V3A85.512 mm(0.217 in)5.552 mm(0.218 in)E01CUTÜOUT02NNN(2)(1)NUTSCREWASNA2529Ü3EN6115V3A6(1)(2)109339(1)32(2)95.512 mm(0.217 in)5.552 mm(0.218 in)5.512 mm(0.217 in)5.552 mm(0.218 in)5.512 mm(0.217 in)5.552 mm(0.218 in)5.512 mm(0.217 in)5.552 mm(0.218 in)FHEAD ON THE HIDDEN SIDEFLHRH102103(102)(103)INBOARDOUTBOARD04REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) DURING THE INSTALLATION OF THE NEW FRAME FOOT0404H84H51DDDDD_SB_536177_5_DAAA_03_01Figure A-FDAAA - Sheet 03Replacement of the Frame foot FR42, LH and RH SidesDATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 5485Printed in FRANCE©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF 003

FWD 

## B B (62) (63)

(5) (4) (3)

RIVET NUT SCREW NAS1726

Ü 5E ASNA2001V5

Ü 8Y HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX

(4) (3) NUT SCREW

ASNA2529

Ü 6 EN6114V6X13 7.102 mm (0.280 in) 7.141 mm (0.281 in) NUT SCREW
ASNA2529

Ü 5 EN6114V5Y8 (3) (4) N 15 16
9.886 mm (0.389 in) 9.925 mm (0.391 in) 4.060 mm (0.160 in) 4.170 mm (0.164 in) ASNA2050DXJ4020 N N N

19 35 12 13 14 7.102 mm (0.280 in) 7.141 mm (0.281 in) NOTE: HEAD ON THE VISIBLE SIDE

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H91 AND H92 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS 01

N

03 USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS 01
01 

## E H98 H97 H96 H95 H93 H91 H92

H94

H99

H100

H101

H102 (57) (58) LH RH H79 H80 03 FR42 STGR36
LH RH 102 103 (102) (103)



## C C (63) (65)

(62)

(64)

01

D_SB_536177_5_DAAA_04_00 Figure A-FDAAA - Sheet 04 Replacement of the Frame foot FR42, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 549 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.@A300-600SERVICE BULLETIN**CONF 003STGR38STGR37H113H112H111H110H109H108H107H106H105H104H103FR42LH SHOWNRH SYMMETRICALVIEW LOOKING AFTFASTENERS NOT AFFECTEDNOTE:HOLESYMBOLITEMPART NUMBERDESCRIPTIONHOLE DIAMETERMINMAX98NUTSCREWASNA2529Ü3EN6115V3A7(3)(4)918NUTSCREWASNA2529Ü3EN6115V3A4(3)(4)19RIVETASNA2050DXJ40204.060 mm(0.160 in)4.170 mm(0.164 in)(5)N917NUTSCREWASNA2529Ü3EN6115V3A5(3)(4)WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H91 AND H9201PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1APPLY MAT No 06ABB1 BETWEEN PARTSUSE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF03STIFFENERSHEAD ON THE VISIBLE SIDENUTSCREWASNA2529Ü3EN6115V3A4(5)9185.512 mm(0.217 in)5.552 mm(0.218 in)5.512 mm(0.217 in)5.552 mm(0.218 in)5.512 mm(0.217 in)5.552 mm(0.218 in)5.512 mm(0.217 in)5.552 mm(0.218 in)NNNN03FN01GFR42FWD(66)(67)H117H116H115LHRHH11401G(66)(67)(68)(69)LHLHRHRHSTGR37FR4201H82H81OUTBOARDINBOARDEEEED_SB_536177_5_DAAA_05_01Figure A-FDAAA - Sheet 05Replacement of the Frame foot FR42, LH and RH SidesDATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 5505Printed in FRANCE©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF 002

FR42

FR47

FR40

FR42 

## A

B B Z140 

### A

C D F

C D F D_SB_536177_5_DAAB_01_00 Figure A-FDAAB - Sheet 01 Replacement of the Frame foot FR42, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 551 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN



## A A F W D 

## C
(55)

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H91 AND H92 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS 01 (56) 56

NOTE: 

### A A

FR42 INBOARD

OUTBOARD

D_SB_536177_5_DAAB_02_01 Figure A-FDAAB - Sheet 02 Replacement of the Frame foot FR42, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 552 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.@A300-600SERVICE BULLETIN**CONF 002NOTE:HEAD ON THE VISIBLE SIDEFASTENERS NOT AFFECTEDNNUTSCREWASNA2529Ü3EN6115V3A6(1)(2)910FHOLESYMBOLITEMPART NUMBERDESCRIPTIONHOLE DIAMETERMINMAXNUTSCREWASNA2529Ü3EN6115V3A9WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H91 AND H92PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1APPLY MAT No 06ABB1 BETWEEN PARTS0102PROTECT THE CUTÜOUT AREA WITH MAT No 04CMA2 AND MAT No 04EAC2NUTSCREWASNA2529Ü3EN6115V3A8NNN(2)(1)NUTSCREWASNA2529Ü3EN6115V3A6(1)(2)109339(1)32(2)95.512 mm(0.217 in)5.552 mm(0.218 in)5.512 mm(0.217 in)5.552 mm(0.218 in)5.512 mm(0.217 in)5.552 mm(0.218 in)5.512 mm(0.217 in)5.552 mm(0.218 in)HEAD ON THE HIDDEN SIDEFH90H68H69H70H71H72H75H76H77H78H67H66H65H64H62H61H63H74H73H60H89H88H87H86H85H83H52H53H54H55H56H57H59H58STGR36STGR37(62)(65)(63)(64)BBDFR42LH SHOWNRH SYMMETRICALVIEW LOOKING AFTCCE01CUTÜOUT02LHRH102103(102)(103)INBOARDOUTBOARD0404H84H51DDDD04REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) DURING THE INSTALLATION OF THE NEW FRAME FOOTD_SB_536177_5_DAAB_03_01Figure A-FDAAB - Sheet 03Replacement of the Frame foot FR42, LH and RH SidesDATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 5535Printed in FRANCE©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF 002

FWD 

## C C (63) (65)

(62)

(64)

(5)

(4) (3) RIVET

NUT SCREW NAS1726

Ü 5E ASNA2001V5

Ü 8Y HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX

(2) (1) NUT SCREW ASNA2529

Ü 6 EN6114V6Y13 8.692 mm (0.342 in) 8.732 mm (0.344 in) NUT SCREW ASNA2529

Ü 5 EN6114V5Y8 (1) (2)
10.282 mm (0.405 in) 10.321 mm (0.406 in) 4.060 mm (0.160 in) 4.170 mm (0.164 in) ASNA2050DXJ4020 N

N 15 16 19 34 12 13 14 NOTE:
HEAD ON THE VISIBLE SIDE

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H91 AND H92 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS 01

N

03 USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS 01

01 

## E

N

N 8.692 mm (0.342 in) 8.732 mm (0.344 in) H98 H97 H96 H95 H93 H91 H92

H94

H99

H100

H101

H102 

## B B (62) (63)

01 (58) (57) LH RH H79 H80 03 FR42 STGR36
LH RH 102 103 (102) (103)

ELECTRICAL BONDING

05 SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 27 mm (1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in) FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in)

05

TYPICAL SECTION FRAME FOOT

05 

## D D

D_SB_536177_5_DAAB_04_01 Figure A-FDAAB - Sheet 04 Replacement of the Frame foot FR42, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 554 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.@A300-600SERVICE BULLETIN**CONF 002FASTENERS NOT AFFECTEDNOTE:HOLESYMBOLITEMPART NUMBERDESCRIPTIONHOLE DIAMETERMINMAX98NUTSCREWASNA2529Ü3EN6115V3A7(3)(4)918NUTSCREWASNA2529Ü3EN6115V3A4(3)(4)19RIVETASNA2050DXJ40204.060 mm(0.160 in)4.170 mm(0.164 in)(5)N917NUTSCREWASNA2529Ü3EN6115V3A5(3)(4)WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H91 AND H9201PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1APPLY MAT No 06ABB1 BETWEEN PARTSUSE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF03STIFFENERSHEAD ON THE VISIBLE SIDENUTSCREWASNA2529Ü3EN6115V3A4(5)9185.512 mm(0.217 in)5.552 mm(0.218 in)5.512 mm(0.217 in)5.552 mm(0.218 in)5.512 mm(0.217 in)5.552 mm(0.218 in)5.512 mm(0.217 in)5.552 mm(0.218 in)NNNNNSTGR38STGR37H113H112H111H110H109H108H107H106H105H104H103FR42LH SHOWNRH SYMMETRICALVIEW LOOKING AFT03F01GFR42FWD(66)(67)H117H116H115LHRHH11401G(66)(67)(68)(69)LHLHRHRHSTGR37FR4201H82H81OUTBOARDINBOARDEEEED_SB_536177_5_DAAB_05_01Figure A-FDAAB - Sheet 05Replacement of the Frame foot FR42, LH and RH SidesDATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 5555Printed in FRANCE©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF 001

FR40 

## A B FR42

FR47

FR42



## B Z140 

### A

C D F

C D F D_SB_536177_5_DAAC_01_00 Figure A-FDAAC - Sheet 01 Replacement of the Frame foot FR42, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 556 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN



## A A F W D 

## C
(55)

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H91 AND H92 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS 01 (56) 56

NOTE: 

### A A

FR42 INBOARD

OUTBOARD

D_SB_536177_5_DAAC_02_01 Figure A-FDAAC - Sheet 02 Replacement of the Frame foot FR42, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 557 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.@A300-600SERVICE BULLETIN**CONF 001DFASTENERS NOT AFFECTEDNOTE:FR42LH SHOWNRH SYMMETRICALVIEW LOOKING AFTWET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H91 AND H9201PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1APPLY MAT No 06ABB1 BETWEEN PARTS010303H90H68H69H70H71H72H75H76H77H78H67H66H65H64H62H61H63H74H73H60H89H88H87H86H85H83H52H53H54H55H56H57H59H58STGR36STGR37LHRH102103H84H51BBE(102)(103)INBOARDOUTBOARD03REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) DURING THE INSTALLATION OF THE NEW FRAME FOOTCCCCD_SB_536177_5_DAAC_03_01Figure A-FDAAC - Sheet 03Replacement of the Frame foot FR42, LH and RH SidesDATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 5585Printed in FRANCE©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF 001

NOTE:

HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX

9 25 NUT SCREW ASNA2529

Ü 3 EN6115V3X6 5.113 mm (0.201 in) 5.152 mm (0.203 in) (5) HEAD ON THE VISIBLE SIDE

9 25 NUT SCREW ASNA2529

Ü 3 EN6115V3X6 5.113 mm (0.201 in) 5.152 mm (0.203 in) (6) (7) 9 25 NUT SCREW ASNA2529

Ü 3 EN6115V3X6 5.113 mm (0.201 in) 5.152 mm (0.203 in) (3) (4) 9 24 NUT SCREW ASNA2529

Ü 3 EN6115V3X7 5.113 mm (0.201 in) 5.152 mm (0.203 in) (3) (4) 9 25 NUT SCREW ASNA2529

Ü 3 EN6115V3X6 5.113 mm (0.201 in) 5.152 mm (0.203 in) (3) (4) N

N

N N F HEAD ON THE HIDDEN SIDE F N

9 23 NUT SCREW ASNA2529

Ü 3 EN6115V3X5 5.113 mm (0.201 in) 5.152 mm (0.203 in) (5)

9 23 NUT SCREW ASNA2529

Ü 3 EN6115V3X5 5.113 mm (0.201 in) 5.152 mm (0.203 in) (6) (7) OR

OR

D_SB_536177_5_DAAC_04_00 Figure A-FDAAC - Sheet 04 Replacement of the Frame foot FR42, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 559 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

FWD 

## B B 102 103 LH RH (58) (57) LH RH H79 H80 FR42

NOTE:

HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX HEAD ON THE VISIBLE SIDE

14 27 NUT SCREW NAS1726

Ü 5E ASNA2001V5

Ü 8X 8.296 mm (0.327 in) 8.335 mm (0.328 in) (3) (4) 16 28 NUT SCREW ASNA2529

Ü 5 EN6114V5X8 8.296 mm (0.327 in) 8.335 mm (0.328 in) (3) (4) 19 RIVET ASNA2050DXJ4020 4.060 mm (0.160 in) 4.170 mm (0.164 in) (19) N

12 35 NUT SCREW ASNA2529

Ü 6 EN6114V6X13 9.886 mm (0.389 in) 9.925 mm (0.391 in) (3) (4)

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H91 AND H92 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS 02 STIFFENERS 02



## E 01 01

N N N N STGR36

H98 H97 H96 H95 H93 H91 H92

H94

H99

H100

H101

H102 (102) (103)

04

TYPICAL SECTION FRAME FOOT

04 

## C C
ELECTRICAL BONDING

04 SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 27 mm (1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in) FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in) D_SB_536177_5_DAAC_05_01 Figure A-FDAAC - Sheet 05 Replacement of the Frame foot FR42, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 560 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

(66) (67) (68) (69) H113 STGR37

STGR38 FR42

FWD (66) (67)

H112 H111 H110 H109 H108 H107 H106 H105 H104 H103

H117 H116 H115

LH LH LH RH

RH RH STGR37 FR42

FASTENERS NOT AFFECTED NOTE: FR42 RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN H114

HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX

9 23 NUT SCREW ASNA2529

Ü 3 EN6115V3X5 5.113 mm (0.201 in) 5.152 mm (0.203 in) (3) (4)
5.113 mm (0.201 in) 5.152 mm (0.203 in) 9 29 NUT SCREW ASNA2529

Ü 3 EN6115V3X4 5.113 mm (0.201 in) 5.152 mm (0.203 in) (3) (4)

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H91 AND H92 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF 02 STIFFENERS HEAD ON THE VISIBLE SIDE HEAD ON THE HIDDEN SIDE F N

9 29 NUT SCREW ASNA2529

Ü 3 EN6115V3X4 5.113 mm (0.201 in) 5.152 mm (0.203 in) 9 24 NUT SCREW ASNA2529

Ü 3 EN6115V3X7 (3) (4) 19 RIVET ASNA2050DXJ4020 4.060 mm (0.160 in) 4.170 mm (0.164 in) (19) 

### G

(19) 02 01

01

N F N N N 01 

## F

G OUTBOARD INBOARD 

### D

D



## D D

D_SB_536177_5_DAAC_06_01 Figure A-FDAAC - Sheet 06 Replacement of the Frame foot FR42, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 561 5

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

# @A300-600 SERVICE BULLETIN

**CONF 003

FR40 

## A B FR47

FR43



## B Z140 

### A

C D F

C D F FR43

D_SB_536177_5_EAAA_01_00 Figure A-FEAAA - Sheet 01 Replacement of the Frame foot FR43, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 562 5

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

# @A300-600 SERVICE BULLETIN

**CONF 003

RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN



## A A F W D 

## C (55)

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H150 AND H151 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS 01 (56) 56

NOTE:



### A A

FR43 INBOARD

OUTBOARD

D_SB_536177_5_EAAA_02_01 Figure A-FEAAA - Sheet 02 Replacement of the Frame foot FR43, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 563 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.@A300-600SERVICE BULLETIN**CONF 003WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H150 AND H15101PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1APPLY MAT. No 06ABB1 BETWEEN PARTSFASTENERS NOT AFFECTEDNOTE:DRH SYMMETRICALVIEW LOOKING AFTLH SHOWNFR43(72)(71)(70)LHRHSTGR36LHRHH136H135H134H149H148H147H146H145H122H124H126H132H128H131H121H123H125H127H133H129H130H140H141H142H143H144E0101PROTECT THE CUTÜOUT AREA WITH MAT. No 04CMA2 AND MAT. No 04EAC20202CUTÜOUTHOLESYMBOLITEMPART NUMBERDESCRIPTIONHOLE DIAMETERMINMAXHEAD ON THE VISIBLE SIDE5.512 mm(0.217 in)5.552 mm(0.218 in)(2)NUTASNA2529Ü3(1)SCREWEN6115V3A59175.512 mm(0.217 in)5.552 mm(0.218 in)(2)NUTASNA2529Ü3(1)SCREWEN6115V3A69105.512 mm(0.217 in)5.552 mm(0.218 in)(2)NUTASNA2529Ü3(1)SCREWEN6115V3A3936HEAD ON THE HIDDEN SIDEFN5.512 mm(0.217 in)5.552 mm(0.218 in)(2)NUTASNA2529Ü3(1)SCREWEN6115V3A7985.512 mm(0.217 in)5.552 mm(0.218 in)(4)NUTASNA2529Ü3(3)SCREWEN6115V3A69105.512 mm(0.217 in)5.552 mm(0.218 in)(4)NUTASNA2529Ü3(3)SCREWEN6115V3A89325.512 mm(0.217 in)5.552 mm(0.218 in)(2)NUTASNA2529Ü3(1)SCREWEN6115V3A798NNNNFFF(104)104(105)105OUTBOARDINBOARDFR43REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) DURING THE INSTALLATION OF THE NEW FRAME FOOT04D_SB_536177_5_EAAA_03_01CCBBBBDD040404DDD_SB_536177_5_EAAA_03_01Figure A-FEAAA - Sheet 03Replacement of the Frame foot FR43, LH and RH SidesDATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 5645Printed in FRANCE©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF 003

