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

# MANDATORYMANDATORYMANDATORY ATA SYSTEM: 53 

### TITLE: FUSELAGE - STRUCTURE - INSPECT FOR CROSSBEAM AT JUNCTION WITH LOWER DECK CARGO DOOR ACTUATOR BEAM **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES Some operators have reported cracks in a crossbeam at the junction with the cargo-door actuator support-beam. The damage was located at the outboard row of rivets on the crossbeam at FR23. The laboratory analysis revealed that the cracks are initiated in the fastener hole propagating vertically. The design of FWD and AFT cargo door attachments are similar to the crossbeams at FR22/23 and FR61/FR62 or FR62/63 should be inspected. On passenger aircraft, in case of cracks being present in a crossbeam (upper and lower web), the floor grid cannot withstand ultimate load condition. On freighter aircraft this is not the case due to different load distribution via the pallets. This Service Bulletin details the inspection procedure for aircraft on which the crossbeams are not previously repaired by the Structure Repair Manual (SRM) or a Repair Approval Sheet (RAS). This inspection procedure details : - High Frequency Eddy Current (HFEC) inspection procedure to inspect the crossbeams at FR22/23 and FR61/62, - High Frequency Eddy Current (HFEC) and a Ultrasonic (US) inspection procedure to inspect the crossbeam at FR22/23 and a High Frequency Eddy Current (HFEC) inspection procedure to inspect the crossbeam at FR61/62. - High Frequency Eddy Current (HFEC) inspection procedure to inspect the crossbeams at FR22/23 and FR62/63, before the accumulation of 10000 total aircraft flight cycles (FC) or 4000FC for freighter aircraft MSN 0805 and subsequent. DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 1 6

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# @A300-600 SERVICE BULLETIN SUMMARY NOTE: For aircraft on which the crossbeams have been previously repaired by the Structure Repair Manual (SRM) or a Repair Approval Sheet (RAS) the operator has to contact AIRBUS before reaching the threshold or the grace period for further instructions. In the case no crack(s) are found : - repeat this inspection at interval not to exceed 600FC (for FR22/23 or FR61/62 area) or 300FC (for FR62/63 area on freighter aircraft MSN 0805 and subsequent)
or - accomplish Modification Service Bulletin No. A300-53-6166 within 600FC (for FR22/23 or FR61/62 area) or within 300FC (for FR62/63 area on freighter aircraft MSN 0805 and subsequent) after the last inspection in accordance with this Inspection Service Bulletin. . The accomplishment of Modification Service Bulletin No. A300-53-6166 cancels the requirements of this Inspection Service Bulletin. In the case crack(s) are found : - longer than 7.0mm 0.27in.) contact AIRBUS before the next flight and follow their instructions. - smaller than or equal to 7.0mm 0.27in.) contact AIRBUS before the next flight and follow their instructions within : . 10FC, if crack(s) were detected by Ultra Sonic inspection procedure, . 50FC, if crack(s) were detected by a High Frequency Eddy Current inspection procedure. The accomplishment of this Service Bulletin : - monitors the structure surrounding the rivet heads between crossbeams at FR22/23 and FR61/62 on passenger aircraft - monitors the structure surrounding the rivet heads between crossbeams at FR22/23 and FR62/63 on freighter aircraft - can prevent heavy repair. The accomplishment of Modification Service Bulletin Nos. A300-53-6166 cancels the requirements of this Inspection Service Bulletin. NOTE: This Service Bulletin is mandatory for all passenger aircraft. It is only recommended for freighter aircraft. NOTE: If operators have previously accomplished the Modification Service Bulletin No. A300-53-6166, the accomplishment of this Inspection Service Bulletin is no longer required. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY CANCELS INSPECTION SB NO
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 2 6

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# @A300-600 SERVICE BULLETIN SUMMARY EVALUATION TABLE 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 MATERIAL PRICE INFORMATION **CONF 001 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Standard tool TOOLD01 2 See SB Support Struts - FWD and AFT Cargo Compartment Doors **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Standard tool TOOLD01 2 See SB Support Struts - FWD and AFT Cargo Compartment Doors **CONF 003 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Standard tool TOOLD01 2 See SB Support Struts - FWD and AFT Cargo Compartment Doors EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

66U AAL AAW ABD AHK AMU CES CSN DLH F2I FDX G8E IRA IRM JAL KAC KAL LAA MNB MON MSR MXU OHY QTR SUD TAR THA UPS UZB CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU None OEB None AOT None DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 3 6

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# @A300-600 SERVICE BULLETIN SUMMARY SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER **CONF 001 Task 536168-832-848-001: Inspection TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 4.00 **CONF 002 Task 536168-832-848-001: Inspection TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 4.00 **CONF 003 Task 536168-832-848-001: Inspection TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 4.00 APPENDICES **CONF ALL None

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 4 6

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# @A300-600 SERVICE BULLETIN SUMMARY
**CONF 001

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 FR21 FR22 FR23 FR24

SEAT TRACK 6

HFEC INSPECTION AREA

**FWD** 

## A **A** Z130

D_SB_536168_6_SAAA_01_00 Figure A-GSAAA - Sheet 01

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 5 6

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# @A300-600 SERVICE BULLETIN SUMMARY
**CONF 001

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 SEAT TRACK 6 FR60 FR61 FR62 FR63

HFEC INSPECTION AREA

**FWD** 

## A Z150


### A

D_SB_536168_6_SAAA_02_00 Figure A-GSAAA - Sheet 02

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 6 6

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# @A300-600 SERVICE BULLETIN SUMMARY
**CONF 002

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 FR21 FR22 FR23 FR24

SEAT TRACK 6

HFEC INSPECTION

**FWD** 

## A AREA US INSPECTION AREA

D_SB_536168_6_SBAA_01_00 

### A Z130

HFEC INSPECTION AREA

Figure A-GSBAA - Sheet 01

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 7 6

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# @A300-600 SERVICE BULLETIN SUMMARY
**CONF 002

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 SEAT TRACK 6

HFEC INSPECTION AREA

**FWD** 

## A FR60 FR61 FR62 FR63



### A Z150

D_SB_536168_6_SBAA_02_00 Figure A-GSBAA - Sheet 02

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 8 6

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# @A300-600 SERVICE BULLETIN SUMMARY
**CONF 003

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 FR21 FR22 FR23 FR24

SEAT TRACK 6

HFEC INSPECTION AREA

**FWD** 

## A **A** Z130

D_SB_536168_6_SCAA_01_00 Figure A-GSCAA - Sheet 01

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 9 6

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# @A300-600 SERVICE BULLETIN SUMMARY
**CONF 003

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 SEAT TRACK 6

HFEC INSPECTION AREA

**FWD** 

## A Z150


### A

D_SB_536168_6_SCAA_02_00 FR62 FR61 FR63 FR64

Figure A-GSCAA - Sheet 02

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 10 6

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# @A300-600 SERVICE BULLETIN
AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51



