@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 - 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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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

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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

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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

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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

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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

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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

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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

FR61 FR63 FR64 FR62

Figure A-GSCAA - Sheet 02

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168

REVISION No.: 00 - Jan 15/10 Page: 10

6

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

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 53

TITLE: 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

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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

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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

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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

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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

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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

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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

Crack(s) found Contact Airbus for Not applicable

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

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

Crack(s) found by Not applicable

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

Crack(s) found by Not applicable

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

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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

Crack(s) found Contact Airbus for Not applicable

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

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@A300-600

SERVICE BULLETIN

**CONF ALL

F. APPROVAL

Approved under EASA Design Organisation Approval No. EASA 21J.031.

If an aircraft listed in the effectivity has a modification or repair embodied that is not of

AIRBUS origin, and which affects the content of this Service Bulletin, the operator is

responsible for obtaining approval by its airworthiness authority for any adaptation necessary

before incorporation of the Service Bulletin.

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

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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

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168

REVISION No.: 00 - Jan 15/10 Page: 11

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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

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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

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168

REVISION No.: 00 - Jan 15/10 Page: 13

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@A300-600

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168

REVISION No.: 00 - Jan 15/10 Page: 14

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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

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168

REVISION No.: 00 - Jan 15/10 Page: 15

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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.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168

REVISION No.: 00 - Jan 15/10 Page: 16

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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).

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168

REVISION No.: 00 - Jan 15/10 Page: 17

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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

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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.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168

REVISION No.: 00 - Jan 15/10 Page: 19

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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).

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168

REVISION No.: 00 - Jan 15/10 Page: 20

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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

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168

REVISION No.: 00 - Jan 15/10 Page: 21

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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).

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168

REVISION No.: 00 - Jan 15/10 Page: 22

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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

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168

REVISION No.: 00 - Jan 15/10 Page: 23

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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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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

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168

REVISION No.: 00 - Jan 15/10 Page: 25

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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

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168

REVISION No.: 00 - Jan 15/10 Page: 26

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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

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168

REVISION No.: 00 - Jan 15/10 Page: 27

6

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

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168

REVISION No.: 00 - Jan 15/10 Page: 28

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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

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-6168

REVISION No.: 00 - Jan 15/10 Page: 29

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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

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

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

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

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

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

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

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

 BENEATH INSPECTION AREA D_SB_536168_6_BEAA_02_01

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:

01 INSPECTION AREA FOR THE US INSPECTION

(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

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

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

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

BENEATH INSPECTION AREA D_SB_536168_6_BGAA_02_01

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

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

FR61 FR64 FR62 FR63

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

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

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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

NO YES

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

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

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

SERVICE BULLETIN

QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

- Quality rating of this SB 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

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