(58) (57) LH RH

9.886 mm (0.389 in) 9.925 mm (0.391 in) NUT SCREW ASNA2529

Ü 6 EN6114V6X14 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX HEAD ON THE VISIBLE SIDE NOTE:

12 26 N

8.692 mm (0.342 in) 8.732 mm (0.345 in) NUT SCREW NAS1726

Ü 5E ASNA2001V5

Ü 8Y 14 13 8.692 mm (0.342 in) 8.732 mm (0.345 in) NUT SCREW ASNA2529

Ü 5 EN6114V5Y8 16 15 4.060 mm (0.160 in) 4.170 mm (0.164 in) RIVET ASNA2050DXJ4020 19 (5)

USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS 03 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H150 AND H151 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1, APPLY MAT. No 06ABB1 BETWEEN PARTS 03

N (4) (3) (4) (3) (4) (3) N N N LH RH (104) 104 (105) 105

FWD 

## E 01 H154 H156

H155 H157 H152 H153 H150 H151 FR43 STGR36

H169

H168

01

05 05 FRAME FOOT



## D D C C

TYPICAL SECTION

SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 27 mm 05 (1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in) FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in) ELECTRICAL BONDING

D_SB_536177_5_EAAA_04_01

Figure A-FEAAA - Sheet 04 Replacement of the Frame foot FR43, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 565 5

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

# @A300-600 SERVICE BULLETIN

**CONF 003

FASTENERS NOT AFFECTED STGR38 STGR37

NOTE: H163 H162 H161 H160 H159 H158 H139 H138 H137

FR43 RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN

5.512 mm (0.217 in) 5.552 mm (0.218 in) NUT SCREW ASNA2529

Ü 3 EN6115V3A9 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX HEAD ON THE VISIBLE SIDE

9 33 N

5.512 mm (0.217 in) 5.552 mm (0.218 in) NUT SCREW ASNA2529

Ü 3 EN6115V3A7 9 8 5.512 mm (0.217 in) 5.552 mm (0.218 in) NUT SCREW ASNA2529

Ü 3 EN6115V3A8 9 32 5.512 mm (0.217 in) 5.552 mm (0.218 in) WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H150 AND H151 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS (4) (3) (4) (3) (4) (3) 

### G



## F

NUT SCREW ASNA2529

Ü 3 EN6115V3A5 9 17 (4) (3) HEAD ON THE HIDDEN SIDE F 01

F F F N FR43

FWD (72) (71)

H167 H166 H165 LH RH

H164

01 

## G OUTBOARD INBOARD

D_SB_536177_5_EAAA_05_00 Figure A-FEAAA - Sheet 05 Replacement of the Frame foot FR43, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 566 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

FR40 

## A B FR47

FR43



## B Z140 

### A

C D F

C D F FR43

D_SB_536177_5_EAAB_01_00 Figure A-FEAAB - Sheet 01 Replacement of the Frame foot FR43, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 567 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN



## A A F W D 

## C (55)

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H150 AND H151 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS 01 (56) 56

NOTE:



### A A

FR43 INBOARD

OUTBOARD

D_SB_536177_5_EAAB_02_01 Figure A-FEAAB - Sheet 02 Replacement of the Frame foot FR43, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 568 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.@A300-600SERVICE BULLETIN**CONF 002WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H150 AND H15101PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1APPLY MAT. No 06ABB1 BETWEEN PARTSFASTENERS NOT AFFECTEDNOTE:DRH SYMMETRICALVIEW LOOKING AFTLH SHOWNFR43(72)(71)(70)LHRHSTGR36LHRHH136H135H134H149H148H147H146H145H122H124H126H132H128H131H121H123H125H127H133H129H130H140H141H142H143H144E0101PROTECT THE CUTÜOUT AREA WITH MAT. No 04CMA2 AND MAT. No 04EAC20202CUTÜOUTHEAD ON THE VISIBLE SIDEHEAD ON THE HIDDEN SIDEFN(104)104(105)105OUTBOARDINBOARDFR43REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) DURING THE INSTALLATION OF THE NEW FRAME FOOT04CCBBBBDD040404HOLESYMBOLITEMPART NUMBERDESCRIPTIONHOLE DIAMETERMINMAX5.512 mm(0.217 in)5.552 mm(0.218 in)(2)NUTASNA2529Ü3(1)SCREWEN6115V3A59175.512 mm(0.217 in)5.552 mm(0.218 in)(2)NUTASNA2529Ü3(1)SCREWEN6115V3A69105.512 mm(0.217 in)5.552 mm(0.218 in)(2)NUTASNA2529Ü3(1)SCREWEN6115V3A39365.512 mm(0.217 in)5.552 mm(0.218 in)(2)NUTASNA2529Ü3(1)SCREWEN6115V3A7985.512 mm(0.217 in)5.552 mm(0.218 in)(2)NUTASNA2529Ü3(1)SCREWEN6115V3A69105.512 mm(0.217 in)5.552 mm(0.218 in)(2)NUTASNA2529Ü3(1)SCREWEN6115V3A89325.512 mm(0.217 in)5.552 mm(0.218 in)(2)NUTASNA2529Ü3(1)SCREWEN6115V3A798NNNNFFFDDD_SB_536177_5_EAAB_03_02Figure A-FEAAB - Sheet 03Replacement of the Frame foot FR43, LH and RH SidesDATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 5695Printed in FRANCE©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF 002

(58) (57) LH RH

HEAD ON THE VISIBLE SIDE NOTE:

N

USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS 03 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H150 AND H151 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1, APPLY MAT. No 06ABB1 BETWEEN PARTS 03 LH RH (104) 104 (105) 105

FWD 

## E 01 H154 H156

H155 H157 H152 H153 H150 H151 FR43 STGR36

H169

H168

01

05 05 FRAME FOOT



## D D C C

TYPICAL SECTION

SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 27 mm 05 (1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in) FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in) ELECTRICAL BONDING

10.282 mm (0.405 in) 10.321 mm (0.406 in) NUT SCREW ASNA2529

Ü 6 EN6114V6Y14 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX 12 11 8.692 mm (0.342 in) 8.732 mm (0.345 in) NUT SCREW NAS1726

Ü 5E ASNA2001V5

Ü 8Y 14 13 8.692 mm (0.342 in) 8.732 mm (0.345 in) NUT SCREW ASNA2529

Ü 5 EN6114V5Y8 16 15 4.060 mm (0.160 in) 4.170 mm (0.164 in) RIVET ASNA2050DXJ4020 19 (5) N (2) (1) (4) (3) (2) (1) N N

N

D_SB_536177_5_EAAB_04_01 Figure A-FEAAB - Sheet 04 Replacement of the Frame foot FR43, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 570 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

FASTENERS NOT AFFECTED STGR38 STGR37

NOTE: H163 H162 H161 H160 H159 H158 H139 H138 H137

FR43 RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN

5.512 mm (0.217 in) 5.552 mm (0.218 in) NUT SCREW ASNA2529

Ü 3 EN6115V3A9 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX HEAD ON THE VISIBLE SIDE

9 33 N

5.512 mm (0.217 in) 5.552 mm (0.218 in) NUT SCREW ASNA2529

Ü 3 EN6115V3A7 9 8 5.512 mm (0.217 in) 5.552 mm (0.218 in) NUT SCREW ASNA2529

Ü 3 EN6115V3A8 9 32 5.512 mm (0.217 in) 5.552 mm (0.218 in) WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H150 AND H151 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS (2) (1) (2) (1) (2) (1) 

### G



## F

NUT SCREW ASNA2529

Ü 3 EN6115V3A5 9 17 (2) (1) HEAD ON THE HIDDEN SIDE F 01

F F F N FR43

FWD (72) (71)

H167 H166 H165 LH RH

H164

01 

## G OUTBOARD INBOARD

D_SB_536177_5_EAAB_05_00 Figure A-FEAAB - Sheet 05 Replacement of the Frame foot FR43, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 571 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

FR40 

## A B FR47

FR43



## B Z140 

### A

C D F

C D F FR43

D_SB_536177_5_EAAC_01_00 Figure A-FEAAC - Sheet 01 Replacement of the Frame foot FR43, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 572 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN



## A A F W D 

## C (55)

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H150 AND H151 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS 01 (56) 56

NOTE:



### A A

FR43 INBOARD

OUTBOARD

D_SB_536177_5_EAAC_02_01 Figure A-FEAAC - Sheet 02 Replacement of the Frame foot FR43, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 573 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001



## D

RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN FR43 LH RH (104) (105)

H18

H14 H13 H12 H19

H10 H11 H23 H22 H21 H20 H15
H16
H17

H8 H6 H4 H2 H1
H3
H5
H7
H9
STGR36 

### E

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H150 AND H151 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 NOTE: FASTENERS NOT AFFECTED 104 105

01 INBOARD

OUTBOARD 03

03 03



### B

B C

C

REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) 03 DURING THE INSTALLATION OF THE NEW FRAME FOOT 

### C

C

APPLY MAT. No 06ABB1 BETWEEN PARTS H136 H135 H134 H149 H148 H146 H145 H122

H124

H126

H132
H128

H131 H121

H123

H125
H127
H133

H129 H130 H140

H141

H142

H143
H144 H147

D_SB_536177_5_EAAC_03_01 Figure A-FEAAC - Sheet 03 Replacement of the Frame foot FR43, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 574 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

5.113 mm (0.201 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in) 5.152 mm (0.203 in) (5)
(7) NUT SCREW

NUT ASNA2529

Ü 3 EN6115V3X5

ASNA2529

Ü 3 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX
(6) SCREW EN6115V3X5 HEAD ON THE VISIBLE SIDE NOTE:

9 23

9 23 5.113 mm (0.201 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in) 5.152 mm (0.203 in) (5)
(7) NUT SCREW

NUT ASNA2529

Ü 3 EN6115V3X6

ASNA2529

Ü 3 (6) SCREW EN6115V3X6 9 25

9 25 5.113 mm (0.201 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in) 5.152 mm (0.203 in) (5)
(7) NUT SCREW

NUT ASNA2529

Ü 3 EN6115V3X7

ASNA2529

Ü 3 (6) SCREW EN6115V3X7 9 24

9 24 5.113 mm (0.201 in) 5.152 mm (0.203 in) (4) NUT ASNA2529

Ü 3 (3) SCREW EN6115V3X9 9 39 5.113 mm (0.201 in) 5.152 mm (0.203 in) (4) NUT ASNA2529

Ü 3 (3) SCREW EN6115V3X6 9 25 5.113 mm (0.201 in) 5.152 mm (0.203 in) (4) NUT ASNA2529

Ü 3 (3) SCREW EN6115V3X8 9 40 N

N

N

F F F OR OR

OR HEAD ON THE HIDDEN SIDE F N

D_SB_536177_5_EAAC_04_00 Figure A-FEAAC - Sheet 04 Replacement of the Frame foot FR43, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 575 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

(58) (57) LH RH

HEAD ON THE VISIBLE SIDE NOTE:

N

USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS 02 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H150 AND H151 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1, APPLY MAT. No 06ABB1 BETWEEN PARTS 02 LH RH (104) 104 (105) 105

FWD 

## E 01 H154 H156

H155 H157 H152 H153 H150 H151 FR43 STGR36

H169

H168

01

04 04 FRAME FOOT

TYPICAL SECTION

SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 27 mm 04 (1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in) FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in) ELECTRICAL BONDING 

## B B

C C

9.886 mm (0.389 in) 9.925 mm (0.391 in) NUT SCREW ASNA2529

Ü 6 EN6114V6X14 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX 12 26 8.296 mm (0.327 in) 8.335 mm (0.328 in) NUT SCREW NAS1726

Ü 5E ASNA2001V5

Ü 8X 14 27 8.296 mm (0.327 in) 8.335 mm (0.328 in) NUT SCREW ASNA2529

Ü 5 EN6114V5X8 16 28 4.060 mm (0.160 in) 4.170 mm (0.164 in) RIVET ASNA2050DXJ4020 19 (19) N N N N (4) (3) (4) (3) (4) (3)

D_SB_536177_5_EAAC_05_01 Figure A-FEAAC - Sheet 05 Replacement of the Frame foot FR43, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 576 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

FASTENERS NOT AFFECTED STGR38 STGR37

NOTE: H163 H162 H161 H160 H159 H158 H139 H138 H137

FR43 RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN

5.113 mm (0.201 in) 5.152 mm (0.203 in) NUT SCREW ASNA2529

Ü 3 EN6115V3X9 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX HEAD ON THE VISIBLE SIDE

9 39 N

5.113 mm (0.201 in) 5.152 mm (0.203 in) NUT SCREW ASNA2529

Ü 3 EN6115V3X7 9 24 5.113 mm (0.201 in) 5.152 mm (0.203 in) NUT SCREW ASNA2529

Ü 3 EN6115V3X8 9 40 5.113 mm (0.201 in) 5.152 mm (0.203 in) WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H150 AND H151 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS (4) (3) (4) (3) (4) (3) 

### G



## F

NUT SCREW ASNA2529

Ü 3 EN6115V3X5 9 23 (4) (3) HEAD ON THE HIDDEN SIDE F

F F F N 01 FR43

FWD (72) (71) LH RH

01 

## G H167 H166 H165 H164 OUTBOARD INBOARD

D_SB_536177_5_EAAC_06_00 Figure A-FEAAC - Sheet 06 Replacement of the Frame foot FR43, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 577 5

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

# @A300-600 SERVICE BULLETIN

**CONF 003



### F D F D

C C FR44

FR44 

## A

B B Z140 

### A
FR40 FR47

D_SB_536177_5_GAAA_01_00 Figure A-FGAAA - Sheet 01 Replacement of the Frame foot FR44, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 578 5

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

# @A300-600 SERVICE BULLETIN

**CONF 003

NOTE: WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H204 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN



## A A F W D 

## C
(55)

01 (56) 56 

### A A

FR44 INBOARD

OUTBOARD

D_SB_536177_5_GAAA_02_01 Figure A-FGAAA - Sheet 02 Replacement of the Frame foot FR44, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 579 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.@A300-600SERVICE BULLETIN**CONF 003DRH SYMMETRICALVIEW LOOKING AFTLH SHOWNFR44STGR37BBH200H201H202H195H196H197H198H199H180H181H183H182H189H190H184H186H188H187H185H194H191H192H193CCCCBBSTGR3602PROTECT THE CUTÜOUT AREA WITH MAT No 04CMA2 AND MAT No 04EAC203USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERSHEAD ON THE VISIBLE SIDENOTE:HEAD ON THE HIDDEN SIDEFFASTENERS NOT AFFECTEDNWET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H20401PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1APPLY MAT No 06ABB1 BETWEEN PARTSHOLESYMBOLITEMPNDESCRIPTIONHOLE DIAMETERMINMAX(1)(2)ASNA2529Ü3EN6115V3A6NUTSCREW1095.552 mm(0.218 in)5.512 mm(0.217 in)(1)(2)ASNA2529Ü3EN6115V3A7NUTSCREW89(1)(2)ASNA2529Ü3EN6115V3A3NUTSCREW369(3)(4)ASNA2529Ü3EN6115V3A7NUTSCREW89(3)(4)ASNA2529Ü3EN6115V3A6NUTSCREW109(5)ASNA2050DXJ4020RIVET194.170 mm(0.164 in)4.060 mm(0.160 in)NNNNFN5.552 mm(0.218 in)5.512 mm(0.217 in)5.552 mm(0.218 in)5.512 mm(0.217 in)5.552 mm(0.218 in)5.512 mm(0.217 in)5.552 mm(0.218 in)5.512 mm(0.217 in)010101ECUTÜOUT02LHRH106107(106)(107)(58)(57)LHRHSTGR36FR4403H221H222FR44(75)(74)(73)RHLHLHRH106107(106)(107)OUTBOARDINBOARD04REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) DURING THE INSTALLATION OF THE NEW FRAME FOOT040404DDDDD_SB_536177_5_GAAA_03_01Figure A-FGAAA - Sheet 03Replacement of the Frame foot FR44, LH and RH SidesDATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 5805Printed in FRANCE©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF 003

FWD 01 

## E NOTE:
HEAD ON THE VISIBLE SIDE N

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H204 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS HOLE SYMBOL ITEM PN DESCRIPTION HOLE DIAMETER MIN MAX (3) (4) ASNA2529

Ü 6 EN6114V6X14 NUT SCREW 26 12 9.925 mm (0.391 in) 9.886 mm (0.389 in) (3) (4) NAS1726

Ü 5E ASNA2001V5

Ü 8Y NUT SCREW 13 14 8.732 mm (0.344 in) 8.692 mm (0.342 in) (3) (4) ASNA2529

Ü 5 EN6114V5Y8 NUT SCREW 15 16 N N N 8.732 mm (0.344 in) 8.692 mm (0.342 in) H207 H208 H205 H206 H203 H204

TYPICAL SECTION FRAME FOOT



## C C 05 05

ELECTRICAL BONDING

SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 05 27 mm (1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in) FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in) D_SB_536177_5_GAAA_04_01 Figure A-FGAAA - Sheet 04 Replacement of the Frame foot FR44, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 581 5