# MANDATORYMANDATORYMANDATORY ATA SYSTEM: 53 

### TITLE: FUSELAGE - STRUCTURE - INSPECT FOR CROSSBEAM AT JUNCTION WITH LOWER DECK CARGO DOOR ACTUATOR BEAM 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 B4-601 B4-603 B4-605R B4-620 B4-622 B4-622R C4-605R/FC4-620 F4-605R F4-622R (2) Effectivity by MSN 0284 0294 0301 0307 0312 0317 0321 0336 0344 0348 0351 0354 0358 0361 0365 0368 0380 0388 0398 0401 0405 0408 0411 0414 0417 0423 0459-0466 0469-0470 0474 0477 0479 0505-0518 0521 0525 0529-0530 0532 0536 0540 0543 0546 0553-0561 0563 0566 0569 0572 0575 0577 0579 0581-0582 0584 0601-0619 0621 0623 0625-0633 0635 0637 0639 0641 0643 0645 0657 0659 0662 0664 0666 0668 0670 0673 0675 0677 0679 0681 0683 0685 0688 0692 0694 0696 0699 0701 0703 0705 0707 0709 0711 0713 0715 0717 0719 0721-0750 0752-0764 0766-0775 0777-0794 0797 0799-0841 0845-0878

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 1 6

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# @A300-600 SERVICE BULLETIN (3) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason. OPERATOR MSN 66U 0733 0734 0739 0750 0762 AAL 0423 0459 0460 0461 0463 0466 0469 0470 0474 0506 0507 0508 0509 0510 0511 0512 0513 0514 0515 0516 0517 0606 0610 0612 0615 0619 0626 0639 0643 0645 0675 AAW 0354 ABD 0529 0557 0755 AHK 0855 0856 0857 0858 0859 0860 0870 0871 AMU 0677 0743 CES 0521 0525 0532 0707 0725 0732 0741 0746 0754 0763 CSN 0756 DLH 0380 0401 0405 0618 0623 0701 0773 F2I 0284 0294 0301 0307 0312 0317 0321 0336 0348 0351 0408 FDX 0358 0361 0365 0388 0417 0477 0479 0530 0536 0543 0555 0559 0572 0575 0579 0581 0611 0613 0625 0630 0633 0657 0659 0664 0668 0688 0709 0713 0715 0726 0728 0735 0736 0738 0742 0745 0748 0752 0757 0759 0760 0761 0766 0768 0769 0771 0772 0774 0777 0778 0779 0780 0781 0789 0790 0791 0792 0793 0794 0799 0800 0801 0802 0803 0804 0873 0874 0875 0876 0877 0878 G8E 0462 0465 IRA 0632 0696 0723 0727 IRM 0411 0414 0546 0553 0608 JAL 0602 0617 0621 0637 0641 0670 0679 0683 0703 0711 0724 0729 0730 0737 0740 0753 0770 0783 0797 0836 0837 0838 KAC 0344 0673 0694 0699 0719 0721 KAL 0582 0609 0627 0631 0662 0685 0692 0731 LAA 0601 0616 MNB 0758 MON 0540 0556 0604 0605 MSR 0561 0607 MXU 0767 0788 0872 OHY 0584 0603 0744 0747 0749 0764 QTR 0554 0560 0614 SUD 0666 0775 TAR 0505 0558 0563 THA 0368 0398 0464 0518 0566 0569 0577 0628 0629 0635 0681 0705 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 0841 0845 0846 0847 0848 0849 0850 0851 0852 0853 0854 0861 0862 0863 0864 0865 0866 0867 0868 0869 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 2 6

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# @A300-600 SERVICE BULLETIN
OPERATOR MSN UZB 0717 0722 (4) Configuration by MSN MSN CONFIGURATION 0284 0294 0301 0307 0312 0317 0321 0336 0348 0351 0354 0358 0361 0365 0368 0380 0388 0398 0401 0405 0408 0411 0414 0417 0423 0459 0460 0461 0462 0463 0464 0465 0466 0469 0470 0474 0477 0479 0505 0506 0507 0508 0509 0510 0511 0512 0513 0514 0515 0516 0517 0518 0521 0525 0529 0530 0532 0536 0540 0543 0546 0553 0554 0555 0556 0557 0558 0559 0560 0561 0563 0566 0569 0572 0575 0577 0579 0581 0582 0584 0601 0602 0603 0604 0605 0606 0607 0608 0609 0610 0611 0612 0613 0614 0615 0616 0617 0618 0619 0621 0623 0625 0626 0627 0628 0629 0630 0631 0632 0633 0635 0637 0639 0641 0643 0645 0657 0659 0662 0664 0666 0668 0670 0673 0675 0677 0679 0681 0683 0685 0688 0692 0694 0696 0699 0701 0703 0705 0707 0709 0711 0713 0715 0717 0719 0721 0722 0723 0724 0725 0727 0729 0730 0731 0732 0733 0734 0737 0739 0740 0741 0743 0744 0746 0747 0749 0750 0753 0754 0756 0762 0763 0764 0767 0770 0773 0775 0782 0783 0784 0785 0786 0787 0788 0797 0836 0837 0838 001

0344 0726 0728 0735 0736 0738 0742 0745 0748 0752 0755 0757 0758 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 002

0805 0806 0807 0808 0809 0810 0811 0812 0813 0814 0815 0816 0817 0818 0819 0820 0821 0822 0823 0824 0825 0826 0827 0828 0829 0830 0831 0832 0833 0834 0835 0839 0840 0841 0845 0846 0847 0848 0849 0850 0851 0852 0853 0854 0855 0856 0857 0858 0859 0860 0861 0862 0863 0864 0865 0866 0867 0868 0869 0870 0871 0872 0873 0874 0875 0876 0877 0878 003

(5) Configuration definition **CONF 001 Config. 001 is valid for all passenger aircraft. **CONF 002 Config. 002 is valid for all the freighter aircraft up to MSN 0804. **CONF 003 Config. 003 is valid for all the freighter aircraft from MSN 0805 and subsequent. (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Standard tool TOOLD01 2

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 3 6

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# @A300-600 SERVICE BULLETIN
B. CONCURRENT REQUIREMENTS None C. REASON (1) History Some operators have reported cracks in a crossbeam at the junction with the cargo-door actuator support-beam. The damage was located at the outboard row of rivets on the crossbeam at FR23. The laboratory analysis revealed that the cracks are initiated in the fastener hole propagating vertically. The design of FWD and AFT cargo door attachments are similar to the crossbeams at FR22/23 and FR61/FR62 or FR62/63 should be inspected. (2) Objective/Action On passenger aircraft, in case of cracks being present in a crossbeam (upper and lower web), the floor grid cannot withstand ultimate load condition. On freighter aircraft this is not the case due to different load distribution via the pallets. This Service Bulletin details the inspection procedure for aircraft on which the crossbeams are not previously repaired by the Structure Repair Manual (SRM) or a Repair Approval Sheet (RAS). This inspection procedure details : - High Frequency Eddy Current (HFEC) inspection procedure to inspect the crossbeams at FR22/23 and FR61/62, - High Frequency Eddy Current (HFEC) and a Ultrasonic (US) inspection procedure to inspect the crossbeam at FR22/23 and a High Frequency Eddy Current (HFEC) inspection procedure to inspect the crossbeam at FR61/62. - High Frequency Eddy Current (HFEC) inspection procedure to inspect the crossbeams at FR22/23 and FR62/63, before the accumulation of 10000 total aircraft flight cycles (FC) or 4000FC for freighter aircraft MSN 0805 and subsequent. NOTE: For aircraft on which the crossbeams have been previously repaired by the Structure Repair Manual (SRM) or a Repair Approval Sheet (RAS) the operator has to contact AIRBUS before reaching the threshold or the grace period for further instructions. In the case no crack(s) are found : - repeat this inspection at interval not to exceed 600FC (for FR22/23 or FR61/62 area) or 300FC (for FR62/63 area on freighter aircraft MSN 0805 and subsequent)
or

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 4 6

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# @A300-600 SERVICE BULLETIN - accomplish Modification Service Bulletin No. A300-53-6166 within 600FC (for FR22/23 or FR61/62 area) or within 300FC (for FR62/63 area on freighter aircraft MSN 0805 and subsequent) after the last inspection in accordance with this Inspection Service Bulletin. . The accomplishment of Modification Service Bulletin No. A300-53-6166 cancels the requirements of this Inspection Service Bulletin. In the case crack(s) are found : - longer than 7.0mm 0.27in.) contact AIRBUS before the next flight and follow their instructions. - smaller than or equal to 7.0mm 0.27in.) contact AIRBUS before the next flight and follow their instructions within : . 10FC, if crack(s) were detected by Ultra Sonic inspection procedure, . 50FC, if crack(s) were detected by a High Frequency Eddy Current inspection procedure. (3) Advantages The accomplishment of this Service Bulletin : - monitors the structure surrounding the rivet heads between crossbeams at FR22/23 and FR61/62 on passenger aircraft - monitors the structure surrounding the rivet heads between crossbeams at FR22/23 and FR62/63 on freighter aircraft - can prevent heavy repair. The accomplishment of Modification Service Bulletin Nos. A300-53-6166 cancels the requirements of this Inspection Service Bulletin. NOTE: This Service Bulletin is mandatory for all passenger aircraft. It is only recommended for freighter aircraft. NOTE: If operators have previously accomplished the Modification Service Bulletin No. A300-53-6166, the accomplishment of this Inspection Service Bulletin is no longer required. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to :

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 5 6

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# @A300-600 SERVICE BULLETIN
**CONF 001 Task 536168-832-848-001: Inspection (1) Special detailed HFEC Inspection for crack(s) at FR22/23 and FR61/62 **CONF 002 Task 536168-832-848-001: Inspection (1) Special detailed HFEC and US inspection for crack(s) at FR22/23 and a special detailed HFEC inspection for crack(s) at FR61/FR62 **CONF 003 Task 536168-832-848-001: Inspection (1) Special detailed HFEC Inspection for crack(s) at FR22/23 and FR62/63 **CONF ALL E. COMPLIANCE (1) Classification MANDATORY (2) Accomplishment Timescale **CONF 001 COMPLIANCE TIME (whichever occurs later) CONDITION ACTION THRESHOLD GRACE PERIOD REPETITIVE INTERVAL NOT TO EXCEED If crossbeams FR22/23 and FR61/FR62 have been repaired previously by SRM or RAS Before reaching the threshold or grace period contact Airbus for further instructions If crossbeams FR22/23 and FR61/FR62 have not been repaired previously by SRM or RAS Inspect in accordance with SUBTASK 536168-832-201-001 (Special detailed HFEC inspection) crossbeams for crack(s) at FR22/23 and FR61/FR62 Before the accumulation of 10000 total Flight Cycles (FC) 600FC from Service Bulletin issuance

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 6 6

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# @A300-600 SERVICE BULLETIN If the crack length is smaller than or equal to 7.0mm 0.27in.) contact AIRBUS before the next flight and follow their instructions within 50FC Not applicable Crack(s) found Contact Airbus for further instructions If a crack length is longer than 7.0mm 0.27in.) contact AIRBUS before the next flight and follow their instructions Not applicable Accomplish Service Bulletin No. A300-53-6166 Accomplish the Modification Service Bulletin A300-53-6166 (for FR22/23 and FR61/62 area) within 600FC after the last inspection in accordance with this Inspection Service Bulletin Not applicable

or No Crack(s) found

Repeat the inspection 600FC Table 1 : Special detailed HFEC inspection for cracks at FR22/23 and FR61/FR62 The accomplishment of Modification Service Bulletin Nos. A300-53-6166 cancels the requirements of this Inspection Service Bulletin. Accomplishment of this Service Bulletin is expected to be rendered mandatory for passenger aircraft by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). It is anticipated that the AD will confirm the (thresholds and/or intervals and/or date) given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale. **CONF 002 COMPLIANCE TIME (whichever occurs later) CONDITION ACTION THRESHOLD GRACE PERIOD REPETITIVE INTERVAL NOT TO EXCEED If crossbeams FR22/23 and FR61/FR62 have been repaired previously by SRM or RAS Before reaching the threshold or grace period contact Airbus for further instructions

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 7 6

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# @A300-600 SERVICE BULLETIN
If crossbeams FR22/23 and FR61/FR62 have not been repaired previously by SRM or RAS Inspect in accordance with SUBTASK 536168-832-201-003 (Special detailed HFEC and US inspection) crossbeams for crack(s) at FR22/23 and (Special detailed HFEC) crossbeams for crack(s) at FR61/FR62 Before the accumulation of 10000 total Flight Cycles (FC) 600FC from Service Bulletin issuance

If the crack length is smaller than or equal to 7.0mm 0.27in.) contact AIRBUS before the next flight and follow their instructions within 50FC Not applicable Crack(s) found by HFEC inspection at FR22, FR61 or FR62 Contact Airbus for further instructions If a crack length is longer than 7.0mm 0.27in.) contact AIRBUS before the next flight and follow their instructions Not applicable If the crack length is smaller than or equal to 7.0mm 0.27in.) contact AIRBUS before the next flight and follow their instructions within 10FC Not applicable Crack(s) found by US inspection at FR23 Contact Airbus for further instructions If a crack length is longer than 7.0mm 0.27in.) contact AIRBUS before the next flight and follow their instructions Not applicable Accomplish Service Modification Bulletin No. A300-53-6166 Accomplish the Modification Service Bulletin A300-53-6166 within 600FC after the last inspection in accordance with this Inspection Service Bulletin Not applicable

or No Crack(s) found

Repeat the inspection 600FC Table 1: Special detailed HFEC and US inspection for cracks at FR22/23 and Special detailed HFEC inspection at FR61/FR62 The accomplishment of Modification Service Bulletin Nos. A300-53-6166 cancels the requirements of this Inspection Service Bulletin. NOTE: The inspection program as stated in this Inspection Service Bulletin (ISB) is mandatory for the aircraft MSNs 0344, 0755 and 0758 because these aircraft can be used as passenger aircraft, as per original Airbus design at delivery. Accomplishment of this Service Bulletin is recommended for freighter aircraft.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 8 6

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# @A300-600 SERVICE BULLETIN
**CONF 003 COMPLIANCE TIME (whichever occurs later) CONDITION ACTION THRESHOLD GRACE PERIOD REPETITIVE INTERVAL NOT TO EXCEED If crossbeams FR22/23 and FR62/FR63 have been repaired previously by SRM or RAS Before reaching the threshold or grace period contact Airbus for further instructions If crossbeams FR22/23 and FR62/FR63 have not been repaired previously by SRM or RAS Inspect in accordance with SUBTASK 536168-832-201-007 Special detailed HFEC inspection for crack(s) at FR22/23 and FR62/FR63 Before the accumulation of 4000 total Flight Cycles (FC) 300FC from Service Bulletin issuance