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

# @A300-600 SERVICE BULLETIN

**CONF 003

NOTE: HEAD ON THE VISIBLE SIDE N

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H204 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS HOLE SYMBOL ITEM PN DESCRIPTION HOLE DIAMETER MIN MAX (3) (4) ASNA2529

Ü 3 EN6115V3A5 NUT SCREW 17 9 5.552 mm (0.218 in) 5.512 mm (0.217 in) (3) (4) ASNA2529

Ü 3 EN6115V3A7 NUT SCREW 8 9 (3) (4) ASNA2529

Ü 3 EN6115V3A4 NUT SCREW 18 9 N N N 5.552 mm (0.218 in) 5.512 mm (0.217 in) 5.552 mm (0.218 in) 5.512 mm (0.217 in) FASTENERS NOT AFFECTED RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN FR44



## F STGR38 STGR37

H216 H215 H214 H213 H212 H211 H210 H209 

### G

01 FWD 01 

## G (74) (75) LH RH

H220 H219 H218 H217 FR44

OUTBOARD INBOARD

D_SB_536177_5_GAAA_05_00 Figure A-FGAAA - Sheet 05 Replacement of the Frame foot FR44, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 582 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002



### F D F D

C C FR44

FR44 

## A

B B Z140 

### A
FR40 FR47

D_SB_536177_5_GAAB_01_00 Figure A-FGAAB - Sheet 01 Replacement of the Frame foot FR44, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 583 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002



## A A F W D NOTE: WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H204 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS 01 (55) (56) 56 RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN 

## C A A

FR44 INBOARD

OUTBOARD

D_SB_536177_5_GAAB_02_01 Figure A-FGAAB - Sheet 02 Replacement of the Frame foot FR44, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 584 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.@A300-600SERVICE BULLETIN**CONF 002DRH SYMMETRICALVIEW LOOKING AFTLH SHOWNFR44STGR37BBH200H201H202H195H196H197H198H199H180H181H183H182H189H190H184H186H188H187H185H194H191H192H193CCCCBBSTGR3602PROTECT THE CUTÜOUT AREA WITH MAT No 04CMA2 AND MAT No 04EAC203USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERSHEAD ON THE VISIBLE SIDENOTE:HEAD ON THE HIDDEN SIDEFFASTENERS NOT AFFECTEDNWET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H20401PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1APPLY MAT No 06ABB1 BETWEEN PARTSHOLESYMBOLITEMPNDESCRIPTIONHOLE DIAMETERMINMAX(1)(2)ASNA2529Ü3EN6115V3A6NUTSCREW1095.552 mm(0.218 in)5.512 mm(0.217 in)(1)(2)ASNA2529Ü3EN6115V3A7NUTSCREW89(1)(2)ASNA2529Ü3EN6115V3A3NUTSCREW369(3)(4)ASNA2529Ü3EN6115V3A7NUTSCREW89(3)(4)ASNA2529Ü3EN6115V3A6NUTSCREW109(5)ASNA2050DXJ4020RIVET194.170 mm(0.164 in)4.060 mm(0.160 in)NNNNN5.552 mm(0.218 in)5.512 mm(0.217 in)5.552 mm(0.218 in)5.512 mm(0.217 in)5.552 mm(0.218 in)5.512 mm(0.217 in)5.552 mm(0.218 in)5.512 mm(0.217 in)010101ECUTÜOUT02LHRH106107(106)(107)(58)(57)LHRHSTGR36FR4403H221H222FR44(75)(74)(73)RHLHLHRH106107(106)(107)OUTBOARDINBOARD04REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) DURING THE INSTALLATION OF THE NEW FRAME FOOT040404DDDDFD_SB_536177_5_GAAB_03_01Figure A-FGAAB - Sheet 03Replacement of the Frame foot FR44, LH and RH SidesDATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 5855Printed in FRANCE©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF 002

NOTE:

HEAD ON THE VISIBLE SIDE N

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H204 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS HOLE SYMBOL ITEM PN DESCRIPTION HOLE DIAMETER MIN MAX (1) (2) ASNA2529

Ü 6 EN6114V6Y14 NUT SCREW 11 12 10.321 mm (0.406 in) 10.282 mm (0.405 in) (3) (4) NAS1726

Ü 5E ASNA2001V5

Ü 8Y NUT SCREW 13 14 8.732 mm (0.344 in) 8.692 mm (0.342 in) (1) (2) ASNA2529

Ü 5 EN6114V5Y8 NUT SCREW 15 16 N 8.732 mm (0.344 in) 8.692 mm (0.342 in) N

N FWD 01 

## E H207 H208 H205 H206 H203 H204

ELECTRICAL BONDING TYPICAL SECTION FRAME FOOT



## C C 05 05

SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 05 27 mm (1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in) FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in) D_SB_536177_5_GAAB_04_01 Figure A-FGAAB - Sheet 04 Replacement of the Frame foot FR44, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 586 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

NOTE: HEAD ON THE VISIBLE SIDE N

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H204 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS HOLE SYMBOL ITEM PN DESCRIPTION HOLE DIAMETER MIN MAX (1) (2) ASNA2529

Ü 3 EN6115V3A7 NUT SCREW 8 9 5.552 mm (0.218 in) 5.512 mm (0.217 in) (1) (2) ASNA2529

Ü 3 EN6115V3A5 NUT SCREW 17 9 (1) (2) ASNA2529

Ü 3 EN6115V3A4 NUT SCREW 18 9 5.552 mm (0.218 in) 5.512 mm (0.217 in) 5.552 mm (0.218 in) 5.512 mm (0.217 in) N N N FASTENERS NOT AFFECTED RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN FR44



## F STGR38 STGR37

H216 H215 H214 H213 H212 H211 H210 H209 

### G

01 FWD 01 

## G (74) (75) LH RH

H220 H219 H218 H217 FR44

OUTBOARD INBOARD

D_SB_536177_5_GAAB_05_00 Figure A-FGAAB - Sheet 05 Replacement of the Frame foot FR44, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 587 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001



### F D F D

C C FR44

FR44 

## A

B B Z140 

### A
FR40 FR47

D_SB_536177_5_GAAC_01_00 Figure A-FGAAC - Sheet 01 Replacement of the Frame foot FR44, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 588 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

NOTE: WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H204 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN



## A A F W D 

## C
(55)

01 (56) 56 

### A A

FR44 INBOARD

OUTBOARD

D_SB_536177_5_GAAC_02_01 Figure A-FGAAC - Sheet 02 Replacement of the Frame foot FR44, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 589 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.@A300-600SERVICE BULLETIN**CONF 001DRH SYMMETRICALVIEW LOOKING AFTLH SHOWNFASTENERS NOT AFFECTEDNOTE:FR44BB0101WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H20401PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1APPLY MAT No 06ABB1 BETWEEN PARTSUSE EXISTING HOLES IN STRINGERS FOR THE02INSTALLATION OF STIFFENERSLHRH106107(106)(107)(58)(57)LHRHSTGR36FR4402H221H222STGR37BBH200H201H202H195H196H197H198H199H180H181H183H182H189H190H184H186H188H187H185H194H192H193STGR36ELHRH106107(106)(107)OUTBOARDINBOARD030303H19103REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) DURING THE INSTALLATION OF THE NEW FRAME FOOTCCCCD_SB_536177_5_GAAC_03_01Figure A-FGAAC - Sheet 03Replacement of the Frame foot FR44, LH and RH SidesDATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 5905Printed in FRANCE©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF 001

NOTE: HEAD ON THE VISIBLE SIDE N
HOLE SYMBOL ITEM PN DESCRIPTION HOLE DIAMETER MIN MAX ASNA2529

Ü 3 EN6115V3X6 (5) OR (6) (7) NUT SCREW

ASNA2529

Ü 3 EN6115V3X6 NUT SCREW 5.152 mm (0.203 in) 5.113 mm (0.201 in) 25 9 25 9 N 5.152 mm (0.203 in) 5.113 mm (0.201 in) ASNA2529

Ü 3 EN6115V3X7 (5) OR (6) (7) NUT SCREW

ASNA2529

Ü 3 EN6115V3X7 NUT SCREW 5.152 mm (0.203 in) 5.113 mm (0.201 in) 24 9 24 9 5.152 mm (0.203 in) 5.113 mm (0.201 in) N

ASNA2529

Ü 3 EN6115V3X5 (5) OR (6) (7) NUT SCREW

ASNA2529

Ü 3 EN6115V3X5 NUT SCREW 5.152 mm (0.203 in) 5.113 mm (0.201 in) 23 9 23 9 5.152 mm (0.203 in) 5.113 mm (0.201 in) N (3) (4) ASNA2529

Ü 3 EN6115V3X7 NUT SCREW 24 9 5.152 mm (0.203 in) 5.113 mm (0.201 in) (3) (4) ASNA2529

Ü 3 EN6115V3X6 NUT SCREW 25 9 5.152 mm (0.203 in) 5.113 mm (0.201 in) (19) ASNA2050DXJ4020 RIVET 19 4.170 mm (0.164 in) 4.060 mm (0.160 in) N F N HEAD ON THE HIDDEN SIDE F

D_SB_536177_5_GAAC_04_00 Figure A-FGAAC - Sheet 04 Replacement of the Frame foot FR44, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 591 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

FWD 01 

## E NOTE:
HEAD ON THE VISIBLE SIDE N

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H204 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS HOLE SYMBOL ITEM PN DESCRIPTION HOLE DIAMETER MIN MAX (3) (4) ASNA2529

Ü 6 EN6114V6X14 NUT SCREW 26 12 9.925 mm (0.391 in) 9.886 mm (0.389 in) N (3) (4) NAS1726

Ü 5E ASNA2001V5

Ü 8X NUT SCREW 27 14 8.335 mm (0.328 in) 8.296 mm (0.327 in) (3) (4) ASNA2529

Ü 5 EN6114V5X8 NUT SCREW 28 16 N N 8.335 mm (0.328 in) 8.296 mm (0.327 in) H207 H208 H205 H206 H203 H204

SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 04 27 mm (1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in) FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in) ELECTRICAL BONDING TYPICAL SECTION FRAME FOOT



## C C 04 04

D_SB_536177_5_GAAC_05_01 Figure A-FGAAC - Sheet 05 Replacement of the Frame foot FR44, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 592 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

NOTE: HEAD ON THE VISIBLE SIDE N

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H204 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS HOLE SYMBOL ITEM PN DESCRIPTION HOLE DIAMETER MIN MAX (3) (4) ASNA2529

Ü 3 EN6115V3X7 NUT SCREW 24 9 5.152 mm (0.203 in) 5.113 mm (0.201 in) (3) (4) ASNA2529

Ü 3 EN6115V3X5 NUT SCREW 23 9 (3) (4) ASNA2529

Ü 3 EN6115V3X4 NUT SCREW 29 9 N N N 5.152 mm (0.203 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in) 5.113 mm (0.201 in) FASTENERS NOT AFFECTED RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN FR44



## F
FWD STGR38 STGR37

H216 H215 H214 H213 H212 H211 H210 H209 

### G

01 01 

## G (74) (75) LH RH

H220 H219 H218 H217 FR44

OUTBOARD INBOARD

D_SB_536177_5_GAAC_06_00 Figure A-FGAAC - Sheet 06 Replacement of the Frame foot FR44, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 593 5

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

# @A300-600 SERVICE BULLETIN

**CONF 003

FR40 

## A B FR47

FR45



## B Z140 

### A

C D F

C D F FR45

D_SB_536177_5_JAAA_01_00 Figure A-FJAAA - Sheet 01 Replacement of the Frame foot FR45, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 594 5

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

# @A300-600 SERVICE BULLETIN

**CONF 003

RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN



## A A F W D 

## C (55)

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H270 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS 01

NOTE:



### A A

FR45 INBOARD

OUTBOARD

(76) 76 OR (56) 56

D_SB_536177_5_JAAA_02_01 Figure A-FJAAA - Sheet 02 Replacement of the Frame foot FR45, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 595 5

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

# @A300-600 SERVICE BULLETIN

**CONF 003

H230 H245 H252 H251 H250 H249 H248 H264 H259 H261 H263 H262 H260 H231
H258

H244 H242

H243 H241 H247 H246 H240 H239 H238 H237 H234 H257 H232 H235

(77)

STGR37 STGR36



## D

RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN FR45 H236

H266 LH RH (72) (71)



## B B FASTENERS NOT AFFECTED NOTE: WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H270 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS PROTECT THE CUT

Ü OUT AREA WITH MAT. No 04CMA2 AND MAT. No 0EAC2 02 01

USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS 03 

### C C LH RH (108) 108 (109) 109 

### E

01 H233

CUT

Ü OUT 02

H265 H253 H254

LH RH (58) (57) LH RH (108) 108 (109) 109 03

H255 H256

STGR36 FR45 INBOARD

OUTBOARD 

### E

E E E

B

B

REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) 06 DURING THE INSTALLATION OF THE NEW FRAME FOOT 06

06 

### D

D

D_SB_536177_5_JAAA_03_01 Figure A-FJAAA - Sheet 03 Replacement of the Frame foot FR45, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 596 5

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

# @A300-600 SERVICE BULLETIN

**CONF 003

5.512 mm (0.217 in) 5.512 mm (0.217 in) 5.552 mm (0.218 in) 5.552 mm (0.218 in) (5)
(94) NUT SCREW

NUT ASNA2529

Ü 3 EN6115V3A5

ASNA2529

Ü 3 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX
(93) SCREW EN6115V3A5 HEAD ON THE VISIBLE SIDE NOTE:

9 17

9 17 5.512 mm (0.217 in) 5.512 mm (0.217 in) 5.552 mm (0.218 in) 5.552 mm (0.218 in) (5)
(94) NUT SCREW

NUT ASNA2529

Ü 3 EN6114V3A6

ASNA2529

Ü 3 (93) SCREW EN6114V3A6 9 42

9 42 5.512 mm (0.217 in) 5.512 mm (0.217 in) 5.552 mm (0.218 in) 5.552 mm (0.218 in) (5)
(94) NUT SCREW

NUT ASNA2529

Ü 3 EN6115V3A6

ASNA2529

Ü 3 (93) SCREW EN6115V3A6 9 10

9 10 5.512 mm (0.217 in) 5.552 mm (0.218 in) (2) NUT ASNA2529

Ü 3 (1) SCREW EN6115V3A9 9 33

4.060 mm (0.160 in) 4.170 mm (0.164 in) (19) RIVET ASNA2050DXJ4020 19 5.512 mm (0.217 in) 5.552 mm (0.218 in) (4) NUT ASNA2529

Ü 3 (3) SCREW EN6115V3A6 9 10 OR OR

OR HEAD ON THE HIDDEN SIDE F N

5.512 mm (0.217 in) 5.552 mm (0.218 in) (4) NUT ASNA2529

Ü 3 (3) SCREW EN6115V3A8 9 32 5.512 mm (0.217 in) 5.552 mm (0.218 in) (4) NUT ASNA2529

Ü 3 (3) SCREW EN6115V3A9 9 33 5.512 mm (0.217 in) 5.512 mm (0.217 in) 5.552 mm (0.218 in) 5.552 mm (0.218 in) (5)
(94) NUT SCREW

NUT ASNA2529

Ü 3 EN6115V3A7

ASNA2529

Ü 3 (93) SCREW EN6115V3A7 9 8

9 8 OR 5.512 mm (0.217 in) 5.552 mm (0.218 in) (2) NUT ASNA2529

Ü 3 (1) SCREW EN6115V3A10 9 43 5.512 mm (0.217 in) 5.552 mm (0.218 in) (2) NUT ASNA2529

Ü 3 (1) SCREW EN6115V3A11 9 44 N

N

N

N F F F N F N N

D_SB_536177_5_JAAA_04_00 Figure A-FJAAA - Sheet 04 Replacement of the Frame foot FR45, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 597 5

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

# @A300-600 SERVICE BULLETIN

**CONF 003

FWD

9.886 mm (0.389 in) 9.925 mm (0.391 in) NUT SCREW ASNA2529

Ü 6 EN6114V6X14 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX HEAD ON THE VISIBLE SIDE NOTE:

12 26 N

10.282 mm (0.405 in) 10.321 mm (0.406 in) NUT SCREW NAS1726

Ü 6E ASNA2001V6

Ü 8Y 46 45 4.060 mm (0.160 in) 4.170 mm (0.164 in) RIVET ASNA2050DXJ4020 19 (19)

USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS 03 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H270 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS (4) (3) (4) (3) 