If the crack length is smaller than or equal to 7.0mm 0.27in.) contact AIRBUS before the next flight and follow their instructions within 50FC Not applicable Crack(s) found Contact Airbus for further instructions If a crack length is longer than 7.0mm 0.27in.) contact AIRBUS before the next flight and follow their instructions Not applicable Accomplish Service Bulletin No. A300-53-6166 Accomplish the Modification Service Bulletin A300-53-6166 (for FR22/23 and FR62/63 area) within 600FC for FR22/23 area or within 300FC for FR62/63 area after the last inspection in accordance with this Inspection Service Bulletin Not applicable

or No Crack(s) found

Repeat the inspection 300FC for FR62/63 area. 600FC for FR22/23 area. Table 1 : Special detailed HFEC inspection for cracks at FR22/23 and FR62/FR63 The accomplishment of Modification Service Bulletin Nos. A300-53-6166 cancels the requirements of this Inspection Service Bulletin. Accomplishment of this Service Bulletin is recommended for freighter aircraft.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 9 6

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# @A300-600 SERVICE BULLETIN
**CONF ALL F. APPROVAL Approved under EASA Design Organisation Approval No. EASA21J.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. Aircraft that listed in this Service Bulletin and have been converted to freighter aircraft may have a difference in the affected area. In this event, the operator should contact the relevant Customer Service to obtain the necessary information about the future/planned Service Bulletins for the converted aircraft. 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 536168-832-848-001: Inspection Get Access 4.00 On Aircraft Special detailed HFEC Inspection for crack(s) at FR22/23 and FR61/62 0.50 Close-Up 3.00 TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 4.00 **CONF 002 Task 536168-832-848-001: Inspection Get Access 4.00 On Aircraft Special detailed HFEC and US inspection for crack(s) at FR22/23 and a special detailed HFEC inspection for crack(s) at FR61/FR62 0.50 Close-Up 3.00 TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 4.00

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 10 6

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# @A300-600 SERVICE BULLETIN
**CONF 003 Task 536168-832-848-001: Inspection Get Access 4.00 On Aircraft Special detailed HFEC Inspection for crack(s) at FR22/23 and FR62/63 0.50 Close-Up 3.00 TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 4.00 **CONF ALL H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-41-53 24-00-00 24-41-00 25-54-10 25-55-10 52-30-00 Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-08 Service Bulletin (SB) A300-53-6166 **CONF 002 Aircraft Maintenance Manual (AMM) 06-41-53 24-00-00 24-41-00 25-54-10 25-55-10 52-30-00 Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-08 51-10-13 Service Bulletin (SB) A300-53-6166 **CONF 003 Aircraft Maintenance Manual (AMM) 06-41-53 24-00-00 24-41-00 25-54-10 25-55-10 52-30-00 Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-08 Service Bulletin (SB) A300-53-6166

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# @A300-600 SERVICE BULLETIN
**CONF ALL K. PUBLICATION AFFECTED Not Applicable L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 12 6

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# @A300-600 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses None (2) Price and Availability None B. INDUSTRY SUPPORT INFORMATION None C. LIST OF COMPONENTS No Kit D. LIST OF MATERIALS - OPERATOR SUPPLIED None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability None (2) Tools Standard tool TOOLD01 ITEM TOOL N ̊ TOOL NAME QTY SEE NOTES 98A52307523000 Support Struts - Fwd And Aft Cargo Compartment Doors 2 (3) Special Tools None

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# @A300-600 SERVICE BULLETIN

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# @A300-600 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 536168-832-848-001 - Inspection WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS : - PUT PROTECTION, SUCH AS PlastIC SHEETING, CLOTHS, ETC; AS NECESSARY ON ELECTRICAL 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. Task Associated Data **CONF 001 Zone 120 130 150 Access Door 811 812 Manpower TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 4.00 **CONF 002 Zone 120 130 150 Access Door 811 812 Manpower TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 4.00

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# @A300-600 SERVICE BULLETIN
**CONF 003 Zone 120 130 150 Access Door 811 812 Manpower TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 4.00 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 536168-910-201-001 - Standard Practices Work Zones and Access Panels Zone Access/Work location 130 Access Door 811 Work location from Frame 22, Seat Track 4/5 to Frame 23, Seat Track 4/5 150 Access Door 812 Work location from Frame 61, Seat Track 4/5 to Frame 62, Seat Track 4/5 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001 (a) For the location of access panels (Refer to AMM 06-41-53, Page Block 001). (2) Subtask 536168-839-201-001 - Documentation Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

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# @A300-600 SERVICE BULLETIN
**CONF 002 (1) Subtask 536168-910-201-001 - Standard Practices Work Zones and Access Panels Zone Access/Work location 130 Access Door 811 Work location from Frame 22, Seat Track 4/5 to Frame 23, Seat Track 4/5 150 Access Door 812 Work location from Frame 61, Seat Track 4/5 to Frame 62, Seat Track 4/5 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001 (a) For the location of access panels (Refer to AMM 06-41-53, Page Block 001). (2) Subtask 536168-839-201-001 - Documentation 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 536168-910-201-001 - Standard Practices Work Zones and Access Panels Zone Access/Work location 130 Access Door 811 Work location from Frame 22, Seat Track 4/5 to Frame 23, Seat Track 4/5 150 Access Door 812 Work location from Frame 61, Seat Track 4/5 to Frame 62, Seat Track 4/5 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001 (a) For the location of access panels (Refer to AMM 06-41-53, Page Block 001).

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# @A300-600 SERVICE BULLETIN (2) Subtask 536168-839-201-001 - Documentation Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 536168-941-201-003 - Job Set-up Work Zones and Access Panels Zone Access/Work location 130 Access Door 811 Work location from Frame 22, Seat Track 4/5 to Frame 23, Seat Track 4/5 150 Access Door 812 Work location from Frame 61, Seat Track 4/5 to Frame 62, Seat Track 4/5 Manpower Resources Skills NON SPECIFIC Material necessary to do the job Standard tool TOOLD01 ITEM TOOL N ̊ TOOL NAME QTY SEE NOTES 98A52307523000 Support Struts - Fwd And Aft Cargo Compartment Doors 2

References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 25-54-10, Page Block 201 25-55-10, Page Block 201 52-30-00, Page Block 301 52-30-00, Page Block 301 (a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page Block 301). (b) Put access platform(s) in position. (c) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301). DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 18 6

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# @A300-600 SERVICE BULLETIN (d) Open the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block 301). (e) Open the AFT cargo-compartment door 812 (Refer to AMM 52-30-00, Page Block 301). (f) Secure the FWD and AFT cargo-compartment doors with : 98A52307523000 Support Struts - Fwd And Aft Cargo Compartment Doors 2
or with the door actuator safety lock(s). Refer to AMM 52-30-00, Page Block 301 (g) Remove and retain the FWD cargo-ceiling panels 132AC and 132BC (Refer to AMM 25-54-10, Page Block 201). (h) Remove the door actuator lining between FR22 and FR23. (i) Remove and retain the AFT cargo-ceiling panels 152DC and 152EC (Refer to AMM 25-55-10, Page Block 201). (j) Remove the door actuator lining between FR61 and FR62. (2) Subtask 536168-865-201-001 - C/B Opening Work Zones and Access Panels Zone Access/Work location 120 Manpower Resources Skills ELECTRICAL (a) Open, safety and tag these circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 128VU HYDRAULIC/ACCU PRESS CTL AND CARGO PUMP 7GX 803/C11 101VU ELEC HYD PUMP 23GX ALT2 NOTE: The location of the circuit breaker(s) can be different from the location given in the table.

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# @A300-600 SERVICE BULLETIN
**CONF 002 (1) Subtask 536168-941-201-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 130 Access Door 811 Work location from Frame 22, Seat Track 4/5 to Frame 23, Seat Track 4/5 150 Access Door 812 Work location from Frame 61, Seat Track 4/5 to Frame 62, Seat Track 4/5 Manpower Resources Skills NON SPECIFIC Material necessary to do the job Standard tool TOOLD01 ITEM TOOL N ̊ TOOL NAME QTY SEE NOTES 98A52307523000 Support Struts - Fwd And Aft Cargo Compartment Doors 2

References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 25-54-10, Page Block 201 25-55-10, Page Block 201 52-30-00, Page Block 301 52-30-00, Page Block 301 (a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page Block 301). (b) Put access platform(s) in position. (c) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301). (d) Open the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block 301). (e) Open the AFT cargo-compartment door 812 (Refer to AMM 52-30-00, Page Block 301).

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# @A300-600 SERVICE BULLETIN (f) Secure the FWD and AFT cargo-compartment doors with : 98A52307523000 Support Struts - Fwd And Aft Cargo Compartment Doors 2
or with the door actuator safety lock(s). Refer to AMM 52-30-00, Page Block 301 (g) Remove and retain the FWD cargo-ceiling panels 132AC and 132BC (Refer to AMM 25-54-10, Page Block 201). (h) Remove the door actuator lining between FR22 and FR23. (i) Remove and retain the AFT cargo-ceiling panels 152DC and 152EC (Refer to AMM 25-55-10, Page Block 201). (j) Remove the door actuator lining between FR61 and FR62. (2) Subtask 536168-865-201-001 - C/B Opening Work Zones and Access Panels Zone Access/Work location 120 Manpower Resources Skills ELECTRICAL (a) Open, safety and tag these circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 128VU HYDRAULIC/ACCU PRESS CTL AND CARGO PUMP 7GX 803/C11 101VU ELEC HYD PUMP 23GX ALT2 NOTE: The location of the circuit breaker(s) can be different from the location given in the table. **CONF 003 (1) Subtask 536168-941-201-004 - Job Set-up Work Zones and Access Panels Zone Access/Work location 130 Access Door 811 Work location from Frame 22, Seat Track 4/5 to Frame 23, Seat Track 4/5 150 Access Door 812 Work location from Frame 62, Seat Track 4/5 to Frame 63, Seat Track 4/5
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# @A300-600 SERVICE BULLETIN Manpower Resources Skills NON SPECIFIC Material necessary to do the job Standard tool TOOLD01 ITEM TOOL N ̊ TOOL NAME QTY SEE NOTES 98A52307523000 Support Struts - Fwd And Aft Cargo Compartment Doors 2

References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 25-54-10, Page Block 201 25-55-10, Page Block 201 52-30-00, Page Block 301 52-30-00, Page Block 301 (a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page Block 301). (b) Put access platform(s) in position. (c) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301). (d) Open the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block 301). (e) Open the AFT cargo-compartment door 812 (Refer to AMM 52-30-00, Page Block 301). (f) Secure the FWD and AFT cargo-compartment doors with : 98A52307523000 Support Struts - Fwd And Aft Cargo Compartment Doors 2
or with the door actuator safety lock(s). Refer to AMM 52-30-00, Page Block 301 (g) Remove and retain the FWD cargo-ceiling panels 132AC and 132BC (Refer to AMM 25-54-10, Page Block 201). (h) Remove the door actuator lining between FR22 and FR23. (i) Remove and retain the AFT cargo-ceiling panels 152GC and 152HC (Refer to AMM 25-55-10, Page Block 201).
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# @A300-600 SERVICE BULLETIN (j) Remove the door actuator lining between FR62 and FR63. (2) Subtask 536168-865-201-001 - C/B Opening Work Zones and Access Panels Zone Access/Work location 120 Manpower Resources Skills ELECTRICAL (a) Open, safety and tag these circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 128VU HYDRAULIC/ACCU PRESS CTL AND CARGO PUMP 7GX 803/C11 101VU ELEC HYD PUMP 23GX ALT2 NOTE: The location of the circuit breaker(s) can be different from the location given in the table. **CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 536168-832-201-001 - Special detailed HFEC Inspection for crack(s) at FR22/23 and FR61/62 Work Zones and Access Panels Zone Access/Work location 120 Access Door 811 Work location from Frame 22, Seat Track 4/5 to Frame 23, Seat Track 4/5 150 Access Door 812 Work location from Frame 61, Seat Track 4/5 to Frame 62, Seat Track 4/5 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-08, Page Block 601 Service Bulletin (SB) A300-53-6166

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# @A300-600 SERVICE BULLETIN
References Fig. A-GBAAA HFEC Inspection between FR22/23 Sheet 01 Sheet 02 Fig. A-GBGAA HFEC Inspection between FR61/62 Sheet 01 Sheet 02 Fig. A-GFAAA Flow-Chart : HFEC Inspection for Cracks between FR22/23 and FR61/62 Sheet 01
(a) Check if the crossbeams between : - FR22 and FR23 and - FR61 and FR62 have been previously repaired by SRM or RAS. 1 In the case the crossbeams are previously repaired by SRM or RAS contact AIRBUS and follow their instructions. 2 In the case the crossbeams are not previously repaired by SRM or RAS : a Perform the special detailed HFEC Inspection for crack(s) in the area around the rivet heads at FR22 and FR23. Refer to NTM 51-10-08, Page Block 601 Refer to Fig. A-GBAAA Sheet 02, Details B and C Refer to Fig. A-GFAAA Sheet 01 b Perform the special detailed HFEC Inspection for crack(s) in the areas around the rivet heads at FR61 and FR62. Refer to NTM 51-10-08, Page Block 601 Refer to Fig. A-GBGAA Sheet 02, Details B and C Refer to Fig. A-GFAAA Sheet 01 c In the case no crack(s) is/are found : <1> Repeat the inspection at interval not to exceed 600FC or <2> Accomplish Service Bulletin No. A300-53-6166 within 600FC after the last inspection in accordance with this Inspection Service Bulletin. No further action is required in accordance with this Service Bulletin.

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# @A300-600 SERVICE BULLETIN
d In the case crack(s) is/are found : <1> In the case the crack(s) is/are longer than 7.0mm (0.27in.) : <a> Contact AIRBUS before the next flight and follow their instructions. <b> No further action is required in accordance with this Service Bulletin. <2> In the case the crack(s) is/are smaller than or equal to 7.0mm (0.27in.) : <a> Contact AIRBUS before the next flight and follow their instructions within the next 50FC. <b> No further action is required in accordance with this Service Bulletin. **CONF 002 (1) Subtask 536168-832-201-003 - Special detailed HFEC and US inspection for crack(s) at FR22/23 and a special detailed HFEC inspection for crack(s) at FR61/FR62 Work Zones and Access Panels Zone Access/Work location 120 Access Door 811 Work location from Frame 22, Seat Track 4/5 to Frame 23, Seat Track 4/5 150 Access Door 812 Work location from Frame 61, Seat Track 4/5 to Frame 62, Seat Track 4/5 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-08, Page Block 601 51-10-13, Page Block 401 Service Bulletin (SB) A300-53-6166 Fig. A-GBEAA HFEC and US Inspection between FR22/23 Sheet 01 Sheet 02 Sheet 03 Fig. A-GBGAA HFEC Inspection between FR61/62 Sheet 01 Sheet 02
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# @A300-600 SERVICE BULLETIN
References Fig. A-GFCAA Flow-Chart : HFEC and Ultra-Sonic Inspection for Cracks between FR22/23 and HFEC Inspection for Cracks between FR61/62 Sheet 01