## E 01 (77) (78) (58) (57) LH RH LH RH (108) 108 (109) 109

N N N H269 H270

H271 H272 STGR37

FR45

01 03

01

STGR37
(78) (58) (57) LH RH (77) H268

H267


## C C

D D ELECTRICAL BONDING

D_SB_536177_5_JAAA_05_01 Figure A-FJAAA - Sheet 05 Replacement of the Frame foot FR45, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 598 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.@A300-600SERVICE BULLETIN**CONF 003IF INSTALLED, REMOVE THE BRACKET, LH SIDE ONLY04WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H27001PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1APPLY MAT. No 06ABB1 BETWEEN PARTSFWDSTGR39STGR38H281H280H279H278H277H276H275H274H273FR45RH SYMMETRICALVIEW LOOKING AFTLH SHOWN04(79)FGGFASTENERS NOT AFFECTEDNOTE:5.512 mm(0.217 in)5.552 mm(0.218 in)NUTSCREWASNA2529Ü3EN6115V3A6HOLESYMBOLITEMPART NUMBERDESCRIPTIONHOLE DIAMETERMINMAXHEAD ON THE VISIBLE SIDE910NSCREW17NUTEN6115V3A595.512 mm(0.217 in)5.552 mm(0.218 in)(4)(3)(3)(4)NUTSCREWASNA2529Ü3EN6115V3A9933(4)(3)HEAD ON THE HIDDEN SIDEF5.512 mm(0.217 in)5.552 mm(0.218 in)NUTSCREWASNA2529Ü3EN6115V3A798(4)(3)REMARKS5.512 mm(0.217 in)5.552 mm(0.218 in)NUTSCREWASNA2529Ü3EN6115V3A8932(4)(3)ASNA2529Ü3OR5.512 mm(0.217 in)5.552 mm(0.218 in)NUTSCREWASNA2529Ü3EN6115V3A5917(4)(3)N05ÜÜÜÜ0101NFFF05ANDARE FOR LH SIDE AND ITEMSANDARE FOR RH SIDEITEMS910917(72)(71)RHLHH285H284H283H282FR45OUTBOARDINBOARD0707FRAME FOOTTYPICAL SECTIONSPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 27 mm07(1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in)FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in)EED_SB_536177_5_JAAA_06_01Figure A-FJAAA - Sheet 06Replacement of the Frame foot FR45, LH and RH SidesDATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 5995Printed in FRANCE©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF 002

FR40 

## A B FR47

FR45



## B Z140 

### A

C D F

C D F FR45

D_SB_536177_5_JAAB_01_00 Figure A-FJAAB - Sheet 01 Replacement of the Frame foot FR45, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 600 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN



## A A F W D 

## C (55)

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H270 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS 01

NOTE:



### A A

FR45 INBOARD

OUTBOARD

(76) 76 OR (56) 56

D_SB_536177_5_JAAB_02_01 Figure A-FJAAB - Sheet 02 Replacement of the Frame foot FR45, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 601 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

H230 H245 H252 H251 H250 H249 H248 H264 H259 H261 H263 H262 H260 H231
H258

H244 H242

H243 H241 H247 H246 H240 H239 H238 H237 H234 H257 H232 H235

STGR37 STGR36



## D

RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN FR45 H236

H266 LH RH (72) (71)



## B B FASTENERS NOT AFFECTED NOTE: WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H270 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS PROTECT THE CUT

Ü OUT AREA WITH MAT. No 04CMA2 AND MAT. No 0EAC2 02 01

USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS 03 

### C C LH RH (108) 108 (109) 109 

### E

01 H233

CUT

Ü OUT 02

H265 H253 H254

LH RH (58) (57) LH RH (108) 108 (109) 109 03

H255 H256

STGR36 FR45 INBOARD

OUTBOARD 

### E

E E E

B

B

REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) 06 DURING THE INSTALLATION OF THE NEW FRAME FOOT 06

06 

### D

D

D_SB_536177_5_JAAB_03_01 Figure A-FJAAB - Sheet 03 Replacement of the Frame foot FR45, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 602 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

5.512 mm (0.217 in) 5.512 mm (0.217 in) 5.552 mm (0.218 in) 5.552 mm (0.218 in) (5)
(94) NUT SCREW

NUT ASNA2529

Ü 3 EN6115V3A5

ASNA2529

Ü 3 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX
(93) SCREW EN6115V3A5 HEAD ON THE VISIBLE SIDE NOTE:

9 17

9 17 5.512 mm (0.217 in) 5.552 mm (0.218 in) (2) NUT ASNA2529

Ü 3 (1) SCREW EN6114V3A6 9 42 5.512 mm (0.217 in) 5.552 mm (0.218 in) (2) NUT ASNA2529

Ü 3 (1) SCREW EN6115V3A6 9 10 5.512 mm (0.217 in) 5.552 mm (0.218 in) (2) NUT ASNA2529

Ü 3 (1) SCREW EN6115V3A9 9 33

4.060 mm (0.160 in) 4.170 mm (0.164 in) (19) RIVET ASNA2050DXJ4020 19 5.512 mm (0.217 in) 5.552 mm (0.218 in) (2) NUT ASNA2529

Ü 3 (1) SCREW EN6115V3A6 9 10 OR HEAD ON THE HIDDEN SIDE F N

5.512 mm (0.217 in) 5.552 mm (0.218 in) (2) NUT ASNA2529

Ü 3 (1) SCREW EN6115V3A8 9 32 5.512 mm (0.217 in) 5.552 mm (0.218 in) (2) NUT ASNA2529

Ü 3 (1) SCREW EN6115V3A9 9 33 5.512 mm (0.217 in) 5.552 mm (0.218 in) (2) NUT ASNA2529

Ü 3 (1) SCREW EN6115V3A7 9 8 5.512 mm (0.217 in) 5.552 mm (0.218 in) (2) NUT ASNA2529

Ü 3 (1) SCREW EN6115V3A10 9 43 5.512 mm (0.217 in) 5.552 mm (0.218 in) (2) NUT ASNA2529

Ü 3 (1) SCREW EN6115V3A11 9 44 N

N F N N N

F F F N N

D_SB_536177_5_JAAB_04_00 Figure A-FJAAB - Sheet 04 Replacement of the Frame foot FR45, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 603 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

10.282 mm (0.405 in) 10.321 mm (0.406 in) NUT SCREW ASNA2529

Ü 6 EN6114V6Y14 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX HEAD ON THE VISIBLE SIDE NOTE:

12 11 N

10.282 mm (0.405 in) 10.321 mm (0.406 in) NUT SCREW NAS1726

Ü 6E ASNA2001V6

Ü 8Y 46 45 4.060 mm (0.160 in) 4.170 mm (0.164 in) RIVET ASNA2050DXJ4020 19 (19)

USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS 03 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H270 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS (2) (1) (4) (3) N N N FWD 

## E 01 (77) (78) (58) (57) LH RH LH RH (108) 108 (109) 109

H269 H270

H271 H272 STGR37

FR45

01 03

01

STGR37
(78) (58) (57) LH RH (77) H268

H267


## C C

D D ELECTRICAL BONDING

D_SB_536177_5_JAAB_05_01 Figure A-FJAAB - Sheet 05 Replacement of the Frame foot FR45, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 604 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.@A300-600SERVICE BULLETIN**CONF 002IF INSTALLED, REMOVE THE BRACKET, LH SIDE ONLY04WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H27001PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1DO SEALANT BEAD AROUND PARTS WITH MAT .No 06ABB1APPLY MAT. No 06ABB1 BETWEEN PARTSSTGR39STGR38H281H280H279H278H277H276H275H274H273FR45RH SYMMETRICALVIEW LOOKING AFTLH SHOWN04(79)FGFASTENERS NOT AFFECTEDNOTE:5.512 mm(0.217 in)5.552 mm(0.218 in)NUTSCREWASNA2529Ü3EN6115V3A6HOLESYMBOLITEMPART NUMBERDESCRIPTIONHOLE DIAMETERMINMAXHEAD ON THE VISIBLE SIDE910NSCREW17NUTEN6115V3A595.512 mm(0.217 in)5.552 mm(0.218 in)(4)(3)(3)(4)NUTSCREWASNA2529Ü3EN6115V3A9933(4)(3)HEAD ON THE HIDDEN SIDEF5.512 mm(0.217 in)5.552 mm(0.218 in)NUTSCREWASNA2529Ü3EN6115V3A798(4)(3)REMARKS5.512 mm(0.217 in)5.552 mm(0.218 in)NUTSCREWASNA2529Ü3EN6115V3A8932(4)(3)ASNA2529Ü3OR5.512 mm(0.217 in)5.552 mm(0.218 in)NUTSCREWASNA2529Ü3EN6115V3A5917(4)(3)N05ÜÜÜÜ01NFFF05ANDARE FOR LH SIDE AND ITEMSANDARE FOR RH SIDEITEMS910917FWDG01(72)(71)RHLHH285H284H283H282FR45OUTBOARDINBOARD0707FRAME FOOTTYPICAL SECTIONEESPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 27 mm07(1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in)FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in)D_SB_536177_5_JAAB_06_01Figure A-FJAAB - Sheet 06Replacement of the Frame foot FR45, LH and RH SidesDATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 6055Printed in FRANCE©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF 001

FR40 

## A B FR47

FR45



## B Z140 

### A

C D F

C D F FR45

D_SB_536177_5_JAAC_01_00 Figure A-FJAAC - Sheet 01 Replacement of the Frame foot FR45, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 606 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN



## A A F W D 

## C (55)

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H270 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS 01

NOTE:



### A A

FR45 INBOARD

OUTBOARD

(76) 76 OR (56) 56

D_SB_536177_5_JAAC_02_01 Figure A-FJAAC - Sheet 02 Replacement of the Frame foot FR45, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 607 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

H230 H245 H252 H251 H250 H249 H248 H264 H259 H261 H263 H262 H260 H231
H258

H244 H242

H243 H241 H247 H246 H240 H239 H238 H237 H234 H257 H232 H235

STGR37 STGR36



## D

RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN FR45 H236

H266 LH RH (72) (71)



## B B FASTENERS NOT AFFECTED NOTE: WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H270 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS 01

USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS 02 

### C C LH RH (108) 108 (109) 109 

### E

01 H233

H265 H253 H254

LH RH (58) (57) LH RH (108) 108 (109) 109 02

H255 H256

STGR36 FR45 INBOARD

OUTBOARD 

### B

B

REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) 05 DURING THE INSTALLATION OF THE NEW FRAME FOOT 05

05 

### D

D D

D

D_SB_536177_5_JAAC_03_01 Figure A-FJAAC - Sheet 03 Replacement of the Frame foot FR45, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 608 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

5.113 mm (0.201 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in) 5.152 mm (0.203 in) (5)
(94) NUT SCREW

NUT ASNA2529

Ü 3 EN6115V3X5

ASNA2529

Ü 3 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX
(93) SCREW EN6115V3X5 HEAD ON THE VISIBLE SIDE NOTE:

9 23

9 23 5.113 mm (0.201 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in) 5.152 mm (0.203 in) (5)
(94) NUT SCREW

NUT ASNA2529

Ü 3 EN6114V3X6

ASNA2529

Ü 3 (93) SCREW EN6114V3X6 9 47

9 47 5.113 mm (0.201 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in) 5.152 mm (0.203 in) (5)
(94) NUT SCREW

NUT ASNA2529

Ü 3 EN6115V3X6

ASNA2529

Ü 3 (93) SCREW EN6115V3X6 9 25

9 25 5.113 mm (0.201 in) 5.152 mm (0.203 in) (4) NUT ASNA2529

Ü 3 (3) SCREW EN6115V3X8 9 40 4.060 mm (0.160 in) 4.170 mm (0.164 in) (19) RIVET ASNA2050DXJ4020 19 5.113 mm (0.201 in) 5.152 mm (0.203 in) (4) NUT ASNA2529

Ü 3 (3) SCREW EN6115V3X7 9 24 OR OR

OR HEAD ON THE HIDDEN SIDE F N

5.113 mm (0.201 in) 5.152 mm (0.203 in) (4) NUT ASNA2529

Ü 3 (3) SCREW EN6115V3X9 9 39 5.113 mm (0.201 in) 5.152 mm (0.203 in) (4) NUT ASNA2529

Ü 3 (3) SCREW EN6115V3X6 9 25 5.113 mm (0.201 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in) 5.152 mm (0.203 in) (5)
(94) NUT SCREW

NUT ASNA2529

Ü 3 EN6115V3X7

ASNA2529

Ü 3 (93) SCREW EN6115V3X7 9 24

9 24 OR N

N

N

F

F F F

N N

D_SB_536177_5_JAAC_04_00 Figure A-FJAAC - Sheet 04 Replacement of the Frame foot FR45, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 609 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

FWD (58) (57) LH RH

9.886 mm (0.389 in) 9.925 mm (0.391 in) NUT SCREW ASNA2529

Ü 6 EN6114V6X14 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX HEAD ON THE VISIBLE SIDE NOTE:

12 26 N

9.886 mm (0.389 in) 9.925 mm (0.391 in) NUT SCREW NAS1726

Ü 6E ASNA2001V6

Ü 8X 46 48 4.060 mm (0.160 in) 4.170 mm (0.164 in) RIVET ASNA2050DXJ4020 19 (19)

USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS 02 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H270 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS

N (4) (3) (4) (3) 

## E C C

N 01 01 LH RH (108) 108 (109) 109 H269 H270

H271 H272 STGR37

FR45
02 H267 H268

N ELECTRICAL BONDING

D_SB_536177_5_JAAC_05_01 Figure A-FJAAC - Sheet 05 Replacement of the Frame foot FR45, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 610 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.@A300-600SERVICE BULLETIN**CONF 001IF INSTALLED, REMOVE THE BRACKET, LH SIDE ONLY03WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H27001PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1APPLY MAT. No 06ABB1 BETWEEN PARTS04FWDSTGR39STGR38H281H280H279H278H277H276H275H274H273FR45RH SYMMETRICALVIEW LOOKING AFTLH SHOWN03(79)(71)(72)RHLHFGGFASTENERS NOT AFFECTEDNOTE:5.113 mm(0.201 in)5.152 mm(0.203 in)NUTSCREWASNA2529Ü3EN6115V3X6HOLESYMBOLITEMPART NUMBERDESCRIPTIONHOLE DIAMETERMINMAXHEAD ON THE VISIBLE SIDE925NSCREW23NUTEN6115V3X595.113 mm(0.201 in)5.152 mm(0.203 in)(4)(3)(3)(4)NUTSCREWASNA2529Ü3EN6115V3X9939(4)(3)HEAD ON THE HIDDEN SIDEFFFF5.113 mm(0.201 in)5.152 mm(0.203 in)NUTSCREWASNA2529Ü3EN6115V3X7924(4)(3)REMARKS5.113 mm(0.201 in)5.152 mm(0.203 in)NUTSCREWASNA2529Ü3EN6115V3X8940(4)(3)ASNA2529Ü3OR5.113 mm(0.201 in)5.152 mm(0.203 in)NUTSCREWASNA2529Ü3EN6115V3X5923(4)(3)NN04ÜÜÜÜ0101ANDARE FOR LH SIDE AND ITEMSANDARE FOR RH SIDEITEMS925923H285H284H283H282FR45OUTBOARDINBOARDSPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 27 mm06(1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in)FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in)0606FRAME FOOTDDTYPICAL SECTIOND_SB_536177_5_JAAC_06_01Figure A-FJAAC - Sheet 06Replacement of the Frame foot FR45, LH and RH SidesDATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 6115Printed in FRANCE©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF 003

FR40 

## A B FR47

FR46



## B Z140 

### A

C D F

C D F FR46

D_SB_536177_5_KAAA_01_00 Figure A-FKAAA - Sheet 01 Replacement of the Frame foot FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 612 5

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

# @A300-600 SERVICE BULLETIN

**CONF 003

RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN



## A A F W D 

## C (55)

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H332 AND H333 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS 01

NOTE:



### A A

FR46 INBOARD

OUTBOARD

(76) 76 OR (56) 56

D_SB_536177_5_KAAA_02_01 Figure A-FKAAA - Sheet 02 Replacement of the Frame foot FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 613 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.@A300-600SERVICE BULLETIN**CONF 003BBSTGR37DRH SYMMETRICALVIEW LOOKING AFTLH SHOWNFR46CC(81)H33180H321H308H307H306H320H319H304H305H318H310H309H313H317H302H303H312H311H301H300H316H324H326H329H330H322H323H327H328H325FASTENERS NOT AFFECTEDHEAD ON THE VISIBLE SIDENOTE:HEAD ON THE HIDDEN SIDEFNLHRH(110)110(111)111EPROTECT THE CUTÜOUT AREA WITH MAT. No 04CMA2 AND MAT. No 04EAC20202CUTÜOUTWET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H332 AND H33301PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1APPLY MAT. No 06ABB1 BETWEEN PARTS01INBOARDOUTBOARDREWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in)04DURING THE INSTALLATION OF THE NEW FRAME FOOT040404DDDDMAX5.552 mm(0.218 in)5.552 mm(0.218 in)5.552 mm(0.218 in)5.552 mm(0.218 in)5.552 mm(0.218 in)5.552 mm(0.218 in)5.552 mm(0.218 in)5.552 mm(0.218 in)HOLESYMBOLITEMPART NUMBERDESCRIPTIONHOLE DIAMETERMIN5.512 mm(0.217 in)(2)NUTASNA2529Ü3(1)SCREWEN6115V3A99335.512 mm(0.217 in)(2)NUTASNA2529Ü3(1)SCREWEN6115V3A109435.512 mm(0.217 in)(2)NUTASNA2529Ü3(1)SCREWEN6115V3A109435.512 mm(0.217 in)(2)NUTASNA2529Ü3(1)SCREWEN6115V3A119445.512 mm(0.217 in)(4)NUTASNA2529Ü3(3)SCREWEN6115V3A69105.512 mm(0.217 in)(4)NUTASNA2529Ü3(3)SCREWEN6115V3A7985.512 mm(0.217 in)5.512 mm(0.217 in)(5)(94)NUTSCREWNUTASNA2529Ü3EN6115V3A6ASNA2529Ü3(93)SCREWEN6115V3A6910910ORNNFNFNND_SB_536177_5_KAAA_03_01Figure A-FKAAA - Sheet 03Replacement of the Frame foot FR46, LH and RH SidesDATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 6145Printed in FRANCE©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF 003