(a) Check if the crossbeams between : - FR22 and FR23 and - FR61 and FR62 have been previously repaired by SRM or RAS. 1 In the case the crossbeams are previously repaired by SRM or RAS contact AIRBUS and follow their instruction. 2 In the case the crossbeams are not previously repaired by SRM or RAS :
a Perform a special detailed HFEC Inspection for crack(s) in the area around the rivet heads at FR22/23. Refer to NTM 51-10-08, Page Block 601 Refer to Fig. A-GBEAA Sheet 02, Detail B Refer to Fig. A-GFCAA b Perform a special detailed Ultra Sonic Inspection for crack(s) in the area around the rivet heads at FR23. Refer to NTM 51-10-13, Page Block 401 Refer to Fig. A-GBEAA Sheet 03, Detail E Refer to Fig. A-GFCAA
c Perform a special detailed HFEC Inspection for crack(s) in the areas around the rivet heads at FR61 and FR62. Refer to NTM 51-10-08, Page Block 601 Refer to Fig. A-GBGAA Sheet 02, Details B and C Refer to Fig. A-GFCAA d In the case no crack(s) is/are found : <1> Repeat the inspection at interval not to exceed 600FC
or

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# @A300-600 SERVICE BULLETIN <2> Accomplish Service Bulletin No. A300-53-6166 within 600FC after the last inspection in accordance with this Inspection Service Bulletin. No further action is required in accordance with this Service Bulletin. e In the case crack(s) is/are found : <1> In the case the crack(s) is/are longer than 7.0mm (0.27in.) : <a> Contact AIRBUS before the next flight and follow their instructions. <b> No further action is required in accordance with this Service Bulletin. <2> In the case the crack(s) is/are crack(s) smaller than or equal to 7.0mm (0.27in.) : <a> Contact AIRBUS before the next flight and follow their instructions within the next : 50FC, if crack(s) were detected by HF-Eddy Current inspection procedure, or 10FC, if crack(s) were detected by Ultra Sonic inspection procedure. <b> No further action is required in accordance with this Service Bulletin. **CONF 003 (1) Subtask 536168-832-201-007 - Special detailed HFEC Inspection for crack(s) at FR22/23 and FR62/63 Work Zones and Access Panels Zone Access/Work location 120 Access Door 811 Work location from Frame 22, Seat Track 4/5 to Frame 23, Seat Track 4/5 150 Access Door 812 Work location from Frame 62, Seat Track 4/5 to Frame 63, Seat Track 4/5 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON DESTRUCTIVE TESTING
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# @A300-600 SERVICE BULLETIN
References Non Destructive Test Manual (NTM) 51-10-08, Page Block 601 Service Bulletin (SB) A300-53-6166 Fig. A-GBCAA HFEC Inspection between FR22/23 Sheet 01 Sheet 02 Fig. A-GBHAA HFEC Inspection between FR62/63 Sheet 01 Sheet 02 Fig. A-GFDAA Flow-Chart : HFEC Inspection for Cracks between FR22/23 and FR62/63 Sheet 01
(a) Check if the crossbeams between : - FR22 and FR23 and - FR62 and FR63 have been previously repaired by SRM or RAS. 1 In the case the crossbeams are previously repaired by SRM or RAS contact AIRBUS and follow their instruction. 2 In the case the crossbeams are not previously repaired by SRM or RAS :
a Perform the special detailed HFEC Inspection for crack(s) in the area around the rivet heads at FR22 and FR23. Refer to NTM 51-10-08, Page Block 601 Refer to Fig. A-GBCAA Sheet 02, Details B and C Refer to Fig. A-GFDAA b Perform the special detailed HFEC Inspection for crack(s) in the areas around the rivet heads at FR62 and FR63. Refer to NTM 51-10-08, Page Block 601 Refer to Fig. A-GBHAA Sheet 02, Details B and C Refer to Fig. A-GFDAA
c In the case no crack(s) is/are found : <1> Either repeat the inspection in accordance with this Inspection Service Bulletin at interval not to exceed 600FC for FR22/23 or accomplish the Modification Service Bulletin No. A300-53-6166 within 600FC after the last inspection in accordance with this Inspection Service Bulletin in area FR22/23
or

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# @A300-600 SERVICE BULLETIN repeat the inspection in accordance with this Inspection Service Bulletin at interval not to exceed 300FC for FR62/63 or accomplish the Modification Service Bulletin No. A300-53-6166 within 300FC after the last inspection in accordance with this Inspection Service Bulletin in area FR62/63. No further action is required in accordance with this Service Bulletin. d In the case crack(s) is/are found : <1> In the case the crack(s) is/are longer than 7.0mm (0.27in.) : <a> Contact AIRBUS before the next flight and follow their instructions. <b> No further action is required in accordance with this Service Bulletin. <2> In the case the crack(s) is/are smaller than or equal to 7.0mm (0.27in.) : <a> Contact AIRBUS before the next flight and follow their instructions within the next 50FC. <b> No further action is required in accordance with this Service Bulletin. **CONF ALL D. TEST **CONF 001 (1) Subtask 536168-700-201-001 - Testing Manpower Resources Skills NON SPECIFIC None **CONF 002 (1) Subtask 536168-700-201-001 - Testing Manpower Resources Skills NON SPECIFIC None

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# @A300-600 SERVICE BULLETIN
**CONF 003 (1) Subtask 536168-700-201-001 - Testing Manpower Resources Skills NON SPECIFIC None **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 536168-865-202-001 - C/B Closing Work Zones and Access Panels Zone Access/Work location 120 Manpower Resources Skills ELECTRICAL (a) Remove the safety clip(s) and tag(s) and close this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 128VU HYDRAULIC/ACCU PRESS CTL AND CARGO 7GX 802/P70 101VU ELEC HYD PUMP 23GX GEN2/B5 NOTE: The location of the circuit breaker(s) can be different from the location given in the table. (2) Subtask 536168-942-201-001 - Close-up Work Zones and Access Panels Zone Access/Work location 120 Access Door 811 130 Access Door 812 Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 25-54-10, Page Block 201 25-55-10, Page Block 201 52-30-00, Page Block 301 (a) Install the FWD cargo-ceiling panels 132AC and 132BC (Refer to AMM 25-54-10, Page Block 201). DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 30 6

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# @A300-600 SERVICE BULLETIN (b) Install the door actuator lining between FR22 and FR23. (c) Install the AFT cargo-ceiling panels 152DC and 152EC (Refer to AMM 25-55-10, Page Block 201). (d) Install the door actuator lining between FR61 and FR62. (e) Make sure that the work areas are clean and clear of tools and other items of equipment. (f) Make sure that the applicable cargo-door safety-equipment is removed from the FWD and AFT cargo-compartment door. (g) Close the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block 301). (h) Close the AFT cargo-compartment door 812 (Refer to AMM 52-30-00, Page Block 301). (i) Remove the access platform(s). **CONF 002 (1) Subtask 536168-865-202-001 - C/B Closing Work Zones and Access Panels Zone Access/Work location 120 Manpower Resources Skills ELECTRICAL (a) Remove the safety clip(s) and tag(s) and close this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 128VU HYDRAULIC/ACCU PRESS CTL AND CARGO 7GX 802/P70 101VU ELEC HYD PUMP 23GX GEN2/B5 NOTE: The location of the circuit breaker(s) can be different from the location given in the table. (2) Subtask 536168-942-201-001 - Close-up Work Zones and Access Panels Zone Access/Work location 120 Access Door 811 130 Access Door 812 Manpower Resources Skills AIRFRAME
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 31 6

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# @A300-600 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) 25-54-10, Page Block 201 25-55-10, Page Block 201 52-30-00, Page Block 301 (a) Install the FWD cargo-ceiling panels 132AC and 132BC (Refer to AMM 25-54-10, Page Block 201). (b) Install the door actuator lining between FR22 and FR23. (c) Install the AFT cargo-ceiling panels 152DC and 152EC (Refer to AMM 25-55-10, Page Block 201). (d) Install the door actuator lining between FR61 and FR62. (e) Make sure that the work areas are clean and clear of tools and other items of equipment. (f) Make sure that the applicable cargo-door safety-equipment is removed from the FWD and AFT cargo-compartment door. (g) Close the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block 301). (h) Close the AFT cargo-compartment door 812 (Refer to AMM 52-30-00, Page Block 301). (i) Remove the access platform(s). **CONF 003 (1) Subtask 536168-865-202-001 - C/B Closing Work Zones and Access Panels Zone Access/Work location 120 Manpower Resources Skills ELECTRICAL (a) Remove the safety clip(s) and tag(s) and close this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 128VU HYDRAULIC/ACCU PRESS CTL AND CARGO 7GX 802/P70 101VU ELEC HYD PUMP 23GX GEN2/B5 NOTE: The location of the circuit breaker(s) can be different from the location given in the table.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 32 6

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# @A300-600 SERVICE BULLETIN (2) Subtask 536168-942-201-003 - Close-up Work Zones and Access Panels Zone Access/Work location 120 Access Door 811 130 Access Door 812 Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 25-54-10, Page Block 201 25-55-10, Page Block 201 52-30-00, Page Block 301 (a) Install the FWD cargo-ceiling panels 132AC and 132BC (Refer to AMM 25-54-10, Page Block 201). (b) Install the door actuator lining between FR22 and FR23. (c) Install the AFT cargo-ceiling panels 152GC and 152HC (Refer to AMM 25-55-10, Page Block 201). (d) Install the door actuator lining between FR62 and FR63. (e) Make sure that the work areas are clean and clear of tools and other items of equipment. (f) Make sure that the applicable cargo-door safety-equipment is removed from the FWD and AFT cargo-compartment door. (g) Close the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block 301). (h) Close the AFT cargo-compartment door 812 (Refer to AMM 52-30-00, Page Block 301). (i) Remove the access platform(s).

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 33 6

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# @A300-600 SERVICE BULLETIN

**CONF 001

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 FR21 FR22 FR23 FR24

SEAT TRACK 6 Z130



### A

**B C** 

**FWD** 

## A

D_SB_536168_6_BAAA_01_00 Figure A-GBAAA - Sheet 01 HFEC Inspection between FR22/23
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 34 6

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# @A300-600 SERVICE BULLETIN

**CONF 001

**NOTE:**
POSSIBLE CRACK IN CROSSBEAM STRUCTURE BENEATH INSPECTION AREA 01 VIEW LOOKING AFT

VIEW LOOKING FWD FR22

FR23

(AROUND RIVET HEADS), REFER TO NTM 51−10−08, PB 601 

### D 01

01

01

01 

### D 

## B

02 INSPECTION AREA FOR THE HFEC INSPECTION 

## D TYPICAL 

## C

D_SB_536168_6_BAAA_02_01 02

Figure A-GBAAA - Sheet 02 HFEC Inspection between FR22/23
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 35 6

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# @A300-600 SERVICE BULLETIN

**CONF 002

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 FR21 FR22 FR23 FR24

SEAT TRACK 6 Z130



### A

**B C** 

**FWD** 

## A **E**

D_SB_536168_6_BEAA_01_00 Figure A-GBEAA - Sheet 01 HFEC and US Inspection between FR22/23
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 36 6

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# @A300-600 SERVICE BULLETIN

**CONF 002

**NOTE:**
POSSIBLE CRACK IN CROSSBEAM STRUCTURE VIEW LOOKING AFT

VIEW LOOKING FWD FR22

FR23 01 

### D

02 

## D TYPICAL 02 01

01 

### D



## B 01

01 (AROUND RIVET HEADS), REFER TO NTM 51−10−08, PB 601 INSPECTION AREA FOR THE HFEC INSPECTION AREA 1 AND 2

AREA 3 

## C

D_SB_536168_6_BEAA_02_01 BENEATH INSPECTION AREA Figure A-GBEAA - Sheet 02 HFEC and US Inspection between FR22/23
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 37 6

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# @A300-600 SERVICE BULLETIN

**CONF 002

VIEW LOOKING AFT 01 AREA 4 

### F

**NOTE:** INSPECTION AREA FOR THE US INSPECTION 01 (AROUND RIVET HEAD), REFER TO NTM 51−10−13, PB 401 POSSIBLE CRACK IN CROSSBEAM STRUCTURE BENEATH INSPECTION AREA 02 03 SEARCH UNIT SCAN MOVEMENT LINE 02 03 

## E

**F**

D_SB_536168_6_BEAA_03_02 FR23

Figure A-GBEAA - Sheet 03 HFEC and US Inspection between FR22/23
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 38 6

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# @A300-600 SERVICE BULLETIN

**CONF 003

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 FR21 FR22 FR23 FR24

SEAT TRACK 6 Z130



### A

**B C** 

**FWD** 

## A

D_SB_536168_6_BCAA_01_00 Figure A-GBCAA - Sheet 01 HFEC Inspection between FR22/23
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 39 6

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# @A300-600 SERVICE BULLETIN

**CONF 003

**NOTE:**
POSSIBLE CRACK IN CROSSBEAM STRUCTURE 01 VIEW LOOKING AFT

VIEW LOOKING FWD FR22

FR23

(AROUND RIVET HEADS), REFER TO NTM 51−10−08, PB 601 01

01 

### D

02 

## D TYPICAL 02 01

01 

### D



## B

**C**

INSPECTION AREA FOR THE HFEC INSPECTION 01

BENEATH INSPECTION AREA D_SB_536168_6_BCAA_02_02 Figure A-GBCAA - Sheet 02 HFEC Inspection between FR22/23
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 40 6

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# @A300-600 SERVICE BULLETIN

**CONF 001 thru 002

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 

### A

SEAT TRACK 6 FR60 FR61 FR62 FR63 Z150

**FWD** 

## A **B C** 

D_SB_536168_6_BGAA_01_00 Figure A-GBGAA - Sheet 01 HFEC Inspection between FR61/62
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 41 6

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# @A300-600 SERVICE BULLETIN

**CONF 001 thru 002

**NOTE:**
POSSIBLE CRACK IN CROSSBEAM STRUCTURE VIEW LOOKING AFT

VIEW LOOKING FWD FR61

FR62 01

01

01

01 

## B

**C**

02 

## D TYPICAL 02 

### D **D**

01 (AROUND RIVET HEADS), REFER TO NTM 51−10−08, PB 601 INSPECTION AREA FOR THE HFEC INSPECTION
D_SB_536168_6_BGAA_02_01 BENEATH INSPECTION AREA Figure A-GBGAA - Sheet 02 HFEC Inspection between FR61/62
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 42 6

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# @A300-600 SERVICE BULLETIN