## C C (80) (81)

FWD

9.886 mm (0.389 in) 9.925 mm (0.391 in) NUT SCREW ASNA2529

Ü 6 EN6114V6X17 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX HEAD ON THE VISIBLE SIDE NOTE:

12 52 N

8.692 mm (0.342 in) 8.732 mm (0.344 in) NUT SCREW NAS1726

Ü 5E ASNA2001V5

Ü 12Y 14 50 8.692 mm (0.342 in) 8.732 mm (0.344 in) NUT SCREW ASNA2529

Ü 5 EN6114V5Y8 16 15 4.060 mm (0.160 in) 4.170 mm (0.164 in) RIVET ASNA2050DXJ4020 19 (19) 

## E

USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS 03 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H332 AND H333 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1, APPLY MAT. No 06ABB1 BETWEEN PARTS 01

(4) (3) (4) (3) (4) (3) N 01 LH RH (110) 110 (111) 111

N N N H337 H336 H334 H332 H333

H335
H339

H340

H338 H341 

## B B (58) (57) LH RH FR46
03

01 STGR37

H315

H314

STGR37
(81) (58) (57) LH RH (80)

05 05

FRAME FOOT

TYPICAL SECTION 

## D D

SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 05 27 mm (1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in) FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in) ELECTRICAL BONDING

D_SB_536177_5_KAAA_04_01

Figure A-FKAAA - Sheet 04 Replacement of the Frame foot FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 615 5

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

# @A300-600 SERVICE BULLETIN

**CONF 003

FASTENERS NOT AFFECTED NOTE: FR46 RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN

5.512 mm (0.217 in) 5.552 mm (0.218 in) NUT SCREW ASNA2529

Ü 3 EN6115V3A7 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX HEAD ON THE VISIBLE SIDE

9 8 N

5.512 mm (0.217 in) 5.552 mm (0.218 in) NUT SCREW ASNA2529

Ü 3 EN6115V3A6 9 10 5.512 mm (0.217 in) 5.552 mm (0.218 in) NUT SCREW ASNA2529

Ü 3 EN6115V3A5 9 17 5.512 mm (0.217 in) 5.552 mm (0.218 in) WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H332 AND H333 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS (4) (3) (4) (3) (4) (3) 

## F

NUT SCREW ASNA2529

Ü 3 EN6115V3A4 9 18 (4) (3) 01 H350 STGR38

STGR39 H349 H348 H347 H346 H345 H344 H343 H342 

### G

N N N N FR46

FWD (82) (83)

H354 H353 H351 LH RH

H352

01 

## G INBOARD

OUTBOARD

D_SB_536177_5_KAAA_05_00 Figure A-FKAAA - Sheet 05 Replacement of the Frame foot FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 616 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

FR40 

## A B FR47

FR46



## B Z140 

### A

C D F

C D F FR46

D_SB_536177_5_KAAB_01_00 Figure A-FKAAB - Sheet 01 Replacement of the Frame foot FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 617 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN



## A A F W D 

## C (55)

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H332 AND H333 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS 01

NOTE:



### A A

FR46 INBOARD

OUTBOARD

(76) 76 OR (56) 56

D_SB_536177_5_KAAB_02_01 Figure A-FKAAB - Sheet 02 Replacement of the Frame foot FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 618 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.@A300-600SERVICE BULLETIN**CONF 002BBSTGR37DRH SYMMETRICALVIEW LOOKING AFTLH SHOWNFR46CC(81)H33180H321H308H307H306H320H319H304H305H318H310H309H313H317H302H303H312H311H301H300H316H324H326H329H330H322H323H327H328H325FASTENERS NOT AFFECTEDHEAD ON THE VISIBLE SIDENOTE:HEAD ON THE HIDDEN SIDEFNLHRH(110)110(111)111EPROTECT THE CUTÜOUT AREA WITH MAT. No 04CMA2 AND MAT. No 04EAC20202CUTÜOUTWET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H332 AND H33301PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1APPLY MAT. No 06ABB1 BETWEEN PARTS01INBOARDOUTBOARDREWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in)04DURING THE INSTALLATION OF THE NEW FRAME FOOT040404DDDDMAX5.552 mm(0.218 in)5.552 mm(0.218 in)5.552 mm(0.218 in)5.552 mm(0.218 in)5.552 mm(0.218 in)5.552 mm(0.218 in)HOLESYMBOLITEMPART NUMBERDESCRIPTIONHOLE DIAMETERMIN5.512 mm(0.217 in)(2)NUTASNA2529Ü3(1)SCREWEN6115V3A99335.512 mm(0.217 in)(2)NUTASNA2529Ü3(1)SCREWEN6115V3A109435.512 mm(0.217 in)(2)NUTASNA2529Ü3(1)SCREWEN6115V3A109435.512 mm(0.217 in)(2)NUTASNA2529Ü3(1)SCREWEN6115V3A119445.512 mm(0.217 in)(2)NUTASNA2529Ü3(1)SCREWEN6115V3A69105.512 mm(0.217 in)(2)NUTASNA2529Ü3(1)SCREWEN6115V3A798NNFN5.552 mm(0.218 in)5.512 mm(0.217 in)(2)NUTASNA2529Ü3(1)SCREWEN6115V3A6910NNFD_SB_536177_5_KAAB_03_01Figure A-FKAAB - Sheet 03Replacement of the Frame foot FR46, LH and RH SidesDATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 6195Printed in FRANCE©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF 002

10.282 mm (0.405 in) 10.321 mm (0.406 in) NUT SCREW ASNA2529

Ü 6 EN6114V6Y17 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX HEAD ON THE VISIBLE SIDE NOTE:

12 49 N

8.692 mm (0.342 in) 8.732 mm (0.344 in) NUT SCREW NAS1726

Ü 5E ASNA2001V5

Ü 12Y 14 50 8.692 mm (0.342 in) 8.692 mm (0.342 in) NUT SCREW ASNA2529

Ü 5 EN6114V5Y8 16 15 4.060 mm (0.160 in) 4.170 mm (0.164 in) RIVET ASNA2050DXJ4020 19 (19) (2) (1) (2) (1) (2) (1)
N N N N 

## C C (80) (81)

FWD 

## E 01 01 LH RH (110) 110 (111) 111

H337 H336 H334 H332 H333

H335
H339

H340

H338 H341 

## B B (58) (57) LH RH FR46
03

01 STGR37

H315

H314

STGR37
(81) (58) (57) LH RH (80)

05 05

FRAME FOOT

TYPICAL SECTION 

## D D

USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS 03 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H332 AND H333 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1, APPLY MAT. No 06ABB1 BETWEEN PARTS SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 05 27 mm (1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in) FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in) ELECTRICAL BONDING

D_SB_536177_5_KAAB_04_01 Figure A-FKAAB - Sheet 04 Replacement of the Frame foot FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 620 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

FASTENERS NOT AFFECTED NOTE: FR46 RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN

5.512 mm (0.217 in) 5.552 mm (0.218 in) NUT SCREW ASNA2529

Ü 3 EN6115V3A7 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX HEAD ON THE VISIBLE SIDE

9 8 N

5.512 mm (0.217 in) 5.552 mm (0.218 in) NUT SCREW ASNA2529

Ü 3 EN6115V3A6 9 10 5.512 mm (0.217 in) 5.552 mm (0.218 in) NUT SCREW ASNA2529

Ü 3 EN6115V3A5 9 17 5.512 mm (0.217 in) 5.552 mm (0.218 in) WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H332 AND H333 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS (4) (3) (4) (3) (4) (3) 

## F

NUT SCREW ASNA2529

Ü 3 EN6115V3A4 9 18 (4) (3) 01 H350 STGR38

STGR39 H349 H348 H347 H346 H345 H344 H343 H342 

### G

N N N N FR46

FWD (82) (83)

H354 H353 H351 LH RH

H352

01 

## G OUTBOARD INBOARD

D_SB_536177_5_KAAB_05_00 Figure A-FKAAB - Sheet 05 Replacement of the Frame foot FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 621 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

FR40 

## A B FR47

FR46



## B Z140 

### A

C D F

C D F FR46

D_SB_536177_5_KAAC_01_00 Figure A-FKAAC - Sheet 01 Replacement of the Frame foot FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 622 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN



## A A F W D 

## C (55)

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H332 AND H333 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS 01

NOTE:



### A A

FR46 INBOARD

OUTBOARD

(76) 76 OR (56) 56

D_SB_536177_5_KAAC_02_01 Figure A-FKAAC - Sheet 02 Replacement of the Frame foot FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 623 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001



### B B

STGR37



## D

RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN FR46 H331 H321 H308 H307 H306 H320 H319 H304 H305 H318
H310 H309 H313 H317 H302 H303 H312 H311 H301 H300 H316 H324 H326 H329 H330 H322 H323 H327 H328 H325

FASTENERS NOT AFFECTED NOTE: LH RH (110) 110 (111) 111



### E

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H332 AND H333 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS 01 INBOARD

OUTBOARD

REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) 03 DURING THE INSTALLATION OF THE NEW FRAME FOOT 03

03

03 

### C

C C

C

D_SB_536177_5_KAAC_03_01 Figure A-FKAAC - Sheet 03 Replacement of the Frame foot FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 624 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

5.113 mm (0.201 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in) 5.152 mm (0.203 in) (5)
(94) NUT SCREW

NUT ASNA2529

Ü 3 EN6115V3X6

ASNA2529

Ü 3 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX
(93) SCREW EN6115V3X6 HEAD ON THE VISIBLE SIDE NOTE:

9 25

9 25 5.113 mm (0.201 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in) 5.152 mm (0.203 in) (5)
(94) NUT SCREW

NUT ASNA2529

Ü 3 EN6115V3X5

ASNA2529

Ü 3 (93) SCREW EN6115V3X5 9 23

9 23 5.113 mm (0.201 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in) 5.152 mm (0.203 in) (5)
(94) NUT SCREW

NUT ASNA2529

Ü 3 EN6115V3X7

ASNA2529

Ü 3 (93) SCREW EN6115V3X7 9 24

9 24 5.113 mm (0.201 in) 5.152 mm (0.203 in) (4) NUT ASNA2529

Ü 3 (3) SCREW EN6115V3X6 9 25 5.113 mm (0.201 in) 5.152 mm (0.203 in) (4) NUT ASNA2529

Ü 3 (3) SCREW EN6115V3X7 9 24 5.113 mm (0.201 in) 5.152 mm (0.203 in) (4) NUT ASNA2529

Ü 3 (3) SCREW EN6115V3X6 9 25 OR OR

OR HEAD ON THE HIDDEN SIDE F N

F

N N N N N

D_SB_536177_5_KAAC_04_00 Figure A-FKAAC - Sheet 04 Replacement of the Frame foot FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 625 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

9.886 mm (0.389 in) 9.925 mm (0.391 in) NUT SCREW ASNA2529

Ü 6 EN6114V6X17 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX 12 52 8.296 mm (0.327 in) 8.335 mm (0.328 in) NUT SCREW NAS1726

Ü 5E ASNA2001V5

Ü 12X 14 53 8.296 mm (0.327 in) 8.335 mm (0.328 in) NUT SCREW ASNA2529

Ü 5 EN6114V5X8 16 28 4.060 mm (0.160 in) 4.170 mm (0.164 in) RIVET ASNA2050DXJ4020 19 (19) (4) (3) (4) (3) (4) (3) N N N FWD 

## E 01 LH RH (110) 110 (111) 111

H337 H336 H334 H332 H333

H335
H339

H340

H338 H341 

## B B (58) (57) LH RH

01

N FR46 STGR37

02 H315

H314

04 04 FRAME FOOT

TYPICAL SECTION 

## C C

HEAD ON THE VISIBLE SIDE NOTE:

N

USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS 02 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H332 AND H333 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1, APPLY MAT. No 06ABB1 BETWEEN PARTS SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 04 27 mm (1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in) FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in) ELECTRICAL BONDING

D_SB_536177_5_KAAC_05_01

Figure A-FKAAC - Sheet 05 Replacement of the Frame foot FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 626 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001

FASTENERS NOT AFFECTED NOTE: FR46 RH SYMMETRICAL VIEW LOOKING AFT LH SHOWN

5.113 mm (0.201 in) 5.152 mm (0.203 in) NUT SCREW ASNA2529

Ü 3 EN6115V3X7 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX HEAD ON THE VISIBLE SIDE

9 24 N

5.113 mm (0.201 in) 5.152 mm (0.203 in) NUT SCREW ASNA2529

Ü 3 EN6115V3X6 9 25 5.113 mm (0.201 in) 5.152 mm (0.203 in) NUT SCREW ASNA2529

Ü 3 EN6115V3X5 9 23 5.113 mm (0.201 in) 5.152 mm (0.203 in) WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H332 AND H333 01 PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1 DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT No 06ABB1 BETWEEN PARTS (4) (3) (4) (3) (4) (3) 

## F

NUT SCREW ASNA2529

Ü 3 EN6115V3X4 9 29 (4) (3) 01 H350 STGR38

STGR39 H349 H348 H347 H346 H345 H344 H343 H342 

### G

N N N N FR46

FWD (82) (83)

H354 H353 H351 LH RH

H352

01 

## G OUTBOARD INBOARD

D_SB_536177_5_KAAC_06_00 Figure A-FKAAC - Sheet 06 Replacement of the Frame foot FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 627 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001, 003

FR40 

## A B FR41

FR47

FR41



## B Z140 

### A

C

C

D_SB_536177_5_LAAA_01_00 Figure A-FLAAA - Sheet 01 Removal/Installation of the Gussets at FR41, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 628 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001, 003

FR41

(122) (123) LH RH



### B B

FWD 

## C FR41 LH SHOWN RH SYMMETRICAL



## A A A A

VIEW LOOKING DOWN FRAME FOOT

(120) (121) LH RH

D_SB_536177_5_LAAA_02_01 Figure A-FLAAA - Sheet 02 Removal/Installation of the Gussets at FR41, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 629 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001, 003

21 30 NUT SCREW ASNA2529

Ü 4 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX EN6114V4X8 6.706 mm (0.264 in) 6.747 mm (0.266 in) (3) (4)

12 26 NUT SCREW ASNA2529

Ü 6 EN6114V6X14 9.886 mm (0.389 in) 9.925 mm (0.391 in) (3) (4) F F 21 31 NUT SCREW ASNA2529

Ü 4 EN6114V4X10 6.706 mm (0.264 in) 6.747 mm (0.266 in) (3) (4) F

01 FOR THE POSITIONING OF THE GUSSET, RESPECT THE THEORICAL DISTANCE OF 2 mm (0.079 in) BETWEEN THE GUSSET AND THE FRAME FOOT 02 FOR THE POSITIONING OF THE GUSSET, RESPECT THE THEORICAL DISTANCE OF 1.3 mm (0.051 in) BETWEEN THE GUSSET AND THE FRAME FOOT NOTE: HEAD ON THE HIDDEN SIDE F 

## B B
FWD FR41

H47 H25 H24 H48 02 01

D_SB_536177_5_LAAA_03_01 Figure A-FLAAA - Sheet 03 Removal/Installation of the Gussets at FR41, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 630 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

FR40 

## A B FR41

FR47

FR41



## B Z140 

### A

C

C

D_SB_536177_5_LAAB_01_00 Figure A-FLAAB - Sheet 01 Removal/Installation of the Gussets at FR41, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 631 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

FR41

(122) (123) LH RH



### B B
FWD 

## C FR41 LH SHOWN RH SYMMETRICAL



## A A A A

VIEW LOOKING DOWN FRAME FOOT

(120) (121) LH RH

D_SB_536177_5_LAAB_02_01 Figure A-FLAAB - Sheet 02 Removal/Installation of the Gussets at FR41, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 632 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

21 20 NUT SCREW ASNA2529

Ü 4 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX EN6114V4Y9 7.102 mm (0.280 in) 7.141 mm (0.281 in) (3) (4) 21 22 NUT SCREW ASNA2529

Ü 4 EN6114V4Y10 7.102 mm (0.280 in) 7.141 mm (0.281 in) (3) (4) 12 11 NUT SCREW ASNA2529

Ü 6 EN6114V6Y14 10.282 mm (0.405 in) 10.321 mm (0.406 in) (1) (2) F F F NOTE: HEAD ON THE HIDDEN SIDE F H25 H24



## B B FWD FR41

02 01

01 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 2 mm (0.079 in) BETWEEN THE GUSSET AND THE FRAME FOOT 02 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 1.3 mm (0.051 in) BETWEEN THE GUSSET AND THE FRAME FOOT H47 H48