**CONF 003

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 

### A

SEAT TRACK 6 Z150

**FWD** 

## A **B C** 

D_SB_536168_6_BHAA_01_00 FR63 FR62 FR61 FR64

Figure A-GBHAA - Sheet 01 HFEC Inspection between FR62/63
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 43 6

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# @A300-600 SERVICE BULLETIN

**CONF 003

**NOTE:**
POSSIBLE CRACK IN CROSSBEAM STRUCTURE VIEW LOOKING AFT

VIEW LOOKING FWD FR62

FR63 01

01

01

01 

## B

**C**

02 

## D TYPICAL 02 

### D **D**

01 (AROUND RIVET HEADS), REFER TO NTM 51−10−08, PB 601 INSPECTION AREA FOR THE HFEC INSPECTION
BENEATH INSPECTION AREA D_SB_536168_6_BHAA_02_00 Figure A-GBHAA - Sheet 02 HFEC Inspection between FR62/63
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 44 6

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# @A300-600 SERVICE BULLETIN

**CONF 001

YES NO CROSSBEAMS FR22/23 AND FR61/62 REPAIRED BY SRM OR RAS PREVIOUSLY

PARA. 1.E.(2), DO A SPECIAL DETAILED HFEC INSPECTION OF THE CROSSBEAMS, REFER TO NTM 51−10−08, PB 601

CRACK FINDINGS
YES

CRACK LENGTH

MORE THAN 7.0mm (0.28 in.) NO

OR
NO YES

NO FURTHER ACTION IS REQUIRED IN ACCORDANCE WITH THIS INSPECTION

SERVICE BULLETIN AT THE THRESHOLD DETAILED IN

REPEAT THE INSPECTION AT INTERVAL NOT TO EXCEED 600FC

ACCOMPLISH SERVICE BULLETIN NO. A300−53−6166 WITHIN 600FC AFTER THE LAST INSPECTION IN ACC. WITH THIS INSPECTION SERVICE BULLETIN

D_SB_536168_6_FAAA_01_04 BEFORE REACHING THE THRESHOLD OR GRACE PERIOD

CONTACT AIRBUS BEFORE THE NEXT FLIGHT AND FOLLOW THEIR INSTRUCTIONS WITHIN 50FC CONTACT AIRBUS BEFORE THE NEXT FLIGHT AND FOLLOW THEIR INSTRUCTIONS CONTACT AIRBUS AND FOLLOW THEIR

INSTRUCTIONS

Figure A-GFAAA - Sheet 01 Flow-Chart : HFEC Inspection for Cracks between FR22/23 and FR61/62
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 45 6

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# @A300-600 SERVICE BULLETIN

**CONF 002

YES NO CROSSBEAMS, FR22/23

IN PARA. 1.E.(2), DO A SPECIAL

INSPECTION OF THE REFER TO NTM 51−10−13, PB 401

OR DO A SPECIAL DETAILED US DETAILED HFEC INSPECTION (AREA 1 THRU 3) AND FR61/62

CRACK FINDINGS IN FR22/23 AND FR61/62
YES

CRACK LENGTH

MORE THAN 7.0mm (0.28 in.)

YES

NO FURTHER ACTION IS REQUIRED IN ACCORDANCE WITH THIS INSPECTION

SERVICE BULLETIN NO AND FR61/62 REPAIRED BY SRM OR RAS PREVIOUSLY

OF THE CROSSBEAMS, FR22/23

CROSSBEAM, FR23 (AREA 4) (AREA 1 THRU 4) AT THE THRESHOLD DETAILED

REFER TO NTM 51−10−08, PB 601

AREA 1 THRU 3 AT FR22/23 AND FR61/62 AREA 4 AT FR23 NO

ACCOMPLISH SERVICE BULLETIN NO. A300−53−6166 WITHIN 600FC AFTER THE LAST INSPECTION IN ACC. WITH THIS INSPECTION SERVICE BULLETIN D_SB_536168_6_FCAA_01_04 IN AREA 1

AND 2 AT INTERVAL REPEAT THE INSPECTION
NOT TO EXCEED 600FC BEFORE REACHING THE THRESHOLD OR GRACE PERIOD

CONTACT AIRBUS BEFORE THE NEXT FLIGHT AND FOLLOW THEIR INSTRUCTIONS WITHIN 50FC CONTACT AIRBUS BEFORE THE NEXT FLIGHT AND FOLLOW THEIR INSTRUCTIONS CONTACT AIRBUS AND FOLLOW THEIR

INSTRUCTIONS

CONTACT AIRBUS BEFORE THE NEXT FLIGHT AND FOLLOW THEIR INSTRUCTIONS WITHIN 10FC

Figure A-GFCAA - Sheet 01 Flow-Chart : HFEC and Ultra-Sonic Inspection for Cracks between FR22/23 and HFEC Inspection for Cracks between FR61/62 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 46 6

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# @A300-600 SERVICE BULLETIN

**CONF 003

YES NO FR22/23 AND FR62/63, REPAIRED BY SRM OR RAS PREVIOUSLY

PARA. 1.E.(2), DO A SPECIAL DETAILED HFEC INSPECTION OF THE CROSSBEAMS, REFER TO NTM 51−10−08, PB 601

CRACK

YES

CRACK LENGTH

MORE THAN 7.0mm (0.28 in.) NO REPEAT THE INSPECTION

NO YES

NO FURTHER ACTION IS REQUIRED IN ACCORDANCE WITH THIS INSPECTION

SERVICE BULLETIN CROSSBEAMS,

FOR FR22/23 REPEAT THE INSPECTION
300 FC AT THE THRESHOLD DETAILED IN

NOT TO EXCEED 600FC

AT INTERVAL FOR FR62/63 NOT TO EXCEED FINDINGS

AT INTERVAL

FR62/63 AREA

ACCOMPLISH SERVICE BULLETIN NO. A300−53−6166

WITHIN 600FC AFTER THE LAST INSPECTION IN ACC. WITH THIS INSPECTION

SERVICE BULLETIN ACCOMPLISH SERVICE BULLETIN NO. A300−53−6166

WITHIN 300FC AFTER THE LAST INSPECTION IN ACC. WITH THIS INSPECTION

SERVICE BULLETIN OR OR

FR22/23 AREA

D_SB_536168_6_FDAA_01_03 BEFORE REACHING THE THRESHOLD OR GRACE PERIOD

CONTACT AIRBUS BEFORE THE NEXT FLIGHT AND FOLLOW THEIR INSTRUCTIONS WITHIN 50FC CONTACT AIRBUS BEFORE THE NEXT FLIGHT AND FOLLOW THEIR INSTRUCTIONS CONTACT AIRBUS AND FOLLOW THEIR

INSTRUCTIONS

Figure A-GFDAA - Sheet 01 Flow-Chart : HFEC Inspection for Cracks between FR22/23 and FR62/63
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 47 6

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# @A300-600 SERVICE BULLETIN REPORTING SHEET 

### TITLE: FUSELAGE - STRUCTURE - INSPECT FOR CROSSBEAM AT JUNCTION WITH LOWER DECK CARGO DOOR ACTUATOR BEAM 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: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 1 6

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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 4 3 2 1 - Quality rating of the Accomplishment Instructions 4 3 2 1 - Quality rating of the Illustrations 4 3 2 1 - Is this SB easy to understand ? Y / N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue. Planning Material Instructions X Effectivity X Kit content X Preparation X Reason X List of Materials 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: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168 REVISION No.: 00 - Jan 15/10 Page: 1 6

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