D_SB_536177_5_LAAB_03_01 Figure A-FLAAB - Sheet 03 Removal/Installation of the Gussets at FR41, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 633 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001, 003

FR40 

## A B FR42

FR47

FR42



## B Z140 

### A

C

C

D_SB_536177_5_NAAA_01_00 Figure A-FNAAA - Sheet 01 Removal/Installation of the Gussets at FR42, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 634 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001, 003

FR42

(124) (125) LH RH (126) (127) LH RH



### B B
FWD 

## A A

VIEW LOOKING DOWN 

## C FR42 LH SHOWN RH SYMMETRICAL 

### A A

FRAME FOOT

D_SB_536177_5_NAAA_02_01 Figure A-FNAAA - Sheet 02 Removal/Installation of the Gussets at FR42, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 635 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001, 003

NOTE:

21 30 NUT SCREW ASNA2529

Ü 4 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX EN6114V4X8 6.706 mm (0.264 in) 6.747 mm (0.265 in) (3) (4) 21 31 NUT SCREW ASNA2529

Ü 4 EN6114V4X10 6.706 mm (0.264 in) 6.747 mm (0.265 in) (3) (4) HEAD ON THE HIDDEN SIDE F

12 35 NUT SCREW ASNA2529

Ü 6 EN6114V6X13 9.886 mm (0.389 in) 9.925 mm (0.391 in) (3) (4) F F F 

## B B FR42

02 01
H118 H92 H91 H119

FWD

01 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 2 mm (0.079 in) BETWEEN THE GUSSET AND THE FRAME FOOT 02 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 1.3 mm (0.051 in) BETWEEN THE GUSSET AND THE FRAME FOOT D_SB_536177_5_NAAA_03_01 Figure A-FNAAA - Sheet 03 Removal/Installation of the Gussets at FR42, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 636 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

FR40 

## A B FR42

FR47

FR42



## B Z140 

### A

C

C

D_SB_536177_5_NAAB_01_00 Figure A-FNAAB - Sheet 01 Removal/Installation of the Gussets at FR42, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 637 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

FR42

(126) (127) LH RH



### B B
FWD 

## C FR42 LH SHOWN RH SYMMETRICAL



## A A A A

VIEW LOOKING DOWN FRAME FOOT

(124) (125) LH RH

D_SB_536177_5_NAAB_02_01 Figure A-FNAAB - Sheet 02 Removal/Installation of the Gussets at FR42, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 638 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

NOTE:

21 20 NUT SCREW ASNA2529

Ü 4 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX EN6114V4Y9 7.141 mm (0.281 in) 7.102 mm (0.279 in) (3) (4) 21 22 NUT SCREW ASNA2529

Ü 4 EN6114V4Y10 7.141 mm (0.281 in) 7.102 mm (0.279 in) (3) (4) HEAD ON THE HIDDEN SIDE

12 34 NUT SCREW ASNA2529

Ü 6 EN6114V6Y13 10.282 mm (0.405 in) 10.321 mm (0.406 in) (1) (2) F F H118 H92 H91 H119



## B B FWD FR42

02 01

01 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 2 mm (0.079 in) BETWEEN THE GUSSET AND THE FRAME FOOT 02 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 1.3 mm (0.051 in) BETWEEN THE GUSSET AND THE FRAME FOOT

F F

D_SB_536177_5_NAAB_03_01 Figure A-FNAAB - Sheet 03 Removal/Installation of the Gussets at FR42, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 639 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001, 003

FR40 

## A B FR47

FR43



## B Z140 

### A

C

C FR43

D_SB_536177_5_PAAA_01_00 Figure A-FPAAA - Sheet 01 Removal/Installation of the Gussets at FR43, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 640 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001, 003

FR43

(128) (129) LH RH (130) (131) LH RH



### B B

FWD 

## C FR43 LH SHOWN RH SYMMETRICAL



## A A A A

FRAME FOOT

D_SB_536177_5_PAAA_02_01 Figure A-FPAAA - Sheet 02 Removal/Installation of the Gussets at FR43, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 641 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001, 003

21 30 NUT SCREW ASNA2529

Ü 4 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX EN6114V4X8 6.706 mm (0.264 in) 6.747 mm (0.265 in) (3) (4) NOTE:

16 41 NUT SCREW ASNA2529

Ü 5 EN6114V5X10 8.296 mm (0.326 in) 8.335 mm (0.328 in) (3) (4) 

## B B
FWD

12 26 NUT SCREW ASNA2529

Ü 6 EN6114V6X14 9.886 mm (0.389 in) 9.925 mm (0.391 in) (3) (4) F HEAD ON THE HIDDEN SIDE F H170 H151 H150 H171 FR43

02 01

F

01 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 2 mm (0.079 in) BETWEEN THE GUSSET AND THE FRAME FOOT 02 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 1.3 mm (0.051 in) BETWEEN THE GUSSET AND THE FRAME FOOT

F

D_SB_536177_5_PAAA_03_01 Figure A-FPAAA - Sheet 03 Removal/Installation of the Gussets at FR43, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 642 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

FR40 

## A B FR47

FR43



## B Z140 

### A

C

C FR43

D_SB_536177_5_PAAB_01_00 Figure A-FPAAB - Sheet 01 Removal/Installation of the Gussets at FR43, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 643 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

FR43

(130) (131) LH RH



### B B
FWD 

## C FR43 LH SHOWN RH SYMMETRICAL



## A A A A

VIEW LOOKING DOWN FRAME FOOT

(128) (129) LH RH

D_SB_536177_5_PAAB_02_01 Figure A-FPAAB - Sheet 02 Removal/Installation of the Gussets at FR43, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 644 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

16 37 NUT SCREW ASNA2529

Ü 5 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX EN6114V5Y10 8.732 mm (0.344 in) 8.692 mm (0.342 in) (3) (4) NOTE:

21 20 NUT SCREW ASNA2529

Ü 4 EN6114V4Y9 7.141 mm (0.281 in) 7.102 mm (0.279 in) (3) (4) 12 11 NUT SCREW ASNA2529

Ü 6 EN6114V6Y14 10.282 mm (0.405 in) 10.321 mm (0.406 in) (1) (2) HEAD ON THE HIDDEN SIDE F

F H170 H171



## B B FWD FR43

02 01

01 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 2 mm (0.079 in) BETWEEN THE GUSSET AND THE FRAME FOOT 02 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 1.3 mm (0.051 in) BETWEEN THE GUSSET AND THE FRAME FOOT H151 H150

F

F

D_SB_536177_5_PAAB_03_01 Figure A-FPAAB - Sheet 03 Removal/Installation of the Gussets at FR43, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 645 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001, 003

Z140 

### A

C C FR44



## B FR44



## A

B FR40 FR47

D_SB_536177_5_QAAA_01_00

Figure A-FQAAA - Sheet 01 Removal/Installation of the Gussets at FR44, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 646 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001, 003

FR44

(132) (133) LH RH (134) (135) LH RH



### B B
FWD 

## C FR44 LH SHOWN RH SYMMETRICAL



## A A VIEW LOOKING DOWN 

### A A

FRAME FOOT

D_SB_536177_5_QAAA_02_01 Figure A-FQAAA - Sheet 02 Removal/Installation of the Gussets at FR44, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 647 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001, 003

NOTE: HEAD ON THE HIDDEN SIDE F HOLE SYMBOL ITEM PN DESCRIPTION HOLE DIAMETER MIN MAX (3) (4) ASNA2529

Ü 5 EN6114V5X10 NUT SCREW 41 16 8.335 mm (0.328 in) 8.296 mm (0.326 in) (3) (4) ASNA2529

Ü 6 EN6114V6X14 NUT SCREW 26 12 (3) (4) ASNA2529

Ü 5 EN6114V5X8 NUT SCREW 28 16 9.925 mm (0.391 in) 9.886 mm (0.389 in) F F F 8.335 mm (0.328 in) 8.296 mm (0.326 in) 

## B B
FWD 02 01 FR44

H223 H224 H204 H203

01 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 2 mm (0.079 in) BETWEEN THE GUSSET AND THE FRAME FOOT 02 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 1.3 mm (0.051 in) BETWEEN THE GUSSET AND THE FRAME FOOT D_SB_536177_5_QAAA_03_01 Figure A-FQAAA - Sheet 03 Removal/Installation of the Gussets at FR44, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 648 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

Z140 

### A

C C FR44



## B FR44



## A

B FR40 FR47

D_SB_536177_5_QAAB_01_00

Figure A-FQAAB - Sheet 01 Removal/Installation of the Gussets at FR44, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 649 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

FR44

(134) (135) LH RH



### B B
FWD 

## C FR44 LH SHOWN RH SYMMETRICAL



## A A A A

VIEW LOOKING DOWN FRAME FOOT

(132) (133) LH RH

D_SB_536177_5_QAAB_02_01 Figure A-FQAAB - Sheet 02 Removal/Installation of the Gussets at FR44, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 650 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

HOLE SYMBOL ITEM PN DESCRIPTION HOLE DIAMETER MIN MAX (3) (4) ASNA2529

Ü 5 EN6114V5Y10 NUT SCREW 37 16 8.692 mm (0.342 in) 8.732 mm (0.344 in) (1) (2) ASNA2529

Ü 6 EN6114V6Y14 NUT SCREW 11 12 10.321 mm (0.406 in) 10.282 mm (0.405 in) NOTE: HEAD ON THE HIDDEN SIDE F H223 H204 H203 H224



## B B FWD FR44

02 01

01 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 2 mm (0.079 in) BETWEEN THE GUSSET AND THE FRAME FOOT 02 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 1.3 mm (0.051 in) BETWEEN THE GUSSET AND THE FRAME FOOT

F F

D_SB_536177_5_QAAB_03_01 Figure A-FQAAB - Sheet 03 Removal/Installation of the Gussets at FR44, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 651 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001, 003



## A Z140 

### A

FR45



## B C

C FR40 

### B FR47

FR45

D_SB_536177_5_TAAA_01_00 Figure A-FTAAA - Sheet 01 Removal/Installation of the Gussets at FR45, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 652 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001, 003



## C FR45 LH SHOWN RH SYMMETRICAL 

### A A

FRAME FOOT



### B B

FWD 

## A A FR45

(136) (137) LH RH (138) (139) LH RH

D_SB_536177_5_TAAA_02_01 Figure A-FTAAA - Sheet 02 Removal/Installation of the Gussets at FR45, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 653 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001, 003

NOTE: HEAD ON THE HIDDEN SIDE

F F

8.296 mm (0.326 in) 8.335 mm (0.328 in) NUT SCREW ASNA2529

Ü 5 EN6114V5X10 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX 16 41 9.886 mm (0.389 in) 9.925 mm (0.391 in) NUT SCREW ASNA2529

Ü 6 EN6114V6X14 12 26 8.296 mm (0.326 in) 8.335 mm (0.328 in) NUT SCREW ASNA2529

Ü 5 EN6114V5X8 16 28 (4) (3) (4) (3) (4) (3) F

F 

## B B
FWD 02 01 FR45

H270 H269 H287 H286

01 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 2 mm (0.079 in) BETWEEN THE GUSSET AND THE FRAME FOOT 02 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 1.3 mm (0.051 in) BETWEEN THE GUSSET AND THE FRAME FOOT D_SB_536177_5_TAAA_03_01 Figure A-FTAAA - Sheet 03 Removal/Installation of the Gussets at FR45, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 654 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002



## A Z140 

### A

FR45



## B C

C FR40 

### B FR47

FR45

D_SB_536177_5_TAAB_01_00 Figure A-FTAAB - Sheet 01 Removal/Installation of the Gussets at FR45, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 655 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

FR45

(138) (139) LH RH



### B B
FWD 

## C FR45 LH SHOWN RH SYMMETRICAL



## A A A A

VIEW LOOKING DOWN FRAME FOOT

(136) (137) LH RH

D_SB_536177_5_TAAB_02_01 Figure A-FTAAB - Sheet 02 Removal/Installation of the Gussets at FR45, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 656 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

NOTE: HEAD ON THE HIDDEN SIDE F

NUT SCREW ASNA2529

Ü 5 EN6114V5Y10 HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX 16 37
NUT SCREW ASNA2529

Ü 6 EN6114V6Y14 12 11 (4) (3) (2) (1) F F 8.732 mm (0.344 in) 8.692 mm (0.342 in) 9.886 mm (0.389 in) 9.925 mm (0.391 in) H286 H270 H269 H287



## B B FWD FR45

02 01

01 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 2 mm (0.079 in) BETWEEN THE GUSSET AND THE FRAME FOOT 02 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 1.3 mm (0.051 in) BETWEEN THE GUSSET AND THE FRAME FOOT D_SB_536177_5_TAAB_03_01 Figure A-FTAAB - Sheet 03 Removal/Installation of the Gussets at FR45, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 657 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001, 003



### C FR40 

## A B FR47

FR46 Z140 

### A FR46



## B C

D_SB_536177_5_UAAA_01_00 Figure A-FUAAA - Sheet 01 Removal/Installation of the Gussets at FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 658 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001, 003



## C FR46 LH SHOWN RH SYMMETRICAL 

### A A

FRAME FOOT



### B B FR46

(140) (141) LH RH (142) (143) LH RH

FWD 

## A A VIEW LOOKING DOWN D_SB_536177_5_UAAA_02_01 Figure A-FUAAA - Sheet 02 Removal/Installation of the Gussets at FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 659 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001, 003

HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX NOTE: HEAD ON THE HIDDEN SIDE

16 54 NUT SCREW ASNA2529

Ü 5 EN6114V5X12 8.296 mm (0.326 in) 8.335 mm (0.328 in) NUT SCREW ASNA2529

Ü 6 EN6114V6X14 9.886 mm (0.382 in) 9.925 mm (0.391 in) (3) (4) 26 12 (3) (4)

NUT SCREW ASNA2529

Ü 6 EN6114V6X17 9.886 mm (0.389 in) 9.925 mm (0.391 in) (3) (4) 52 12 F

F F F 

## B B
FWD 02 01 FR46

H355 H333 H332 H356

01 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 2 mm (0.079 in) BETWEEN THE GUSSET AND THE FRAME FOOT 02 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 1.3 mm (0.051 in) BETWEEN THE GUSSET AND THE FRAME FOOT D_SB_536177_5_UAAA_03_01 Figure A-FUAAA - Sheet 03 Removal/Installation of the Gussets at FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 660 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002



### C FR40 

## A B FR47

FR46 Z140 

### A FR46



## B C

D_SB_536177_5_UAAB_01_00 Figure A-FUAAB - Sheet 01 Removal/Installation of the Gussets at FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 661 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

FR46

(142) (143) LH RH



### B B
FWD 

## C FR46 LH SHOWN RH SYMMETRICAL



## A A A A

VIEW LOOKING DOWN FRAME FOOT

(140) (141) LH RH

D_SB_536177_5_UAAB_02_01 Figure A-FUAAB - Sheet 02 Removal/Installation of the Gussets at FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 662 5

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

# @A300-600 SERVICE BULLETIN

**CONF 002

HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX NOTE: HEAD ON THE HIDDEN SIDE

16 51 NUT SCREW ASNA2529

Ü 5 EN6114V5Y12 8.732 mm (0.344 in) 8.692 mm (0.342 in) 12 11 NUT SCREW ASNA2529

Ü 6 EN6114V6Y14 10.282 mm (0.405 in) 10.321 mm (0.406 in) (3) (3) (4) (4) NUT SCREW ASNA2529

Ü 6 EN6114V6Y17 10.282 mm (0.405 in) 10.321 mm (0.406 in) (1) (2) 49 12 F H335 H333 H332 H356



## B B FWD FR46

02 01

01 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 2 mm (0.079 in) BETWEEN THE GUSSET AND THE FRAME FOOT 02 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 1.3 mm (0.051 in) BETWEEN THE GUSSET AND THE FRAME FOOT

F F F

D_SB_536177_5_UAAB_03_01 Figure A-FUAAB - Sheet 03 Removal/Installation of the Gussets at FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 663 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

FR41 FR42 FR43 FR44 FR45 FR46

FR47

FR40 

## A Z140 

### A

RH SHOWN LH SYMMETRICAL FWD STGR35

STGR39 STGR40 

### C D E F G H

FR41 FR42 FR43 FR44 FR45 FR46 

## B B B

D_SB_536177_5_VAAA_01_01 Figure A-FVAAA - Sheet 01 Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 664 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003



### A

A

RH SHOWN LH SYMMETRICAL STRINGER DATUM

HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX RIVET

ASNA2529

Ü 3 EN6114V3X5 NUT SCREW EN6080D6X

Ü 32 RIVET 5.630 mm (0.221 in) 5.530 mm (0.218 in) 5.152 mm (0.203 in) 5.113 mm (0.201 in) 5.190 mm (0.204 in) 5.130 mm (0.202 in) NOTE: HEAD ON THE HIDDEN SIDE F

PROTECT THE FASTENERS WITH MATERIAL No 06ABA1 01 F OR ASNA2019

Ü 56

Ü 25 (5) (3) (4) (19) 90 91 9 92 01 FR41 TYPICAL SECTION STGR35

STGR36

STGR37

STGR38

STGR39 

## A A FR41 

### A

A

A

A A

A A

A 

## C

F D_SB_536177_5_VAAA_02_00 Figure A-FVAAA - Sheet 02 Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 665 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003



### A

A

RH SHOWN LH SYMMETRICAL STRINGER DATUM

HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX RIVET

ASNA2529

Ü 3 EN6114V3X5 NUT SCREW EN6080D6X

Ü 32 RIVET 5.630 mm (0.221 in) 5.530 mm (0.218 in) 5.152 mm (0.203 in) 5.113 mm (0.201 in) 5.190 mm (0.204 in) 5.130 mm (0.202 in) NOTE: HEAD ON THE HIDDEN SIDE F

PROTECT THE FASTENERS WITH MATERIAL No 06ABA1 01 OR ASNA2019

Ü 56

Ü 25 01 FR42 TYPICAL SECTION STGR36

STGR37

STGR38

STGR39 

## A A A

A A

A A

A FR42



## D

(5) (3) (4) (19) 90 91 9 92 F

F D_SB_536177_5_VAAA_03_00 Figure A-FVAAA - Sheet 03 Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 666 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003



### A

A

RH SHOWN LH SYMMETRICAL STRINGER DATUM

HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX RIVET

ASNA2529

Ü 3 EN6114V3X6 NUT SCREW EN6080D6X

Ü 32 RIVET 5.630 mm (0.221 in) 5.530 mm (0.218 in) 5.152 mm (0.203 in) 5.113 mm (0.201 in) 5.190 mm (0.204 in) 5.130 mm (0.202 in) NOTE: HEAD ON THE HIDDEN SIDE F

PROTECT THE FASTENERS WITH MATERIAL No 06ABA1 01 OR ASNA2019

Ü 56

Ü 25 01 FR43 STGR36

STGR37

STGR38

STGR39 

## A A A

A A

A A

A FR43



## E

(5) (3) (4) (19) 90 47 9 92 TYPICAL SECTION

F

F D_SB_536177_5_VAAA_04_00 Figure A-FVAAA - Sheet 04 Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 667 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003



### A

A

RH SHOWN LH SYMMETRICAL STRINGER DATUM

HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX RIVET

ASNA2529

Ü 3 EN6114V3X5 NUT SCREW EN6080D6X

Ü 32 RIVET 5.630 mm (0.221 in) 5.530 mm (0.218 in) 5.152 mm (0.203 in) 5.113 mm (0.201 in) 5.190 mm (0.204 in) 5.130 mm (0.202 in) NOTE: HEAD ON THE HIDDEN SIDE F

PROTECT THE FASTENERS WITH MATERIAL No 06ABA1 01 OR ASNA2019

Ü 56

Ü 25 01 FR44 TYPICAL SECTION STGR36

STGR37

STGR38

STGR39 

## A A A

A A

A A

A FR44

(5) (3) (4) (19) 90 91 9 92 F

F 

## F

D_SB_536177_5_VAAA_05_00 Figure A-FVAAA - Sheet 05 Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 668 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003



### A

A

RH SHOWN LH SYMMETRICAL STRINGER DATUM

HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX RIVET

ASNA2529

Ü 3 EN6114V3X6 NUT SCREW EN6080D6X

Ü 32 RIVET 5.630 mm (0.221 in) 5.530 mm (0.218 in) 5.152 mm (0.203 in) 5.113 mm (0.201 in) 5.190 mm (0.204 in) 5.130 mm (0.202 in) NOTE: HEAD ON THE HIDDEN SIDE F

PROTECT THE FASTENERS WITH MATERIAL No 06ABA1 01 OR ASNA2019

Ü 56

Ü 25 01 FR45 TYPICAL SECTION STGR36

STGR37

STGR38

STGR39

STGR40 

## A A FR45 

### A

A

A

A A

A A

A 

## G

(5) (3) (4) (19) 90 47 9 92 F

F D_SB_536177_5_VAAA_06_00 Figure A-FVAAA - Sheet 06 Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 669 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003 

### A

A

RH SHOWN LH SYMMETRICAL STRINGER DATUM

HOLE SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX RIVET

ASNA2529

Ü 3 EN6114V3X6 NUT SCREW 5.630 mm (0.221 in) 5.530 mm (0.218 in) 5.152 mm (0.203 in) 5.113 mm (0.201 in) NOTE: HEAD ON THE HIDDEN SIDE F

PROTECT THE FASTENERS WITH MATERIAL No 06ABA1 01 OR ASNA2019

Ü 56

Ü 25 01 FR46 TYPICAL SECTION STGR37

STGR38

STGR39

STGR40 

## A A A

A A

A A

A FR46

RIVET

ASNA2529

Ü 3 EN6114V3X5 NUT SCREW 5.630 mm (0.221 in) 5.530 mm (0.218 in) 5.152 mm (0.203 in) 5.113 mm (0.201 in) OR ASNA2019

Ü 56

Ü 25 (3) (4) 91 9 EN6080D6X

Ü 32 RIVET 5.190 mm (0.204 in) 5.130 mm (0.202 in) (19) 92 (5) (3) (4) (5) 90 47 9 90 F

F

F 

## H

D_SB_536177_5_VAAA_07_00 Figure A-FVAAA - Sheet 07 Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 670 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 SEE FIG. A

Ü FFAAA

NOT INSPECTED AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER SERVICE BULLETIN OR SHEET 04
YES NO A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER R53810329

FRAME FOOT PREVENTIVELY REPAIRED (NO CRACK) AS PER YES NO SERVICE BULLETIN A300

Ü 53

Ü 6111

FRAME FOOT REPAIRED IN AREA 1 AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR R53810329 YES NO SEE FIG. A

Ü FFAAA SHEET 02

SEE FIG. A

Ü FFAAA SHEET 03

SEE FIG. A

Ü FFAAA SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND CONTACT AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR41 ON LH SIDE (IN ACCORDANCE INFORMATION PARAGRAPH E.(2) WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN FRAME FOOT

D_SB_536177_5_FAAA_01_03 Figure A-FFAAA - Sheet 01 Flow Chart for Frame 41 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 671 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR41 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 001

Ü 001) SEE FIG. A

Ü FFAAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
BEFORE NEXT FLIGHT (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001) REPLACE THE CRACKED FRAME FOOT BY NEW ONE

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR41 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFAAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR41 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFAAA SHEET 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT D_SB_536177_5_FAAA_02_02 Figure A-FFAAA - Sheet 02 Flow Chart for Frame 41 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 672 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR41 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 001

Ü 001) SEE FIG. A

Ü FFAAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001) REPLACE THE CRACKED FRAME FOOT BY NEW ONE

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR41 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFAAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR41 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFAAA SHEET 01

D_SB_536177_5_FAAA_03_02 Figure A-FFAAA - Sheet 03 Flow Chart for Frame 41 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 673 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT AT FR41 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 001

Ü 001) SEE FIG. A

Ü FFAAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001) REPLACE THE CRACKED FRAME FOOT BY NEW ONE

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR41 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFAAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR41 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFAAA SHEET 01

D_SB_536177_5_FAAA_04_02 Figure A-FFAAA - Sheet 04 Flow Chart for Frame 41 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 674 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 SEE FIG. A

Ü FFBAA OR SHEET 04
YES NO

FRAME FOOT PREVENTIVELY REPAIRED (NO CRACK) AS PER YES NO SERVICE BULLETIN A300

Ü 53

Ü 6111

FRAME FOOT REPAIRED IN AREA 1 AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR R53810329 YES NO SEE FIG. A

Ü FFBAA SHEET 02

SEE FIG. A

Ü FFBAA SHEET 03

SEE FIG. A

Ü FFBAA SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND CONTACT AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR41 ON RH SIDE (IN ACCORDANCE INFORMATION PARAGRAPH E.(2) WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN NOT INSPECTED AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER R53810329 FRAME FOOT

D_SB_536177_5_FBAA_01_03 Figure A-FFBAA - Sheet 01 Flow Chart for Frame 41 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 675 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR41 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 002

Ü 001) SEE FIG. A

Ü FFBAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
BEFORE NEXT FLIGHT (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001) REPLACE THE CRACKED FRAME FOOT BY NEW ONE

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR41 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFBAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR41 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFBAA SHEET 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT D_SB_536177_5_FBAA_02_02 Figure A-FFBAA - Sheet 02 Flow Chart for Frame 41 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 676 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR41 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 002

Ü 001) SEE FIG. A

Ü FFBAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001) REPLACE THE CRACKED FRAME FOOT BY NEW ONE

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR41 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFBAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR41 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFBAA SHEET 01

D_SB_536177_5_FBAA_03_02 Figure A-FFBAA - Sheet 03 Flow Chart for Frame 41 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 677 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT AT FR41 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 002

Ü 001) SEE FIG. A

Ü FFBAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001) REPLACE THE CRACKED FRAME FOOT BY NEW ONE

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR41 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFBAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR41 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFBAA SHEET 01

D_SB_536177_5_FBAA_04_02 Figure A-FFBAA - Sheet 04 Flow Chart for Frame 41 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 678 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 SEE FIG. A

Ü FFCAA OR SHEET 04

YES NO

FRAME FOOT PREVENTIVELY REPAIRED (NO CRACK) AS PER YES NO SERVICE BULLETIN A300

Ü 53

Ü 6111

FRAME FOOT REPAIRED IN AREA 1 AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR R53810330 YES NO SEE FIG. A

Ü FFCAA SHEET 02

SEE FIG. A

Ü FFCAA SHEET 03

SEE FIG. A

Ü FFCAA SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND CONTACT AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR42 ON LH SIDE (IN ACCORDANCE INFORMATION PARAGRAPH E.(2) WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN NOT INSPECTED AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER R53810330 FRAME FOOT

D_SB_536177_5_FCAA_01_02 Figure A-FFCAA - Sheet 01 Flow Chart for Frame 42 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 679 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR42 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 003

Ü 001) SEE FIG. A

Ü FFCAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
BEFORE NEXT FLIGHT REPLACE THE CRACKED FRAME FOOT BY NEW ONE (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001)
REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR42 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFCAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR42 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFCAA SHEET 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT D_SB_536177_5_FCAA_02_01 Figure A-FFCAA - Sheet 02 Flow Chart for Frame 42 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 680 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR42 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 003

Ü 001) SEE FIG. A

Ü FFCAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT REPLACE THE CRACKED FRAME FOOT BY NEW ONE (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001)
REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR42 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFCAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR42 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFCAA SHEET 01

D_SB_536177_5_FCAA_03_01 Figure A-FFCAA - Sheet 03 Flow Chart for Frame 42 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 681 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT AT FR42 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 003

Ü 001) SEE FIG. A

Ü FFCAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR

AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT REPLACE THE CRACKED FRAME FOOT BY NEW ONE (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001)
REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR42 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFCAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR42 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFCAA SHEET 01

D_SB_536177_5_FCAA_04_01 Figure A-FFCAA - Sheet 04 Flow Chart for Frame 42 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 682 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 SEE FIG. A

Ü FFDAA OR SHEET 04
YES NO

YES NO

YES NO SEE FIG. A

Ü FFDAA SHEET 02

SEE FIG. A

Ü FFDAA SHEET 03

SEE FIG. A

Ü FFDAA SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND CONTACT AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR42 ON RH SIDE (IN ACCORDANCE INFORMATION PARAGRAPH E.(2) WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN FRAME FOOT PREVENTIVELY REPAIRED (NO CRACK) AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111

FRAME FOOT REPAIRED IN AREA 1 AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR R53810330

NOT INSPECTED AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER R53810330 FRAME FOOT

D_SB_536177_5_FDAA_01_02 Figure A-FFDAA - Sheet 01 Flow Chart for Frame 42 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 683 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR42 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 004

Ü 001) SEE FIG. A

Ü FFDAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR

BEFORE NEXT FLIGHT REPLACE THE CRACKED FRAME FOOT BY NEW ONE (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001) REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR42 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFDAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR42 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFDAA SHEET 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT D_SB_536177_5_FDAA_02_01 Figure A-FFDAA - Sheet 02 Flow Chart for Frame 42 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 684 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR42 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 004

Ü 001) SEE FIG. A

Ü FFDAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR

AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT REPLACE THE CRACKED FRAME FOOT BY NEW ONE (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001)
REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR42 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFDAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR42 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFDAA SHEET 01

D_SB_536177_5_FDAA_03_01 Figure A-FFDAA - Sheet 03 Flow Chart for Frame 42 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 685 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT AT FR42 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 004

Ü 001) SEE FIG. A

Ü FFDAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT REPLACE THE CRACKED FRAME FOOT BY NEW ONE (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001)
REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR42 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFDAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR42 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFDAA SHEET 01

D_SB_536177_5_FDAA_04_01 Figure A-FFDAA - Sheet 04 Flow Chart for Frame 42 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 686 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 SEE FIG. A

Ü FFEAA OR SHEET 04
YES NO

FRAME FOOT PREVENTIVELY REPAIRED (NO CRACK) AS PER YES NO SERVICE BULLETIN A300

Ü 53

Ü 6111

FRAME FOOT REPAIRED IN AREA 1 AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR R53810331 YES NO SEE FIG. A

Ü FFEAA SHEET 02

SEE FIG. A

Ü FFEAA SHEET 03

SEE FIG. A

Ü FFEAA SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND CONTACT AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR43 ON LH SIDE (IN ACCORDANCE INFORMATION PARAGRAPH E.(2) WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN NOT INSPECTED AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER R53810331 FRAME FOOT

D_SB_536177_5_FEAA_01_02 Figure A-FFEAA - Sheet 01 Flow Chart for Frame 43 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 687 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR43 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 005

Ü 001) SEE FIG. A

Ü FFEAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR

BEFORE NEXT FLIGHT (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001) REPLACE THE CRACKED FRAME FOOT BY NEW ONE

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR43 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFEAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR43 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFEAA SHEET 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT D_SB_536177_5_FEAA_02_01 Figure A-FFEAA - Sheet 02 Flow Chart for Frame 43 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 688 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR43 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 005

Ü 001) SEE FIG. A

Ü FFEAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR

AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001) REPLACE THE CRACKED FRAME FOOT BY NEW ONE

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR43 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFEAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR43 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFEAA SHEET 01

D_SB_536177_5_FEAA_03_01 Figure A-FFEAA - Sheet 03 Flow Chart for Frame 43 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 689 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT AT FR43 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 005

Ü 001) SEE FIG. A

Ü FFEAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR

AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT REPLACE THE CRACKED FRAME FOOT BY NEW ONE (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001) REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR43 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFEAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR43 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFEAA SHEET 01

D_SB_536177_5_FEAA_04_01 Figure A-FFEAA - Sheet 04 Flow Chart for Frame 43 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 690 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 SEE FIG. A

Ü FFFAA OR SHEET 04
YES NO

FRAME FOOT PREVENTIVELY REPAIRED (NO CRACK) AS PER YES NO SERVICE BULLETIN A300

Ü 53

Ü 6111

FRAME FOOT REPAIRED IN AREA 1 AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR R53810331 YES NO SEE FIG. A

Ü FFFAA SHEET 02

SEE FIG. A

Ü FFFAA SHEET 03

SEE FIG. A

Ü FFFAA SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND CONTACT AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR43 ON RH SIDE (IN ACCORDANCE INFORMATION PARAGRAPH E.(2) WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN NOT INSPECTED AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER R53810331 FRAME FOOT

D_SB_536177_5_FFAA_01_02 Figure A-FFFAA - Sheet 01 Flow Chart for Frame 43 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 691 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR43 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 006

Ü 001) SEE FIG. A

Ü FFFAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR

BEFORE NEXT FLIGHT (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001) REPLACE THE CRACKED FRAME FOOT BY NEW ONE

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR43 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFFAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR43 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFFAA SHEET 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT D_SB_536177_5_FFAA_02_01 Figure A-FFFAA - Sheet 02 Flow Chart for Frame 43 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 692 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR43 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 006

Ü 001) SEE FIG. A

Ü FFFAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR

AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001) REPLACE THE CRACKED FRAME FOOT BY NEW ONE

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR43 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFFAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR43 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFFAA SHEET 01

D_SB_536177_5_FFAA_03_01 Figure A-FFFAA - Sheet 03 Flow Chart for Frame 43 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 693 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT AT FR43 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 006

Ü 001) SEE FIG. A

Ü FFFAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR

AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001) REPLACE THE CRACKED FRAME FOOT BY NEW ONE

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR43 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFFAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR43 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFFAA SHEET 01

D_SB_536177_5_FFAA_04_01 Figure A-FFFAA - Sheet 04 Flow Chart for Frame 43 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 694 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 SEE FIG. A

Ü FFGAA OR SHEET 04
YES NO

FRAME FOOT PREVENTIVELY REPAIRED (NO CRACK) AS PER YES NO SERVICE BULLETIN A300

Ü 53

Ü 6111

FRAME FOOT REPAIRED IN AREA 1 AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR R53810332 YES NO SEE FIG. A

Ü FFGAA SHEET 02

SEE FIG. A

Ü FFGAA SHEET 03

SEE FIG. A

Ü FFGAA SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND CONTACT AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR44 ON LH SIDE (IN ACCORDANCE INFORMATION PARAGRAPH E.(2) WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN NOT INSPECTED AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER R53810332 FRAME FOOT

D_SB_536177_5_FGAA_01_02 Figure A-FFGAA - Sheet 01 Flow Chart for Frame 44 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 695 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR44 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 007

Ü 001) SEE FIG. A

Ü FFGAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
BEFORE NEXT FLIGHT REPLACE THE CRACKED FRAME FOOT BY NEW ONE (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001)
REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR44 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFGAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR44 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFGAA SHEET 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT D_SB_536177_5_FGAA_02_01 Figure A-FFGAA - Sheet 02 Flow Chart for Frame 44 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 696 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR44 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 007

Ü 001) SEE FIG. A

Ü FFGAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT REPLACE THE CRACKED FRAME FOOT BY NEW ONE (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001)
REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR44 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFGAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR44 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFGAA SHEET 01

D_SB_536177_5_FGAA_03_01 Figure A-FFGAA - Sheet 03 Flow Chart for Frame 44 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 697 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT AT FR44 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 007

Ü 001) SEE FIG. A

Ü FFGAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT REPLACE THE CRACKED FRAME FOOT BY NEW ONE (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001)
REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR44 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFGAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR44 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFGAA SHEET 01

D_SB_536177_5_FGAA_04_01 Figure A-FFGAA - Sheet 04 Flow Chart for Frame 44 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 698 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 SEE FIG. A

Ü FFHAA OR SHEET 04
YES NO

FRAME FOOT PREVENTIVELY REPAIRED (NO CRACK) AS PER YES NO SERVICE BULLETIN A300

Ü 53

Ü 6111

FRAME FOOT REPAIRED IN AREA 1 AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR R53810332 YES NO SEE FIG. A

Ü FFHAA SHEET 02

SEE FIG. A

Ü FFHAA SHEET 03

SEE FIG. A

Ü FFHAA SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND CONTACT AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR44 ON RH SIDE (IN ACCORDANCE INFORMATION PARAGRAPH E.(2) WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN NOT INSPECTED AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER R53810332 FRAME FOOT

D_SB_536177_5_FHAA_01_02 Figure A-FFHAA - Sheet 01 Flow Chart for Frame 44 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 699 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR44 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 008

Ü 001) SEE FIG. A

Ü FFHAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
BEFORE NEXT FLIGHT REPLACE THE CRACKED FRAME FOOT BY NEW ONE (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001)
REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR44 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFHAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR44 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFHAA SHEET 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT D_SB_536177_5_FHAA_02_01 Figure A-FFHAA - Sheet 02 Flow Chart for Frame 44 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 700 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR44 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 008

Ü 001) SEE FIG. A

Ü FFHAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT REPLACE THE CRACKED FRAME FOOT BY NEW ONE (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001)
REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR44 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFHAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR44 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFHAA SHEET 01

D_SB_536177_5_FHAA_03_01 Figure A-FFHAA - Sheet 03 Flow Chart for Frame 44 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 701 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT AT FR44 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 008

Ü 001) SEE FIG. A

Ü FFHAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT REPLACE THE CRACKED FRAME FOOT BY NEW ONE (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001)
REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR44 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFHAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR44 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFHAA SHEET 01

D_SB_536177_5_FHAA_04_01 Figure A-FFHAA - Sheet 04 Flow Chart for Frame 44 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 702 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 SEE FIG. A

Ü FFIAA

YES NO

FRAME FOOT PREVENTIVELY REPAIRED (NO CRACK) AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 YES NO

FRAME FOOT REPAIRED IN AREA 1 AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR R53810322 YES NO SEE FIG. A

Ü FFIAA SHEET 02

SEE FIG. A

Ü FFIAA SHEET 03

SEE FIG. A

Ü FFIAA SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND CONTACT AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR45 ON LH SIDE (IN ACCORDANCE INFORMATION PARAGRAPH E.(2) WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN OR SHEET 04 NOT INSPECTED AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER R53810322 FRAME FOOT

D_SB_536177_5_FIAA_01_02 Figure A-FFIAA - Sheet 01 Flow Chart for Frame 45 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 703 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR45 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 009

Ü 001) SEE FIG. A

Ü FFIAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
BEFORE NEXT FLIGHT (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001) REPLACE THE CRACKED FRAME FOOT BY NEW ONE

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR45 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFIAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR45 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFIAA SHEET 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT D_SB_536177_5_FIAA_02_01 Figure A-FFIAA - Sheet 02 Flow Chart for Frame 45 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 704 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR45 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 009

Ü 001) SEE FIG. A

Ü FFIAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001) REPLACE THE CRACKED FRAME FOOT BY NEW ONE

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR45 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFIAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR45 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFIAA SHEET 01

D_SB_536177_5_FIAA_03_01 Figure A-FFIAA - Sheet 03 Flow Chart for Frame 45 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 705 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT AT FR45 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 009

Ü 001) SEE FIG. A

Ü FFIAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001) REPLACE THE CRACKED FRAME FOOT BY NEW ONE

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR45 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFIAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR45 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFIAA SHEET 01

D_SB_536177_5_FIAA_04_01 Figure A-FFIAA - Sheet 04 Flow Chart for Frame 45 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 706 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 SEE FIG. A

Ü FFJAA

YES NO

FRAME FOOT PREVENTIVELY REPAIRED (NO CRACK) AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 YES NO

FRAME FOOT REPAIRED IN AREA 1 AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR R53810322 YES NO SEE FIG. A

Ü FFJAA SHEET 02

SEE FIG. A

Ü FFJAA SHEET 03

SEE FIG. A

Ü FFJAA SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND CONTACT AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR45 ON RH SIDE (IN ACCORDANCE INFORMATION PARAGRAPH E.(2) WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN OR SHEET 04 NOT INSPECTED AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER R53810322 FRAME FOOT

D_SB_536177_5_FJAA_01_02 Figure A-FFJAA - Sheet 01 Flow Chart for Frame 45 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 707 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR45 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 010

Ü 001) SEE FIG. A

Ü FFJAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
BEFORE NEXT FLIGHT (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001) REPLACE THE CRACKED FRAME FOOT BY NEW ONE

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR45 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFJAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR45 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFJAA SHEET 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT D_SB_536177_5_FJAA_02_01 Figure A-FFJAA - Sheet 02 Flow Chart for Frame 45 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 708 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR47 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 010

Ü 001) SEE FIG. A

Ü FFJAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001) REPLACE THE CRACKED FRAME FOOT BY NEW ONE

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR45 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFJAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR45 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFJAA SHEET 01

D_SB_536177_5_FJAA_03_01 Figure A-FFJAA - Sheet 03 Flow Chart for Frame 45 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 709 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT AT FR45 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 010

Ü 001) SEE FIG. A

Ü FFJAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001) REPLACE THE CRACKED FRAME FOOT BY NEW ONE

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR45 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFJAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR45 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFJAA SHEET 01

D_SB_536177_5_FJAA_04_01 Figure A-FFJAA - Sheet 04 Flow Chart for Frame 45 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 710 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 SEE FIG. A

Ü FFKAA OR SHEET 04
YES NO

FRAME FOOT PREVENTIVELY REPAIRED (NO CRACK) AS PER YES NO SERVICE BULLETIN A300

Ü 53

Ü 6111

FRAME FOOT REPAIRED IN AREA 1 AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR R53810323 YES NO SEE FIG. A

Ü FFKAA SHEET 02

SEE FIG. A

Ü FFKAA SHEET 03

SEE FIG. A

Ü FFKAA SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND CONTACT AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR46 ON LH SIDE (IN ACCORDANCE INFORMATION PARAGRAPH E.(2) WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN NOT INSPECTED AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER R53810323 FRAME FOOT

D_SB_536177_5_FKAA_01_02 Figure A-FFKAA - Sheet 01 Flow Chart for Frame 46 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 711 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR46 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 011

Ü 001) SEE FIG. A

Ü FFKAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
BEFORE NEXT FLIGHT REPLACE THE CRACKED FRAME FOOT BY NEW ONE (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001)
REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR46 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFKAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR46 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFKAA SHEET 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT D_SB_536177_5_FKAA_02_01 Figure A-FFKAA - Sheet 02 Flow Chart for Frame 46 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 712 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR46 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 011

Ü 001) SEE FIG. A

Ü FFKAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT REPLACE THE CRACKED FRAME FOOT BY NEW ONE (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001)
REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR46 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFKAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR46 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFKAA SHEET 01

D_SB_536177_5_FKAA_03_01 Figure A-FFKAA - Sheet 03 Flow Chart for Frame 46 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 713 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT AT FR46 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 011

Ü 001) SEE FIG. A

Ü FFKAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT REPLACE THE CRACKED FRAME FOOT BY NEW ONE (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001)
REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR46 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFKAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR46 ON LH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFKAA SHEET 01

D_SB_536177_5_FKAA_04_01 Figure A-FFKAA - Sheet 04 Flow Chart for Frame 46 on LH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 714 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 SEE FIG. A

Ü FFLAA OR SHEET 04
YES NO

FRAME FOOT PREVENTIVELY REPAIRED (NO CRACK) AS PER YES NO SERVICE BULLETIN A300

Ü 53

Ü 6111

FRAME FOOT REPAIRED IN AREA 1 AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR R53810323 YES NO SEE FIG. A

Ü FFLAA SHEET 02

SEE FIG. A

Ü FFLAA SHEET 03

SEE FIG. A

Ü FFLAA SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND CONTACT AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR46 ON RH SIDE (IN ACCORDANCE INFORMATION PARAGRAPH E.(2) WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN NOT INSPECTED AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER SERVICE BULLETIN A300

Ü 53

Ü 6111 OR NOT REPAIRED AS PER R53810323 FRAME FOOT

D_SB_536177_5_FLAA_01_02 Figure A-FFLAA - Sheet 01 Flow Chart for Frame 46 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 715 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR46 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 012

Ü 001) SEE FIG. A

Ü FFLAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
BEFORE NEXT FLIGHT REPLACE THE CRACKED FRAME FOOT BY NEW ONE (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001)
REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR46 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFLAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR46 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFLAA SHEET 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT D_SB_536177_5_FLAA_02_01 Figure A-FFLAA - Sheet 02 Flow Chart for Frame 46 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 716 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 1 OR AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT AT FR46 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 012

Ü 001) SEE FIG. A

Ü FFLAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT REPLACE THE CRACKED FRAME FOOT BY NEW ONE (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001)
REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR46 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFLAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR46 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFLAA SHEET 01

D_SB_536177_5_FLAA_03_01 Figure A-FFLAA - Sheet 03 Flow Chart for Frame 46 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 717 5

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

# @A300-600 SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN AREA 2 YES NO DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT AT FR46 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177

Ü 832

Ü 012

Ü 001) SEE FIG. A

Ü FFLAA SHEET 01

CRACK HIGHER THAN 30 mm (1.181 in) NO YES
AFFECTED FRAME FOOT FOR LABORATORY INVESTIGATIONS AND INFORM AIRBUS, SEND THE PERFORM THE FOLLOWING STEPS OR
AND DO THE CUTTING

Ü OUT BEFORE NEXT FLIGHT REPLACE THE CRACKED FRAME FOOT BY NEW ONE (IN ACCORDANCE WITH TASK 536177

Ü 833

Ü 801

Ü 001)
REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE REPLACED FRAME FOOT AT FR46 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02

THE ACCOMPLISHMENT OF THE SB 53

Ü 6176 REPLACES 01 ALL FRAME FEET BETWEEN FR41 AND FR46 SEE FIG. A

Ü FFLAA SHEET 01 OR APPLY SERVICE BULLETIN

A300

Ü 53

Ü 6176 BEFORE NEXT FLIGHT 01 REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE NO FURTHER ACTION

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN
REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME 02 FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT REPORT TO AIRBUS WITHIN 1 MONTH FROM INSPECTION DATE REPEAT THE INSPECTION OF THE FRAME FOOT AT FR46 ON RH SIDE (IN ACCORDANCE WITH TASK 536177

Ü 832

Ü 801

Ü 001) AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) 02 SEE FIG. A

Ü FFLAA SHEET 01

D_SB_536177_5_FLAA_04_01 Figure A-FFLAA - Sheet 04 Flow Chart for Frame 46 on RH side DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 718 5

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# @A300-600 SERVICE BULLETIN

**CONF ALL



### C INSPECTION REPORT SERVICE BULLETIN No : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A300

Ü 53

Ü 6177

DATE OF INSPECTION : INSPECTION METHOD : DETAILED INSPECTION

C L FR41

FR42

FR43

FR44

FR45

FR46



## A FR40 FR47



### C 

## B AREA 1 AREA 2

LH SHOWN RH SYMMETRICAL 

## C RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING

Ü SEES1 DOORS

Ü FUSELAGE

Ü CWB

Ü WINDOWS 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE E

Ü MAIL: structure.sbinspectionresult@airbus.com FAX: +33 (0)5 61 93 36 14

NOTE: AREA TO BE INSPECTED 

### A B B

D_SB_536177_5_RAAA_01_01 Figure A-FRAAA - Sheet 01 Inspection report DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 719 5

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# @A300-600 SERVICE BULLETIN

**CONF ALL INSPECTION REPORT SERVICE BULLETIN No : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A300

Ü 53

Ü 6177

DATE OF INSPECTION : INSPECTION METHOD : DETAILED INSPECTION

FRAME CRACK NOT CHECKED NO YES LENGTH AREA 1

NO YES

CRACK LENGTH AREA 2 REPLACED FRAME FOOT

NO YES 41 LH 42 LH 43 LH 44 LH 45 LH 46 LH 41 RH 42 RH 43 RH 44 RH 45 RH 46 RH
SB 53

Ü 6176 APPLIED: YES NO

PLEASE PRECISE OTHER FINDINGS: RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING

Ü SEES1 DOORS

Ü FUSELAGE

Ü CWB

Ü WINDOWS 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE E

Ü MAIL: structure.sbinspectionresult@airbus.com FAX: +33 (0)5 61 93 36 14

D_SB_536177_5_RAAA_02_01 Figure A-FRAAA - Sheet 02 Inspection report DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 720 5

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# @A300-600 SERVICE BULLETIN Appendix 01 - Elapsed Time Assumptions **CONF 001 thru 003 For an explanation of the manhours and elapsed time, refer to the following Gantt Chart. **CONF 004 None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 1 5

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# @A300-600 SERVICE BULLETIN Appendix 01 - Elapsed Time Assumptions

**CONF 001 thru 003

ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A300 **Ü** 53 **Ü** 6177

GET ACCESS MH ET/S

TOTAL MANHOURS SB ELAPSED TIME 8.00 2.50 STEPS
1.00 1.00

2.5 0 CLOSE

Ü UP

MH ET/S: PER MANHOURS ELAPSED TIME PER STEP NUMBER OF PERSONS 01 02

THIS CHART IS ONLY A PROPOSAL. OPERATORS MAY DETERMINE THAT ANOTHER WAY TO DO THE WORK IS MORE SUITABLE FOR THEM. 01
02 NOTE: PER
1

: : SB ELAPSED TIME (HOURS) 0.5 1 1.5 2

IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS ARE NOT REFLECTED IN THIS GANTT CHART. DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR41 ON LH SIDE DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR41 ON RH SIDE DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR42 ON LH SIDE DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR42 ON RH SIDE DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR43 ON LH SIDE DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR43 ON RH SIDE DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR44 ON LH SIDE DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR44 ON RH SIDE DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR45 ON LH SIDE DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR45 ON RH SIDE DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR46 ON LH SIDE DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR46 ON RH SIDE 0.50 0.50 1 0.50 0.50 1 0.50 0.50 1 0.50 0.50 1 0.50 0.50 1 0.50 0.50 1 0.50 0.50 1 0.50 0.50 1 0.50 0.50 1 0.50 0.50 1 0.50 0.50 1 0.50 0.50 1 1.00 1.00 1

D_SB_536177_5_AAAA_01_00 Figure A-FAAAA - Sheet 01 Gantt Chart DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 2 5

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# @A300-600 SERVICE BULLETIN REPORTING SHEET 

### TITLE: FUSELAGE - CENTER FUSELAGE - INSPECT LOWER FRAME BASE FITTING BETWEEN FRAMES 41 AND 46 MODIFICATION No.: None Please complete the appropriate item (A or B): A - SB WILL BE embodied YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiment:

B - SB HAS BEEN embodied on aircraft: Operator comments:
From Airline: Name/Title: Signature: Date: If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service(s): Either: Modification Operational Impact (MOI), if available YES/NO Or : Intermediate revision YES/NO Important Information: This SB will only be incorporated in your maintenance and operational documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With the next feasible revision, this will result in - Updating of maintenance documentation to show pre and post SB data. - Updating of maintenance and operational documentation to show post SB data after embodiment. If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically include them in the manual revisions. Refer to SIL 00-037 for detailed information. Please return this completed sheet to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn: SDC32 Technical Data and Documentation Services FAX: (+33) 5 61 93 28 06 e-mail: sb.reporting@airbus.com or via your Resident Customer Support Office. Alternatively, SB lists via letters or fax are also accepted.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 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: May 20/15 SERVICE BULLETIN No.: A300-53-6177 REVISION No.: 00 - May 20/15 Page: 1 5

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